Abstract:
An air/space craft propelled by a cubic three-dimension motive machine capable of generating an outwardly-directed, steerable, variable centrifugal force to propel the craft in three dimensions. The apparatus comprises a ridged cubic housing containing a means to guide a mass in a circular path that is movable within a circular outer rim centered within the housing. The diameter of the circular path is fixed and the diameter of the outer rim is defined by the confines of the housing. The center of the mass revolving along the path is variable in three dimensions within the housing to effect the direction and magnitude of the vector sum of the centrifugal force created by the mass as it is rotated.

Description:
FIELD OF THE INVENTION  
       [0001]     The present invention relates to an air and space vehicle and propelling means therefore comprised of a Three-Dimension Motive Machine, hereinafter referred to as the cubic TDMM craft, which converts centrifugal force into unidirectional force.  
       BACKGROUND OF THE INVENTION  
       [0002]     Heretofore, various mechanical devices have been proposed for converting centrifugal force into unidirectional force for use in pile drivers, earth compactors, . . . etc . . . , and to move various types of water craft or land wheeled-vehicles. However, except for pile drivers and earth compactors, these devices have inefficient mechanisms which do not produce sufficient motive force for practical use in any water, land, air or space craft.  
         [0003]     These inventions/devices generally fall into three groups, each utilizing a different technical approach for converting rotational motion into linear motion—namely, those using: 
    1) various weight types, rotating at the end of radii whose lengths are varied by the use of cams or by other means (such as changing the amount of liquid inside cylinders to move piston and rod assemblies back and forth) in order to convert centrifugal force into a unidirectional force along a selected path,     2) electromagnets of one type or another, to control the continually varying distances of weights from their common axis of rotation (in order to convert centrifugal force into a unidirectional force) and     3) various gyroscopic configurations to do the same as above.    
 
         [0007]     Selected examples of the above-mentioned three basic approaches (one in each of the three groups) are presented in the following section.  
       DISCUSSION OF THE RELATED ARTS  
       [0008]     U.S. Pat. No. 5,488,877 for “Centrifugal Inertia Drive”, issued Feb. 6, 1996 to Richard L. Lieurance, uses a “centrifugal inertia drive to produce a resultant force vector with amplitude and direction”, with the possibility of a two-dimensional capability. In its basic mechanism, as shown in FIG. 9 of Lieurance, a single cell composed of two phases that are connected by interconnections 7 (with a fixed length D of 12 inches) moves back and forth along two guides 2. The two guides are connected to a fixed, off-center rotational shaft 1 and interact with circular paths through rollers. This causes the radius of each of the two phases to vary their respective lengths from their center of rotation (shaft 1). As a result, two separate and differently varying anti-parallel force vectors are then created which vectorially combine to produce a single resultant force vector in one selected linear direction (in the direction of the greater force vector). However, because the use of that single cell alone causes a pulsing force in the selected direction, the inventor suggests using four cells on the single rotational shaft 1 (see FIG. 5 of Lieurance) in order to obtain “a more uniform resultant force vector”, varying between 5 lbs and 120 lbs, as the rotation varies from 100 to 600 rpm (see graph in FIG. 8 of Lieurance).  
         [0009]     Although the two-phase single cell model in FIG. 9 of Lieurance (which the inventor selected to demonstrate and describe his theory behind the Centrifugal Inertia Drive) works well when used alone, the four-cell concept shown in FIG. 5 of Lieurance may not work at all—because, as the four cells rotate about their common axis (shaft 1 of FIG. 9 of Lieurance) and continually move back and forth in different directions (45 degrees apart) along their guides 2, their respective constant-length interconnections 7 (which, as shown in FIGS. 6 a  to 6 d  and 9 of Lieurance, are centered in the center of the top and bottom sides of each phase) appear as if they might interfere with one another as they move back and forth in the same physical space.  
         [0010]     The Summary and Scope section, column 7, lines 54-57, states that force retainer 4 (which is shown as stationary in FIG. 9 of Lieurance) “may be realigned or movable to redirect the resultant force vector within a 360-degree plane of shaft 1 rotation”. How this is accomplished is not explained. However, if done, this would give the four-cell Centrifugal Inertia Drive a two-dimensional capability (assuming that the above-mentioned possible interconnection 7 interference problem is solved).  
         [0011]     U.S. Pat. No. 5,782,134 for “Electromagnetically Actuated Thrust Generator”, issued Jul. 21, 1998 to James D. Booden, discloses an electromagnetically-actuated thrust generator, which converts electricity into unidirectional thrust”. It consists of “a hybrid of electromagnetically-operated elements” which, in conjunction with a number of other mechanical components rotating about a common axis, produces a resultant centrifugal force in a desired direction. The thrust generator is basically composed of an outside 4-inch radius circular housing, an electric motor (for rotating the housing about a common axis) and five equally-spaced assemblies of weights—which are each independently actuated by an electromagnet (controlled by a central microprocessor) from a retracted radius of 4 inches (0.3333 ft) to an extended radius of 5 inches (0.4167 ft) from a common axis of rotation. The inventor calculated a few thrust generator performance values (see table in column 4 of Booden) using the standard force equation F=MA, in which the mass M=(2 lbs)/(32.174 ft/sec 2 )=0.062162 slugs and the radial component of acceleration A=V 2 /R, in which the tangential velocity V=2πR(rps), where R is the variable-length radius in feet and rps is the number of revolutions per second. The calculations were done for 600 rpm to 1200 rpm (or 10 rps to 20 rps) in increments of 100 rpm. At 600 rpm, the thrust generator produces a thrust of 102.8 lbs with the 5-inch extended radius (or, F=MA=(0.062162 slugs)(2 π(0.417 ft)10 rps) 2 )/0.417 ft=102.33 lbs) and a thrust lbs with the 4-inch retracted radius in the opposite direction, which vectorially add to a net thrust (102.8−82.2)=20.6 lbs. Similarly, at 1200 rpm, the generator produces a net thrust of 82.43 lbs.  
         [0012]     However, the above two net thrust values are only approximations, which should not have been calculated as if they were opposite (anti-parallel) vectors—because, as shown in FIGS. 1 and 2 of Booden, there are 5 equally-spaced (72 degrees apart) electromagnet/weight assemblies (with none of them being opposite pairs). In order to obtain a more accurate net thrust value, one should instead have first calculated the respective distances (radial lengths) of the 5 weights from their common axis separately (which should vary between 4 and 5 inches) as functions of their angle of rotation, and then use these 5 radial lengths to obtain their five different force vectors (for both the 600 and the 1200 rpm)—which, with the use of the triangle and the polygon methods shown in FIG. 33 herein, could finally be vectorially combined into a single, more accurate and representative net resultant thrust vector value for the thrust generator.  
         [0013]     Furthermore, if one assumes a realistic total weight approximation (because the patent does not provide any part/system weight information) for the entire thrust generator, there is a possibility that the total net weight for the entire thrust generator will greater than even its larger inventor-calculated net thrust of 82.43 lbs at 1200 rpm can handle in a vertical ascent against the force of gravity on earth. This is because, since the system includes two counter-rotating units and that each counter-rotating assembly includes 5 weights, 5 electromagnetic actuators, a circular 4-inch radius housing, an electronic controller, an electric motor, some kind of power supply, various structures and an outer frame enclosing the entire thrust generator, the thrust generator&#39;s total weight might limit its operation to a two-dimensional, horizontal plane only.  
         [0014]     Finally, at the end of the inventor&#39;s abstract, the patent suggests that several such thrust generator systems, arranged in counter-rotating co-planar pairs along the three X, Y and Z axes, can be “utilized to produce a smooth unidirectional thrust along any vector” in three dimensions. Based on the teachings of the patent, this is not likely to be feasible. Firstly, the abstract is the only place in the entire document where such a suggested possibility is mentioned. Therefore, since the inventor fails to explain how to put together all his hardware to build a machine capable of three-dimensional operation, one has to assume that the patent is primarily interested in explaining the concept of “converting electricity into unidirectional thrust in two dimensions” on a flat, horizontal surface. In addition, because a single thrust generator system&#39;s net thrust of 82.43 lbs at 1200 rpm may not be sufficient to handle its total estimated weight in a vertical ascent from earth (working against the earth&#39;s force of gravity), trying to arrange several of them “in counter-rotating coplanar pairs along the X, Y and Z axes” is not likely to produce a three-dimensional operation either—since a larger and heavier frame structure would certainly be required. Secondly, based on several statements within the patent, namely: “The present description set forth is one of a variety of possible configurations . . . ”, at column 2, lines 20 et seq., . . . etc . . . , and others (column 2, lines 62 and seq., column 3, lines 49 and seq., column 3, lines 64 and seq., column 4, lines 10 and seq., . . . etc . . . ), it may not be possible, even for “a person versed in the art”, to easily make and operate the thrust generator (or some of the other suggested possible options thereof, which were not discussed), mostly due to a lack of information on how exactly to do it. In conclusion, this system&#39;s two-dimensional plane capability is not by itself a feature that can easily be changed into a three-dimensional plane capability without the proper information on how to do it.  
         [0015]     U.S. Pat. No. 5,860,317 for “Propulsion System”, issued Jan. 19, 1999 to Eric Laithwaite et al., “relates to a propulsion and positioning system for a vehicle”, with “particular utility in the propulsion and/or positioning of space vehicles” (which suggests a three-dimensional capability). Basically, the propulsion system relies solely on controlling four sets of spinning gyroscopes (with built-in assemblies of rotating masses) to create the required propulsion along a desired path. However, due to a lack of gyroscopically-generated propulsion force results for propelling the combined weight of the apparatus/vehicle (which was not mentioned), it is impossible to evaluate the capability of such an apparatus. Even though the patent claims that a person “skilled in the art will be able to envisage a number of ways of supplying the required controlling torque power to the apparatus” to make it work properly, it appears to be a complicated way for obtaining a controlled propulsion along a desired direction.  
         [0016]     All three inventions discussed above (which were selected for review and evaluation because they are most closely related to the present cubic TDMM craft invention) suggest the possibility of being able to develop a single resultant force along any selected direction in three dimensions, by simply doing or adding one thing or another to them. However, after carefully reviewing the three patents, and although their inventors claim a three dimensional propulsion capability for their inventions, they appear to be limited to a two-dimensional plane capability only—mostly because the inventors do not provide enough information in their patents to help a persons interested in their “art” to: 
    1) make the necessary changes and/or modifications to their inventions to give them a three-dimensional capability, for use on vehicles or crafts (which they leave to persons “versed in the art” to figure out) and/or     2) calculate, or at least estimate, the total weight of their inventions/devices, in order to determine whether or not their calculated thrust would be sufficient to provide them with vertical lift capability against the force of gravity on earth (which would be an important first requirement for three-dimensional motion in a “near-earth” environment).    
 
         [0019]     Furthermore, the detailed (and sometimes complex) descriptions provided by the inventors in the write-ups and accompanying drawings of the three selected patents often makes it difficult to detect any possible mechanical/electrical operational flaws in their inventions. For example, such a possible design flaw may exist with the interconnection 7 which, as described in the most closely related patent to Lieurance, might create a physical/operational interference problem when several two-phase cells are added to his basic one two-phase cell mechanism.  
       Comparison of the Prior Art with the Present Cubic TDMM Craft Invention  
       [0020]     By comparison with the above three selected patents (as well as others), the cubic TDMM craft invention uses a built-in steerable, variable resultant centrifugal force motive mechanism to propel itself with unparalleled performance and maneuverability in three dimensions on earth and in outer space—and, unlike present-day aircrafts, doesn&#39;t need wings nor tails to be flown in any atmospheric environment.  
         [0021]     The full complement of the 600-lb cubic TDMM craft model basically consists of an external 100-inch cubic frame  10 , a 96×9×24-inch parallelepiped internal frame  13  (a dashed outline of which is shown in  FIG. 1 , inside the external cubic frame) and a steerable, variable centrifugal force motive machine mechanism, hereinafter simply referred to as the Machine (which is enclosed in the internal housing frame  13 ).  
         [0022]     As shown in  FIG. 2 , the internal housing frame  13  is divided into two equal halves,  16 A on the left and  16 B on the right, separated by the central square plate  15 . The internal housing frame  13  (which encloses the Machine) can be horizontally rotated in either direction about a central, vertical axis  14  (shown as a vertical dashed line in  FIG. 1 ) inside the larger external cubic frame  10 . The said Machine is itself also divided into two identical mirror-image halves—with each Machine half mounted inside its own internal housing frame half.  
         [0023]     The cubic TDMM craft&#39;s spectacular performance capability (see  FIGS. 41 through 48 ) is basically and solely due to the innovative, combined use of only three simple mechanical component parts in each Machine mirror-image half, namely: 
    1) a fixed 4-foot-radius circular outer rim  34  (see  FIG. 10 ),     2) a smaller, movable 3-foot-radius circular inner rim  33  (see  FIG. 8 ) and     3) a telescoping full extension slide  46  (see  FIGS. 3, 4  and  5 ), which is extendable from 2 ft (fully closed) to 4 ft (fully opened).    
 
         [0027]     The telescoping slide  46  in (3) above is used in two different (and very important) applications in each Machine mirror-image half, namely: 
    1) in a set of 8 rotating variable-length (telescoping) subassemblies  40  (each comprised of one slide  46  and of one 2-wheel device  47 —see  FIGS. 9, 11  and  12 ) and     2) in a two-dimension, all-way movable mechanism  49 , in which it is used in two pairs of slide assemblies  21 L and  21 R (to vertically move plate  25  up and down) and 27U and 27D (to horizontally move plate  29  back and forth), as shown in  FIGS. 6, 7  and  8 .    
 
         [0030]     By combining the variable vertical motion of plate  25  with the variable horizontal motion of plate  29  (which is mounted on plate  25  —see  FIGS. 7 and 8 ), plate  29  can be moved anywhere within the area outlined by the central square plate  15  (see  FIG. 6 ), thereby causing inner rim  33  (which, as shown in  FIG. 8 , is mounted on the opposite side of plate  29 ) to also move with plate  29  anywhere within the vertical plane of the fixed, circular outer rim  34 .  
         [0031]     Each set of 8 variable-length subassemblies  40  in the Machine rotates inside the vertical plane of its own inner rim about a fixed axis (point  0 ), which is aligned with the common center of both the fixed outer rim  34  and the central square plate  15 , in either the “neutral position” (see  FIG. 11 ), in which inner rim  33  is in the center of outer rim  34  (with its center point P superimposed on the fixed point  0  of outer rim  34 ), or in the “active position” (see  FIG. 12 ), in which inner rim  33  has been moved to make contact with the inside surface of outer rim  34  at 180 degrees—thereby providing the cubic TDMM craft with the maximum vertical motive force. The fixed outer rim  34  (see  FIG. 10 ), which is mounted inside the left  16 A side half of the internal housing frame  13  (see  FIG. 2 ), acts as a circular boundary for the movable inner rim  33  which, in turn, acts as a movable circular track for the 2-wheel devices  47  (which, as shown in  FIG. 9 , are mounted at the ends of the 8 variable-length subassemblies  40 ).  
         [0032]     In the cubic TDMM craft invention, the external cubic frame  10 , the internal housing frame  13  and its enclosed Machine are designed to work together as one unit, to generate a single, smooth, steerable and variable motive force capable of propelling the cubic craft with unmatched (unequaled) performance and maneuverability (not presently available in any air and space craft) in any desired direction in three dimensions—thereby giving the cubic craft four major advantages over the three most closely related inventions discussed earlier, namely: 
    1) the three-dimensional operation and re-direction capabilities of the cubic TDMM craft are already incorporated (built-in) in its design (as indicated and described in the drawings, diagrams and related write-ups and specifications),     2) only one TDMM mechanism is required to propel the said cubic craft in any chosen direction in three dimensions (instead of, for example, having to use “a plurality of Thrust Generator systems, arranged in counter-rotating coplanar pairs along the three X, Y and Z axes of three-dimensional space, in order to produce a smooth, unidirectional thrust along any vector”, as suggested in the abstract of Booden),     3) the cubic TDMM craft&#39;s Machine can generate a single, outwardly-directed, maximum resultant centrifugal force (ResF) of 3,978.8 lbs (which is obtained by doubling the 1,989.4 lbs generated by each of the Machine&#39;s two sets of 8 variable-length subassemblies  40 —see  FIGS. 32 and 33 ) in any selected direction (in which, as shown in  FIGS. 12, 13 ,  14  and  51 , the inner rims are making contact with their respective outer rims) and     4) the cubic TDMM craft&#39;s maximum propulsion capability is simply obtained by combining the selected direction of the ResF mentioned in (3) above with the chosen horizontal direction (azimuth) of the internal housing frame  13  inside the external cubic frame  10 —thereby providing a steerable, powerful maximum motive force, capable of propelling the said cubic craft (or any other air/space craft type) in any desired direction in three dimensions, anywhere on earth and in outer space.    
 
         [0037]     The cubic TDMM craft&#39;s maximum ResF mentioned in (3) above is many times greater than is needed to propel the 600-lbs cubic craft (see Table 2) in any selected direction in three dimensions (which is far greater than Booden&#39;s net thrust of 82.43 lbs at 1200 rpm). Also, as a result of the features mentioned in (1), (2), (3) and (4) above, the said cubic craft can: 
    1) quickly make any turn in three-dimensional space (including a 90-degree or a 180-degree turn) while in flight without having to make a long arced turn (like most aircrafts, missiles and rockets presently must do),    
 
         [0039]     2) take off and land anywhere, or remain stationary over any selected point, on earth and in outer space, and, 
    3) by using only the 50 rad/sec angular velocity in the Machine (to counter-rotate the two sets of 8 subassemblies  40 ), be able to reach a vertical 250-mile “near-earth” orbit in less than 6 minutes, go to the moon&#39;s “far-earth” distance of about 230,000.0 miles from earth and safely land there in about 3.0 hours and even go to the planet Mars (when it is about 35 million miles from earth) and also safely land there in about 33 hours.    
 
         [0041]     The two one-way fight times to the moon and to Mars mentioned in (3) above are based on a constant cubic craft acceleration and deceleration of 53.4 ft/sec 2  rad/sec (see the 50 rad/sec plots of  FIGS. 41 and 45 ), which are respectively used in each half-way distances to the moon and to Mars—assuming the availability of a sufficient and constant source of electrical power to operate and propel the cubic TDMM craft during those two“far-earth” entire space voyages.  
         [0042]     All the above capabilities can simply be accomplished by first moving the Machine&#39;s two circular inner rims towards a new selected direction inside the fixed vertical planes of their respective outer rims and then by giving the internal housing frame  13  a new horizontal direction (bearing) inside, and relative to, the external cubic frame  10  (see  FIGS. 1, 2  and  53 ).  
       OBJECTIVES OF THE INVENTION  
       [0043]     The underlying objective of the invention is to provide a variable centrifugal force steerable in three dimensions.  
         [0044]     A primary objective of the invention is to adapt centrifugal force as a variable motive power source for moving any air and space craft type through three dimensional space.  
         [0045]     Another objective of the invention is to provide an internal motive power source for a wingless and tailless air/space cubic craft, using centrifugal force as a steerable, variable motive force—to thereby eliminate the need for propellers, fans, jets, rockets or other reaction generating motive means.  
         [0046]     A further objective of the invention is to provide a steerable, variable centrifugal force motive machine that is capable of moving any government and/or civilian land-wheeled-vehicle and of propelling any water, air and space craft in any chosen direction in three dimensions with greater performance and maneuverability capabilities than are presently available anywhere.  
       SUMMARY OF THE INVENTION  
       [0047]     The invention is presented herein as a 600-lb wingless and tailless cubic air/space craft model with a built-in steerable, variable centrifugal force “Three-Dimension Motive Machine” (TDMM), herein simply referred to as the cubic TDMM craft. This example of the invention is exemplary only and intended to provide what is deemed to be the a “best mode” considering the present state of the relevant arts. It is not meant to be limiting and manned and unmanned versions of various sizes are contemplated.  
         [0048]     The TDMM mechanism part of the invention gives the cubic craft unparalleled three-dimensional motion and maneuverability capabilities—which can also be implemented for use in any land-wheeled-vehicle, water, air and space craft, and even in missiles and rockets.  
         [0049]     The cubic TDMM craft selected as an exemplary embodyment basically consists of an external 100-inch cubic frame  10 , a 96×96×24-inch parallelepiped internal housing frame  13  and a steerable, variable centrifugal force two-dimension motive machine (which is enclosed in the internal housing frame  13 ) and is herein simply referred to as the Machine. As shown in  FIGS. 1, 2  and  53 , the internal housing frame  13  is rotatable, inside the larger external cubic frame  10  about a central, vertical axis  14  (which runs between the two swivel assemblies  11  and  12 , through the middle of the central square plate  15 ) towards any chosen horizontal direction (azimuth)—thereby causing the enclosed Machine to rotate with it. Therefore, the function of the two swivel assemblies  11  and  12  is to support and rotate the internal housing frame  13  (see  FIGS. 51 and 52 ).  
         [0050]     The Machine is divided into two identical mirror-image halves, separated by the central square plate  15 —which, as shown in  FIGS. 2 and 51 , also divides the internal housing frame  13  into two equal halves,  16 A on the left and  16 B on the right. Each half of the internal housing frame  13  encloses one Machine mirror-image half. However, since both Machine mirror-image halves are identical, only the left half (in the internal housing frame  16 A side) is described next.  
         [0051]     The left Machine mirror-image half basically consists of: 
    1) one set of 8 identical, equally-spaced subassemblies  40  (rotating about a fixed axis at point  0 —see  FIGS. 11 and 12 ), with each subassembly consisting of a telescoping slide  46  (see  FIGS. 3 , and  4 ) and of a two-wheel device  47  mounted at its other end (see  FIG. 9 ),     2) one movable, circular inner rim  33  (see  FIGS. 8, 9 ,  11  and  12 ), which acts as a circular track for the 2-wheel devices  47 , and     3) one fixed circular outer rim  34  (which, as shown in  FIG. 10 , is vertically-mounted inscribed on the four inside surfaces of the left  16 A side half of the internal housing frame  13 ), and which also acts as a circular boundary for the movable inner rim  33  in (2) above.    
 
         [0055]     When the movable inner rim  33 , which is initially in the “neutral position” in the center of the fixed outer rim (see  FIG. 11 ), is moved sideways in any selected direction until it makes contact with the inside surface of outer rim  34  (see  FIG. 12 ), then the  8  telescoping subassemblies  40  are now rotating in the maximum “active position”—in which they continually vary their radial lengths as they rotate counterclockwise (inside the vertical plane of the movable inner rim  33 ) about their now off-center, fixed point  0  (relative to the inner rim&#39;s center point P). As a result, according to the centrifugal force equation (1) in ¶0113, these 8 different variable-length subassemblies  40  also simultaneously generate 8 different centrifugal forces F c —which automatically vectorially combine into a single resultant centrifugal force ResF, which is always pointing in the same selected outward direction in which the inner rim is making contact with the outer rim&#39;s inside surface.  
         [0056]     Finally, by combining the selected direction of the above-mentioned ResF (which is generated by the two sets of 8 subassemblies  40 , counter-rotating in the vertical planes of their respective inner rims) with the chosen horizontal direction (azimuth) of the internal housing frame  13 , a powerful motive force is then available for impelling the cubic TDMM craft in any desired direction in three dimensions with unparalleled performance and maneuverability. 
     
