Abstract:
A method and device for producing a controlled combustion by placing a combustion chamber in communication with a feed chamber that contains a solid propellant/body, introducing at least a portion of the body into the combustion chamber, isolating the combustion chamber from the feed chamber, and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber.

Description:
This application claims the benefit of priority of provisional patent application No. 60/208,914 filed in the U.S. Patent &amp; Trademark Office on Jun. 5, 2000. 
    
    
     BACKGROUND OF THE INVENTION 
     The present invention relates to propulsion and gas generating systems which utilize solid fuel. 
     In the current state of the art, either liquid or solid fuel, or propellant, is used in propulsion systems. Liquid fuel can easily be introduced at a controlled rate into a combustion chamber in order to allow the propulsion energy level to be adjusted in a simple manner. In addition, combustion can be halted and restarted simply by stopping and restarting the flow of liquid fuel into the combustion chamber. 
     However, liquid fuels tend to be relatively toxic, creating both storage and environmental safety problems, as well as some risk of destructive malfunction of the propulsion system in which they are employed. Furthermore, known liquid propellants have a lower energy density than do solid propellants. 
     However, solid propellants, despite their inherent advantages, do not lend themselves to controllable propulsion requirements or to controlled shut-off when intermittent propulsion is desired. 
     BRIEF SUMMARY OF THE INVENTION 
     The present invention provides an improved method of producing a controlled combustion, comprising: placing a combustion chamber in communication with a feed tube or chamber that contains a solid propellant body; introducing at least a portion of the body into the combustion chamber; isolating the combustion chamber from the feed chamber; and igniting the solid propellant in the combustion chamber while the combustion chamber is isolated from the feed chamber. 
     The invention further provides a novel device for producing a controlled combustion, comprising: a combustion chamber; a feed chamber containing a solid propellant; an outlet from the combustion chamber in communication with either a nozzle or an accumulator; an igniter communicating with the combustion chamber; and displacement means coupled to one of the chambers for establishing a first position in which the combustion chamber in communication with the feed chamber to allow at least a portion of the solid propellant to be introduced into the combustion chamber, and a second position in which the combustion chamber is isolated from the feed chamber and in communication with the outlet nozzle. 
    