    
     BRIEF DESCRIPTIONS OF THE DRAWINGS  
       [0057]     There is a total of 54 figures, representing the various drawings, diagrams and plots of the cubic TDMM craft invention&#39;s performance results.  
         [0058]      FIG. 1  shows a simple three-dimensional view of an exemplary form of the cubic TDMM craft, which consists of the external cubic frame  10 , the parallelepiped internal housing frame  13  (shown as a dashed outline) and the bottom and top swivel-and-sprocket assemblies  11  and  12 . Swivel assemblies  11  and  12  are used for supporting the internal housing frame (in which the Machine is enclosed) and for horizontally rotating it about the central vertical axis  14  (shown as a dashed line, running between the centers of both) in either direction inside the external cubic frame  10 .  
         [0059]      FIG. 2  shows a top view of the cubic TDMM craft, showing the relationship between the external cubic frame  10 , the internal housing frame  13  (which encloses the Machine), the top swivel-and-sprocket assembly  12 , a top end-view of the square central plate  15  (which divides the internal housing frame  13  into two equal halves,  16 A on the left and  16 B on the right) and the clearance required to allow the internal housing frame a full 360-degree rotation about its central axis  14  in either direction without interference with the inside surfaces the external cubic frame. A dashed circle, representing the circular external cylindrical frame  60  (which is used later in  FIG. 54 ), is also shown in this figure.  
         [0060]      FIGS. 3, 4  and  5  show three diagrams (on the same page) of a commercially available (hardware-store-bought) “telescoping full extension slide”, hereinafter referred to as slide  46 . Slide  46  is shown in the closed, opened and closed end-view positions respectively. The telescoping (variable-length) slide  46  is the most important and most rotationally efficient part in the Machine, in which it is used in two separate applications, namely: 
    1) in the two sets of 8 counter-rotating variable-length subassemblies  40  (with one set in each Machine mirror-image half—see  FIGS. 11 and 12  for example) and     2) in slide assemblies  21 L,  21 R,  22 L, 22 R,  27 H,  27 D,  28 U and  28 D (see  FIGS. 6, 7 ,  13   14 ), in which it is joined in pairs to movably couple the central square plate  15  to the vertically-movable plates  25  and  26  and to movably couple plates  25  and  26  to the horizontally-movable plates  29  and  30 .      
         [0063]      FIG. 6  shows a front-view diagram of the fixed 96-inch square central plate&#39;s left  15 A side, upon which a pair of vertically-moving slide assemblies, respectively numbered  21 L on the left and  21 R on the right, are mounted as shown. Each slide assembly consists of a pair of telescoping slides  46  (one open and one closed—see  FIGS. 3 and 4 ) which are joined in pairs, end to end, so as to allow them to alternately slide back and forth together, such that when one is fully opened, the other one is fully closed and vice versa.  
         [0064]      FIG. 7  is a diagram of the 72-inch square plate  25 , which is mounted directly onto the four movable sections  43  (see  FIG. 4 ) of the two pairs of vertical slide assemblies  21 L and  21 R on the square plate&#39;s left  15 A side (see  FIG. 6 ), thereby enabling vertical movement of plate  25  with respect to the square central plate  15 . Two more pairs of slide assemblies,  27 U and  27 D, are also horizontally-mounted on the opposite side of plate  25  (away from the central plate  15 ).  
         [0065]      FIG. 8  is a diagram of a second 72-inch square plate  29 , which is mounted directly onto the four movable sections  43  of the two horizontal pairs of slide assemblies  27 U and  27 D of  FIG. 7 , thereby enabling horizontal movement of plate  29  with respect to plate  15 . A 72-inch-diameter circular inner rim  33  is also mounted inscribed on the other side of plate  29  as shown.  
         [0066]      FIG. 9  shows how each of the 8 rotating subassemblies  40  (shown in the “neutral position” in  FIG. 11  and in the “active position” in  FIG. 12 ) consists of one telescoping slide  46  and of one 2-wheel device  47  (attached at the end of its sliding section  43 ) and how its stationary (non-movable) section  41  (see  FIG. 4 ) is mounted directly as shown onto a 16-inch-radius circular metal disk  31 , which is itself secured onto a high-speed hub  44  with 4 bolts (see  FIG. 50 ). The set of 8 subassemblies  40 , the metal disk  31  and the hub  44  all rotate together as one unit about the fixed stub axle  45 , located at the fixed point  0 .  
         [0067]      FIG. 10  shows how the fixed 96-inch-diameter outer rim  34  is mounted inscribed onto the inside surfaces of the four rectangular 96×12-inch side-walls of the internal housing frame&#39;s right  16 A-side (see  FIG. 2 ) in 8 equally-spaced places, as shown in the front-view diagram. The internal housing frame&#39;s side-view diagram shows end-views of both the outer rim  34 , which is vertically mounted in the middle of the internal housing frame&#39;s left  16 A-side, and of the 96-inch square central plate  15  (see  FIG. 2 ).  
         [0068]      FIG. 11  is a diagram showing the relationship between the fixed outer rim  34  (see  FIG. 10 ), the movable circular inner rim  33  (see  FIG. 8 ) and the set of 8 equally-spaced subassemblies  40 . Inner rim  33  is shown here in the “neutral position” (in the center of outer rim  34 ), in which, as shown in  FIG. 9 , the 8 subassemblies  40  (each consisting of one slide  46  and one 2-wheel device  47 ) are all forced to be of equal lengths, rotating at 100 rad/sec about both superimposed point P (the movable inner rim&#39;s center) and point  0  (the outer rim&#39;s fixed center) inside the vertical plane of the movable circular inner rim  33 . The 8 subassemblies  40  are numbered from 1 to 8 for future reference.  
         [0069]      FIG. 12  shows another diagram illustrating the relationship between the fixed outer rim  34  (see  FIG. 10 ), the movable circular inner rim  33  (see  FIG. 8 ) and the 8 equally-spaced variable-length (telescoping) subassemblies  40 , rotating at 100 rad/sec about the outer rim&#39;s fixed, off-center point  0  (with respect to the inner rim&#39;s center point P). Here, inner rim  33  is shown in the maximum “active position”, in which it has been vertically moved up by the two-dimension all-way movable mechanism  49  to make contact with the inside surface of outer rim  34  at 180 degrees, thereby forcing the 8 subassemblies  40  to all have different lengths, as functions of their angles of rotation. The 8 subassemblies  40  are also numbered from 1 to 8 for future reference.  
         [0070]      FIGS. 13 and 14  show two sets of three diagrams (on the same page), each representing the relationship of the various slide assemblies, plates, inner rims and outer rims (shown in  FIGS. 6, 7  and  8 ) in each mirror-image half of the two-dimension, all-way movable mechanism  49  (respectively mounted on sides  15 A and  15 B of the central plate). These two figures can be used as reference maps for visually locating the various plates, slide assemblies, inner rims and outer rims in the Machine&#39;s two-dimension, movable mechanism  49 .  
         [0071]      FIG. 15  illustrates the trigonometric relationships between sides a, b and c and angles A, B and C of any triangle. Sides a, b and c respectively represent the variable-length radius R 3   W  (i.e., subassembly  40 ), the constant-length radius R 1   W  of inner rim  33  and segment R 2  (shown between points P and  0 ). As shown in  FIGS. 9, 11  and  12 , the subscript ( W ) is used in both R 1   W  and R 3   W  to indicate that their radial lengths are from points P and  0  respectively to the inside surface of inner rim  33  (see  FIG. 8 )—on the inside surface of which the two-wheel devices  47  (hereinafter also referred to as W for wheels) run. The angles A, B and C and their opposite sides R 3   W , R 1   W  and R 2  (representing the triangle&#39;s sides a, b and c respectively) are used in the derivation of the variable-length radius R 3   W  (see equations A1 through A5), in which R 3   W  is calculated as a function of angle theta0, rotating about the fixed, off-center point  0 . In this figure, the variable-length R 3   W =3.62 ft, for an angle value theta0=135 deg.  
         [0072]      FIG. 16  shows two diametrically opposite (antiparallel) variable-length radii R 3   W  of different lengths, along the 0-to-180 degree line through the fixed off-center point  0 , when rotating in the maximum “active position” about point  0 .  
         [0073]      FIG. 17  shows two diametrically opposite (antiparallel) variable-length radii R 3   W  of different lengths, along the 45-to-225 degree line through the fixed off-center point  0 , when rotating in the maximum “active position” about point  0 .  
         [0074]      FIG. 18  shows two diametrically opposite (antiparallel) variable-lengths radii R 3   W  of equal lengths, along the 90-to-270 degree line through the fixed off-center point  0 , when rotating in the maximum “active position” about point  0 .  
         [0075]      FIG. 19  illustrates the constant-length radius R 1   W  of inner rim  33  (with center at point P) and its radius of gyration R 1   br  (with center at point S), running along the dashed circular locus of R 1   br . Here, both R 1   W  and R 1   br  rotate in the “neutral position” about the fixed point  0 , upon which their respective points P and S are superimposed.  
         [0076]      FIG. 20  shows the variable-length radius R 3   W  (from the fixed, off-center point  0  to the inside surface of inner rim  33 ) and its variable-length radius of gyration R 3   br  (from the fixed point  0  to its circular locus, shown as a dashed circle with center at point S and constant-length radius R s ). Both R 3   W  and R 3   br  rotate about the fixed point  0  in the maximum “active position”.  
         [0077]      FIG. 21  is a graphical representation of the rotational tangential force FT, the radial force FR and the resultant centrifugal force ResF) and their related angles ALF (between FR and ResF), A (which is the direction of FR from point P) and DIRA (which is the direction of ResF from the fixed point  0 ). All angles and forces shown here are for theta0=40 degrees.  
         [0078]      FIG. 22  presents plots of angles ALF, A and DIRA as functions of theta0. Note that the ALF, A and DIRA angle values shown in  FIG. 21  can also be found at theta0=40 degrees.  
         [0079]      FIG. 23  presents plots of the variable-length radius R 3   W , for W (running along the inside surface of inner rim  33 ) and of the variable-length bar&#39;s radius of gyration R 3   br , for slide  46  (running along the dashed circular locus of R 3   br —see  FIG. 20 ) as functions of theta0. R 3   W  and R 3   br  were obtained with one variable-length subassembly  40  only, rotating about the fixed, off-center point  0 . Plots of the constant-length radii R 1   W , for W, and R 1   br , for the bar (see  FIG. 19 ), rotating about points P, S and  0 , are also shown here for comparison with R 3   W  and R 3   br .  
         [0080]      FIG. 24  presents plots of the variable tangential velocities VT W , for W, (running along the inside surface of inner rim  33 ), and VT br , for the bar, (running along the locus of its radius of gyration R 3   br —see  FIG. 20 ), as functions of theta0. VT W  and VT br  were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0 . Plots of the constant tangential velocities VT 1   W , for W, and VT 1   br , for the bar, rotating at 100 rad/sec about the inner rim&#39;s center, at point P, are also shown here for comparison with VT W  and VT br .  
         [0081]      FIG. 25  presents a plot of the variable relative angular velocity ω 2 , for W, as a function of theta0. The ω 2  plot was obtained with one subassembly  40  only, as if W were rotating about the inner rim&#39;s center point P, at the end of R 1   W  (see  FIG. 12 ), with variable tangential velocity VT W , instead of rotating at a constant 100 rad/sec about the fixed, off-center point  0 , at the end of R 3   W  with variable tangential velocity VT W . The input constant angular velocity ω 0  plot is shown here for comparison with the variable ω 2  plot.  
         [0082]      FIG. 26  presents plots of the average variable tangential acceleration AT brav  for the bar, AT Wav  for W, and AT av  for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0 .  
         [0083]      FIG. 27  presents plots of the variable radial accelerations AR br  for the bar, AR W  for W and AR for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0 . Their bell shapes depends directly on the tangential velocity plot of VT W  in  FIG. 24 .  
         [0084]      FIG. 28  presents plots of the variable resultant accelerations ResA br  for the bar, ResA W  for W, and ResA for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0 .  
         [0085]      FIG. 29  presents plots of the variable tangential forces FT brav  for the bar, FT Wav  for W and FT av  for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0  (using the basic force equation F=MA, in which M is the mass of the rotating body in slugs and A is its acceleration in ft/sec 2 ).  
         [0086]      FIG. 30  presents plots of the variable radial forces FR br  for the bar, FR W  for W and FR for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0  (using the basic force equation F=MA, in which M is the mass of the rotating body in slugs and A is its acceleration in ft/sec 2 ).  
         [0087]      FIG. 31  presents plots of the variable resultant centrifugal forces ResF br  for the bar, ResF W  for W and ResF for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0  (also using equation F=MA).  
         [0088]      FIG. 32  is a graphical representation of the 8 different centrifugal forces generated by the 8 equally-spaced, variable-length subassemblies  40  shown in  FIG. 12 , acting simultaneously at the fixed, off-center point  0 , about which the 8 subassemblies  40  rotate at 100 rad/sec. These 8 forces can be found in the plot of  FIG. 31 , 45 degrees apart, starting at theta0=0 degree.  
         [0089]      FIG. 33  is a graphical representation of the combined use of the triangle and the polygon methods for vectorially combining the 8 forces shown in  FIG. 32  into a single resultant centrifugal force vector ResF of 1,989.4 lbs, in the direction of 180 degrees (from the fixed, off-center point  0  to the head of the 8th vector), shown as a heavy black arrow closing the polygon.  
         [0090]      FIG. 34  is a plot of 10 SOUCVOL-calculated resultant forces (ResF), obtained for the same set of 8 subassemblies  40  shown in  FIG. 12 , rotating about the fixed, off-center point  0  at 100 rad/sec. They were obtained at every 5-degree starting position of the #1 subassembly  40  (see  FIG. 12 ) from 0 degree to 45 degrees. The 10 calculated ResF values in this plot were also obtained with the combined use of the triangle and the polygon methods shown in  FIG. 33 . The other constant plot represents the average ResF plot of 1,989.46 lbs for the 10 calculated ResF values shown between 1,989.39 lbs and 1,989.54 lbs (for one Machine mirror-image half only).  
         [0091]      FIG. 35  shows another plot of resultant centrifugal force (ResF) results versus angular velocity, generated by one Machine mirror-image half only, using the same set of 8 variable-length subassemblies  40  shown in  FIG. 12 . These ResF values are plotted every 25 rad/sec, from 0 rad/sec to 350 rad/sec. In the upper left corner of this figure, a small table shows the rpm and ResF values associated with each indicated angular velocity, along with two equations to obtain the rpm and the ResF values for any given angular velocity.  
         [0092]      FIG. 36  shows three plots of resultant centrifugal force (ResF) results as functions of 6, 8 and 10 identical, equally-spaced variable-length subassemblies  40 , rotating at 100 rad/sec in each Machine mirror-image half. The IX plot represents the 6, 8 and 10 subassemblies  40  cases, run with one slide  46  (the bar) and one 2-wheel device  47  (W) weighing 1 lb each, a fixed outer rim&#39;s radius R 0 =4 ft and a movable inner rim&#39;s radius R 1 =3 ft. The 2X and 3X plots are for the other two cases run with 2 and 3 times the above weights and radii lengths.  
         [0093]      FIG. 37  presents plots of three constant rotational kinetic energy (KE) results, KE0 br  for the bar, KE0 W  for W and KE0 for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about both superimposed points P and  0  in the “neutral position” (see  FIGS. 11 and 19 ).  
         [0094]      FIG. 38  shows plots of three variable rotational KE results, KE1 br  for the bar, KE1 W  for W and KE1 for both combined, as functions of theta0. They were obtained with one subassembly  40  only, rotating at 100 rad/sec about the fixed, off-center point  0  (relative to the of the inner rim&#39;s center point P) in the maximum “active position” (see  FIGS. 12 and 20 ).  
         [0095]      FIG. 39  is a graphical representation of the 8 rotational KE1 results, shown 45 degrees apart (obtained from  FIG. 38 —with subassembly #1 at 0 degree on inner rim  33 ). They were generated simultaneously by the 8 variable-length subassemblies  40  shown in  FIG. 12 , rotating counterclockwise at 100 rad/sec about the fixed, off-center point  0 .  
         [0096]      FIG. 40  presents both a constant KE2 plot (obtained from the KE0 lot of  FIG. 37 ) and a variable KE3 plot (obtained from the KE1 plot of FIGS.  38 —and/or from  FIG. 39 ) as functions of the cumulative number of identical, equally-spaced, variable-length subassemblies  40  (from 1 to 8, as shown in  FIG. 12 ), rotating at 100 rad/sec about the fixed, off-center point  0 . Both the KE2 and KE3 plots respectively represent the 8 cumulatively-added KE0 and KE1 plotted results, obtained every 45 degrees apart from  FIG. 37  (for the “neutral position”) and from  FIG. 38  (for the “active position”). Note that both the KE2 and KE3 plots are different for the 1 to 7 cumulatively-added KE values, but that both plots end up with the same total cumulative KE values of 14,918.9 ft*lbs when their respective 8th KE values are added.  
         [0097]      FIG. 41  shows five acceleration plots versus vertical “near-earth” altitude, from 0 miles up to 250.0 miles, in the direction of the moon. Three of these plots represent the three cubic TDMM craft accelerations (A cc ), respectively obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec. The other two plots represent the moon&#39;s positive acceleration of gravity (g m ) and the earth&#39;s negative acceleration of gravity (g e ), acting simultaneously on the three cubic craft A cc  plots as functions of “near earth” vertical altitude from earth.  
         [0098]      FIG. 42  presents five plots of force versus vertical “near-earth” altitude, from 0 miles up to 250.0 miles, in the direction of the moon. Three of these plots represent the three cubic TDMM craft motive forces (F cc ), respectively obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec. The other two plots represent the moon&#39;s positive gravitational force (F m ) and the earth&#39;s negative gravitational force (F e ), acting simultaneously on the three cubic craft motive force F cc  plots as functions of “near earth” altitude from earth.  
         [0099]      FIG. 43  shows three plots of cubic TDMM craft velocity (V cc ) versus “near-earth” altitude from earth, from 0 mile up to 250.0 miles, in the direction of the moon. They represent the instantaneous cubic TDMM craft velocities obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec respectively.  
         [0100]      FIG. 44  shows three plots of cubic TDMM craft average flight time (T cc ) from earth launch time (at 0 sec) versus “near-earth” altitude from earth, from 0 mile up to 250.0 miles, in the direction of the moon. They were obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec respectively.  
         [0101]      FIG. 45  shows five acceleration plots versus “far-earth” distance from earth, from 0 miles all the way to the moon, 230,000.0 miles away. Three of these plots represent the three cubic TDMM craft accelerations (A cc ), respectively obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec. The other two plots represent the moon&#39;s positive acceleration of gravity (g m ) and the earth&#39;s negative acceleration of gravity (g e ), acting simultaneously on the three cubic TDMM craft A cc  plots as functions of “far-earth” distance from earth.  
         [0102]      FIG. 46  presents five plots of force versus “far-earth” distance from earth, from 0 miles all the way to the moon, 230,000.0 miles away. Three of the plots represent the three cubic TDMM craft motive forces (F cc ), respectively obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec. The other two plots show the effects of the moon&#39;s positive force (F m ) and the earth&#39;s negative force (F e ), acting simultaneously on the above three cubic TDMM craft F cc  plots as functions of “far-earth” distance from earth.  
         [0103]      FIG. 47  shows three plots of cubic TDMM craft velocity (V cc ) versus “far-earth” distance from earth, from 0 miles all the way to the moon, 230,000.0 miles away. They represent the instantaneous cubic TDMM craft velocities obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec respectively.  
         [0104]      FIG. 48  shows three plots of cubic TDMM craft average flight time (T cc ) from earth launch time (at 0 sec) versus vertical “far-earth” distance from earth, from 0 miles all the way to the moon, 230,000.0 miles away. They were obtained with the three Machine angular velocities (ω) of 50, 75 and 100 rad/sec respectively.  
         [0105]      FIG. 49  shows diagrams of an 11-inch square heavy-duty swivel and of three different sprockets  66 ,  53  and  52 , with 60, 40 and 20 teeth respectively. These sprockets are variously used with motors and chains in the swivel-and-sprocket assemblies  11  and  12  (see  FIG. 51 ) and in the idler subassembly  72  (see  FIG. 53 ), for horizontally-rotating the internal housing frame  13  (see  FIGS. 1, 2 ), and for providing rotation to the Machine&#39;s two sets of 8 subassemblies  40  (see  FIGS. 11, 12 ,  50  and  51 ).  
         [0106]      FIG. 50  presents a cross-sectional diagram of the right Machine mirror-image half (which is enclosed in the right  16 B half side of the internal housing frame  13 ), along with front and side-view diagrams of the heavy-duty, high-speed hub  44  (which comes with two tapered ball-bearings) and a side view of the stub axle  45 . Stub axle  45  is used as the fixed axis, about which the hub  44 , the circular 16-inch radius metal disk  31  (see  FIG. 9 ) and the set of 8 telescoping subassemblies  40  rotate together as one unit. This figure also shows the relationship between the upper part of the circular inner rim  35  (making contact with the inside surface of outer rim  36 ), the set of 8 telescoping subassemblies  40 , rotating about the fixed stub axle  45  (which is shown mounted in line with the fixed center point  0 ) and the ½ hp, 1800 rpm electric motor  51  and its motor mount  57  (which are mounted on the square 96×96-inch  16 A-side-wall of the internal housing frame  13  as shown). The 20-tooth sprocket  52  of motor  51  provides rotation to the coupled 40-tooth sprocket  53  and the set of 8 subassemblies  40  by means of a #35 chain  54  (which goes around both sprockets  52  and  53 ).  
         [0107]      FIG. 51  consists of two parts, A and B. The upper part A shows a cross-sectional cut-away view diagram of the entire cubic TDMM craft, illustrating the relationship between the external cubic frame  10 , the internal housing frame  13  and the two Machine mirror-image halves, separated by the central square plate  15 . Also shown in part A are the two motors  51 , which (as shown in  FIG. 50 ) provide counter-rotation to the two sets of 8 subassemblies  40 , and the other two motors  64  which, via sprockets, chains and swivel-and-sprocket assemblies  11  and  12 , provide horizontal counter-rotations to both the internal housing frame  13  and to the external cubic frame  10 . A power and control unit (P/CU)  67  is also shown mounted in the center of the lower left outside of the internal housing frame&#39;s  16 A side. The lower part B of  FIG. 51  shows two side-view halves of the swivel-and-sprocket assemblies  12  and  11  respectively, and how they are both mounted sandwiched between the bottom and top centers of both the external cubic frame  10  and the internal housing frame  13 .  
         [0108]      FIG. 52  shows a diagram of the cross-sectional side-view of the left Machine mirror-image half (mounted in the  16 A-side of the internal housing frame  13 ), showing the relationship between the external cubic frame  10 , the internal housing frame  13 , the bottom and top swivel-and-sprocket assemblies  11  and  12 , the fixed outer rim  34 , the movable circular inner rim  33  (shown in the maximum “active position”, making contact with the inside surface of outer rim  34  at 180 degrees) and the set of 8 variable-length subassemblies  40 , rotating at 100 rad/sec about the fixed off-center point  0  (relative to the movable inner rim&#39;s center point P).  
         [0109]      FIG. 53  is a top-view diagram of the cubic TDMM craft, showing the relationship between the external cubic frame  10 , the alternate cylindrical frame  60  (shown as a 100-inch-diameter dashed circle for use in  FIG. 54 ), the internal housing frame  13  (which encloses the Machine) and the central square plate  15  (separating the internal housing frame  13  into two half sides  16 A and  16 B). It also illustrates the top two-stage rpm-reducing arrangement that is used for reducing the 1800 rpm of motor  64  down to 32 rpm at the swivel assembly  12 —which, being coupled to the internal housing frame  13 , also causes the said internal housing frame  13  to rotate horizontally with it at 32 rpm inside the external cubic frame  10 . The two-stage rpm-reducing arrangement consists of motor  64  and its 8-tooth sprocket  65  (which, as shown in  FIG. 51 , is secured onto the upper outside of the internal housing frame  13  with motor mount  63 ), of idler subassembly  72  (which consists of a pair of free-wheeling sprockets  65  and  66 , secured together as one unit), mounted on top of the internal housing frame  13  as shown, of the top swivel assembly  12  and its coupled 60-tooth sprocket  66  (see part B of  FIG. 51 ) and of the two #35 chains  54 .  
         [0110]      FIG. 54  is a diagram of an application of the invention, depicting a “flying saucer”. The alternate internal cylindrical frame  60 , which is first shown in  FIGS. 2 and 53  (looking like a dashed circle) is shown here looking like a square in the upper part A side-view diagram and looking like a circle in the lower part B top-view diagram. In this figure, the cubic craft&#39;s built-in TDMM has been adapted to drive this conceptual reduction of the invention to practice. 
     
    
     DESCRIPTION OF THE PREFERRED EMBODIMENT  
       [0111]     A preferred reduction to practice, the best mode of practicing the invention within the bounds of known engineering arts, is illustrated  FIG. 1 . The wingless and tailless cubic air and space craft with a built-in Three Dimension Motive Machine (TDMM), herein simply referred to as the cubic TDMM craft, basically consists of three separate functional parts, namely: 
        1) an external 100-inch cubic framework  10 ,     2) a 96×96×24-inch internal parallelepiped housing framework  13  (which is sized to fit and freely rotate inside the larger external cubic frame  10 ) and     3) a variable centrifugal force motive machine mechanism (the Machine), which is enclosed inside (2) above.        
 
         [0115]     The physical dimensions mentioned in (1) and (2) above are arbitrary but relative to each other and are a function of both the size and power output desired of the cubic TDMM craft invention.  
         [0116]     To demonstrate the preferred embodiment of the invention, the Machine is enclosed inside the internal housing frame  13 , which can be oriented towards any chosen horizontal direction (azimuth), relative to the external cubic frame  10 , by rotating it about a central, vertical axis  14 , which, as shown in  FIG. 1 , runs between the centers of the two swivel-and-sprocket assemblies  11  and  12 . As also shown in  FIGS. 51 and 52 , the two swivel assemblies  11  and  12  are sandwiched between the centers of the bottom and top sides of both the external cubic frame  10  and the internal housing frame  13 , supporting and rotating the internal housing frame  13  (and its enclosed Machine) inside the larger external cubic frame  10  (see  FIG. 51 ).  
         [0117]     The external 100-inch cubic frame  10  represents the wingless and tailless outer body of the cubic TDMM craft, which is sized to accommodate the dimensions of the smaller rotating internal housing frame  13  (see  FIGS. 1 and 2 ). The external cubic frame  10  is also used in the cubic craft as a variably counter-rotating part to balance out the opposite rotating action of the internal housing frame  13 , in order to obtain a true horizontal orientation (azimuth) for the internal housing frame  13  (and its enclosed Machine).  
         [0118]     The Machine (which is housed in the internal housing frame  13 ) is divided into two identical mirror-image halves, separated by a 96-inch square central plate  15 , which is itself aligned on the central vertical axis  14  (see  FIGS. 1, 2  and  51 ). Each Machine mirror-image half consists of two separate functional parts, working together as one unit in the vertical plane of internal housing frame  13 , namely: 
    1) a two-dimension, all-way movable mechanism  49  (made up of parts shown in  FIGS. 6, 7  and  8 ) and     2) a set of 8 variable-length subassemblies  40 , rotating about a common, fixed axis, at point  0  (see  FIGS. 11 and 12 ).    
 
         [0121]     Each Machine mirror-image half occupies an opposite 96×96×12-inch half side of the internal housing frame  13 , respectively referred to as sides  16 A on the left and  16 B on the right, separated by the 96×96-inch square central plate  15  (see  FIG. 2 ), as dictated by the arbitrary size selected for the exemplary Machine.  
         [0122]     The most important part used in both (1) and (2) above is shown in  FIGS. 3, 4  and  5 , which respectively show three schematic diagrams of the commercially-available telescoping full extension slide  46  in the “closed”, “opened” and “closed end-view” positions on the same page. Slide  46  (which is made of heavy-duty steel with steel ball bearings and a 100-lb load rating when fully extended to 48 inches) consists of three sections of equal lengths but different widths, respectively numbered  41 ,  42  and  43 . Section  41 , which is the widest of the three sections, is the fixed (non-movable) part of the slide, which is directly mountable onto any flat surface with two bolts  24  and nuts  23  through two ¼-inch mounting holes  19  (see  FIGS. 6, 7 ,  8  and  9 ). The second section  42  slides back and forth, on electro-plated steel ball bearings  48 , half-way inside the fixed section  41  and the third section  43  also slides back and forth, also on electro-plated ball bearings  48 , half-way inside section  42 . As a result, the combined, all-ball bearing, half-way progressive sliding actions of both sections  42  and  43  enables section  43  to slide back and forth the entire 24-inch length of the fixed section  41 —thereby causing the telescoping, full extension slide  46  to extend to any desired length, from a closed length of 24 inches up to a maximum opened length of 48 inches.  
         [0123]     Identical slides  46  are used in both the two-dimension, all-way movable mechanism  49  (comprised of parts shown in  FIGS. 6, 7  and  8 ) and in the two sets of 8 counter-rotating variable-length subassemblies  40  (one set of which is shown in  FIG. 12  for example). Both the two-dimension movable mechanism  49  and the two sets of 8 subassemblies  40  comprise the cubic TDMM craft&#39;s Machine mechanism. As shown in  FIG. 9 , each subassembly  40  consists of one telescoping bar (slide  46 ) and of one two-wheel device  47  (which is herein also referred to as W for wheels). Because slide  46  can be extended from a closed 24 inches up to a fully opened 48 inches, it enables both the two-dimension all-way mechanism  49  and the two rotating sets of eight variable-length subassemblies  40 , working together as one integrated unit in the Machine, to give the cubic TDMM craft far greater motive power, performance and maneuverability than any of the other related inventions (see the “Discussion Of The Related Arts” section) are capable of achieving with their various means and mechanical devices described in the “Background Of The Invention” section. That is the reason why, the above-mentioned uses of the telescoping (variable-length) full extension slide  46  in the Machine mechanism makes it the most important component part of the cubic TDMM craft invention.  
         [0124]     For example, slide  46  enables the two-dimension, all-way movable mechanism  49  to move both circular inner rims  33  and  35  to any position within the vertical, two-dimensional planes of outer rims  34  and  36  (see  FIGS. 13 and 14  for reference)—thereby making it possible for the two sets of 8 subassemblies  40  (counter-rotating inside the vertical planes of their respective inner rims  33  and  35 ) to generate together any variable amount of outwardly-directed, single resultant centrifugal force (ResF) in any desired direction inside the vertical planes of both circular inner rims. This is accomplished in the two-dimension, all-way movable mechanism  49 , by incorporating slides  46  in pairs, mounted end to end (one “closed” and one “opened”) to form one slide assembly, in which the two slides  46  alternately slide back and forth together. As shown in  FIGS. 6, 7  and  8 , these pairs of slide assemblies are used in the two-dimension, all-way movable mechanism  49  for variably moving plates  25  and  26  vertically and plates  29  and  30  (and their associated inner rims  33  and  35 ) horizontally on both sides of the central square plate  15  (see also  FIGS. 13 and 14 ).  
         [0125]     The central square plate&#39;s two sides,  15 A and  15 B (see  FIG. 2 ), are used for mounting, in mirror-image reversed order, all the various parts comprising the two-dimension, all-way movable mechanism  49  (see  FIGS. 6, 7 ,  8 ,  13  and  14 ), which is used for moving inner rims  33  and  35  anywhere inside the vertical, circular plane of their respective fixed outer rims  34  and  36 . These outer rims act as fixed circular boundaries for the movable inner rims which, in turn, act as circular tracks for the 2-wheel devices  47  (W), which are mounted at the ends of the two sets of 8 counter-rotating, variable-length subassemblies  40  (see  FIGS. 9, 11  and  12 ).  
         [0126]     However, to simplify the following, more complete description of the exemplary embodiment of the invention, only the left side of the mirror-image half of the Machine mechanism (which is mounted on the  15 A-side of the square central plate  15 ) is described next—because, since each Machine half is a mirror-image of the other half, an explanation of one half is applicable to the other half.  
         [0127]     To begin with,  FIG. 6  presents a front-view diagram of the left  15 A-side of the fixed 96-inch square central plate  15  with center at the fixed point  0  (see  FIG. 2 , which shows a top-side view of the square central plate  15  and its two opposite sides  15 A and  15 B). In this figure, the two pairs of vertical slide assemblies  21 L (on the left side) and  21 R (on the right side) are secured in parallel, with their four non-movable sections  41  mounted directly onto the central plate&#39;s  15 A-side by any fastening means (such as bolts  24  and nuts  23  through mounting holes  19 , as shown). Another pair of identical vertical slide assemblies  22 L and  22 R are similarly secured in parallel onto the central plate&#39;s opposite  15 B-side (see  FIG. 14 ).  
         [0128]      FIG. 7  illustrates how the vertically-movable plate  25  (shown in the center of the central 96×96-inch square plate&#39;s  15 A side) is mounted directly on top of the four movable sections  43  (see  FIGS. 3 and 4 ) of the two vertically-movable pairs of slide assemblies  21 L and  21 R shown in  FIG. 6 . Slide assemblies  21 L an  21 R are used for variably moving plate  25  vertically up or down, thereby allowing the center of plate  25  to be moved up and down by as much as 12 inches from the fixed point  0  along the vertical  0  line to any position between and on the two (+0) and (−0) horizontal lines. Two more pairs of slide assemblies  27 U (on the up side) and  27 D (on the down side) are horizontally-mounted as shown onto the opposite side of plate  25  (facing out, away from the central plate&#39;s  15 A-side), such that the four end-holes  19  of their fixed sections  41  (see  FIG. 4 ) are aligned with the four end-holes  19  of the fixed sections  41  of slide assemblies  21 L and  21 R on the other side of plate  25  facing the central square plate  15 —thereby making it possible to secure the four slide assemblies to plate  25  with bolts and nuts through their end-holes  19 . A similar arrangement of a vertically-movable plate  26 , secured on top of vertical slide assemblies  22 L and  22 R, with a pair of horizontal slide assemblies  28 U and  28 D mounted on its opposite side (away from the central square plate  15 ) is also mounted on the central plate&#39;s  15 B-side (see  FIG. 14 ).  
         [0129]      FIG. 8  shows how the 72-inch square plate  29  is secured onto the four movable sections  43  of the two horizontal slide assemblies  27 U and  27 D (shown in  FIG. 7 ) with bolts  24  and nuts  23 . Slide assemblies  27 U and  27 D are used for variably moving plate  29  horizontally left or right, thereby allowing the center point P of plate  29  to be moved by up to 12 inches from the fixed point  0  to any position between and on the two (+0) and (−0) vertical lines. A 72-inch-diameter circular inner rim  33  is also secured directly onto the opposite side of the horizontally-moving plate  29  facing out (away from the central plate&#39;s  15 A-side), inscribed inside the plate&#39;s four sides as shown. Thus, by combining the variable vertical motion of plate  25  with the variable horizontal motion of plate  29 , the circular inner rim  33  can be moved anywhere inside the vertical, circular plane of the fixed outer rim  34  (shown inscribed inside the four sides of the square central plate&#39;s  15 A-side). A second identical inner rim  35  is also similarly mounted on the opposite side of the horizontally-moving plate  30 , on the central plate&#39;s  15 B-side (see  FIG. 14 ).  
         [0130]     The above-described vertically-moving slide assemblies  21 L,  21 R and plate  25  and the horizontally-moving slide assemblies  27 U,  27 D and plate  29  (with inner rim  33  mounted on its opposite side, facing away from the central square plate  15 ) make up the left mirror-image half of the two-dimension, all-way movable mechanism  49 , which is mounted on the central plate&#39;s  15 A-side. Similarly, as shown in  FIG. 14 , the vertically-moving slide assemblies  22 L,  22 R and plate  26  and the horizontally-moving slide assemblies  28 U,  28 D and plate  30  (see  FIG. 14 ), with inner rim  35  mounted on its opposite side, constitute the right mirror-image half of the two-dimension, all-way movable mechanism  49 , mounted on the central plate&#39;s other  15 B-side.  
         [0131]     Both pairs of vertically-movable plates  25  and  26  and horizontally-movable plates  29  and  30  (see  FIGS. 13 and 14 ) are each connected (i.e., coupled together) in a manner consistent with acceptable engineering practice, so that both pairs of coupled plates can respectively be simultaneously, independently and variably moved vertically and horizontally. As a result, the combined vertical motions of the coupled plates  25  and  26  with the horizontal motions of the coupled plates  29  and  30  enables the two-dimension, all-way movable mechanism  49 : 
    1) to move both inner rims  33  and  35  together, from their “neutral position” (in which, as shown in the example of  FIG. 11 , the 8 rotating subassemblies  40  are all of equal lengths) to any other position between their “neutral position” and their maximum “active position” (in which, as shown in the example of  FIG. 12 , the same 8 rotating subassemblies  40  now all have different lengths, as functions of their angles of rotation), and     2) to cause the two sets of 8 variable-length subassemblies  40 , counter-rotating in the “active position” in the vertical planes of their respective inner rims, to each generate 8 different centrifugal forces (see F c  equation A1), as functions of both their different lengths and angles of rotation (see  FIG. 32 ).    
 
         [0134]     When the 8 subassemblies  40  mentioned in (2) above are rotating in the maximum “active position” in each Machine mirror-image half, they each successively achieve their maximum radial lengths in the direction in which their movable inner rim is making contact with the inside surface of their associated outer rim (which act as fixed circular boundary for the inner rim). Also, as illustrated in  FIG. 32 , the 8 different F c  centrifugal forces mentioned in (2) above (which are simultaneously generated in each inner rim&#39;s vertical plane) automatically vectorially combine (see the polygon of  FIG. 33 ) into a single, outwardly-directed maximum resultant centrifugal force (ResF) of 1,989.4 lbs (which always points in the same direction in which the inner rim is making contact with the inside surface of its associated outer rim)—and, since there are two counter-rotating sets of 8 subassemblies  40  in the Machine, then the total maximum ResF generated doubles to 3,978.8 lbs.  
         [0135]     Finally, by combining the selected directions of the above-mentioned total maximum ResF with the chosen direction (azimuth) of the internal housing frame  13  (and its enclosed Machine) which, as shown in  FIGS. 1, 2 , and  53 , can be horizontally rotated inside the external cubic frame  10  in either direction about its vertical central axis  14 , a powerful, steerable and variable centrifugal motive force is then available to smoothly propel the cubic TDMM craft (or any other water, air and outer space craft type) with spectacular performance (see  FIGS. 41 through 48  and the “Discussion Of The Cubic TDMM Craft Performance Results” section) and maneuverability in three dimensions, anywhere on earth and in outer space.  
         [0136]     The identical telescoping (variable-length) slides  46  used in both the slide assemblies of the two-dimension, all-way movable mechanism  49  and the two counter-rotating sets of 8 subassemblies  40  may be of any desired form and design consistent with acceptable engineering practice. For example, the pair of slide assemblies  21 L and  22 R and the other pair of slide assemblies  21 R and  22 L (see  FIGS. 13 and 14 ), which are respectively mounted on opposite sides of the central square plate  15 , may instead be combined into two slide assemblies  21  and  22 , which would be located within open slots in the central square plate  15  and be adapted to support and to simultaneously vertically move both plates  25  and  26  together to any position on opposite sides of the central plate  15 . Furthermore, the central square plate  15  may itself be replaced by a lighter, square central framework  15  of the same size, upon which the above-mentioned single slide assemblies  21  and  22  and their associated vertically-movable plates  25  and  26  may be properly mounted. However, in the exemplary cubic TDMM craft invention described herein, all the slides assemblies used in the Machine each consists of a pair of commercially available telescoping full extension slides  46 —similar to the one illustrated in  FIGS. 3, 4  and  5 .  
         [0137]     The 8 identical, equally-spaced, variable-length subassemblies  40  in the Machine&#39;s left mirror-image half are shown in  FIG. 11  rotating about both superimposed points P and  0  in the “neutral position” (in which inner rim  33  is in the center of fixed outer rim  34 —thereby causing the lengths of the 8 subassemblies  40  to all be equal to the inner rim&#39;s radius R 1   W ) and are shown in  FIG. 12  rotating about the fixed, off-center point  0  in the maximum “active position” (in which inner rim  33  is making contact with outer rim  34  at 180 degrees—thereby causing the lengths of the same 8 subassemblies  40  to all be different). In both  FIGS. 11 and 12 , the 8 subassemblies all look very much like the spokes of a wheel, radiating from point  0 .  
         [0138]     As best shown in  FIG. 9 , each identical, variable-length subassembly  40  consists of one bar (telescoping full extension slide  46 ) and of one 2-wheel device  47  (also referred to as W for wheels). Each slide  46  has the 2-wheel device  47  mounted onto the end of its moving section  43  and has its fixed section  41  secured directly onto a circular metal disk  31 , which is itself mounted onto a high-speed hub  44  with four lug bolts  39  on a 4-inch circle (see  FIG. 50 ). Therefore, the set of 8 subassemblies  40 , the metal disk  31  and the hub  44  all rotate together as one unit about the 2000-lb capacity stub axle  45  which, as shown in  FIG. 50 , is mounted onto the right  16 B-side square end-wall of the internal housing  13 , perpendicular to the vertical plane of the central plane  15  and axially aligned with the central plate&#39;s fixed center at point  0 .  
         [0139]     In the full side-view diagram of the exemplary cubic TDMM craft shown in  FIG. 51  (in which one Machine mirror-image half is shown mounted on each side of the central square plate  15 ), the 8 variable-length subassemblies  40  in each Machine mirror-image half continuously change their radial length R 3   W  (see  FIGS. 12 and 23 ), from a fully closed minimum of 24 inches up to a fully opened maximum 48 inches and vice versa, as they rotate in the maximum “active position” inside the vertical plane of its movable inner rim. As a result, the outwardly-directed centrifugal force generated by each rotating subassembly  40  causes it to extend its variable length from its fixed point  0  and to force the 2-wheel device  47  (at its movable end) to make contact with the inside surface of its movable inner rim  33  and to push against it with a resultant centrifugal force ResF as a function of its angle of rotation theta0 (see  FIGS. 31 and 32 ).  
         [0140]      FIG. 11  shows movable inner rim  33  in the “neutral position” (in the center of the larger outer rim  34 ), with its center point P superimposed on the fixed outer rim&#39;s center point  0 . In this “neutral position” the lengths of the 8 variable-length subassemblies  40 , rotating about both superimposed points P and  0 , are all equal to the length of the inner rim&#39;s radius R 1   W =3 ft in the exemplary apparatus. On the other hand, as shown in  FIGS. 12 and 15  through  18 , when inner rim  33  is moved its maximum allowable distance from its “neutral position” in any direction to make contact with the inside surface of outer rim  34  (shown here to arbitrarily be at 180 degrees), then inner rim  33  is now in the maximum “active position”, in which its center point P is now separated from the outer rim&#39;s fixed, off-center point  0  by a distance R 2 =(R 0 −R 1   W )=1 ft.  
         [0141]      FIG. 12  also shows that when the 8 variable-length subassemblies  40  rotate in the maximum “active position” they successively achieve their maximum length of 48 inches at 180 degrees, and their minimum length of 24 inches at 360/0 degrees on the inside surface of outer rim  34  respectively. Although the movable inner rim  33  is arbitrarily shown to make contact with outer rim  34  at 180 degrees, the contact point could just as easily have been at 225 degrees, or 315 degrees, and the 8 subassemblies&#39; different lengths would still be the same as they were at 180 degrees (but relative to the new selected contact point)—with the 8 rotating subassemblies  40  achieving their maximum lengths of 48 inches at that new contact point between the two rims.  
         [0142]     To more fully understand the concept of using rotational centrifugal force as a motive force, let&#39;s look at the equation for centrifugal force (which is the reaction against centripetal force), namely:
 
F c =Mω 2 R  (1)
        in which: F c =centrifugal force, lbs 
            M=mass of one rotating body, slugs,     ω=angular velocity, rad/sec, and     R=radius, ft.    
               
 
         [0147]     Equation (1) above basically says that, if M and ω are both constant parameters (see Table 1), then F c  varies in direct proportion to R—or F c  increases as R increases and vice versa. However, as shown in  FIG. 9 , since each rotating variable-length subassembly  40  used in the Machine consists of two separate parts (namely: a telescoping slide  46  and a 2-wheel device  47 , also referred to as W), each with a different variable-length radius R (which both continually vary as they rotate in the “active position” about the fixed point  0 ), the two different slide  46  and W radial lengths must therefore first be calculated separately, in order to later be able to calculate their associated rotational velocities, forces, . . . etc . . . , and combine them for each subassembly  40 .  
         [0148]     Therefore, in order to identify the separate equations for the bar (slide  46 ) and for W, it is necessary to use the subscripts “ br ” and “ W ” respectively—because, as shown in  FIG. 20 , the mass of W (mass W ) runs on the inside surface of inner rim  33  (at the telescoping end of the bar) while the mass of the bar (mass br ) runs along the locus of its radius of gyration R 3   br  (which is the bar&#39;s radial distance from its axis of rotation to where its mass, mass br , is concentrated without altering its moment of inertia I br  (see equation A7). For example, in the “neutral position” case (see figures  11  and  19 ), the two constant-length radii are respectively identified as R 1   br  for the bar&#39;s radius of gyration and as R 1   W  for W (at the end of the bar&#39;s radius) and, likewise, in the “active position” case (see  FIGS. 12 and 20 ), the two variable-length radii are identified as R 3   br  for the bar&#39;s radius of gyration and R 3   W  for W. Thus, using equations A5 and A8, the variable-length radii R 3   W  and R 3   br  results are first obtained separately as functions of theta0 (see  FIG. 23 ) and are then used in equations B1a through B8c to obtain all the other cubic TDMM&#39;s various performance results (such as velocities, centrifugal forces, . . . etc . . . , for the bar and for W as functions of theta0, which are then combined for the entire subassembly  40  (see  FIGS. 24 through 31 , where they are shown as functions of the angle of rotation theta0). All the above-mentioned equations derived for the bar and W are respectively presented in both the Derivation Of The Variable-Length Radius R 3   W  Equation in part A and the Derivation Of The Ten Basic Rotational Equations in part B—see pages 34 through 37.  
         [0149]      FIG. 19  shows the constant-length radii R 1   W  for W and R 1   br  for the bar, both rotating in the “neutral position” about the superimposed points P and  0 , and the bar&#39;s circular locus of R 1   br  (shown as a dashed circle with constant-length radius R s =1.732 ft, superimposed on R 1   br ).  
         [0150]      FIG. 20  shows the variable-length radii R 3   W  for W and R 3   br  for the bar, both rotating in the “active position” about the fixed, off-center point  0  only, and the bar&#39;s circular locus of R 3   br , shown as a dashed circle with constant-length radius R s  and center at point S. Unlike in  FIG. 19 ,  FIG. 20  shows that the constant-length radius R s  and the variable-length radius R 3   br  are separate and unequal, except at 100 and 260 degrees, where they are both equal to 1.732 ft respectively (see  FIG. 23 , in which plots of R 3   W  for W and R 3   br  for the bar are also shown as functions of the angle of rotation theta0, along with the plots for R 1   W  for W and R 1   br  for the bar, shown here for comparison with R 3   W  and R 3 ).  
         [0151]     To assist in the derivation of the variable-length radius R 3   W  equation, an additional line segment R 2  (see  FIGS. 15 through 18 ) has been introduced between the center of outer rim  34 , at the fixed point  0  (which is also the center of the central plate  15 ) and the center of the movable inner rim  33 , at point P (along a line from point  0  to the point of contact of inner rim  33  with outer rim  34 ). In these figures, R 2  is shown as a heavy black line, representing the difference between the constant-length radius R 0  of the fixed, circular outer rim  34  (which is also the maximum achievable variable-length R 3   W ) and the constant-length radius R 1   W  of the movable circular inner rim  33 —which is shown making contact with outer rim  34  at the arbitrarily chosen 180 degrees. Therefore, in  FIGS. 15 through 18 , since the outer rim&#39;s constant-length radius R 0 =4 ft and the inner rim&#39;s constant-length R 1   W =3 ft (see Table 1), then R 2 =(R 0 −R 1   W )=(R 3   W −R 1   W )=(4 ft−3 ft)=1 ft—which is also the maximum R 2  length achievable, as dictated by the selected size of the cubic TDMM craft invention.  
         [0152]     However, if the movable inner rim  33  is moved in any direction towards outer rim  34  without making contact with its inside surface, then the length of R 2  in that direction will be less than 1 ft. For example, looking at  FIGS. 16 through 18 , if inner rim  33  is moved only 0.5 ft from its “neutral position” towards outer rim  34  in the direction of 180 degrees, such that its center point P is only 0.5 ft away from the fixed point  0 , then R 2 =0.5 ft in that same direction.  
         [0153]     The above-mentioned variable R 2  capability feature (which is made possible by the capability of the Machine&#39;s two-dimension, all-way movable mechanism  49  to move inner rim  33  any given distance from its “neutral position” towards, and up to, the inside surface of outer rim  34  in any direction) is most important, because it can be used to control the rotating variable-length of radius R 3   W  which, in turn, and according to the F c  centrifugal force equation (1), can be used to obtain the appropriate amount of variable resultant centrifugal force (ResF) output desired of the cubic TDMM craft in order to: 
    1) keep it accelerating, decelerating or just cruising along on any “far-earth” voyage,     2) keep it stationary (hovering) at any desired point anywhere on earth and in outer space,     3) keep it moving at any given “near-earth” orbital velocity at any altitude, and     4) most importantly, control its descent velocity when re-entering any atmospheric environment (such as that of earth) without burning up and safely land (thereby making the use of thermal tiles unnecessary and obsolete).    
 
         [0158]     The input parameters used in SOUCVOL to obtain all the various cubic TDMM craft&#39;s rotational and kinetic energy performance results presented herein in  FIGS. 22 through 40  are listed in the following Table 1.  
                                                                         TABLE 1                           R0 = 4 ft = constant-length radius of the fixed, circular outer rim 34,                (Note: R0 is also the maximum achievable variable-length radius           R3 w )            R1 w  = 3 ft = constant-length radius of the movable, circular inner rim 33,                ω 0  = 100 rad/sec = constant angular velocity of variable-length           subassembly 40,            Delrot = 0.5 deg = small “delta” incrementation of the angle of rotation       theta0,                W w  = 1 lb = weight of 2-wheel device 47 (rotating at end of variable-           length bar R3 w ),            W br  = 1 lb = weight of the rotating variable-length bar R3 br .                (Note: The SOUCVOL input parameter values listed in Table 1 are           arbitrary and can therefore be assigned any other values, as needed           for different model sizes).                      
 
 A) Derivation of the Variable-length Radius R 3   W  Equation. 
 
         [0159]     As shown in  FIG. 15 , the three line segments R 1   W  (the constant-length radius of inner rim  33 ), R 2  (the variable segment length, or difference between the outer rim&#39;s fixed, off-center point  0  and the inner rim&#39;s center point P) and R 3   W  (the variable-length radius of the subassembly  40 , which consists of one telescoping slide  46  and of one 2-wheel device  47 , also referred to as W) represent the three sides of a plane triangle—which continuously changes its shape as the variable-length radius R 3   W  rotates around the fixed, off-center point  0  (as shown in  FIGS. 15 through 18 ).  
         [0160]     From geometry, the relationship between sides a, b and c and angles A, B and C of any plane triangle is obtained by the law of Sines. Therefore, after substituting the variable-length radius R 3   W  for side a, the inner rim&#39;s constant-length radius R 1   W  for side b and the line segment R 2  for side c, the law of Sines gives the following relationship:
 
R 3   W /(SIN  A )= R   1   W /(SIN  B )= R   2 /(SIN  C )  (A1)
 
         [0161]     In equation A1, the constants radius R 1   W  and the maximum line segment R 2 =(R 0 −R 1   W ) are already known (see Table 1) and angle B, which depends directly on angle theta0 for its value (see  FIGS. 15 through 18 ), can be obtained as follows:  
         [0162]     When angle theta0 is: 
        1)=0 degree (or 360 degrees), then angle B=180 degrees,     2)&lt;180 degrees, then angle B=(180 degrees−theta0),     3)=180 degrees, then angle B=0 degree,     4)&gt;180 degrees, then angle B=(theta0−180 degrees).        
 
         [0167]     Therefore, from equation A1, angle C is obtained as follows:
 
 R   1   W /(SIN  B )= R   2 /(SIN  C )  (A2)
 
 which, when solving for angle C, gives:
 
 C =SIN − (( R   2 / R   1   W )(SIN  B ))  (A3)
 
         [0168]     Now that we have an equation for angle C, we can easily obtain a value for angle A, which is needed to calculate R 3   W  in equation A1. From plane trigonometry, we know that the sum of the three angles A, B and C in any triangle is always equal to 180 degrees, therefore:
 
angle  A =(180 degrees)−angle  B −angle  C   (A4)
 
         [0169]     Then, going back to the first two terms of equation A1 and solving for R 3   W  gives the following equation, namely:
 
 R   3   W   =R   1   W (SIN  A /SIN  B )  (A5)
 
 in which the value of SIN A is obtained by using the value of angle A given in equation A4. 
 