    
     BRIEF DESCRIPTION OF THE SEVERAL VIEWS OF THE DRAWING 
     FIG. 1 is a perspective view of the basic components of a first embodiment of a device according to the invention, with the component parts disassembled to facilitate viewing. 
     FIGS. 2A and 2B are simplified pictorial cross-sectional views showing the device of FIG. 1 in an assembled state and in two respective operating states. 
     FIGS. 3A and 3B are views similar to that of FIGS. 2A and 2B showing a modified version of the device of FIG. 1 in two respective operating states. 
     FIG. 4 is a view similar to that of FIG. 1 showing another embodiment of a device according to the invention. 
     FIGS. 5A and 5B are cross-sectional views similar to those of FIGS. 2A and 2B, relating to the embodiment of FIG.  4 . 
     FIGS. 6A and 6B are assembled and disassembled, respectively, perspective views of a further embodiment of a device according to the invention. 
     FIGS. 7A and 7B are views similar to those of FIGS. 2A and 2B relating to the embodiment of FIGS. 6A and 6B. 
     FIGS. 8A and 8B are, respectively, an assembled perspective view and an exploded perspective view of another embodiment of a device according to the invention. 
     FIGS. 9A and 9B are cross-sectional views similar to those of FIGS. 2A and 2B, relating to the embodiment of FIGS. 8A and 8B. 
     FIG. 10 is a mathematical model of an exemplary embodiment of a device according to the invention. 
     FIG. 11 provides diagrams of thrust and pressure versus time of transient ballistics in the operation of a first example of a device according to the invention. 
     FIG. 12 provides diagrams similar to those of FIG. 11 for a second example of a device according to the invention. 
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     The present invention essentially provides methods and devices for producing thrust, or a quantity of gas under pressure, in throttleable, controllable amounts, using solid propellants. The invention takes advantage of the realization that higher fuel consumption efficiency is obtained in chemical propulsion systems by the production of high pressure, high thrust, short duration pulses, as opposed to thrust forces produced by continuous, or long duration, combustion. Devices according to the invention can be constructed to have a reduced inert weight and increased mass fraction, in comparison with liquid propellant systems having similar performance characteristics. Devices according to the invention can be constructed in ways that allow extremely simple introduction of successive bodies of solid propellant into the combustion chamber. 
     One example of a device according to the invention is illustrated in FIGS. 1,  2 A and  2 B. This embodiment is composed essentially of a hollow cylindrical housing  12  having a lateral opening  14  that receives an outlet nozzle  16  and a further opening (not visible in FIG. 1) for introduction of solid propellant into a combustion chamber. Housing  12  may also be provided, at a point diametrically opposite opening  14 , with a pressure transducer port  18  in which a pressure transducer will be installed before the device is placed into operation, thereby blocking port  18 . 
     The device further includes a cylindrical combustion chamber housing  20  which contains the combustion chamber, a feed tube  22  and a support element  24  which holds feed tube  22  in place on housing  12 , in line with the propellant introduction opening provided in the cylindrical wall of housing  12 . 
     The device shown in FIG. 1 further includes a mounting member  26  that will be secured to one end of housing  12  and will serve to mount the device on any suitable support surface within an air, ground, or space vehicle, including, but not limited to, an aircraft, missile, spacecraft, automobile, personnel carrier, in which the device is to serve as a gas generator or propulsion motor particularly for station keeping and attitude adjustment. 
     Referring specifically to FIGS. 2A and 2B, combustion chamber housing  20  is formed to include a combustion chamber  30 , a combustion gas outflow path  32  and an igniter housing  34 . In a complete device, housing  34  will contain an igniter that seals housing  34  to prevent escape of combustion gas therethrough. 
     In the embodiment shown in FIGS. 1 and 2, housing  20  is movable in translation along the longitudinal axis of housing  12  between a propellant loading position shown in FIG. 2A and a propellant combustion position shown in FIG.  2 B. This movement is controlled by a suitable displacement mechanism (not shown) that can be constructed and operated according to techniques already known in the art. Optionally, housing  12  may be provided with stop element,  38  which helps to assure that housing  20  will be correctly placed in the propellant combustion position. 
     At the start of a propulsion cycle, housing  20  is in the position shown in FIG. 2A, with propulsion chamber  30  in line with the propellant introduction opening in housing  12  and with feed tube  22 . Feed tube  22  is coupled to a propellant storage device (not shown) having any desired size and shape. In the embodiment illustrated in FIGS. 1 and 2, the propellant is in the form of discrete bodies, or charges,  40 , each dimensioned to fit into combustion chamber  30  in a desired manner. This may involve dimensioning a body  40  to substantially completely fill combustion chamber  30 , or to fill a defined portion thereof. Each body  40  may be a homogeneous body made entirely of a combustible material or may be composed of a mass of a combustible material held in a casing which is itself made of a combustible material so that the entire body will be consumed upon being ignited. After a body  40  has been introduced into chamber  30 , housing  20  will be displaced in the direction of the arrow shown in FIG.  2 A and by the displacement mechanism into the position shown in FIG.  2 B. Combustion chamber  30  is then isolated from the propellant introduction opening and is in communication with pressure transducer port  18 , while path  32  is aligned, and in communication, with nozzle  16 . 
     An igniter inserted in housing  34  may then be actuated to ignite body  40 , producing combustion gases that travel through path  32  and are expelled via nozzle  16  to generate a thrust pulse. 
     The sequence illustrated in FIGS. 2A and 2B can be repeated at a desired rate, which can be up to several times per minute or faster, depending on the mechanisms employed. The duration of each thrust pulse will depend on the size and composition of each propellant body  40 . By varying the cycle rate, any level of average propulsion force can be produced. 