         [0170]     A value for the variable-length radius R 3   W (from the fixed point  0  to any contact point on the inside surface of the circular inner rim  33 ) can now be easily obtained as a function of the angle of rotation theta0—by using the appropriate angle B value from one of the four theta0options given above. For example, as shown in  FIG. 15 , when theta0=135 degrees (which is less than 180 degrees), then angle B=180−135=45 degrees.  
         [0171]     For the purpose of illustration, let&#39;s also look at  FIGS. 16, 17  and  18 . In  FIG. 16 , when theta0=0 degree, R 3   W =(R 1   W −R 2 )=(3 ft−1 ft)=2 ft (which is the shortest achievable R 3   W  length), and when theta0=180 degrees, R 3   W =(R 1   W  +R 2 )=(3 ft+1 ft)=4 ft which is the maximum, longest achievable R 3   W  length)—which is also equal to the circular outer rim&#39;s input parameter R 0 =4 ft. Also note that, in  FIG. 16 , both the shortest and the longest radii R 3   W  lengths add up to 6 ft—which is the diameter length of circular inner rim  33 . In  FIG. 17 , at theta0=45 degrees, R 3   W =2.208 ft and, at theta0=225 degrees, R 3   W =3.623 ft (when using the appropriate angle B values obtained from one of the 4 angle B relationships given earlier). Finally, in  FIG. 18 , when theta0 is equal to either 90 degrees or 270 degrees, both R 3   W  radii are each equal to 2.828 ft.  
         [0172]     Furthermore, since R 3   W  is a variable-length bar (telescoping slide  46 ) with a given mass br , it is also necessary to obtain an equation for the bar&#39;s radius of gyration R 3   br , which is given as:
 
 R   3   br ={square root}{square root over (()} I   br /mass br )  (A6)
 
 and, for a bar with the axis of rotation through one end, its moment of inertia I br  is:
 
 I   br =(mass br /3)( R   3   W ) 2   (A7)
 
 which, after substituting the right side of equation A7 for I bar  in equation A6, gives:
 
 R   3   br   =R   3   W /{square root}{square root over (3)}  (A8)
 
 and, for the purpose of simplifying many other calculations, let
 
1/{square root}{square root over (3)} =M   br =0.5773503  (A9)
 
 (in which, for example, the value of M br  is used as a constant multiplier to quickly calculate the variable-length of the bar&#39;s radius of gyration R 3   br =R 3   W (0.5773503). 
 
         [0173]     As shown in  FIG. 20 , the circular locus of the variable-length R 3   br (rotating in the maximum “active position” about the fixed point  0 ) has its center at point S and a radius R S . Similarly, as shown in  FIG. 19  (in which points P and S are superimposed on the fixed point  0 ), the circular locus of the constant-length radius of gyration R 1   br (rotating in the “neutral position” about al three points P, S and  0 ) has its center at point S but has its radius=R 1   W (M br ), which is superimposed on and equal to R S . Note that the sizes of both the circular loci of R 1   br in  FIG. 19  and of R 3   br  in  FIG. 20  are identical, with the same radius R S =1.73 ft, as measured from point S in both figures.  
         [0174]     Plots of the variable-length radii R 3   W  and R 3   br  are presented in  FIG. 23  as functions of theta0(along with plots of the constant-length radii R 1   W  and R 1   br , for comparison with the plots of R 3   W  and R 3   br )—and can now be used to derive the other rotational equations needed to obtain the cubic TDMM craft velocity, acceleration, force and kinetic energy plots as functions of theta0. The R 3   W  and R 3   br  plots presented in  FIG. 23  are all based on calculations obtained at every incremented 0.5 degree (see delrot in Table 1) of angle theta0(for greater accuracy), using one subassembly  40  only, rotating counterclockwise, but are only plotted every 10 degrees.  
         [0000]     B) Derivation of the Ten Basic Rotational Equations.  
         [0175]     To aid in the calculations of the Machine&#39;s 10 rotational results presented herein, a dedicated computer simulation program, identified by the acronym “SOUCVOL” (formed from the initial letters of SOUCoupe VOLante) throughout this patent was written. The SOUCVOL calculations performed in each iteration first require the use of the variable-length radius R 3   W  equations A1 through A9(presented in the above section A), in order to obtain the various angles and radii values needed as inputs into the following 10 basic rotational equations B1a through B10.3c. However, the detailed program coding is not presented herein in the interest of brevity.  
         [0176]     Briefly, all 10 basic rotational equations are used in each successive iteration, at the start of which, angle theta0(which, as shown in  FIGS. 11 and 12 , is the angle of rotation of the 8 subassemblies  40  about the fixed point  0 ) is incremented by a small delta rotation of 0.5 degrees (see “delrot” in Table 1)—the value of which was arbitrarily selected to be the primary incrementation input parameter used in SOUCVOL. Next, SOUCVOL obtains the appropriate angle B value (from the four theta0 options given in paragraph 0124) and angle C (see equation A3), which are then used to calculate the variable-length radius R 3   W (see equation A5) and the bar&#39;s radius of gyration R 3   br (see equation A8), which are then respectively used in the 10 rotational equations B1a through B10.3c to obtain the 10 sets of rotational performance results presented in  FIGS. 22 and 24  through  31 —upon which they depend, directly or indirectly, for their values.  
         [0177]     Furthermore, since there are 360 degrees per each theta0 rotation about the fixed point  0  inside the circular movable inner rim  33  (see  FIGS. 11 and 12 ), there is therefore a total of 721 iterations per each SOUCVOL run (namely: (360 deg/0.5 deg)+1), each with one complete set of 10 rotational results obtained at the end of each delrot-incremented iteration. There is therefore a total of 721 sets of 10 different rotational results for each of the 8 equally-spaced (45 degrees apart) subassemblies  40 —regardless of where the number 1 subassembly  40  (in the set of 8 rotating subassemblies  40  shown in both  FIGS. 11 and 12 ) is located on the inside surface of the circular inner rim  33 .  
         [0178]     As already mentioned, both subscripts “ W ” and “ br ” are used in the following 10 sets of equations to differentiate the results obtained for the 2-wheel device W (on the inside surface of the movable inner rim  33 ) from those obtained for the bar (on the locus of its radius of gyration, represented by the dashed circles in both  FIGS. 19 and 20 ). The subscript “ 0 ” is also used in some equations to indicate either an initial input parameter (such as in the constant input angular velocity ω 0 ), or a parameter value obtained in a previous iteration, such as, for example, in VT W0  (which is used in equation B2a to calculate the average tangential acceleration AT Wav =(VT W −VT W0 )/deltm.  
         [0179]     The 10 sets of rotational equations for both W (at the end of the rotating variable-length bar R 3   W ) and for the variable-length bar (at its radius of gyration R 3   br ), are:  
         [0180]     1) TANGENTIAL VELOCITY (VT), ft/sec. 
        a) For W,
 
 VT   W   =R   3   W ω 0   (B1a)
     (in which ω 0  is the input constant angular velocity given in Table 1)     b) For the bar,
 
 VT   br   =R   3   br ω 0   =VT   W ( M   br )  (B1b)
     (in which the constant multiplier M br =0.57773503—see equation A9).        
 
         [0185]     2) AVERAGE TANGENTIAL ACCELERATION (AT av ), ft/sec 2 . 
        a) For W,
 
 AT   Wav =( VT   W   −VT   W0 )/deltm  (B2a)
     (in which “deltm”=0.5 deg/(5729.578 deg/sec)=8.726646 −5  sec).     b) For the bar,
 
 AT   brav =( VT   br   −VT   br0 )/deltm  (B2b)
    c) For both W and bar combined,
 
 AT   av   =AT   Wav   +AT   brav   B2c)
       
 
         [0190]     3) RELATIVE ANGULAR VELOCITY (ω 2 ), relative to R 1   W  instead of R 3   W , rad/sec. 
        a) For W,
 
ω 2   =VT   W   /R   1   W   =VT   br   /R   1   br   (B3a)
       
 
         [0192]     4) AVERAGE TANGENTIAL FORCE (FT av ), lbs. 
        a) For W,
 
 FT   Wav =mass W ( AT   Wav )  (B4a)
    b) For the bar
 
 FT   brav =mass br ( AT   brav )  (B4b)
    c) For W and bar combined,
 
 FT   av   =FT   Wav   +FT   brav   (B4c)
       
 
         [0196]     5) RADIAL ACCELERATION (AR), ft/sec 2 . 
        a) For W,
 
 AR   W =( VT   W ) 2   /R   3   W   (B5a)
    b) for the bar,
 
 AR   br =( VT   br ) 2   /R   3   br   =AR   W ( M   br )  (B5b)
    c) for W and bar combined,
 
 AR=AR   W   +AR   br   (B5c)
       
 
         [0200]     6) RADIAL FORCE (FR), lbs. 
        a) For W,
 
 FR   W =mass W ( AR   W )  (B6a)
    b) For the bar,
 
 FR   br =mass br ( AR   br )  (B6b)
    c) For W and bar combined,
 
 FR=FR   W   +FR   br   (B6c)
       
 
         [0204]     7) RESULTANT CENTRIFUGAL ACCELERATION (ResA), ft/sec. 
        a) For W,
 
 ResA   W ={square root}{square root over (()}( AT   Wav ) 2 +( AR   W ) 2 )  (B7a)
    b) For the bar,
 
 ResA   br ={square root}{square root over (()}( AT   brav ) 2 +( AR   br ) 2 )  (B7b)
    c) For W and bar combined,
 
 ResA=ResA   W   +ResA   br ={square root}{square root over (()} AT   av   2   +AR   2 )  (B7c)
       
 
         [0208]     8) RESULTANT CENTRIFUGAL FORCE (ResF), lbs. 
        a) For W,
 
 ResF   W =mass W ( ResA   W )  (B8a)
    b) For the bar,
 
 ResF   br =mass br ( ResA   br )  (B8b)
    c) Combined resultant force
 
 ResF=ResF   W   +ResF   br   (B8c)
       
 
         [0212]     9) ANGLE DIRA=DIRECTION ANGLE FOR BOTH THE CENTRIFUGAL ACCELERATION AND THE CENTRIFUGAL FORCE, degrees. 
        a) Angle ALF (between AT av  and AR),
 
 ALF =TAN −1 ( AT   av   /AR )=TAN −1 ( FT   av   /FR )  (B9a)
    b) Angle DIRA (direction angle of both ResA and ResF),
 
DIRA=Angle  A +angle  ALF   (B9b)
       
 
         [0215]     NOTES: 1) Angle A is defined in equation A4. 
        2) See  FIG. 21  for the graphical representation of angles A, ALF and DIRA for theta0=40 degrees.     3) See  FIG. 22  for plots of angles ALF, A and DIRA as functions of theta0.        
 
         [0218]     10) R 0 TATIONAL KINETIC ENERGY (KE), ft*lbs,  
         [0219]     The following set of KE equations is based on the standard rotational kinetic energy (KE) equation, namely:
 
 KE =Σ(1/2) M ( Rω ) 2   (10.1)
 
         [0220]     in which 1) M=mass of the rotating body, slugs, 
        2) R=length of radius, ft, and     3) ω=angular velocity of the rotating body, rad/sec.        
 
         [0223]     These kinetic energy (KE) equations are also used with only one rotating subassembly  40 , which consists of one 2-wheel device  47  (also referred to as W for wheels) plus one slide  46  (referred to as the bar). The KE calculations are first done separately for W and then for the bar and are then combined to obtain the KE result for the entire subassembly  40  in each SOUCVOL iteration, which occurs each time the subassembly  40  angle of rotation theta0 is incremented by a small input delrot value of 0.5 degree (see Table 1). Therefore, as already mentioned, since there is a total of 721 angle theta0 increments (one every 0.5 degree, from 0 degree to 360 degrees) around the circular inner rim  33 , there is also a total of 721 sets of W, bar and subassembly  40  KE results per each SOUCVOL run—or, one complete set of KE results is simultaneously available for each of the 8 equally-spaced (45 degrees apart) subassemblies  40  (see  FIG. 39 ), no matter where the #1 subassembly  40  starts on the 360-degree circular inner rim  33 .  
         [0224]     In the following tenth set of KE equations, mass W  and mass br  represent the masses of the two-wheel device  47  (W) and of the telescoping slide  46  (bar) respectively. They are used in each SOUCVOL iteration (after first incrementing theta0 by delrot=0.5 degree) for calculating the rotational KE values of both W and the bar separately and then combining them to obtain the KE value for one subassembly  40  in both the “neutral position” and the “active position”. These two sets of KE equation are: 
    1) The first set of kinetic energy equations is called KE0, which represents the “neutral position” case shown in  FIGS. 11 and 19  (in which the constant-lengths of both the inner rim&#39;s constant radius R 1   W  and of the bar&#39;s constant radius of gyration R 1   br  (which are of equal lengths) rotate about superimposed points P, S and  0 ). 
        a) For W,
 
 KE 0 W =(1/2)mass W ( R   1   W ω 0 ) 2   (B10.2a)
    b) For the bar,
 
 KE 0 br =(1/2)mass br ( R   1   br ω 0 ) 2   (B10.2b)
     (in which R 1   br =R 1   W (M br )—see equation A9 for the definition of M br )     c) For W and the bar combined,
 
 KE 0= KE 0 W   +KE 0 br   (10.2c)
    2) The second set of kinetic energy equations is called KE1, which represents the “active position” case shown in  FIGS. 12 and 20  (in which the radii lengths of R 3   W , for W, and of R 3   br , for the bar&#39;s radius of gyration, continually vary as a function of theta0(se  FIG. 23 ).     a) For W,
 
 KE 1 W =(1/2)mass W ( R   3   W ω 0 ) 2   (B10.3a)
    b) For the bar,
 
 KE 1 br =(1/2)mass br ( R   3   br ω 0 ) 2   (B10.3b)
     (in which R 3   br =R 3   W (M br ))     c) For W and the bar combined,
 
 KE 1= KE 1 W   +KE 1 br   (B10.3c)
 
 C) Equations for Evaluating the Performance of the Cubic TDMM Craft. 
   
       
 
         [0235]     In order to perform all the parametric calculations needed for evaluating the performance of the cubic TDMM craft, I wrote a small computer program in QBASIC named “PRFMEVL” (for performance evaluation), in which the following equations (C1) through (C11) were used for calculating the various performance results of the said cubic craft. The initial input parameters used in the following equations are presented in the following Table 2, which is divided into four sections.  
                                                                                                                                                                                                                                                                                                                                                                                                                                                                               TABLE 2                           1) Initial Constant Input Parameters:                ResF = total resultant centrifugal force generated by the Machine&#39;s two sets of                 8 subassemblies 40, counter-rotating at the following given angular            velocities respectively:           = 995.0 lbs at 50 rad/sec.           = 2,238.1 lbs at 75 rad/sec.           = 3,979.8 lbs at 100 rad/sec.                Rinc = altitude (distance) range increment, miles.           Rmax = maximum cubic craft range, miles.           R e  = 3,950.0 miles = average earth&#39;s radius.           R m  = 1,071.0 miles = average moon&#39;s radius.           D em  = 230,000.0 miles = average distance between earth and moon.           g e  = 32.174 ft/sec 2  = acceleration of gravity at the earth&#39;s surface.           g m  = 5.32 ft/sec 2  = acceleration of gravity at the moon&#39;s surface.           W cc  = 600 lbs = approximate weight of cubic craft at the earth&#39;s surface.            2) Initialization of parameters at start of PRFMEVL run:                T e  = 0 sec = cubic craft elapsed time from launch.           ALT = 0 miles = altitude of cubic craft from earth (at T e  = 0 sec).           ALT1 = 0 feet = altitude of cubic craft (at T e  = 0 sec).           X e  = R e  = altitude of cubic craft from earth&#39;s center (at T e  = 0 sec).           X m  = D em  = distance of cubic craft from moon&#39;s surface (at T e  = 0 sec).           K e  = g e  R e   2  = constant parameter, obtained from equation g e  = (GM e )/R e   2  =                K e /R e   2 , in which G = gravitational constant, M e  = the earth&#39;s                mass and R e  = distance to earth&#39;s center from the surface.                K m  = g m  R m   2  = constant parameter, similarly obtained as above, but for the                moon.                M cc  = (W cc /g e ) = 600/32.174 = 18.6486 slugs = Cubic craft&#39;s constant                mass.            3) Performance Evaluation Equations and algorithms used in “PRFMEVL”:         Negative earth&#39;s acceleration of gravity on cubic craft at time T e  after launch from         earth, ft/sec 2 .                g e  = −(K e /X e   2 )   (C1)                Positive moon&#39;s acceleration of gravity on cubic craft at time T e  after launch from           earth, ft/sec 2 .                g m  = K m /(X m  + R m ) 2     (C2)                Negative force on cubic craft at time T e  after launch due to earth&#39;s gravity, lbs.                F e  =M cc g e     (C3)                Positive force on cubic craft at time T e  after launch due to moon&#39;s gravity, lbs.                F m  = M cc g m     (C4)                Cubic craft motive force versus vertical altitude, lbs.                F cc  = F e  + ResF + F m     (C5)                Cubic craft Instantaneous acceleration versus vertical altitude from earth, ft/sec 2 .                A e  = F cc /M cc     (C6)                Cubic craft elapsed flight time from launch time from earth, sec.                IF ALT &gt; 0 THEN T e  = {square root}(ALT1/(0.5A e ))   (C7)                Cubic craft instantaneous velocity at time T e  after launch from earth, miles/sec.                V e  = (A e T e )/5280.0   (C8)                Cubic craft average acceleration in the nth incremented range (Rinc), ft/sec 2 .                A cc  = ((V e   2  − V e0   2 )/2Rinc)5280   (C9)                (in which V e0  was obtained in the previous iteration).                Cubic craft average flight time (T av ) in the nth incremented range (Rinc), sec.                IF ALT &gt; 0 THEN T av  = ((V e  − V e0 )5280)/A cc     (C10)                Cubic craft average flight time from earth launch to the end of the nth incremented           range (Rinc), sec.                T cc  = T cc  + T av     (C11)            NOTE: Read the “Discussion Of The Cubic TDMM Craft Performance Results”                section for an explanation of the two flight times T e  and T cc .            4) Increment new parameter values for the next iteration:                V e0  = V e , mi/sec.                (V e0  is saved in this iteration for use in the next iteration)           X e  = (X e  + Rinc) = new incremented altitude from earth at time T e , miles.           ALT = (X e  − R e ) = new decreased altitude from earth at time T e , miles.           ALT1 = (ALT) 5280 = new cubic craft altitude at time T e  from earth, ft.           X m  = (D em  − ALT) = new decreased distance from earth to moon&#39;s surface                at time T e , miles.                IF ALT &gt; Rmax THEN END.                Otherwise, go back to g e (equation C1) above for another iteration with the           new incremented parameter values.                      
 