     Propellant bodies  40  can have the form of cubes, cylinders, spheres, etc. 
     As an alternative to the provision of a plurality of discrete bodies  40 , there can be provided a continuous rod of propellant material whose leading end is fed into combustion chamber  30 , after which movement of chamber  20  into the position shown in FIG. 2B will act to sever the portion of the propellant material rod which is then in chamber  30  from the remainder of the rod. This simply requires that the end of chamber  20  which traverses the propellant introduction opening between tube  22  and chamber  30  be provided with, or shaped to function as, a suitable cutting tool. In the case of this embodiment, the distance through which the rod of propellant material is advanced at the start of each propulsion cycle will control the amount of propellant material which is present in chamber  30  when ignition occurs, i.e., in the position shown in FIG. 2B, thereby providing an additional control parameter for the generation of propulsion forces. 
     FIGS. 3A and 3B are views similar to those in FIGS. 2A and 2B illustrating a second form of construction of an embodiment having the general configuration shown in FIG.  1 . The embodiment shown in FIGS. 3A and 3B differs from that of FIGS. 2A and 2B in that nozzle  16  is disposed at the same side of the longitudinal axis of housing  12 ′ as the opening via which solid propellant bodies  40  are introduced into the combustion chamber. Therefore, combustion chamber housing  20 ′ does not have a passage corresponding to passage  32  in the embodiment of FIGS. 2A and 2B. Housing  12 ′ may be provided with a suitably located pressure transducer port corresponding in function to port  18  of FIGS. 2A and 2B and would be provided with an igniter, although this is not illustrated in FIGS. 3A and 3B. 
     According to a further variation, bodies  40  may be brought into position with the opening for introduction into the combustion chamber by first being moved in a direction  50  parallel to the longitudinal axis of housing  12 ′, and then in a direction  52  perpendicular to direction  50 . 
     In all other respects, the embodiment shown in FIGS. 3A and 3B is constructed and operated in the manner described above with respect to FIGS. 2A and 2B. 
     FIGS. 4,  5 A and  5 B show a second embodiment of a device according to the invention which differs from the first embodiment essentially in that it includes a combustion chamber housing that is rotatable, rather than being movable in translation. 
     The device according to this embodiment is composed essentially of a rectangular housing  112  provided with a passage in the form of a cylindrical through bore which is open at two opposite sides of housing  112 . In addition, housing  112  is provided with a rectangular propellant inlet opening  108 , a passage  134  defining a housing for receiving an igniter  136 , and a combustion gas outlet passage  140  that opens into a nozzle  142  (not visible in FIG.  4 ). The through bore in housing  112  receives a circular cylindrical combustion chamber housing  120  provided with a rectangular, or parallelepiped shaped, combustion chamber  130  and a passage  132  which is arranged to communicate with gas outlet passage  140  when combustion chamber housing  120  is in an ignition position. 
     In this embodiment, the propellant is in the form of essentially cubic bodies  146  that will be introduced in succession into combustion chamber  130  and will then be ignited. Any desired type of mechanism can be provided to supply propellant bodies  146  to combustion chamber  130  at a desired rate. Alternatively, the propellant can initially be in the form of a rod having a square cross section and housing  112  can be provided with a suitable device for severing the leading end of the rod to form a discrete propellant body that is introduced into chamber  130  for each combustion event. 
     The device according to this embodiment operates in much the same way as the embodiment of FIGS. 1 and 2, with the exception that here combustion chamber housing  120  is rotated between a loading position, shown in FIG. 5A, and an ignition position, shown in FIG  5 B. In the loading position of FIG. 5A, a propellant body  146  can be introduced into chamber  130  by any suitable mechanism. Then, housing  120  is rotated to the ignition position shown in FIG  5 B, in which passage  132  is aligned with passage  140  and igniter  136  is in position to cause ignition of propellant body  146 . With the device in the position shown in FIG. 5B, the propellant body in chamber  130  is ignited by actuation of igniter  136 , producing combustion gasses that pass through passage  132  and passage  140  and are then expelled via nozzle  142  in order to produce a thrust pulse. 
     As in the case of the embodiments shown in FIGS. 1,  2  and  3 , thrust pulses can be produced at any desired rate within the capabilities of the propellant body feed mechanism and combustion chamber housing rotation mechanism. 
     A third embodiment of the invention is shown in FIGS. 6A,  6 B,  7 A and  7 B and includes a circular cylindrical housing  212  and a circular disc-shaped combustion chamber housing  220 . Housing  220  is installed in housing  212  and is connected to a suitable drive system (not shown) to rotate housing  220  within, and about the longitudinal axis of, housing  212 . 
     Housing  212  is provided with a propellant introduction opening  208  and four nozzles  216 , spaced at intervals of  90 ° about the periphery of housing  212 . Housing  220  is provided with four combustion chambers  230  spaced at intervals of 90° about the periphery of housing  220 . In the illustrated embodiment, each chamber  230  has a square cross section and the device operates with propellant bodies  240  each having a cubic form. In the operation of this embodiment, each combustion chamber  230  receives a propellant body  240  when that chamber is in alignment with propellant introduction opening  208 . Housing  220  can be rotated by a suitable mechanism in the direction of the arrow shown in FIG.  7 A and each combustion chamber  230  is provided with an igniter (not shown) which can be actuated at any time when the associated chamber  230  is isolated from introduction opening  208 . Thus, a propellant body  240  in any one of combustion chambers  230  can be ignited when its associated combustion chamber is in line with any selected one of nozzles  216 , or before the associated combustion chamber comes into alignment with the respective nozzle. In the latter case, as shown particularly in FIG. 7B, a propellant body can be ignited when its associated combustion chamber  230  is completely sealed so that a mass of combustion gasses under pressure accumulates in the associated combustion chamber. Then, when housing  220  is rotated to bring the combustion chamber into alignment with a respective nozzle  216 , the combustion gasses will be expelled through the nozzle to produce a thrust pulse. 
     Thus, the embodiment shown in FIGS. 6 and 7 can be operated to produce thrust pulses in any one of four different directions. 
     In a variant of the embodiment shown in FIGS. 6 and 7, a different number of combustion chambers  230  can be provided. This number can be between one and a number greater than four. As the number of combustion chambers  230  is increased, the rate at which thrust pulses can be produced and the possible number of thrust directions increase correspondingly. 
     The invention can also be embodied in a device having a fixed combustion chamber housing, a movable shutter mechanism for sealing the combustion chamber off from the feed tube prior to a combustion phase and a single nozzle that is in permanent communication with the combustion gas outflow path. The nozzle can either be fixed to the combustion chamber housing or can be gimbaled relative thereto. 
     The embodiments shown in FIGS. 4-7 can be easily modified so that the associated combustion chamber housing is displaced in translation, rather than in rotation. 
     Another embodiment of the invention is illustrated in FIGS. 8A,  8 B,  9 A and  9 B. As will be seen, this embodiment differs from that of FIGS. 6 and 7 in that the direction of introduction of propellant bodies in a direction in which thrust is produced are parallel to the axis of rotation of the combustion chamber. 
     The embodiment shown in FIGS. 8A,  8 B and  9 A,  9 B includes a device housing  312  composed essentially of a base plate  314  and a cover  316 . A combustion chamber housing  320  is installed within housing  312  and includes a plate member  322  and a stem or shaft,  324 . Plate member  322  and shaft  324  formed as a one piece unit and shaft  324  extends through a hub forming a part of cover  316 . A shaft  324  is provided, at its upper end, with a coupling element  326  that can be coupled to any suitable drive mechanism (not shown) to rotate combustion chamber housing  320  about the longitudinal axis of shaft  324 . 
     Combustion chamber housing  320  is provided with one or more combustion chambers  328 . 
     This embodiment further includes a feed unit  330  composed of a magazine  332  for storing a supply of propellant bodies  40  and a feed tube  334  which extends between magazine  332  and an introduction opening provided in cover  316  in order to supply individual bodies  40  in succession to chamber or chambers  328 . Feed unit  330  can be constructed in any suitable conventional manner to reliably deliver a succession of propellant bodies  40  to combustion chamber or chambers  328 . 
     The unit is completed by an igniter  340  that communicates with a recess  342  provided in cover  316 . 
     Finally, plate  314  is provided with a propellant gas outlet passage coupled to a nozzle  350 . 
     In operation, combustion chamber housing  320  is rotated, by operation of a mechanism coupled to element  326 , to bring a combustion chamber  328  into line with feed tube  334  and to allow a propellant body  40  to be introduced into that combustion chamber. Combustion chamber housing  320  is then rotated to bring a combustion chamber  328  containing a body  40  into line with the combustion gas outlet passage coupled to nozzle  350 , as well as into line with igniter  340 . Igniter  340  can then be activated to ignite body  40  and produced a thrust pulse. 
     If combustion chamber housing  320  is provided with a plurality of combustion chambers  328 , spaced angularly from one another about the axis of rotation of shaft  324 , each combustion chamber  328  will receive a propellant body  40  in turn, shown in FIG. 9A, and will subsequently be brought to the position shown in FIG. 9B, where propellant body  40  is ignited. 
     It will be noted that one feature of the present invention is that the direction of introduction of a propellant body  40  into a combustion chamber  328  and the direction of each thrust pulse are parallel to one another and to the axis of rotation of shaft  324 . Furthermore, in all of the embodiments disclosed herein, combustion chamber housing is movable relative to the device housing so that the, or each, combustion chamber undergoes a rotary or transverse linear motion relative to the above-mentioned directions of introduction and of each thrust pulse to isolate the combustion chamber from the exit nozzle or accumulator during introduction of a propellant body  40  and to isolate the combustion chamber from the feed unit when a thrust pulse is being produced. 
     Various types of igniters can be used in any of the embodiments of the present invention. A suitable igniter could be, for example, a simple impact-type firing pin that would cooperate with a consumable primer embedded in the propellant body at a location to be aligned with the firing pin when the body is in a combustion chamber and the combustion chamber is in a position at which ignition is to occur. Use may also be made of capacitor discharge and laser igniters. 
     The functions of propellant feed and combustion chamber housing displacement may be performed by separate systems, including stepper or servo motors, solenoids, etc. These mechanisms, and ignition, can be controlled by a suitable computerized control system to determine the exact timing and sequence of functions. Such a control system can easily be implemented by those skilled in the art. It should also be apparent that some or all of the various functions can be combined with the use of mechanical linkages and/or springs. 
     As an alternative to achieving ignition of a propellant body when the combustion chamber is in communication with a nozzle, combustion can occur when the combustion chamber is in communication with an accumulator which could store a quantity of combustion exhaust gas and subsequently distribute that gas through valves for the performance of various functions, including the production of thrust pulses, the driving of miniature turbo-alternators for electrical energy, or for feeding fuel-rich effluent to a pulse detonation engine or other air breathing engine. 
     In addition, as already described above with respect to the embodiment of FIGS. 6 and 7, combustion can occur while the combustion chamber is completely sealed and the resulting exhaust gasses under pressure can be released either to a nozzle or to an accumulator. 
     FIG. 10 shows a mathematical model of a device according to the invention. 
     Table 1, below, lists the propellant properties that were assumed in developing that model. 
     