 Discuccion of the Cubic TDMM Craft Rotational Results 
 
         [0236]     The following plots of the cubic TDMM craft&#39;s rotational results, presented in  FIGS. 22 through 40 , were obtained with the computer simulation program SOUCVOL—in which equations A1 through A9, which were used in the derivation of the variable-length radius R 3   W , and the 10 basic rotational equations B1a through B10.3c were all used in each of the previously-mentioned 721 iterations. The plots presented in  FIGS. 22 through 31  and in  FIGS. 37 and 38  as functions of theta0(from 0 to 360 degrees) were all obtained using one subassembly  40  only, rotating about the fixed point  0  at a constant counterclockwise angular velocity ω 0 =100 rad/sec.  FIGS. 32 through 36  and  FIGS. 39 and 40  present other aspects of the cubic TDMM craft&#39;s Machine performance rotational results in which, for example, the number of rotating subassemblies  40  and/or the angular velocity values were variously used and/or combined.  
         [0237]     The performance results for one rotating subassembly  40  were calculated at every 0.5 degree “delrot” incrementation of the angle of rotation theta0, in order to provide several simultaneously-obtained, more accurate sets of rotational results for the 8 equally-spaced (45 degrees apart), variable-length subassemblies  40 , no matter where the #1 subassembly  40  starts on the inside surface of inner rim  33  (see  FIGS. 11 and 12 ). However, for simplicity and clarity in the figures, the cubic TDMM craft&#39;s performance results are plotted every 10 degrees only, from 0 to 360 degrees (which should not affect the accuracy of the results).  
         [0238]     In  FIGS. 22 through 31 , the subscripts ( W ) and ( br ) are used with some parameters (such as with VT W  and VT br ) to refer to rotational results obtained for the 2-wheel device W (also referred to as part number  47  in both  FIGS. 11 and 12 ), running at the end of the variable-length radius R 3   W  along the inside surface of inner rim  33 , and for the variable-length bar&#39;s variable-length radius of gyration R 3   br , running along its circular locus of R 3   br (which is shown as a dashed circle in both  FIGS. 19 and 20 ).  
         [0239]      FIG. 22  shows plots of angles ALF, A and DIRA as functions of theta0. As illustrated in  FIG. 21 , angle ALF (see equation B9a) is the angle between the resultant centrifugal force ResF and the radial force FR, angle A (see equation A4) is the angle (measured from 0 degree) representing the direction of FR from point P, and angle DIRA (see equation B9b) is the angle (also measured from 0 degree) representing the direction of ResF from the fixed off-center point  0 . As also shown in  FIG. 21 , the direction of FR was chosen to start at point P (the center of inner rim  33 ) to ensure that the tangential force FT is always at right angle with the radial force FR on inner rim  33  and that the direction of angle DIRA, which is equal to angle A+angle ALF, should always be equal to the angle of rotation theta0. As also indicated in the “Derivation Of The Variable-length Radius R 3   W  Equation” in section A, these angles are used (directly or indirectly) for deriving the equation for the variable-length R 3   W (see equation A5), on which the other 10 basic rotational equations presented in section B, such as the tangential velocity VT W (see equation B1a), the tangential acceleration (see equation B1b), . . . etc . . . ) all depend for their derivations. For example,  FIG. 21  shows that, when theta0=40 degrees, R 3   W  (which is subassembly  40 )=2.16 ft, angle ALF=12.3 degrees, angle A=27.7 degrees and angle DIRA=A+ALF=40.0 degrees, which are all used to calculate the tangential force FT=231.3 lbs in the direction of 117.6 degrees (as measured from 0 degree), making a right angle with the direction of the radial force FR=1061.1 lbs in the direction of 27.7 degrees (from 0 degree) and the vectorially combined resultant centrifugal force ResF=1086.0 lbs in the direction of angle DIRA=40.0 degrees. Note that the direction of DIRA is the same as that of theta0 and that the direction of FR is also the same as that of angle A at point P. The three angles ALF, A and DIRA, shown in  FIG. 21  for theta0=40 degrees, can also be found in  FIG. 22 .  
         [0240]      FIG. 23  presents plots of the variable-length radii R 3   W  and R 3   br  and of the constant-length radii R 1   W  and R 1   br  as functions of theta0. The R 1   W  and R 1   br  plots are also presented in this figure for visual comparison with the R 3   W  and R 3   br  plots. As shown in  FIG. 20 , R 3   W  represents the variable radial length of the 2-wheel device  47  (W), from the fixed, off-center point  0  to a point on inner rim  33 , and R 3   br  is the variable-length of the bar&#39;s radius of gyration, also from the fixed, off-center point  0  to a point on the locus of the bar&#39;s radius of gyration (shown as a dashed circle with radius R S  and center at point S). The R 3   W  and R 3   br  plots were obtained with equations A5 and A8 respectively, using one subassembly  40  only. The R 1   W  plot represents the constant-length radius of inner rim  33  and the R 1   br  plot (which is equal to R 1   W M br ) represents the constant-length radius of gyration of the bar (slide  46 ). The variable-length R 3   W  plot is the most important of all the plots, because all the other plots (including R 3   br ) depend on it directly or indirectly for their plotted values as functions of theta0. The trigonometric relationships between angles A (see equation A4), B (see the four angle B options on page 35) and C (see equation A3) and the radial lengths of R 3   W , R 1   W  and R 2  for angle theta0=135 degrees is shown in  FIG. 15 . Angles A, B and C were all used (directly or indirectly) to derive the variable-length radius R 3   W (see equation A5).  
         [0241]      FIG. 24  shows plots of the variable tangential velocities VT W =(R 3   W )ω 0 , in which ω 0 =100 rad/sec, and VT br =VT W (M br )—in which the constant multiplier M br =0.5773503(see equation A9) is used to calculate it. The constant tangential velocity plots of VT 1   W  and VT 1   br  are also presented here for comparison with the VT W  and VT br  plots. The VT W  and VT br  plots were obtained with equations B1a and B1b respectively, using one subassembly  40  only, rotating at 100 rad/sec. The reason why the four tangential velocity plots appear to be identical to the four radii plots in  FIG. 23  is because an initial input angular velocity ω 0 =100 rad/sec was used in the above variable and constant tangential velocity equations, thus causing the Y-axis tangential velocity scale to be 100 times greater than that of the Y-axis radius scale in  FIG. 23 .  
         [0242]      FIG. 25  presents an interesting angular velocity ω 2  plot, representing the relative variable angular velocity of subassembly  40  as a function of theta0. It shows another aspect of the angular velocity of the 2-wheel device  47  (W), running along on the inside surface of the movable inner rim  33  as if it were rotating at the end of the constant-length radius R 1   W  about the inner rim&#39;s center point P with the same variable tangential velocity VT W (see  FIG. 24 ) obtained when W was rotating at the end of the variable-length radius R 3   W  about the fixed, off-center point  0  (see  FIGS. 11 and 12 ) with a constant angular velocity ω 0 =100 rad/sec. The reason for this variable ω 2  plot (which appears to conflict with the actual constant input angular velocity ω 0 =100 rad/sec) is found in the expanded relationship ω 2 =VT W /R 1   W =(R 3   W ω 0 )/R 1   W =R 3   W (ω 0 /R 1   W ), in which the last term shows that, since R 1   W  and ω 0  are both constant input parameters (see Table 1), then ω 2  varies proportionately with the variable-length radius R 3   W . As a result, and unlike the constant input angular velocity ω 0  of 100 rad/sec, the angular velocity plot of ω 2  varies continually from 66.67 rad/sec, at both theta0=0 degree and at 360 degrees, to 133.33 rad/sec, at theta0=180 degrees. Note that, at both theta0=100 degrees and 260 degrees, the variable relative ω 2  and the constant ω 0  plots are both equal to 100 rad/sec, because, as shown in  FIG. 23 , both R 3   W  and R 1   W  are equal to 3 ft at those same two theta0 angles. The input constant angular velocity plot of 100 rad/sec is shown here for comparison with the variable angular velocity plot.  
         [0243]      FIG. 26  shows three average variable tangential acceleration plots with similar sinusoidal shapes. They were obtained with equations AT Wav =(VT W −VT W0 )/deltm and AT brav =(VT br −VT br0 )/deltm (see equations B2a and B2b), which are both combined in equation AT av =AT Wav +AT brav (see equation B2c). The sinusoidal shapes of these three tangential plots are caused by the numerators (WT W −WT W0 ) and (WT br −WT br0 ) respectively, which both represent small changes in the tangential velocities of W (running along the inside surface of movable inner rim  33 —see  FIGS. 11 and 12 ) and of the bar&#39;s radius of gyration R 3   br (running along its locus, shown as a dashed circle in  FIG. 20 ), which occur between the start and the end of the small elapsed delta time “deltm”, which is the time required for subassembly  40  to rotate about the fixed off-center point  0  through each incremented 0.5 degree of angle theta0(see delrot in Table 1). For example (keeping in mind that angle theta0 rotates counterclockwise around the fixed point  0 ), VT W  and VT br  in the above two numerators always represent the exact calculated angular velocities at the start of the newly 0.5-degree-incremented theta0 interval in the current iteration while VT W0  and VT br0 (at the end of each 0.5 degree interval) represent the velocities which were obtained 0.5 degree earlier, or “deltm” (see equation B2a) earlier, in the previous iteration. Therefore, as shown in  FIG. 24 , both VT W  and VT br  values in both numerators (VT W −VT W0 ) and (VT br −VT br0 ) are always identical at any two symmetrical theta0 values on each side of 180 degrees in the current iteration (such as at 45 and 315 degrees), while the VT W0  and VT br0  values, which were obtained 0.5 degree earlier in the previous iteration (such as at 44.5 and 314.5 degrees instead of 45 and 315 degrees), are always slightly smaller that the VT W  and VT br  between 0 and 180 degrees and slightly larger than the VT W  and VT br  values between 180 and 360 degrees. That is why the numerators (VT W −VT W0 ) and (VT br −VT br0 ) always cause the AT Wav  and AT brav  plots to be positive between 0 and 180 degrees and negative between 180 and 360 degrees—thereby causing the sinusoidal shapes of the three tangential acceleration plots.  
         [0244]     However, the small difference between the two VT W  and VT W0  tangential velocities in the (VT W −VT W0 ) numerator introduces a small, insignificant discrepancy when calculating the absolute average AT Wav  values on each symmetrical side of 180 degrees every time theta0 is incremented by 0.5 degree. For example, as shown in  FIG. 24 , the two symmetrical VT W  values shown at both theta0=110 and 250 degrees are both equal to 319.1 ft/sec respectively (which is as it should be) while VT W0 , which was obtained 0.5 degree earlier, has a value of 318.18 ft/sec when theta0 was at 109.5 degrees (which is slightly smaller than that of VT W  at 110 degrees) and a value of 320.02 ft/sec when theta0 was at 249.5 degrees (which is slightly larger than that of VT W  at 250 degrees). As a result, the absolute values of AT Wav =(VT W −VT W0 )/deltm is equal to [+10,528.6] ft/sec 2  at 110 degrees and is equal to [−10,521.3] ft/sec at 250 degrees respectively (indicating a small, insignificant difference of 6.7 ft/sec 2  between the two average tangential accelerations—or a difference of about 0.0006%). Also, because there&#39;s no change in tangential velocities between VT W  and VT W0 at theta0=0, 180 and 360 degrees, AT Wav  is equal to 0 ft/sec at those three theta0 values. The same argument also applies to the plot of AT brav =(VT br −VT br0 )/deltm. Finally, since both AT Wav  and AT brav  are parrallel vectors, they were simply added to obtain the AT av  plot.  
         [0245]      FIG. 27  shows three variable radial acceleration plots of AR br =VT br   2 /R br =AR W  (M br ), AR W =VT W   2 /R 3   W  and AR=AR br +AR W (see equations B5b, B5a and B5c) which, unlike the plots of  FIG. 26 , are bell-shaped and positive between 0 and 360 degrees—because these plots depend directly on the tangential velocity plots of  FIG. 24  for their plotted values. Also, because both AR W  and AR br  are parallel vectors, they are simply added to obtain the AR plot.  
         [0246]      FIG. 28  shows three variable resultant acceleration plots of ResA br ={square root}{square root over (()}AT brav   2 +AR br   2 ), ResA W ={square root}{square root over (()}AT Wav   2 +AR W   2 ) and ResA=ResA W +Res br (see equations B7b, B7a and B7c respectively). Both the ResA br  and the ResA W  plots were obtained from the tangential and radial acceleration plots shown in  FIGS. 26 and 27 . Here, since both the tangential and radial accelerations and their related forces (see  FIG. 21 ) always intersect at right angles on inner rim  33  for any given theta0 value, they are vectorially combined by using the Pythagorean theorem to obtain their resultant accelerations. For example, at theta0=110 degrees, AT brav =6,078.6 ft/sec in  FIG. 26  and AR br =18,423.5 ft/sec in  FIG. 27 , which both vectorially combine to give ResA br =19,400.4 ft/sec 2  at theta0=110 degrees in this figure. Here also, because both ResA W  and ResA br  are parallel vectors, they are simply added to obtain the ResA plot.  
         [0247]      FIGS. 29, 30  and  31  respectively present plots of the average tangential forces FT brav , FT Wav  and FT av (see equations B4b, B4a and B4c), radial forces FR br , FR W  and FR (see equations B6b, B6a and B6c) and resultant centrifugal forces ResF br , ResF W  and ResF (see equations B8b, B8a and B8c), which were all generated using one rotating subassembly  40  only. They were all obtained by substituting the tangential, radial and resultant acceleration plot results (see  FIGS. 26, 27  and  28  plots) respectively into the basic force equation F=MA, in which M is the mass of the rotating body and A is its acceleration. As given in Table 1, the weights of both the 2-wheel device  47  (W W ), at the end of the variable-length bar&#39;s radius R 3   W , and of the variable-length bar R 3   br  (W br ), in each subassembly  40 , are each arbitrarily equal to one pound (which is equal to a mass of 0.031081 slug). Thus, for example, when substituting M=0.031081 slug and ResA=53,003.0 ft/sec 2  at 110 degrees in  FIG. 28  in the above F=MA equation, a resultant centrifugal force ResF=1,647.4 lbs is obtained at 110 degrees in  FIG. 31 . This same ResF value of 1,647.4 lbs in  FIG. 31  can also be obtained directly by substituting the values FT av =516.17 lbs at 110 degrees in  FIG. 29  and FR=1,564.4 lbs at 110 degrees in  FIG. 30  in equation ResF={square root}{square root over (()}FT av   2 +FR 2 ). Also note that the maximum value of ResF=1,961.0 lbs at 180 degrees and the minimum values of ResF=980.5 lbs at both theta0=0 and 360 degrees in  FIG. 31  are the same as those of the FR values at the same theta0 values in  FIG. 30 —simply because FT av =0 lbs at those same theta0 values of 0, 180 and 360 degrees in  FIG. 29  and therefore does not contribute anything to the combined values of ResF at those same angles in  FIG. 31 .  
         [0248]      FIG. 32  shows a graphical representation of the 8 equally-spaced centrifugal forces (ResF) simultaneously acting at the fixed, off-center point  0 . They were generated by the 8 equally-spaced, variable-length subassemblies  40  (see  FIG. 12 ), rotating at 100 rad/sec about the fixed, off-center point  0 . These 8 forces and their associated directions can also be obtained, 45 degrees apart (starting at theta0=0 degree), from the ResF plot of  FIG. 31 .  
         [0249]      FIG. 33  presents a graphical representation of the use of both the triangle and the polygon methods for vectorially combining the 8 forces (numbered from 1 to 8) shown in  FIG. 32  into a single resultant centrifugal force vector ResF=1,989.4 lbs, shown as a heavy black arrow closing the polygon, from the fixed, off-center point  0  (which is also the tail of force vector #1) to the head of the last force vector #8(which is the head of force vector #8), in the direction of 180 degrees. The direction of this vectorially combined, single ResF vector of 1,989.4 lbs always points outwardly, from the fixed, off-center point  0  to where inner rim  33  makes contact with the inside surface of outer rim  34 —the contact point of which was arbitrarily chosen to be at 180 degrees. The 180-degree direction of this single ResF vector could just as easily have been chosen to be in some other direction, such as at 225 degrees, or 90 degrees, and still give the same single ResF vector result—by simply moving inner rim  33  to make contact with the inside surface of outer rim  34  in that other new direction (which is also the direction in which the variable-length subassembly  40  achieves its greatest maximum length).  
         [0250]     Two methods can be used to combine the 8 forces in  FIG. 32 . The first method consists of drawing all 8 equally-spaced force vectors in succession on a graph paper, with the tail of each at the head of the vector preceding it, and then close the polygon by drawing a final vector from the tail of the first vector to the head of the last vector. However, while this technique is good to use when there is only one polygon to draw, it is preferable to write a computer program and use it to quickly do all the calculations needed to vectorially combine all the 8 separate force vectors when many polygons are involved (as is the case in the ResF plots of  FIGS. 34 and 35 ).  
         [0251]     The second triangle and polygon method mentioned above has therefore been programmed in SOUCVOL—using the law of cosine equation c 2 =a 2 +b 2 −2ab(cos C), in which a, b and c represent the three force vectors of any oblique triangle and A, B and C are the angles opposite those three sides (see  FIGS. 15 and 33 ). Then, if the triangle&#39;s sides a and b are replaced with the appropriate two known force vectors F a  and F b (from  FIG. 32 ) in each of the seven triangles of  FIG. 33 , then side c becomes the force vector F c (shown as a dashed line closing each triangle), which is obtained with the above law of cosine equation, which then becomes F c ={square root}{square root over (()}F a   2 +F b   2 −2F a F b (cos C)). However, before being able to solve this F c  equation, angle C (between vectors F a  and F b  in each of the seven triangles in the polygon in  FIG. 33 ) must first be obtained as follows: 
    1) if the direction of F a (i.e., DirF a ) is less than or equal to 180 deg, then angle C=(180 deg+DirF a −DirF b ) and     2) if DirF a  is greater than 180 degrees, then angle C=(DirF a +DirF b −180 deg).    
 
         [0254]     For example, triangle #1 in  FIG. 33  shows that force vector F a =980.5 lbs in the direction of 0 deg and force vector F b =1,113.7 lbs in the direction of 45 degrees (which respectively represent force vectors 1 and 2 in  FIG. 32 ). Now, according to (1) above, angle C=(180 deg+0 deg−45 deg)=135 degrees for triangle #1, between vectors F a  and F b . Next, after substituting these three F a , F b  and angle C values in the above law of cosine equation gives F c =1,936.0 lbs, in the direction of 24 degrees (from 0 degree)—which is shown as a dashed line from the tail of F a =980.5 lbs (at the fixed, off-center point  0 ) to the head of F b =1,113.7 lbs, closing triangle #1. As shown in  FIG. 33 , this first F c  direction of 24.0 degrees for triangle #1 is also the value of angle B for triangle #1, which was obtained from the law of sines equation A1 (in which F b  and F c  are substituted for R 1   W  and R 2 ) which, after being solved for angle B, gives angle B=sin −1 ((F b /F c )sin C). For example, substituting the above three known values for F b , F c  and angle C obtained for triangle #1 into the above angle B equation gives angle B=sin −1  ((1,113.7 lbs)/(1,936.0 lbs))(0.7071)=24.0 degrees. Next, this first F c  value of 1,936.0 lbs of triangle #1 now becomes F a =1,936 lbs in the direction of 24 degrees for triangle #2, with the second vector F b =1,470.5 lbs at 90 degrees (which is force vector #3 in  FIG. 32 ). Again, from the angle C relationship in (1) above, angle C for triangle #2 is equal to (180+24−90)=114.0 degrees and, after substituting this second set of known F a , F b  and angle C values of triangle #2 in the law of cosine equation, gives F c =2,868.1 lbs in the direction of (27.9 deg+24 deg)=51.9 degrees (again from 0 deg)—in which 27.9 degrees, which is the value of angle B for triangle #2(which was obtained with the above angle B equation), was added to the angle B value of 24 degrees of triangle #1 to get the direction of 51.9 degrees. This second F c =2,868.1 lbs then becomes the F a  value for triangle #3 . . . and so on . . . , until, as shown in triangle #7, the last calculated F. value represents the resultant centrifugal force ResF=1,989.4 lbs, in the direction of 180 degrees, which is shown as a heavy black arrow closing the polygon, from the tail of the first F a (at the fixed point  0 ) to the head the 8th force vector F b =1,114.4 lbs, in the direction of 45 degrees (counterclockwise from 180 degrees). Again, since the above ResF of 1,989.4 lbs is for one Machine mirror-image half only, then the combined total ResF generated by the cubic TDMM craft&#39;s entire Machine doubles to 3,978.8 lbs—also in the same 180-degree direction.  
         [0255]      FIG. 34  presents two plots of resultant centrifugal force (ResF) results for one Machine half only obtained for the 8 equally-spaced subassemblies  40  shown in  FIG. 12 , rotating in the maximum “active position” at 100 rad/sec about the fixed, off-center point  0 . One plot represents the 10 calculated ResF results obtained at each successive 5-degree starting positions of the #1 subassembly  40  (see  FIG. 12 ), from 0 degree to 45 degrees, and the other represents the average plot of the 10 calculated ResF results (obtained between 1,989.39 and 1,989.54 lbs)—with an average value of 1,989.46 lbs across the 45-degree range. The 0-to-45 degree range used in the 10 calculated ResF plot is all that is needed here because, as shown in  FIG. 12 , when the #1 subassembly  40  has moved from theta0=0 degree to theta0=45 degrees, the # 8 subassembly  40  has also moved from theta0=315 degrees to theta0=360/0 degrees (which was where the #1 subassembly  40  started from) and, after that, the same sequence of the 10 plotted ResF values repeats itself in each successive 45-degree range. The 10 plotted ResF values were also obtained with the combined use of both the triangle and the polygon methods (shown in  FIG. 33 ), using the computer program SOUCVOL to calculate each of the 10 results.  
         [0256]     The insignificant deviations shown between the 10 calculated ResF plot and the average ResF plot (which represents an average deviation of about 0.04 lbs from the average plot of 1989.46 lbs—which is about 0.002%) is not an indication of the presence of any unwanted rotational vibrations (impulses), which might affect the smooth flight of the cubic TDMM craft. They may only be the result of slight differences in the way SOUCVOL calculated the 10 ResF results and are not therefore an indication that they were caused by the different positions of the #1 subassembly  40  between 0 and 45 degrees.  
         [0257]      FIG. 35  presents another plot of SOUCVOL-generated resultant centrifugal force (ResF) results as a function of angular velocity (from 0 to 350 rad/sec respectively) for one Machine mirror-image half only, using the set of 8 variable-length subassemblies  40 , rotating about the fixed, off-center point  0  (see  FIG. 12 ). A table in the upper left corner shows the equivalent rpm and ResF values for each of the indicated angular velocities, along with a couple of equations for obtaining the equivalent rpm and ResF values for any given angular velocity. For example, the table shows that when the set of 8 subassemblies  40  rotates at an angular velocity of 100 rad/sec (954.3 rpm) it generates a vectorially-combined ResF of 1,989.5 lbs. The same table also shows that when the same set of 8 subassemblies  40 , rotating at 350 rad/sec (3,342.3 rpm), an impressive combined ResF of 24,370.5 lbs would be generated. As another example of the use of the two above-mentioned rpm and ResF equations, one set of 8 subassemblies  40 , rotating at 700 rad/sec (6,684.5 pm), would generate an outwardly-directed, resultant centrifugal force (ResF) of 97,482.1 lbs in each Machine mirror-image half—. and, since there are two such mirror-image halves in the cubic TDMM craft, then the ResF results versus angular velocity presented in  FIG. 35  would respectively double.  
         [0258]     The plot of ResF results versus angular velocity presented in  FIG. 35  really shows the truly amazing power of centrifugal force—which makes it possible for the two counter-rotating sets of 8 variable-length subassemblies  40  in the small-scale, 600-lb cubic TDMM craft&#39;s Machine to generate such spectacular motive forces. This kind of spectacular ResF performance is solely due to the innovative use of the variable-length slide  46  (see  FIGS. 3, 4  and  5 ) which, because of its full extension capability (from 2 to 4 ft), enables the Machine to generate such powerful resultant centrifugal forces. However, any angular velocities above 50 rad/sec can only be safely achieved in the Machine by using a more technologically-advanced design of the said “telescoping full extension slide”—one that would be capable of withstanding much greater rotational centrifugal forces than is now possible with the “hardware-store-bought” slide  46  that is now used in the exemplary cubic TDMM craft&#39;s Machine.  
         [0259]      FIG. 36  presents three plots of resultant centrifugal force (ResF) results as functions of 6, 8 and 10 identical, equally-spaced variable-length subassemblies  40 , each rotating at 100 rad/sec about the fixed outer rim&#39;s center, point  0 , in each Machine mirror-image half&#39;s movable inner rim. These three ResF plots show a wide spectrum of resultant centrifugal force results, obtained with three different sizes of rotating sets of subassemblies  40 , labeled 1X, 2X and 3X respectively. The 1X plot represents the three 6, 8 and 10-subassembly  40  cases run with a fixed outer rim&#39;s radius R 0 =4 ft, a movable inner rim&#39;s radius R 1   W =3 ft, a variable-length subassembly&#39;s radius R 3   W (which alternatively varies its length from a minimum of 2 ft to a maximum of 4 ft) and with both the 2-wheel device  47  (W) and the bar (slide  46 ) in each subassembly  40  weighting 1 pound each. The other 2X and 3X plots were obtained with 2 and 3 times the subassembly&#39;s variable-length radii and weights used in the 1X plot for the 6, 8 and 10-subassembly  40  cases—representing ResF results obtained with a cubic TDMM craft two and three times the size of the one used in the 1X-plot. For example, in the 2X plot, R 0 =8 ft, R 1   W −6 ft, R 3   W  varies between 4 and 8 ft and W and the bar weigh 2 lbs each.  
         [0260]     The wide spectrum of ResF results shown in the three plots of  FIG. 36 , which range from a minimum of 1,493.0 lbs for the 6-subassembly  40  system in the 1X plot to a maximum of 22,381.0 lbs for the 10-subassembly  40  system in the 3X plot, suggests other possible ways for increasing the ResF output of each Machine mirror-image half, besides increasing the angular velocity, as is shown in  FIG. 35 . For example, the ResF value of 22,381.0 lbs obtained in the 3X plot with 10 subassemblies  40  rotating at 100 rad/sec is about equal to the ResF value obtained with 8 subassemblies  40  rotating at about 330 rad/sec in the plot of  FIG. 35 .  
         [0261]      FIGS. 37 through 40  respectively present different aspects of rotational kinetic energy (KE) results. They were all obtained with the basic rotational KE equation (B10.1), namely:
   KE=   Σ (1/2) M ( Rω   0 ) 2 = Σ (1/2) MR   2 ω 0   2 =(1/2) Mω   0   2   Σ   R   2   
 in which M and (ω 0  are constant input parameters (see Table 1) and R represents the constant-length radii R 1   W  and R 1   br  for the “neutral position” case (see  FIGS. 11 and 19 ) and the variable-length radii R 3   W  and R 3   br  for the “active position” case (see  FIGS. 12 and 20 ) respectively. These different radii are successively used in the above KE equation to separately calculate the individual KE results for slide  46  (bar), the 2-wheel device  47  (W) and for both W and the bar combined as one assembly  40 —the KE results of which are presented in  FIGS. 37 and 38 . 
 
         [0262]      FIG. 37  presents three constant rotational KE plots, respectively labeled KE0 br  for the bar (slide  46 ), KE0 W  for the 2-wheel device  47  (W) and KE0 for both W and the bar (combined as one subassembly  40 ) as functions of theta0. Both the bar and the W plots were separately obtained by using the two constant-length radii, R 1   br  for the bar&#39;s radius of gyration and R 1   W  for W, both rotating as one unit at 100 rad/sec about superimposed points P,  0  and S in the “neutral position” (see  FIG. 19 , in which the circular locus of R 1   br  is shoed circle with radius R S  which is equal to radius R 1   br ) and center at point S. They each were obtained by using equations (B10.2a), (B10.2b) and (B10.2c), and remain constant at 466.2, 1,398.6 and 1,864.9 ft*lbs respectively.  
         [0263]      FIG. 38  presents three variable rotational KE plots, respectively labeled KE1 br  for the bar (slide  46 ), KE1 W  for the 2-wheel device  47  (W) and KE1 for both W and the bar (combined as one subassembly  40 ) as functions of theta0. Both the bar and the W plots were separately obtained by using the two variable-length radii R 3   br  for the bar&#39;s radius of gyration and R 3   W  for W, both rotating as one unit at 100 rad/sec about the fixed, off-center point  0  in the maximum “active position” (see  FIG. 20 , in which the circular locus of R 3   br  is shown as a dashed circle with radius R S  and center at point S). They each were obtained by using equations (B10.3a), (B10.3b) and (B10.3c), and show minimum rotational KE values of 207.2, 621.6 and 628.8 ft*lbs at both theta0=0 degree and 360 degrees and maximum KE values of 828.8, 2,486.5 and 3,315.3 ft*lbs at theta0=180 degrees respectively. Their bell shapes are directly dependent on the variable-length radii R 3   br  and R 3   W  plots in  FIG. 23  which, because M and ω 0  are both constant parameters in the above rotational KE equation, cause the plots in this FIG. to vary with R/2)F c , as shown in the expanded rotational equation KE=(1/2)(Mω 2 R 2 )=(1/2)(MRω 2 )R=(R/2)F c , in which F c  is the centrifugal force equation (1) for one rotating body.  
         [0264]      FIG. 39  shows a graphical representation of the 8 different, equally-spaced (45 degrees apart) rotational KE1 results, obtained from the plot of  FIG. 38 . They were simultaneously generated by the 8 variable-length subassemblies  40  (see  FIG. 12 ), rotating at 100 rad/sec in the maximum “active position” about the fixed, off-center point  0  (with subassembly #1 shown at 360/0 degree on the inner rim  33 ) in one Machine mirror-image half only.  
         [0265]      FIG. 40  shows two different rotational KE plots as functions of the number of subassemblies  40 , from 1 to 8, respectively labeled KE2 and KE3. The KE2 plot represents the 8 cumulatively-added constant KE0 values from  FIG. 37  and the KE3 plot represents the 8 cumulatively-added variable KE1 values from  FIG. 38  (or  FIG. 39 ), whose values were simultaneously obtained, 45 degrees apart (starting at 0 degree), by the 8 subassemblies  40 , rotating in both the “neutral position” (see  FIG. 11 ) and in the “active position” (see  FIG. 12 ) respectively. For example, the first 3 cumulatively-added constant KE0 values from  FIG. 37  in the KE2 plot are equal to 5,594.6 ft*lbs and the first 3 cumulatively-added variable KE1 values from  FIG. 38  (or  FIG. 39 ) in the KE3 plot are equal 3,497.0 ft*lbs respectively.  
         [0266]     However, although  FIG. 40  shows that both sets of KE0 and KE1 values shown in the KE2 and KE3 plots are different between the 1 through the 7 cumulatively-added KE0 and KE1 values, they each end up with the same total cumulative KE value of 14,918.9 ft*lbs when their 8th KE0 and KE1 values are added to the KE2 and KE3 plots—and the reason for this is simply because they were both generated by the same set of 8 subassemblies  40 , rotating in the “neutral position” in  FIG. 11  (with constant-length subassemblies  40 ) and in the “active position” in  FIG. 12  (with variable-length subassemblies  40 ).  
         [0267]     First, before considering a very important aspect associated with the set of 8 variable rotational KE results presented in  FIG. 39  and cumulatively-added in the KE3 plot, let&#39;s first look at the principle of conservation of angular momentum equation L=Iω), in which ω is the velocity of a body (such as one subassembly  40 , rotating about a fixed axis, point  0 ) and I is its moment of inertia. In the above angular momentum equation, I=MR 2 , in which M is the mass of the rotating body and R is its radius. Therefore, the conservation of angular momentum equation basically says that, in order for L to remain constant when I increases, ω must decrease, and vice versa. However, when returning to the 8 rotational KE1 results shown in  FIG. 39  (and in the KE3 plot of  FIG. 40 ), there seems to be quite a different situation in which: 
    1) although, as shown in  FIG. 23 , each of the 8 rotating variable-length subassembly  40  shown  FIG. 12  continuously changes its radial length R 3   W  as a function of theta0, which should cause ω to change inversely with R 3   W  in order to keep L constant, yet     2) each subassemblies  40  keeps on rotating about the fixed, off-center point  0  with a constant input angular velocity ω 0 =100 rad/sec while, at the same time, continually varying its radial length R 3   W —thereby contradicting the principle of conservation of angular momentum stated above.    
 