       
         
               
             
               
               
               
               
             
           
               
                 TABLE 1 
               
               
                   
               
               
                 Propellant Parameters for Ballistic Model 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 Burn rate equation (in/sec) 
                 6.6 
                 (P/25000) 0.9   
               
               
                   
                 Propellant Impetus (RT) 
                 1164 
                 J/g 
               
               
                   
                 Flame Temperature 
                 3475 
                 K. 
               
               
                   
                 Propellant Density 
                 1.573 
                 g/cc 
               
               
                   
                 Ratio of Specific Heats 
                 1.238 
               
               
                   
                 Characteristic Velocity 
                 5403 
                 ft/sec 
               
               
                   
                 Molecular Weight 
                 24.76 
               
               
                   
                   
               
             
          
         
       
     
     Table 2, below, shows the resulting geometry for a 100-lbf thruster and FIG. 11 shows the form of the pressure and thrust pulses that will be produced in a device according to the mathematical model of FIG. 10, using the dimensions set forth in Table 2. 
     
       
         
               
             
               
               
               
               
             
               
               
               
               
             
           
               
                 TABLE 2 
               
               
                   
               
               
                 Geometry for 100-lbf Thruster 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 Dimensions of cube 
                 0.354 in. × 0.354 in. × 0.827 in. 
                   
               
             
          
           
               
                   
                 Initial free volume 
                 0.15 
                 in 3   
               
               
                   
                 Throat Diameter 
                 0.0391 
                 in. 
               
               
                   
                 Expansion Ratio 
                 500:1 
               
               
                   
                 Vacuum Thrust Coeff. 
                 1.975 
               
               
                   
                   
               
             
          
         
       
     
     Table 3 shows corresponding values for a 10-lbf thruster, while FIG. 12 shows the form of the pressure and thrust pulses that would be produced in a device according to the mathematical model of FIG.  10  and with the dimensions of Table 3. 
     
       
         
               
             
               
               
               
               
             
               
               
               
               
             
           
               
                 TABLE 3 
               
               
                   
               
               
                 Geometry for 10-lbf Thruster 
               
               
                   
               
             
             
               
                   
               
             
          
           
               
                   
                 Dimensions of cube 
                 0.2 in. × 0.2 in. × 0.2 in. 
                   
               
             
          
           
               
                   
                 Initial free volume 
                 0.02 
                 in 3   
               
               
                   
                 Throat Diameter 
                 0.0113 
                 in 
               
               
                   
                 Expansion Ratio 
                 500:1 
               
               
                   
                 Vacuum Thrust Coeff. 
                 1.975 
               
               
                   
                   
               
             
          
         
       
     
     Although only a few exemplary embodiments of this invention have been described in detail above, those skilled in the art will readily appreciate that many modifications are possible in the exemplary embodiments without materially departing from the novel teachings and advantages of this invention. Accordingly, all such modifications are intended to be included within the scope of this invention.