         [0270]     Therefore, since the principle of conservation of angular momentum doesn&#39;t seem to apply directly to any of the 8 rotational KE1 results, rotating at a constant 100 rad/sec in  FIG. 39 , one must therefore look more closely at the rotational KE increases and decreases occurring simultaneously in either: 
    1) the four pairs of anti-parallel KE1 interval increases and decreases shown in  FIG. 39  (such as between KE numbers 1 and 2, 5 and 6, 2 and 3, 6 and 7 . . . etc . . . ), or     2) the two larger sets of anti-parallel sets of 4 combined KE1 interval increases and decreases on each side of 180 degrees of  FIG. 39  (such as between KE numbers 1 and 5 on one side and KE numbers 5 and 1 on the other side).    
 
         [0273]     For example, first looking at the #1 case above (with the four pairs of anti-parallel KE results),  FIG. 39  shows that when subassembly #1 moves to where subassembly #2 is, there is a rotational KE increase of +181.7 ft* lbs, while its anti-parallel subassembly #5 shows a KE decrease of −596.1 ft*lbs when it moves to where subassembly #6 is—which adds up to a KE decrease of −414.4 ft*lbs. Next, when subassembly #2 moves to where subassembly #3 is, there is a KE increase of +647.2 ft*lbs, while its anti-parallel subassembly #6 shows a KE decrease of −1061.5 ft*lbs when it moves to where subassembly #7 is—which adds up to a KE decrease of −414.3 ft*lbs. Similarly, the next two counterclockwise moves of numbered pairs of anti-parallel subassemblies add up to KE increases of +414.4 ft*lbs and +414.3 ft*lbs respectively. Then, when the first two KE decreases are added to the second two KE increases, they add up to exactly 0 ft*lbs.  
         [0274]     Next, when looking at the #2 case above,  FIG. 39  shows that the two sets of 4 rotational KE1 intervals on each side of 180 degrees,  FIG. 39  shows a total KE decrease of −2486.5 ft*lbs (between 180 degrees and 360 degrees) and a total KE increase of +2,486.5 ft*lbs (between 0 degree and 180 degrees), which also adds up to exactly 0 ft*lbs.  
         [0275]     Therefore, the above discussion regarding the decreasing and increasing rotational KE results taking place on each side of 180 degrees in  FIG. 39  strongly suggests that a transfer of rotational KE is automatically occurring from the decreasing KE side to the increasing KE side, in order to keep the 8 different variable-length assemblies  40  rotating at a constant 100 rad/sec and not violate the principle of conservation of angular momentum. This KE transfer occurs spontaneously through the rigid connection which the 8 variable-length subassemblies  40  make with the 16-inch-radius metal disk  31  and the high-speed hub  44 , as they all rotate together as one unit about the stub axle  45  (at the fixed, off-center point  0 —see  FIGS. 9 and 12 ) inside the vertical plane of the movable inner rim  33 . As a result of this spontaneous KE transfer, both the constant input angular velocity ω 0 =100 rad/sec and the total rotational KE of 14,918.88 ft*lbs per revolution (shown in the cumulatively-added KE2 and KE3 plots of  FIG. 40 ) are therefore preserved. It is also therefore logical to conclude that this KE transfer represents a case of self-adjusting conservation of angular momentum as well as of rotational KE, occurring only when the 8 variable-length subassemblies  40  rotate in the “active position” (see  FIG. 12 ) but not in the “neutral position” (see  FIG. 11 ).  
         [0276]     Furthermore, as a result of the conservation of both the angular momentum and the total rotational KE mentioned above (from the decreasing KE side to the increasing KE side of  FIG. 39 ),  FIG. 40  also indicates that, because both the constant KE2 and the variable KE3 plots show the same total amount of cumulatively-added total rotational KE of 14,918.9 ft*lbs, the set of 8 constant-length subassemblies  40 , rotating in the “neutral position” in  FIG. 11 , and the set of 8 variable-length subassemblies  40 , rotating in the “active position” in  FIG. 12 , are really the same set. That is why, as indicated by the two KE2 and KE3 plots of  FIG. 40 , this same set of 8 subassemblies  40  produces and stores the same total amount of rotational KE of 14,918.9 ft*lbs per revolution when rotating at 100 rad/sec in either the “neutral position” or in the “active position”—which also means that this same rotating 8-subassemblies  40  system also acts just like a flywheel in both cases.  
         [0277]     However, apart from the fact that the set of 8 subassemblies  40  system (in each Machine mirror-image half) generates a total amount of rotational KE of 14,918.9 ft*lbs per revolution when rotating at 100 rad/sec in both the “neutral position” (see  FIG. 11 ) and the “active position” (see  FIG. 12 ), there is a most important difference between the two cases. When rotating in the “active position”, in which the 8 subassemblies  40  all have different radial lengths, they all generate different amounts of centrifugal forces F c  which, when vectorially combined (see polygon of  FIG. 33 ) generate a single, outwardly-directed resultant centrifugal force (ResF) of 1,989.4 lbs in any selected direction (from (inside its circular inner rim&#39;s vertical plane), but when the same 8 subassemblies  40  rotate in the “neutral position”, in which they all have the same radial lengths, they therefore all generate the same amount of centrifugal forces (F c ) which, when vectorially combined (see the polygon of  FIG. 33 ), do not generate any ResF at all in any direction. In summary, since there are two Machine mirror-image halves in the exemplary cubic TDMM craft embodiment, each with a set of 8 subassemblies  40  rotating at 100 rad/sec, then the two sets of 8 subassemblies  40  in the entire Machine generate a combined, single, outwardly-directed ResF of 3,978.8 lbs in the “active position” case only, but store a total, combined rotational KE of 29,837.8 ft*lbs per revolution in both the “active position” and the “neutral position” cases.  
         [0278]     Finally, when the selected direction of the Machine&#39;s total ResF of 3,978.8 lbs (generated in the vertical planes of both movable circular inner rims  33  and  35  by the two counter-rotating sets of 8 subassemblies  40 ) is combined with the chosen horizontal direction (azimuth) of the rotatable internal housing frame  13  (in which the Machine is enclosed), a steerable, variable and powerful motive force is then made available (see  FIGS. 42 and 46 ) for propelling the small-scale, 600-lbs cubic TDMM craft of the invention with unparalleled performance and maneuverability in three dimensions, anywhere on earth and in outer space.  
         [0000]     Discussion of the Cubic TDMM Craft Performance Results  
         [0279]     As stated in the “Brief Description of the Drawings” section,  FIGS. 41 through 48  present 8 sets of performance result plots of the 600-lb cubic TDMM craft as functions of vertical altitude (distance) from earth. In order to do the many calculations required to obtain these 8 sets of performance result plots, I wrote a computer program in QBASIC named PRFMEVL (for performance evaluation), which incorporates equations C1 through C11, into which the appropriate input parameters from Table 2 were used.  
         [0280]     These 8 sets of cubic TDMM craft performance result plots are divided into two separate groups of 4 sets each—with the 4 sets in each group respectively representing the cubic TDMM craft&#39;s average acceleration (A cc ), motive force (F cc ), instantaneous velocity at time T e  from earth launch (V e ) and average flight time (T cc ) from earth launch time as functions of vertical “near-earth” altitude in the first group and “far-earth” distance from earth in the second group.  
         [0281]     The first group of 4 sets of “near-earth” performance results are presented in  FIGS. 41 through 44 , in which they are plotted every 10 miles of vertical altitude from the earth&#39;s surface up to 250 miles in the direction of the moon. The second group of 4 sets of “far-earth” performance results are presented in  FIGS. 45 through 48 , in which they are plotted every 5,000.0 miles of vertical distance from the earth&#39;s surface all the way to the moon, 230,000.0 miles away.  
         [0282]      FIGS. 41 through 48  each show 3 plots of cubic TDMM craft&#39;s performance results, respectively labeled 50, 75 and 100 rad/sec. As indicated in Table 2, these 3 angular velocities were first used in SOUCVOL (using the proper sequence of equations B1a through B8c) to calculate the three cubic craft&#39;s constant resultant centrifugal motive forces (ResF) of 995.0, 2,238.1 and 3,979.8 lbs (respectively generated by the Machine&#39;s two sets of 8 subassemblies  40 ) that were used in the PRFMEVL program to obtain all the various cubic TDMM craft&#39;s performance result plots for each of the three 50, 75 and 100 rad/sec plots as functions of both the “near-earth” altitude and “far-earth” distance from earth.  
         [0283]     The combined effects of both the earth&#39;s negative gravitational acceleration (g e ) and its associated force of gravity (F e ) and of the moon&#39;s positive gravitational acceleration (g m ) and its associated force of gravity (F m ), the equations of which are given in Table 2, are included in the cubic TDMM craft A cc , F cc , V e  and T cc  performance plots presented in both groups of “near-earth” (see  FIGS. 41 through 44 ) and “far-earth” (see  FIGS. 45 through 48 ) as a function of the distance from earth. For example, the three 50, 75 and 100 rad/sec cubic TDMM craft motive force plots (F cc ) of  FIGS. 42 and 46  show how the three input cubic TDMM craft constant ResF values of 995.0, 2,238.1 and 3,979.8 lbs given in Table 2 are each affected by the combined earth and moon gravities as functions of altitude and distance from earth—thereby causing two different stages of cubic TDMM craft motive force in the three “near-earth” angular velocity plots of  FIG. 42  and three different stages of cubic TDMM craft motive force in the same three “far-earth” angular velocity plots of  FIG. 46 .  
         [0284]     Although the cubic craft average flight time T cc  (see equation C11) is used in the three 50, 75 and 100 rad/sec plots of  FIGS. 44 and 48 , as a function of vertical altitude (distance) from earth, a second elapsed flight time from earth, T e  (see equation C7), is also derived and used in PRFMEVL to do several important initial calculations that are needed to obtain a more representative time T cc . This second T e  equation is derived from the standard rectilinear motion equation X=0.5 AT 2 , in which X represents the distance traveled by a body under a constant acceleration A after a given time interval T has elapsed from launch time (at T=0 sec). Then, after substituting the elapsed flight time T e  for T, the vertical altitude (distance) ALT 1  for X and the instantaneous acceleration A e  for A into the above standard rectilinear motion equation and solving for T e  finally gives equation C7, namely: T e ={square root}{square root over (()}ALT 1 /0.5A e .  
         [0285]     The reason why T cc  was selected for plotting rather than T e  is because T cc  gives a more representative and accurate cubic TDMM craft flight time as a function of vertical altitude (distance) from earth than T e  does. First, let&#39;s look at how the equation for T e  was obtained and how it is used in PRFMEVL to develop the equation for T cc , and then compare their flight time results. Starting with equation C5, notice that the cubic craft motive force F cc =(F e +ResF+F m ) directly depends for its value on the combined, variable effects (see  FIGS. 42 and 46 ) of both the earth&#39;s negative force of gravity F e (see equation C3) and the moon&#39;s positive force of gravity F m (see equation C4) on its constant resultant centrifugal force ResF (see Table 2)—thereby causing the cubic craft motive force F cc  to also vary as a function of vertical altitude (distance) from earth launch time. This variable F cc  is next used in equation C6 to obtain the cubic craft&#39;s instantaneous acceleration A e , thereby causing A e  to also vary—which contradicts the proposition that acceleration A in the standard rectilinear motion equation is supposed to be constant. Finally, this variable acceleration A e  is then used in equation C7 to obtain T e , which represents the instantaneous elapsed time from earth launch time (at T e =0 sec) to any given vertical altitude (distance) from earth. But, since T e &#39;s value depends on the variable (non-constant) acceleration A e , it does create a little problem when plotted as a function of vertical altitude (distance) from earth—because the calculated elapsed time T e  can end up being a little smaller than the average flight time T cc  at a longer distance from earth (where the variable instantaneous acceleration A e  is greater) and be a little larger at a shorter distance from earth, where A e  is smaller (which is an impossibility). Thus, in order to avoid this little problem associated with T e , a more representative and more accurate flight time equation was developed for use in the plots of  FIGS. 44 and 48 , namely: the cubic craft average flight time T cc (see equation C11).  
         [0286]     As indicated in equation C11, this second cubic TDMM craft average flight time from earth, T cc , represents the cumulative addition of all the average flight times, T av , that are separately calculated, at the start of each new PRFMEVL iteration, in each successively incremented range interval Rinc (see Table 2)—which, as shown in the T av  equation C10, depend on the two variable A cc (see equation C9) and V e (see equation C8) for their values in each successive range increment Rinc.  
         [0287]     The T av  equation is derived from the second equation of motion V=V 0 +AT, in which V 0  is the initial velocity of a body at an earlier time (such as at the beginning of each incremented range interval Rinc), V is its velocity at a later time (such as at the end of each incremented range interval Rinc) and A is its average acceleration in each successive range Rinc. Then, after substituting the instantaneous velocities V e0  and V e  for V 0  and V, the average cubic craft acceleration A cc (see equation A9) for A and T av  for T in the above second equation of motion gives equation T av =((V e −V e0 )5280)/A cc (in which, because both V e  and V e0  are in miles/sec and A cc  is in ft/sec 2 , 5280 ft/sec was added to the equation to obtain T av  in secs). This T av  equation can then be used to get the average flight time T av  value required by the cubic TDMM craft to go through each successive range interval Rinc. Thus, by cumulatively adding each successive T av  value to the previously-obtained average cubic craft flight time equation T cc =(T cc +T av ) as a function of vertical altitude (distance) from earth (see the cubic craft T cc  plots of  FIGS. 44 and 48 ), gives a T cc  value representing a more accurate cubic craft average flight time from earth than does the elapsed time T e (see equation C7)—which, as explained earlier, depends for its value on the calculated instantaneous, variable acceleration A e (see equation C6) as a function of altitude (distance) from earth launch time (at T e =0 sec). For example, to show the above-mentioned small difference between the elapsed flight time T e  and the more accurate and representative cubic craft average flight time T cc  required to go from earth to the moon, the following T e  values were calculated for both the 230,000 mile and 225,000 mile “far-earth” distances from earth—and then compared with the T cc  values at those same distances on the 50 rad/sec plot of  FIG. 48 .  
         [0288]     To begin with, using the F cc  value of 1,094.0 lbs at 230,000 miles (from the 50 rad/sec plot of  FIG. 46 ) and the 600-lb cubic craft&#39;s mass, M cc =18.6486 slugs (from Table 2) in equation C6, gives an instantaneous acceleration A e  of 58.7 ft/sec 2  which, when used in equation C7, gives a T e  value of 6,432.5 seconds to go to the 230,000 mile distance from earth to the moon, versus an average flight time T cc  value of 6,840.9 seconds (see the 50 rad/sec plot of  FIG. 48 ) to go 230,000 miles from earth to the moon—which represents a small flight time difference of 408.4 seconds (6.81 minutes) between the two T e  and T cc  times. Finally, as shown in  FIG. 48 , the T cc  of 6,840.9 seconds fits better on the 50 rad/sec plot than would the T e  of 6,432.5 seconds (which would instead cause the 50 rad/sec plot to dip between the 250,000-to-230,000 distance from earth—indicating a shorter T e  elapsed flight time from earth to go to 230,000 miles than it would to go to 225,000 miles).  
         [0289]     Furthermore, because the cubic craft&#39;s acceleration A cc  is shown to be fairly constant in the 10,000-to-225,000 miles of the “far-earth” middle range distance from earth (see  FIG. 45 ), then A e  should also be about equal to A cc  in that same middle range—which also mean that, as shown in  FIG. 46 , because both the moon&#39;s force of gravity F m  and the earth&#39;s force of gravity F e  on the cubic craft are practically non-existent in that same “far-earth” middle range from earth, then both the constant cubic TDMM craft&#39;s acceleration A cc  and motive force F cc  can be used to determine the average flight time T cc  required to go anywhere into deep space—such as to the planet Mars. For example, from the 50 rad/sec plots of  FIG. 45  and  46 , the cubic TDMM craft&#39;s constant average acceleration A cc  of 53.4 ft/sec 2  and constant motive force F cc  of 994.3 ft/sec 2 (found at the half-way “far-earth” distance between the earth and the moon) can be used to calculate the cubic craft&#39;s flight times T cc  required for a one-way trip to the planet Mars, and safely land there on its surface (as is later done and shown in ¶ 0214).  
         [0290]      FIG. 41  presents five acceleration plots as functions of “near-earth” vertical altitude up to 250 miles in the direction of the moon. The first three plots represent the cubic TDMM craft&#39;s average accelerations A cc , which were obtained with equation C9 for each of the three indicated 50, 75 and 100 rad/sec plots. The other two plots represent the moon&#39;s positive acceleration of gravity g m (see equation C2) and that of the earth&#39;s negative acceleration of gravity g e (see equation C1) on the cubic craft—the combined effects of which are included in the above three cubic craft A cc  plots as functions of “near-earth” vertical altitude. For example, with the successive uses of equations C1 through C9, an A cc  value of 21.34 ft/sec 2  is shown on the 50 rad/sec plot at a “near-earth” vertical altitude of 10 miles.  
         [0291]     The three cubic TDMM craft A cc  plots of  FIG. 41  show two different stages of acceleration versus “near earth” vertical altitude. In the first stage, all three 50, 75 and 100 rad/sec plots show rapid acceleration increases between 0 and 10 miles from earth, at which point they level off and enter the second stage, in which they show gradual acceleration increases all the way up to 250 miles. The reason for these initial rapid A cc  increases in the first acceleration stage is because, just before the start of the cubic craft&#39;s vertical ascent, the Machine part of the TDMM was being operated in the “neutral position” (with an A cc  of 0 ft/sec 2 ), during which it was just resting on the earth&#39;s surface, held down by the earth&#39;s negative force of gravity. Then, immediately after the Machine&#39;s maximum “active position” (see  FIGS. 12, 13  and  14 ) was activated, the three cubic craft accelerations suddenly kicked in (see the 50, 75 and 100 rad/sec plots) and quickly overcame the initial effects of the negative earth&#39;s gravity (see the g e  plot) on the cubic craft, thus causing the three A cc  plots to show rapid increases in the 0-to-10 mile “near-earth” vertical altitude range, at which point they level off, after having achieved their respective constant A cc  accelerations (obtained with the sequential uses of equation C5 through C9). In the second acceleration stage, the three A cc  plots only show gradual increases the rest of the way up to 250 miles, where they respectively end up with A cc  values of 28.16, 94.82 and 188.22 ft/sec 2  on their indicated angular velocity plots.  
         [0292]      FIG. 42  presents five force plots as functions of “near-earth” vertical altitude up to 250 miles in the direction of the moon. The first three plots represent the cubic TDMM craft&#39;s motive force F cc , which were obtained with equation C5 for each indicated 50, 75 and 100 rad/sec plots. The other two plots respectively represent the moon&#39;s positive force of gravity F m  (see equation C4) and that of the earth&#39;s negative force of gravity F e (see equation C3)—the combined effects of which are included in the three F cc  plots as functions of “near-earth” vertical altitude. For example,  FIG. 42  shows a cubic TDMM craft motive force F cc  of 398.0 lbs on the 50 rad/sec plot at a “near-earth” vertical altitude of 10 miles from earth.  
         [0293]     The three F cc  plots were all obtained by first using equation C3 and C4 to calculate the F g  and F m  values as functions of altitude which, along with the appropriate constant ResF values from Table 2(see ¶ 0149), were then used in equation C5. Just like in the three A cc  plots of  FIG. 41 , the three F cc  plots show two different stages of motive force versus “near earth” vertical altitude. In the first stage, rapid motive force increases are shown between the 0 mile and the 10 mile from earth, at which point they level off and only show gradual increases as functions of vertical altitude the rest of the way up to 250 miles from earth, where they respectively end up with F cc  values of 464.3, 1,707.4 and 3,449.1 lbs on their indicated angular velocity plots. The three motive force F cc  calculations were obtained for a small-scale 600-lb cubic TDMM craft. As in  FIG. 41 , the reason for the three rapid F cc  increases in the first stage is because the cubic TDMM craft was initially in the “neutral position” (with an F cc  of 0 lb) and, when the Machine&#39;s maximum “active position” (see  FIGS. 12, 13  and  14 ) was activated, the three cubic crafts&#39; motive forces suddenly kicked in (see the 50, 75 and 100 rad/sec plots) and quickly overcame the initial effects of the earth&#39;s negative force of gravity (see the F e  plot) on the cubic craft, thus causing the three F cc  plots to show rapid increases in the 0-to-10 vertical altitude range, at which point they level off—after having achieved their respective constant F cc  motive forces (obtained with equation C4).  
         [0294]      FIG. 43  presents three plots of the cubic TDMM craft velocity V e  as functions of “near-earth” vertical altitude from the earth, up to 250 miles in the direction of the moon. They represent the cubic craft&#39;s instantaneous velocities that were obtained with equation C8 for each of the three 50, 75 and 100 rad/sec plots indicated. They respectively show velocities of 1.54 miles/sec (5,544 miles/hr), 2.94 miles/sec (10,584.0 miles/hr) and 4.19 miles/sec (15,084.0 miles/hr) at the 250 mile vertical altitude from earth.  
         [0295]      FIG. 44  presents three plots of the cubic TDMM craft average flight time T cc  as functions of “near-earth” vertical altitude from the earth, up to 250 miles in the direction of the moon. They represent the cubic craft&#39;s T cc  average flight times that were obtained with equation C11 for each of the three 50, 75 and 100 rad/sec plots indicated. Each T cc  value on the three plots represents the sum of all the flight time T av  values (see equation C10) obtained at each successive range increment Rinc as a function of vertical altitude. The 50, 75 and 100 rad/sec respectively show that it took the cubic craft 342.9 sec (5.72 min), 172.1 sec (2.88 min) and 120.3 sec (2.01 min) to get to the 250 mile altitude from earth.  
         [0296]      FIG. 45  presents five acceleration plots as functions of “far-earth” distance from the earth to the moon&#39;s surface, 230,000 miles away. The first three plots represent the cubic TDMM craft&#39;s average acceleration A cc , which were obtained with equation C9 for each of the three indicated 50, 75 and 100 rad/sec plots. The other two plots represent the moon&#39;s positive acceleration of gravity g m (see equation C2) and that of the earth&#39;s negative acceleration of gravity g e (see equation C1) on the cubic craft—the combined effects of which are included in the above three A cc  plots as functions of “far-earth” distance from earth. For example, an A cc  of 54.5 ft/sec 2 , which was obtained with the successive uses of equations C1 through C9, is shown on the 50 rad/sec plot at the 220,000 mile distance from earth (or 10,000 miles from the moon).  
         [0297]     The three TDMM cubic craft A cc  plots in  FIG. 45  show three different stages of acceleration versus “far-earth” distance from earth. In the first stage, rapid acceleration increases are shown between 0 and 5,000 miles from earth, at which point they begin to slow down and level off at about 10,000 miles from earth, with A cc  values of 54.5, 121.1 and 214.5 ft/sec 2  on their indicated 50, 75 and 100 rad/sec plots. In the second stage, between about 10,000 miles and about 220,000 miles from earth, the three 50, 75 and 100 rad/sec A cc  plots respectively appear to remain fairly constant at around 53.4, 120.1 and 213.4 ft/sec 2  until, at about 220,000 miles from earth, when the moon&#39;s gravity begins to act on the cubic craft, they begin to show gradual increases between 220,000 and 225,000 miles. Finally, in the third stage, the three A cc  plots again show rapid increases between 225,000 and 230,000 miles from earth (or during the last 5,000 miles to the moon&#39;s surface), where they respectively show final A cc  values of 290.6, 375.3 and 450.7 ft/sec 2  at the 50, 75 and 100 rad/sec plots.  
         [0298]     These three distinct and different acceleration stages in the three A cc  plots of  FIG. 45  are the results of the combined effects of: 
    1) the earth&#39;s negative gravity which, as indicated by the g e  plot, rapidly decreases from −32.174 ft/sec 2  at 0 miles (the earth&#39;s surface) to about 0 ft/sec 2  at about 20,000 miles from earth and remains practically non-existent the rest of the way to the moon, and     2) the moon&#39;s gravity which, as indicated by the g m  plot, is almost non-existent until about 225,000 miles from earth (or 5,000 miles from the moon), at which point it begins to rapidly increase until it reaches 5.32 ft/sec 2  at the moon&#39;s surface (which is about 6 times less than the force of gravity g e  at the earth&#39;s surface).    
 
         [0301]      FIG. 46  presents five force plots as functions of “far-earth” distance from the earth&#39;s surface to the moon&#39;s surface, 230,000 miles away. The first three plots represent the cubic TDMM craft&#39;s motive force F cc  which were obtained with equation C5 for each indicated 50, 75 and 100 rad/sec plot. The other two plots respectively represent the moon&#39;s positive force of gravity F m (see equation C4) and that of the earth&#39;s negative force of gravity F e (see equation C3), the combined effects of which are included in the three 50, 75 and 100 rad/sec F cc  plots as functions of “far-earth” distance from earth. For example,  FIG. 46  shows a cubic craft F cc  of 878.1 lbs on the 50 rad/sec plot at the 5,000 mile “far-earth” distance from earth. The three F cc  plots were obtained by first using equations C3 and C4 to calculate the F e  and F m  as functions of distance from earth which, along with the appropriate ResF values from Table 2, were used in equation C5.  
         [0302]     The three cubic craft motive force F cc  plots in  FIG. 46  also show three different stages of motive force versus “far-earth” distance from earth. In the first stage, rapid force increases are shown from 0 mile to about 5,000 miles, at which point they begin to slowly decrease until about 20,000 miles from earth, where they level off. In the second stage, between about 20,000 and 225,000 miles from earth, they appear to remain fairly constant at around 994.3, 2237.4 and 3979.1 lbs on their respective 50, 75 and 100 rad/sec plots (which are all very close to the three constant ResF values of 995.0, 2,238.1 and 3,079.8 lbs presented in Table 2—indicating that the gravitational forces of both the earth and the moon are practically non-existent in that “far-earth” middle range). Finally, in the third stage, the three F cc  plots again show small increases from 225,000 to 230,000 miles (or from 5,000 miles from the moon&#39;s surface), which are due to the moon&#39;s force of gravity F m  on the 600-lb cubic craft, which increases from about 0.0084 lbs at 225,000 miles from earth to 99.21 lbs at the moon&#39;s surface. For example, the 50 rad/sec F cc  plot increases from 997.9 lbs at 225,000 miles from earth to 1,094.0 lbs at the moon&#39;s surface.  
         [0303]      FIG. 47  presents three cubic TDMM craft velocity V e  plots as functions of “far-earth” distance from the earth&#39;s surface all the way to the moon, 230,000 miles away. They represent the cubic craft&#39;s instantaneous velocities that were obtained for the three indicated 50, 75 and 100 rad/sec plots, using equation C8. The three 50, 75 and 100 rad/sec plots also indicate that the cubic craft achieved instantaneous velocities V e  of 71.49, 104.49 and 138.0 miles/sec respectively at the moon&#39;s surface.  
         [0304]      FIG. 48  presents three cubic TDMM craft average flight time T cc  plots as functions of “far-earth” distance from the earth&#39;s surface all the way to the moon, 230,000 miles away. The T cc  plots were obtained with equation C11, in which the average flight times T av  values (see equation C10), which were separately obtained in each successive range increment Rinc, were cumulatively-added to the T cc  value as a function of “far earth” distance from earth. The 50, 75 and 100 rad/sec plots respectively show that it took the cubic craft 6,840.9 sec (1.9 hrs), 4,525.2 sec (1.26 hrs) and 3,384.6 sec (0.94 hr) of average flight times T cc  to get to the moon from earth.  
         [0305]     The spectacular performance of the small-scale, wingless and tailless 600-lb cubic TDMM craft is most graphically illustrated in both the “near-earth” and “far-earth” velocity and flight time plots. For example, the three 50, 75 and 100 rad/sec plots of  FIG. 44  respectively show that it takes the cubic craft 342.9 seconds (5.72 minutes), 172.1 seconds (2.87 minutes) and 120.3 seconds (2.01 minute) of average flight time (T cc ) to reach a vertical altitude of 250 miles where, according to the three 50, 75 and 100 rad/sec plots of  FIG. 43 , the cubic craft achieves final instantaneous velocities V e  of 1.54 miles/sec (5,544 miles/hr), 2.94 miles/sec (10,584 miles/hr) and 4.19 miles/sec (15,084.0 miles/hr). Similarly, the three 50, 75 and 100 rad/sec plots of  FIG. 48  respectively show that it takes the said cubic craft 6,840.9 seconds (1.9 hrs), 4,525.2 seconds (1.257 hrs) and 3,384.6 seconds (0.94 hrs) of average flight time (T cc ) to reach the moon, 230,000 miles away where, according to the three 50, 75 and 100 rad/sec plots of  FIG. 47 , the cubic craft achieves final instantaneous velocities (V e ) of 71.49 miles/sec (257,364.0 miles/hr), 104.49 miles/sec (376,164.0 miles/hr) and 138.0 miles/sec (496,800.0 miles/hr).  
         [0306]     However, rather than “crash” the cubic TDMM craft on the moon&#39;s surface, a more realistic and practical approach would be, as indicated by the 50 rad/sec plot in both  FIGS. 48 and 47 , to go to the half-way 115,000-mile-distance between the earth and the moon in 4,866.3 seconds (1.35 hours), where it would have an instantaneous velocity of 48.19 miles/sec (137,484.0 miles/hour), and then reverse the cubic craft&#39;s constant acceleration of about 53.4 ft/sec 2 (see  FIG. 45 ), in order to cause the cubic craft to decelerate the rest of the way to the moon and safely land on its surface in less than 3.0 hours of total flight time from earth.  
         [0307]     Furthermore, using only the slower angular velocity of 50 rad/sec, both  FIGS. 44 and 43  respectively indicate that the cubic craft would reach the “near-earth” vertical altitude of 250 miles in 342.9 seconds (5.72 minutes) and have a velocity of 1.54 miles/sec (5,544.0 miles/hour)—at which point the cubic craft&#39;s direction would be changed to put it in an earth orbit, in which it would continue to accelerate until the proper orbital velocity has been achieved.  
         [0308]     Finally, the ultimate space travel challenge for the cubic TDMM craft would be to go the planet Mars, when it is closest to earth (at a distance of about 35 million miles away—where the gravitational forces from both the earth and the moon are non-existent). For example, just to get an idea of how long it would take for the said cubic craft to go to Mars, let&#39;s first go to Table 2, in which the cubic craft&#39;s Machine-generated ResF of 995 lbs at 50 rad/sec and its mass M cc  of 18.65 slugs are listed and use them in equation C6, to obtain a deep space acceleration A e  of 53.36 ft/sec 2 (which is about equal to the cubic craft constant acceleration A cc  of 53.4 ft/sec 2  at the “far-earth” middle range distance on the 50 rad/sec plot of  FIG. 45 ). This A e  value can now be used in equation C7, along with an ALT 1  value of 9.2410 ft (which is the half-way above-mentioned distance of about 17.5 million miles between the earth and Mars) to obtain a cubic craft elapsed flight time T e  of about 58,850 seconds (or 16.35 hours) needed to get half-way to Mars. Next, using both the above A e  and T e  values in equation C8, yields a spectacular cubic craft&#39;s velocity V e  of about 595 miles/sec (or 2,141,070.0 miles/hour) at that half-way distance to Mars. Then, at the half-way distance to Mars, the deep space, constant acceleration A e  is reversed, to act in the opposite-direction, thereby causing the cubic craft to gradually decelerate at the same A e  of 53.36 ft/sec 2  during the remaining 17.5 million miles to Mars and safely land on it after about 33.0 hours of flight time from earth.  
         [0309]     The above cubic TDMM craft spectacular “far-earth” average flight times of 3.0 hrs to go to the moon and 33 hrs to go to Mars assume the availability of a constant source of electrical power (obtainable from a combination of batteries and solar cells and/or from other sources, including nuclear), in order for the TDMM&#39;s Machine to continuously be able to propel the 600-lb small-scale cubic craft with the same constant motive force of about 995 lbs at 50 rad/sec (see  FIG. 44  and Table 2) during both “far-earth” and deep space flight durations.  
         [0310]     However, the primary purpose of the “near-earth” and “far-earth” performance plots presented in  FIGS. 41 through 48  is to illustrate the spectacular and unmatched capability of the cubic TDMM craft invention—which is only made possible by the combined, innovative use of three simple, basic component parts, working together as one unit in each cubic TDMM craft&#39;s Machine mirror-image half, namely: 
    1) a fixed, 96-inch-diameter circular outer rim (see  FIG. 10 ),     2) a movable circular 72-inch-diameter inner rim (see  FIG. 8 ) and     3) a commercially-available telescoping full extension slide  46  (see  FIGS. 3, 4  and  5 ). 
 
 As previously mentioned, the outer rim in (1) above acts as a fixed circular boundary for the movable inner rim in (2) above, which in turn, acts as a circular track for the 2-wheel device  47 , which is mounted at the telescoping end of slide  46  in (3) above, which both make up one variable-length subassembly  40  (see  FIG. 9 ). 
   
 
         [0314]     As a result of the combined use of the different functions of the above-mentioned three parts working together as one unit, when the inner rim in each Machine mirror-image half is moved from its “neutral position” (in which the lengths of all the 8 subassemblies  40  are all equal to the inner rim&#39;s radius—see  FIG. 11 ) to its maximum “active position” (in which the 8 variable-length subassemblies  40  now all have different lengths—see  FIG. 12 ) to make contact with the inside surface of the outer rim, it then causes these 8 subassemblies  40  to generate 8 different centrifugal forces F c  as functions of their angle of rotation theta0(see  FIG. 31 ). Then, as they rotate about the fixed, off-center point  0  (see  FIG. 32 ), these 8 different F c  forces automatically vectorially combine into one single, outwardly-directed resultant centrifugal force ResF—always pointing in the selected direction in which the inner rim is making contact with the outer rim. For example, as shown in the polygon of  FIG. 33 , the 8 different F c  forces shown in  FIG. 32  vectorially combine into one single, resultant centrifugal force ResF of 1,989.4 lbs (shown as a heavy black arrow pointing from the tail of the first triangle&#39;s F a  force to the head of the seventh triangle&#39;s F b  force) in the 180-degree direction. Furthermore, since there are two such identical Machine mirror-image halves (separated by the central plate  15  inside the parallelepiped internal housing frame  13 —see  FIGS. 2 and 51 ), each with a set of 8 rotating subassemblies  40 , then the entire Machine therefore generates a total maximum ResF of 3,978.8 lbs (in that same 180-degree direction).  
         [0315]     As shown in  FIGS. 1, 2 ,  51  and  53 , the internal housing frame  13  (in which the Machine is enclosed) is freely horizontally rotatable about the vertical central axis  14  towards any selected direction (azimuth) inside the larger outer cubic frame  10 . Finally, when the selected direction of the above-mentioned, Machine-generated total maximum ResF of 3,978.8 lbs is combined with the chosen direction (azimuth) of the rotatable internal housing frame  13 , a single, steerable and powerful motive force is then made available for propelling the 600-lb cubic TDMM craft model of the invention with spectacular unparalleled performance and maneuverability in three dimensions, anywhere on earth and in outer space.  
         [0316]     As noticeable, the above-mentioned steerable, total motive force of 3,978.8 lbs (generated at 100 rad/sec in the Machine) is considerably more than is required to propel the 600-lb cubic TDMM craft in three dimensions, and is also considerably more than is available from the three most-closely related inventions (presented in the “Discussion Of The Related Arts” section) which, as far as I can understand, are at best really limited to two dimensions—even though their inventors suggest the possibility of being able to develop a single resultant force along any selected directions in three dimensions by simply doing, or adding, one thing or another, to their inventions (without showing and/or explaining how to do it), which they leave to others to figure out, as is the case in the following three most-closely-related patents: 
    1) U.S. Pat. No. 5,488,877—in which Richard L. Lieurance claims that, when using four cells in his “centrifugal inertia drive” it can generate a unidirectional force of 120.0 lbs at 600 rpm,     2) U.S. Pat. No. 5,782,134—in which James D. Booden claims that his “electromagnetically actuated thrust generator” is capable of generating a net thrust of 82.43 lbs of force at 1200 rpm, and     3) U.S. Pat. No. 5,860,317—in which Eric Laithwaite et al do not provide any gyroscopically-generated propulsion force results. 
 
 Description of the Cubic TDMM Craft and its Operation 
   
 
         [0320]     The above-mentioned cubic TDMM craft of the invention basically consists of an external cubic framework  10 , a parallelepiped internal housing frame  13  (see  FIGS. 1, 2 ,  51  and  52 ) and a variable, steerable centrifugal force generating Machine (which, as shown in  FIGS. 51 and 52 , is enclosed in the internal housing frame  13 ). The Machine&#39;s two sets of 8 variable-length subassemblies  40 , counter-rotating at 100 rad/sec, can generate a combined, outwardly-directed, maximum resultant centrifugal force (ResF) of 3,978.8 lbs in any one of the 360-degree directions inside the vertical planes of their respective circular inner rims  33  and  35  (which depends on the selected direction in which the inner rims make contact with the inside surfaces of their respective outer rims—see  FIGS. 12, 13  and  14 ).  
         [0321]      FIG. 1  presents a simplified three-dimensional view of the cubic TDMM craft model, showing the relationship between the external cubic frame  10  and the internal housing frame  13  (shown as a dashed parallelepiped enclosed inside the external cubic frame  10 ). The internal housing frame  13  is horizontally rotatable in either direction about a vertical central axis  14  (shown as a vertical dashed line, running between the centers of both the top and the bottom heavy-duty swivel assemblies  11  and  12 ) towards any selected direction (azimuth} inside the larger external cubic frame  10  (see  FIGS. 1, 2 ,  51  and  53 )—thereby causing the enclosed Machine to rotate with it. Also notice that, in this diagram, the external cubic frame  10  is wingless and tailless, which means that the cubic TDMM craft can propel itself in any desired direction in three dimensions (in any atmospheric environment and in the void of outer space) by simply using its internally-built variable, steerable motive force TDMM mechanism.  
         [0322]      FIG. 2  presents another simplified, top-view cutaway diagram of the cubic TDMM craft, showing the relationship between the external 100-inch cubic frame  10 , the 96×24-inch rectangular top-end of the parallelepiped internal housing frame  13  and the top swivel assembly  12  (which, as shown in  FIGS. 51 and 52 , is sandwiched between the top centers of both the external cubic frame  10  and of the internal housing frame  13 ). A top-view of the 100-inch-diameter alternate external cylindrical frame  60  is also shown in this diagram as a dashed circle inscribed inside the external cubic frame  10  (inside of which the internal housing frame  13  is also freely rotatable about the central axis  14  in either direction without any interference). The external cylindrical frame  60  is intended for use as a replacement for the external 100-inch cubic frame  10  in a future application of the basic invention presented in  FIG. 54 .  
         [0323]      FIG. 2  also shows that the parallelepiped internal housing frame  13  is divided into two equal halves (numbered  16 A on the left and  16 B on the right), separated by the central square plate  15 . The Machine (which is enclosed inside the internal housing frame  13 ) is also divided into two identical, mirror-image halves (with one half in each internal housing frame&#39;s half side).  
         [0324]     Each Machine mirror-image half consists of two separate and different major functional parts, namely: 1) a two-dimension, all-way movable mechanism  49  mirror-image half (comprised of parts shown in  FIGS. 6, 7  and  8 ) and  2 ) a set of 8 variable-length subassemblies  40  (see  FIGS. 9, 11  and  12 ), rotating about the fixed point  0 . These two major Machine parts are designed to work together as one integrated unit to generate a single, outwardly-directed, variable resultant centrifugal force (ResF) in any desired direction inside the vertical, two-dimensional plane of each movable, circular inner rim in each Machine mirror-image half.  
         [0325]     For simplification of the exemplary embodiment, most of the following figures and accompanying write-ups are about the left side A of the Machine&#39;s mirror-image half only (see  FIGS. 13, 50  and  51 ), because the other right side B half is an identical mirror-image half.  
         [0326]     As previously described with the aid of  FIGS. 1 through 15 , the Machine&#39;s left side A half basically consists of three parts, working together as one unit, namely: 
    1) a set of 8 identical, evenly-spaced, variable-length (telescoping) subassemblies  40  (each with a 2-wheel device  47  mounted at its moving end and with its other fixed end securely mounted onto a 16-inch-radius disk  31 —see  FIG. 9 ), in which the 8 subassemblies continually vary their lengths (from a fully closed 24 inches to a fully opened 48 inches—see  FIGS. 3, 4  and  23 ) as they rotate in the “active position” about the fixed, off-center axis at point  0  (see  FIG. 12 ),     2) a movable 72-inch-diameter circular inner rim  33  (see  FIG. 8 ), which acts as a movable, circular track for the 2-wheels  47  mentioned in (1) above (and which is also an integral part of the mirror-image half of the two-dimension movable mechanism  49 ), and     3) a 96-inch-diameter, fixed circular outer rim  34  (see  FIG. 10 ), which acts as a fixed circular boundary for (2) above, and which is vertically-mounted on the inside surface of the internal housing frame&#39;s left side  16 A half (see  FIG. 2 ).    
 
         [0330]     The two-dimension, all-way movable mechanism in (2) above basically consists of one vertically-moving square plate  25  (see  FIG. 7 ) and of one horizontally-moving square plate  29 , on which, as shown in  FIG. 8 , circular inner rim  33  is mounted inscribed on its opposite side (away from the central square plate  15 ). The purpose of the all-way movable mechanism  49  is to variably move plate  25  vertically and plate  29  horizontally (together or independently), in order to position inner rim  33  (see  FIG. 8 ) anywhere inside the vertical plane of the fixed, circular outer rim  34  (namely, to position it at any distance and direction from its “neutral position”, at the center of the vertical plane of outer rim  34 , up to its maximum “active position”, in which, as shown in  FIG. 12 , it is making contact with the inside surface of outer rim  34  at 180 degrees). When the inner rim is in its “active position”, the 8 evenly-spaced subassemblies  40  mentioned in (1) above continually vary their lengths as functions of their angle of rotation theta0(see  FIG. 23 ) which, in turn, causes them to simultaneously generate 8 different resultant centrifugal forces F c , also as functions of their angle of rotation theta0(see  FIGS. 31 and 32 ). Then, as shown in the polygon example of  FIG. 33 , the 8 different F c  forces shown in  FIG. 32  automatically combine into one single, outwardly-directed, variable and smooth resultant centrifugal force (ResF), which is always pointing in the same selected direction in which inner rim  33  is closest to, or is making contact with, the inside surface of outer rim  34 . The direction of the vectorially combined ResF shown in  FIG. 33  was arbitrarily selected to be at 180 degrees, but could also have been selected to be at 225 degrees—and still have the same ResF results. Finally, by combining the above-mentioned selected direction of the outwardly-directed, vectorially combined ResF with the chosen horizontal direction (azimuth) of the internal housing frame  13  (and its enclosed Machine), which is established by rotating the internal housing frame  13  about its vertical axis  14  (see  FIGS. 1 and 2 ), a steerable and variably powerful motive force is then available for propelling the cubic TDMM craft in any desired direction in three dimensions with unparalleled performance (see  FIGS. 41 through 48 ) and maneuverability anywhere on earth and in outer space.  
         [0331]     Due to the 24-inch difference between the 72-inch-diameter of inner rim  33  and the larger 96-inch-diameter of outer rim  34  (see  FIGS. 8 and 10 ), inner rim  33  can only be moved a maximum distance of up to 12 inches in any direction from its “neutral position”. In other words, as shown in  FIG. 8 , the center of inner rim  33  (point P) can only be moved up to a maximum distance of 12 inches from the fixed center point  0  of outer rim  34  in any chosen direction within the small 12-inch-radius dashed circle  32 . For example,  FIG. 12  shows that when point P is vertically moved the entire 12 inches up from the fixed point  0  to the horizontal “+ 0 ” dashed line, the upper inner rim&#39;s outside surface is now making contact with the outer rim&#39;s inside surface at 180 degrees, where it is stopped, 48 inches up from the fixed point  0 . However, if the inner rim&#39;s point P is moved 12 inches away from the fixed point  0  in any other direction, such as 225 degrees, then the inner rim&#39;s outside surface will make contact with the outer rim&#39;s inside surface at 225 degrees and also be stopped there, at a point also 48 inches from the fixed point  0 .  
         [0332]     Therefore, the movable inner rim  33 , which is shown in  FIG. 11  in the “neutral position” and in  FIG. 12  in the “active position”, performs two very important functions, namely: 
    1) it acts as a movable circular track for the 2-wheel devices  47  (at the telescoping end of the 8 subassemblies  40 ), which are forced to make contact with the inner rim&#39;s inside surface by the outwardly-directed centrifugal forces generated by the 8 subassemblies  40 , as they rotate about the fixed off-center point  0  (see  FIGS. 9, 11  and  12 ), and     2) when it is moved in any direction inside the vertical plane of the circular outer rim  34  (see  FIG. 12 , for example), it then causes the 8 variable-length subassemblies  40  in (1) above to continually vary their lengths (R 3   W ) as they rotate about the fixed, off-center point  0  (see  FIGS. 12, 23  and  32 ) and to simultaneously generate 8 different centrifugal forces F c —which then automatically vectorially combine to create a single, outwardly-directed resultant centrifugal force ResF (which, as shown in the polygon of  FIG. 33 , always points in the same selected direction in which inner rim  33  is making contact with outer rim  34 ).    
 
         [0335]     Furthermore, and most importantly, if inner rim  33  is moved only part of the distance away from its “neutral position” in any direction, without making contact with the inside surface of outer rim  34 , such that its center point P is less than 12 inches away from the fixed point  0  anywhere inside the 12-inch-radius dashed circle (see  FIG. 8 ), then the single ResF in (2) above will be smaller in that direction than the maximum ResF of 1,989.4 lbs shown in  FIG. 33 . Finally, since there are two such Machine mirror-image halves in the internal housing frame, the maximum variable ResF generated by the entire Machine automatically doubles to 3,978.4 lbs.  
         [0336]     The above-mentioned variable ResF capability of the Machine is very important to the operation of the cubic TDMM craft, because it allows its built-in mechanism to develop just enough outwardly-directed ResF in any selected direction (inside the vertical planes of the two circular inner rims) which, when combined with the chosen horizontal direction (azimuth) of the internal housing frame  13  (and its enclosed Machine), makes it possible for the wingless and tailless cubic craft to be propelled with any desired amount of variable motive force in three dimensions anywhere on earth and in outer space.  
         [0337]     For example, the cubic TDMM craft&#39;s variable motive force capability would enable it: 
    1) to accelerate or decelerate at any desired rate in any direction in three dimensions anywhere on earth and in outer space for as long as needed,     2) to coast at any velocity in any selected flight path,     3) to make any angle turn (including a 180-degree turn) while in flight, without having to make a long arced turn (like all air/space crafts, missiles and rockets presently must do),     4) to remain motionless, either up-side down or down-side up (or in any other position), anywhere on earth and in outer space (a desirable and very useful capability when getting near any outer space bodies),     5) to take off and land at any flight angle and velocity on earth, or on any other space body (such as a space station, planet, moon, comet, asteroid, . . . etc . . . ), and, most importantly,     6) to control the cubic TDMM craft&#39;s velocity when entering any atmospheric environment on earth or any other planets, to prevent it from burning up (thereby rendering the present use of thermal tiles unnecessary and obsolete) and make a safe landing.    
 
         [0344]     To briefly summarize, all the above-mentioned performance and maneuvering capabilities can be quickly and simply accomplished in the cubic TDMM craft: 
    1) by moving both inner rims any given distance (between their “neutral position” and their maximum “active position”) in any selected direction inside the vertical planes of their respective circular outer rims (in order to get the desired outwardly-directed single ResF output in that chosen direction) and     2) by simultaneously orienting the internal housing frame  13  (and its enclosed Machine) towards any new direction (azimuth), relative to the external cubic frame  10 —the direction of which, when combined with the chosen ResF direction in (1) above, will give the cubic TDMM craft complete flight control capability in three dimensions.    
 
         [0347]      FIG. 9  illustrates how each of the 8 telescoping subassemblies  40  (see  FIGS. 11 and 12 ) has the fixed section  41  of its slide  46  (see  FIGS. 3 and 4 ) mounted directly onto a circular 16-inch-radius metal disk  31  with a pair of bolts and nuts and how a 2-wheel device  47  is secured onto the moving end of its other section  43 . The disk  31  has a 2.5-inch circular hole in its center, which allows it to slide over the right side of the 2.5-inch outside diameter of the cylindrical high-speed hub  44  (see  FIG. 50 ) all the way to its flange, onto which it is secured with four ½×⅞-inch bolts  39  in a 4-inch-diameter circle. The 2-wheel devices  47 , which consists of a set of two roller blade wheels with tapered high-speed bearings turning on axle  50 , run along the inside surface of inner rim  33  (which acts as a circular track for the two-wheel devices  47 ), driven by the variable-length subassemblies  40  as they rotate about the fixed stub axle  45  (which is mounted on the inside surface of the left half side  16 B of the internal housing frame  13 , in line with the fixed point  0  (see  FIGS. 50 and 51 ). The hub  44 , the disk  31  and the set of 8 variable-length subassemblies  40  all rotate together as one unit about the fixed stub axle  45 .  
         [0348]      FIG. 10  presents diagrams of a front and side views of the fixed 96-inch-diameter circular outer rim  34 . The front-view diagram shows how the outside surface of outer rim  34  is mounted in 8 equally-spaced places on the inside surfaces of the four 96×12-inch rectangular side-walls of the left half side  16 A of the internal housing frame  13  (see  FIG. 2 ). Four of these mounting places consist of four metal corners  17  and the other four mounting places are simply contact points  18  (which are all used for securing outer rim  34  to the center of the four 96×12-inch rectangular side-walls). The side-view diagram also shows how the 3-inch wide edge of the fixed outer rim  34  is mounted in the middle of the four 96×12-inch rectangular side-walls of the internal housing frame&#39;s left half side  16 A (about 4.5 inches away from both the internal housing frame&#39;s 96-inch square end-wall and the central square plate  15 ). The 3-inch circular edge of the fixed outer rim  34  acts as a circular boundary for the smaller movable 72-inch-diameter circular inner rim  33 , shown here in the “neutral position”. A second 96-inch-diameter outer rim  36  is also similarly mounted inside the other internal housing frame&#39;s right half side  16 B (see  FIG. 2 ).  
         [0349]      FIG. 11  shows a diagram of the movable circular inner rim  33  in the “neutral position” (in the center of outer rim  34 ), in which the lengths of the 8 equally-spaced subassemblies  40  are all exactly equal to the inner rim&#39;s constant-length radius R 1   W =3 feet—thereby causing the 8 subassemblies  40  to all generate equal, constant centrifugal forces (F c ) as they rotate about both the superimposed inner rim&#39;s center point P and the outer rim&#39;s fixed center point  0 . In this “neutral position”, the 8 equal F c  vectors do not generate any single, outwardly-directed resultant centrifugal force (ResF) in any direction—because, when vectorially combined, they do not generate any ResF at all.  FIG. 11  is a typical example of a perfectly balanced flywheel.  
         [0350]     However, as shown in  FIG. 12 , when the Machine&#39;s left mirror-image half of the 2-dimension all-way movable mechanism  49  vertically moves circular inner rim  33  up 12 inches from its “neutral position” (such that its center point P is now superimposed on point +0), it is now in its maximum “active position” (in which the outside surface of inner rim  33  is now making contact with the inside surface of outer rim  34  at 180 degrees). As a result, the same 8 identical, equally-spaced, variable-length subassemblies  40  shown in  FIG. 11  now all have different lengths R 3   W  which, as shown in  FIGS. 12 and 23 , continually vary as functions of their angle of rotation theta0, as they rotate about the fixed off-center point  0  (with respect to the inner rim&#39;s center point P). Therefore, according to equations B8a, for slide  46  (W), B8b, for the bar, and B8c for both combined into subassembly  40 , these 8 equally-spaced, variable-length subassemblies  40  now generate 8 different rotational resultant centrifugal forces ResF (see  FIG. 32 ) which, according to the basic centrifugal force equation (1) in ¶ 0113, are directly proportional to their radial lengths R 3   W (see  FIG. 12 ). These 8 different F c  vectors shown in  FIG. 32 , then instantaneously vectorially combine into a single resultant centrifugal force ResF =1,989.4 lbs in the outward 180-degree direction (as shown by the heavy black arrow in the polygon of  FIG. 33 ). As already mentioned, this 180-degree outwardly-directed single ResF is arbitrary and can be quickly changed to any other chosen direction (such as 225 degrees) by simply moving inner rim  33  to make contact with the inside surface of outer rim  34  in that other chosen direction—and still get the same single ResF result.  
         [0351]      FIG. 49  shows diagrams of an 11-inch square, all-ball-bearing, heavy-duty swivel with a 650-lb load rating and of three different sprockets  66 ,  53  and  52 , each with 60, 40 and 20 teeth respectively. A fourth, smaller sprocket  65  with 8 teeth (not shown), which is similar to sprocket  52 , is also used in the Machine with motors  64  (see  FIG. 51 ). The swivel, which consists of two independently rotatable square parts  61  and  62  (each with a ⅓-inch mounting holes  71  near its four corners), is used in the two swivel assemblies  11  and  12  with the 60-tooth sprocket  66  (which is mounted sandwiched between two circular spacers  55 , as shown in the bottom part B of  FIG. 51 ).  
         [0352]      FIG. 50  presents diagrams of the Machine&#39;s right mirror-image half mechanism, the high-speed hub  44  and the 8-inch stub axle. The Machine&#39;s mirror-image half mechanism, which consists of the right half of the two-dimension, all-way movable mechanism  49  and of a set of 8 rotatable, variable-length subassemblies  40  system, is mounted directly in the right  16 B-side of the inner housing frame  13  (see  FIG. 2 ). This figure illustrates the spatial side-view relationship between the various following parts found in: 
    A) the two-dimension, all-way movable mechanism  49 , which is made up of parts found in  FIGS. 6, 7  and  8  (which are all mounted directly onto the right  15 B-side of the fixed, 96×96-inch central square plate  15 —which, as shown in  FIG. 2 , evenly divides the inner housing frame  13  into two sides  16 A and  16 B), namely: 
        1) the vertically-moving slide assemblies  22 L and  22 R, which are mounted on the left and the right sides of the  15 B-side of the central square plate  15  (see  FIG. 6 , for example, and  FIG. 14 ),     2) the vertically-moving 72-inch square plate  26 , mounted on A(1) above (see  FIG. 7 , for example, and  FIG. 14 ),     3) the horizontally-moving slide assemblies  28 U and  28 D, which are mounted on the up and the down sides of the opposite side of A(2) above (see  FIG. 7 , for example, and  FIG. 14 ),     4) the horizontally-moving 72-inch square plate  30 , mounted directly on A(3) above (see  FIG. 8 , for example, and  FIG. 14 ),     5) the 72-inch-diameter, two-dimension movable circular inner rim  35 , mounted on the opposite side of A(4) above (see  FIG. 8 , for example, and  FIG. 14 ), and in    
        B) the set of 8 variable-length subassemblies  40  system, which is mounted on the center of the inside surface of the right  16 B-side square end-wall of the internal housing frame  13  as shown and which consists of the following parts: 
        1) the 16-inch radius metal disk  31  (see  FIG. 9 ),     2) the set of 8 identical, equally-spaced telescoping subassemblies  40 , which is mounted on B(1) above (each of which, as shown in  FIGS. 3 and 4 , extend from a closed 24 inches to a fully opened 48 inches),     3) the spacer  55  (between the set of 8 subassemblies  40  and the 40-tooth sprocket  53 ),     4) the high-speed hub  44 , onto which B(1), B(2) and B(3) above are mounted),     5) the fixed stub axle  45  (which is secured with mounting plate  56  onto the inside center of the right  16 B-side square end-wall of the internal housing frame  13 ), which is aligned with the fixed point  0  dashed line and about which B(1), B(2), B(3) and B(4) above all rotate as one unit,     6) the fixed outer rim  36  (which is similarly mounted as outer rim  34  is in  FIG. 10 ) and     7) motor  51 , which is mounted below B(5) above and provides rotation to B(1), B(2), B(3) and B(4) above via chain #  54 .    
         
         [0367]     The commercially-available high-speed hub  44  in B(4) above comes with two tapered high-speed bearings and a 3,000-lb load capacity and the stub axle  45  in B(5) above comes with a 2,000-lb load capacity. The fixed stub axle  45  serves as a fixed axis, about which B(1), B(2), B(3) and B(4) all rotate together as one unit. The movable inner rim  35  in A(5), which is mounted on the opposite side of the 72-inch square plate  30  in A(4), facing away from the 96×96-inch square plate  15 , acts as a circular track for the 2-wheel devices  47  at the telescoping ends of the 8 subassemblies  40  (see  FIG. 9 ) in B(2) above. Inner rim  35  is shown here in the maximum “active position”, making contact with the inside surface of outer rim  36  at 180 degrees, with its center point P shown superimposed on point + 0  (also see  FIGS. 12, 51  and  52 ).  
         [0368]     In the exemplary embodiment of the Machine&#39;s right  16 B-side mirror-image half mechanism shown in  FIG. 50 , the set of 8 subassemblies  40 , the 16-inch-radius disk  31 , the spacer  55  and the 40-tooth sprocket  53  are all secured together as one unit, which is mounted directly onto the high-speed hub&#39;s flange  44  with four bolts  39 , rotating about the fixed axle  45  (which is aligned with the fixed center point  0  of outer rim  36 ), driven by the reversible ½ HP, 1800 rpm variable-speed electric motor  51 . Motor  51  uses an rpm-reduction drive consisting of a 20-tooth sprocket  52  (mounted on its shaft), a 40-tooth sprocket  53  (mounted on the flange of the high-speed hub  44 ) and a #35 chain  54  (which goes around both sprockets  52  and  53 ), to provide the set of 8 subassemblies  40  with a 50% reduced rotation of 900 rpm (namely: 1800(20/40)). Motor  51  and its mounting plate  57  are secured directly onto the 96-inch quare end-wall of the internal housing frame&#39;s right  16 B-side as shown, directly below the stub axle  45 .  
         [0369]     A similar mounting arrangement of items A(1) through A(5) and B(1) through B(7) above also makes up the Machine&#39;s left mirror-image half mechanism in the  16 A-side of the internal housing frame  13 . As shown in  FIG. 51 , both the left and the right Machine mirror-image halves make up the entire Machine&#39;s centrifugal motive force machine of the cubic TDMM craft.  
         [0370]      FIG. 51  consists of two parts, A and B. The upper part A presents a cross-sectional side-view of the entire cubic TDMM craft, showing the Machine&#39;s two identical mirror-image halves, separated by the 96-inch square central plate  15  (which also divides the 96×96×24-inch parallelepiped internal housing frame  13  into two equal half sides,  16 A on the left and  16 B on the right). Part A illustrates the side-view spatial relationship between the external cubic frame  10 , the internal housing frame  13 , the lower and upper swivel assemblies  11  and  12  (shown sandwiched between the top and bottom parts of both the external cubic frame  10  and the internal housing frame  13 ), as well as the various other parts comprising the Machine&#39;s two mirror-image halves (mentioned in the  FIG. 50  write-up above).  
         [0371]     Four reversible 1800 rpm electric motors (two ½ HP motors  51  and two ¼ motors  64 ) are variably and independently used for propelling the cubic TDMM craft in any chosen direction in three dimensions. The two motors  51  (one on each side of the internal housing frame  13 ) provide the two sets of 8 variable-length subassemblies  40  in the Machine with the appropriate counter-rotations (inside the vertical planes of their respective inner rims  33  and  35 ) to balance out their equal and opposite torque reactions. The other two motors  64  (one at the upper end and the other at the lower end of the internal housing frame&#39;s right outside  16 B square end-wall) separately provide the appropriate horizontal counter-rotations to both the internal housing frame  13  and the external cubic frame  10  respectively—in order to variably balance out their equal and opposite torque reactions and obtain the desired heading (azimuth) for the internal housing frame  13  (and its enclosed Machine), inside of and relative to the external cubic frame  10 .  
         [0372]     A power-and-control unit (P/CU), which is mounted on the lower outside of the left 96-inch square  16 A-side end-wall of the internal housing frame  13 , is used for routing all the various command/control signals needed to operate and propel the cubic TDMM craft in three dimensions. Different PC/U signals are used for turning the four electric motors on and off (together or independently), for making the two-dimension, all-way movable mechanism  49  move the two inner rims to their selected positions inside the vertical planes of their outer rims (in order to obtain the needed amount of ResF in that direction) and for rotating the internal housing frame  13  (in either horizontal direction) towards a desired bearing (azimuth) inside the external cubic frame  10 —the combined directions of which causes the cubic TDMM craft to be propelled in any desired heading in three dimensions.  
         [0373]     As an example of the use of the P/CU, when the cubic TDMM craft is in a quiescent state on the earth&#39;s surface, a first set of command/control signals is first sent to turn on the two motors  51 , in order to start the two sets of 8 subassemblies  40  counter-rotating in the “neutral position” (see  FIG. 11 , for example) inside the vertical planes of their respective inner rims  33  and  35 . Then, a second set of signals from the P/CU causes the two-dimension, all-way movable mechanism  49  to move both inner rims up a given distance from their “neutral position” towards 180 degrees on their respective outer rims without making contact with them. The two inner rims  33  and  35  are now in a reduced “active position”, in which the two sets of 8 counter-rotating subassemblies  40  are generating a single, combined resultant centrifugal force (ResF) just powerful enough to make the cubic craft ascend in a controlled vertical lift.  
         [0374]     The above-mentioned cubic TDMM craft&#39;s controlled vertical lift can be achieved in either of two ways by: 
    1) counter-rotating the two sets of 8 subassemblies  40  at the same constant input angular velocity (such as, for example, at 100 rad/sec) inside their respective inner rims and moving both inner rims to a reduced “active position” (somewhere between their “neutral position” and their “maximum active position”) towards 180 degrees on their outer rims, in order to cause the TDMM&#39;s Machine to generate just enough outwardly-directed ResF for a controlled vertical lift of the 600-lb cubic craft against the local force of gravity, on earth or anywhere else, or     2) counter-rotating the two sets of 8 subassemblies  40  at a reduced angular velocity (such as 70 rad/sec for example) and moving both inner rims all the way to their maximum “active position” at 180 degrees on the inside surfaces of their respective outer rims, in order to cause the TDMM&#39;s Machine to also generate just enough outwardly-directed ResF for a controlled vertical lift of the 600-lb cubic craft against the local force of gravity, on earth or anywhere else.    
 
         [0377]     For example, using the angular velocity of 70 rad/sec given in (2) above into the ResF equation shown in  FIG. 35  gives an ResF output of 974.8 lbs—which is more than is required to lift the 600-lb cubic craft from the earth&#39;s surface. Therefore, the cubic TDMM craft can be made to ascend at any desired rate of speed (depending on both the amount of Machine-generated ResF in the cubic craft and the local force of gravity). Then, when the cubic craft is nearing the desired vertical altitude, a new set of command/control signals is sent to simultaneously move the two inner rims to a new position (inside the vertical planes of their respective circular outer rims) and to rotate the inner housing frame  13  (and its enclosed Machine) towards a given chosen horizontal direction (inside the external cubic frame  10 ), in order to place the cubic craft in the desired orbital altitude (around the earth or any other outer space bodies). Finally, when the cubic TDMM craft is in the desired orbit, then the amount of Machine-generated ResF that is now needed has to be such that its vertical component will be equal to the local force of gravity at that orbital altitude and that its horizontal component will provide the desired forward motive force to propel the cubic craft at that cruising altitude until its orbital velocity has been reached—and then, the TDMM&#39;s Machine mechanism can be returned to its “neutral position”.  
         [0378]     In addition to all the above-mentioned capabilities, the proper control signals from the P/CU can cause the cubic TDMM craft to make a 180-degree turn while in flight (without having to make a long arced turn, like all air and space crafts, missiles and rockets, must presently do), accelerate, decelerate or simply coast along, either right side up or upside down (or in any other desired position) in any direction in three dimensions—or simply remain stationary at any designated place anywhere above earth or in outer space.  
         [0379]     Part B of  FIG. 51  presents two small diagrams of the left and right side-view halves of the top and bottom swivel assemblies  12  and  11 . They respectively show how the two swivel assemblies are mounted, sandwiched between the centers of the top and bottom sides of the internal housing frame  13  and of the external cubic frame  10 . The two swivel assemblies perform two functions, namely: to vertically support the internal housing frame  13  inside the center of the external cubic frame  10  and to horizontally counter-rotate both the internal housing frame  13  and the external cubic frame  10  about a central vertical axis  14  (see  FIGS. 1 and 2 ). The left side-view half of the top swivel assembly  12  shows how its independently rotatable 11-inch square part  62  (see  FIG. 49 ) is mounted directly onto the center of the top inside surface of the external cubic frame  10 , using any acceptable fastening means (such as bolts and nuts through the mounting holes  71 ) while its other independently rotatable square part  61  is secured to a 60-tooth sprocket  66 , which is shown sandwiched between two spacers  55 . The rotatable square part  61 , the sprocket  66  and the two spacers  55  are mounted together as one unit onto the center of the top outside surface of the internal housing frame  13 —such that, when its sprocket  66  is driven by the top bi-directional electric motor  64  (see  FIG. 51 ), it causes the internal housing frame  13  (and its enclosed Machine) to also rotate horizontally in either direction, inside and relative to the external cubic frame  10 . The right side-view half of the bottom swivel assembly  11  is similarly mounted, except that its independently rotatable 11-inch square part  62  is secured directly onto the center of the bottom outside surface of the internal housing frame  13  and that its independently rotatable unit, consisting of parts  61 , sprocket  66  and spacers  55 , is mounted onto the center of the bottom inside surface of the external cubic frame  10 —such that, when its sprocket  66  is driven by the bottom bi-directional electric motor  64  (see  FIG. 51 ), it causes the external cubic frame  10  to also rotate horizontally in either direction, relative to the internal housing frame  13  (and its enclosed Machine). The two spacers  55 , used on both sides of the top and bottom 60-tooth sprockets  66  in both subassemblies  12  and  11 , keep the chains  54  from rubbing against the internal housing frame  13  and the external cubic frame  10 .  
         [0380]     Therefore, by controlling the amounts of horizontal counter-rotations of both the internal housing frame  13  and the external cubic frame  10 , the internal housing frame can be oriented towards any desired horizontal direction (azimuth) which, when combined with the chosen direction of the Machine-generated total ResF, gives the cubic TDMM craft an unmatched three-dimensional, variable propulsion capability for use anywhere on earth and in outer space.  
         [0381]      FIG. 52  presents another cross-sectional side-view diagram of the cubic TDMM craft&#39;s left Machine mirror-image half, showing the relationship between the external cubic frame  10 , the internal housing frame  13 , the two heavy-duty swivel-and-sprocket assemblies  11  and  12 , the central plate&#39;s left side  15 A, the two-dimension, movable circular inner rim  33  (shown in the maximum “active position” making contact with the inside surface of the outer rim  34  at 180 degrees) and the 8 variable-length subassemblies  40  (each consisting of one telescoping slide  46  and of one 2-wheel device  47 ), rotating counterclockwise about the fixed, off-center point  0 .  
         [0382]      FIG. 53  shows a top-view diagram of the cubic TDMM craft, showing the spatial relationship between the external cubic frame  10 , the 96×24-inch rectangular top-view of the internal housing frame  13  (see  FIG. 2 ) and the two-stage rpm-reducing subassembly used for providing a 32-rpm drive to the top swivel assembly  12 —which is used for rotating the internal housing  13  (and its enclosed Machine) in any chosen horizontal direction (azimuth) inside the external cubic frame  10 . Also shown is the 100-inch-diameter alternate cylindrical frame  60  (shown as a dashed circle), which is used in  FIG. 54  as a replacement for the external cubic frame  10 . The two rpm-reducing stages are: 
    1) First stage: A reversible ¼ HP, 1800 rpm electric motor  64 , with an 8-tooth sprocket  65  (mounted on its shaft) and a motor mount  63  (for securing motor  64  onto the outside top of the 96-inch square right  16 B side-wall of the internal housing frame  13 —see  FIG. 51 ), is coupled to the 60-tooth sprocket  66  of the idler subassembly  72  (on top of the internal housing frame  13 —about half-way between motor  64  and the top swivel assembly  12 ) by means of a #35 chain  54 , which provides the idler subassembly&#39;s 60-tooth sprocket  66  and its secured 8-tooth sprocket  65  with a reduced 240-rpm rotation (or, 1800(8/60)), and     2) Second stage: The idler subassembly&#39;s 8-tooth sprocket  65  which, as mentioned above, rotates at 240 rpm, is in turn coupled to the 60-tooth sprocket  66  of the top swivel assembly  12  by means of a second #35 chain  54 , thereby causing the internal housing frame  13  to also rotate with a reduced 32 rpm rotation (or, 240(8/60)).      
         [0385]     A second, identical two-stage rpm-reducing subassembly, also consisting of motor  64 , sprockets and chains, is similarly mounted onto the outside bottom part of the internal housing frame  13  (see  FIG. 51 ), where it provides the same reduced 32 rpm counter-rotation to the external cubic frame  10 . The two small diagrams show how the top and bottom swivel assemblies  12  and  11  are respectively mounted sandwiched between the centers of the top and bottom sides of both the internal housing frame  13  and the external cubic frame  10 .  
         [0386]     Both the top and bottom rpm-reducing subassemblies can separately and variably be used together for counter-rotating (at the same or at different angular velocities) the internal housing frame  13  and the external cubic frame  10  (which encloses the rotatable internal housing frame  13 ), in order to balance out their opposite rotational torque reactions and give the internal housing frame  13  (and its enclosed Machine) the desired horizontal direction (azimuth) inside, and relative to, the external cubic frame  10 . The internal housing frame  13  rotates (inside the larger external cubic frame  10 ) about a central vertical axis  14 , which runs between the centers of both the top and bottom swivel assemblies  12  and  11  and which is aligned with the vertical center of central plate  15  (see  FIGS. 1, 2 , and  51 ). Therefore, the two rpm-reducing subassemblies&#39; bottom and top swivel assemblies are used for both supporting the internal housing frame  13  inside the external cubic frame  10  and for variably counter-rotating the internal housing frame  13  and the external cubic frame  10  until a desired horizontal direction (azimuth) is obtained (by selectively adjusting their respective torque reactions) for the internal housing frame  13  (and its enclosed Machine), relative to the external cubic frame  10 .  
         [0387]     Finally, by combining the selected direction of the combined, single, outwardly-directed ResF, generated by the Machine&#39;s two sets of 8 subassemblies  40  (counter-rotating in the “active position” in their respective movable inner rims), with the chosen horizontal direction (azimuth) of the internal housing frame  13  (and its enclosed Machine), a steerable and variably powerful motive force is then available for propelling the small-scale, 600-lb cubic TDMM craft in three dimensions, with spectacular performance and maneuverability, on earth and in outer space.  
         [0388]      FIG. 54  presents two diagrams of a simple reduction to practice of the basic invention (represented by  FIG. 1  in its most basic cubic form), looking like a “flying saucer”. The top diagram A shows a side view of the “flying saucer” and the bottom diagram B shows a top view of the same “flying saucer”. In the A-side-view, the alternate external cylindrical frame  60  (a top-view of which is shown as a 100-inch dashed circle in  FIGS. 2 and 53 ) is seen in this figure from the side, looking like a shaded 100-inch square, and looking like a circle in the B-top-view. The external cylindrical frame  60  is used in this embodiment (instead of the external 100-inch external cubic frame  10  of  FIG. 1 ) because it fits better with the circular shape of this exemplary saucer-shaped TDMM craft.  
         [0389]     Both the top A-side-view and the bottom B-top-view diagrams of the “flying saucer” show the peripheral area  38 , which is used for storage of equipments and supplies and for a small crew&#39;s quarters. The cockpit area  58  includes a platform  69 , supporting a pilot/navigator chair  68  and a command/control console  70  (with a control panel displaying all the various flight control switches, dials and monitoring instruments needed by the pilot/navigator to “fly” the craft in three dimensions). The various wires and cables between the command/control console  70  and the alternate cylindrical frame  60  run under platform  69 . The bottom B-top-view also shows two passageways  59 , between the cockpit  58  and the craft&#39;s area  38 , for use by the crew. The top A-side-view diagram also shows the sharp lower circular edge of the craft, with an angle no larger than 60 degrees—in order for the saucer-shaped TDMM craft to be flown at a given inclination inside the envelope of the shock wave that is created when traveling at high velocities through any atmospheric environment. The final shape and size of the said flying saucer-shaped TDMM craft will be determined later, during the engineering design, development and building phases.  
         [0390]     Finally, a more technologically advanced design of the telescoping full extension slide  46  (see  FIGS. 3, 4  and  5 ), which is used in the two sets of 8 counter-rotating subassemblies  40 , will be required in order to withstand angular velocities above 50 rad/sec (477.5 rpm), namely: one that would enable the Machine&#39;s mechanism to propel either the cubic TDMM craft or the much heavier exemplary “flying saucer” in three dimensions with the kind of spectacular performance (shown in the plots of  FIGS. 35 and 41  through  48 ) and maneuverability described earlier.  
       Conclusion  
       [0391]     The cubic air/space craft with a built-in “Three Dimension Motive Machine” (TDMM), herein referred to as the cubic TDMM craft, is a unique and innovative engineering invention, capable of generating an outwardly-directed, steerable, variably powerful and smooth resultant centrifugal force (ResF) to propel the 600-lb cubic craft with unparalleled performance and maneuverability (including making a 180-degree turn while in flight without having to make a long arced turn) in three dimensions. For example, the said cubic craft can generate total ResFs of 995, 2,238.1 and 3,979.8 lbs when its Machine&#39;s two sets of 8 variable-length subassemblies  40  are counter-rotating at 50, 75 and 100 rad/sec respectively. Furthermore, while using only the 50 rad/sec flight time plots of  FIGS. 44 and 48 , the cubic TDMM craft can reach an orbital altitude of 250 miles in 5.72 minutes, go to the moon (230,000 miles away) in about 3 hrs and even go to Mars (when it is about 35 million miles from earth) in less than 33 hrs. Both above flight times to the moon and to Mars are based on a constant acceleration and a constant deceleration of 53.4 ft/sec 2 (see  FIG. 45 ) during each “far-earth” half-way distances to the moon and to Mars. Such capabilities, built into a larger, full-scale model of the cubic TDMM craft (with sufficient space for equipments, parts, supplies and crew) would be ideal for long space voyages—especially when using a given constant acceleration to provide a substitute gravity (for the crew&#39;s benefit). More importantly, with a steady supply of electrical power, from solar panels, batteries and/or other sources (including nuclear), to operate and propel the cubic TDMM craft, there would be no need for propulsion jets and fuel for take-offs, landings and for various other maneuvers, because the motive force capability is built into the cubic craft (thereby greatly reducing its total weight as well as its manufacturing and operating costs). Moreover, because of the flywheel kinetic energy storage capacity of the two sets of 8 variable-length subassemblies  40  (see  FIG. 40 ), less electrical power would be needed to keep them counter-rotating at their selected angular velocities in the “active position”. Finally, the cubic craft&#39;s variable motive force capability makes it possible to control its velocity when re-entering any atmosphere from outer space without burning up (thus making the use of thermal tiles obsolete). The TDMM part of the cubic craft could also be used in land wheeled-vehicles and in all types of water, air and space crafts (in which the present use of propellers, fans and/or jets would no longer be needed).