Abstract:
A mechanism geometrically constituted with twelve axes can be manipulated for spherical coordinate kinematics. Concerning the major improvement of the invention, one of the two geometric tetrahedron frames which were ever specified by our two pre-inventions (U.S. Pat. No.  8,579,714  B 2/ US 20120083347 A 1  and US 20150082934 A 1 ) is decoupled and reconstructed as two separated terminal frames which are constituted by two individual geometric arcs. The other one of the two geometric tetrahedron frames without changing its original geometric definition is inherited in the invention and renamed as a base frame. Comparing to the original single geometric tetrahedron, the mechanism newly developed by two individual geometric arcs is suffering fewer constraints and gaining more work space. If a terminal saddle is equipped onto a terminal frame, the newly developed mechanism can be increased extra payload capability. Therefore, this improvement is substantially extending the utility of twelve axes mechanism for spherical coordinate kinematics.

Description:
BACKGROUND OF THE INVENTION 
       [0001]    Field of the Invention 
         [0002]    A mechanism geometrically constituted with twelve axes can be manipulated for spherical coordinate kinematics. This mechanism is able to implement in multi-shaft composite machining center and coordinate measuring machine or apply as a robot&#39;s shoulder joint and hip joint. 
         [0003]    Description of Related Art 
         [0004]    The invention is referred to the applicant&#39;s two pre-inventions, the first pre-invention is issued by USPTO (U.S. Pat. No. 8,579,714 B2/US20120083347A1), and the second pre-invention has sequentially received notice of allowance from USPTO (US20150082934A1) 
         [0005]    The invention is inherited the same twelve axes geometric configuration from our two pre-inventions. An important issue is how to make a twelve axes mechanism operate smoothly without mutual interference and/or singularity while contemplating practical design and regulating geometric limitation. Therefore, the invention is directed to a new approach regarding to interference and singularity avoidance in comparing to our first pre-invention. After synthesizing our two pre-inventions, four orbit specifications are classified. More especially, “at least one” end effect arc-link assemblies introduced in our second pre-invention are improved as “at most two” crank sets in the invention. Concerning the major improvement of the invention, one of the two geometric tetrahedron frames which were ever specified by our two pre-inventions is decoupled and reconstructed as two separated terminal frames which are constituted by two individual geometric arcs. The other one of the two geometric tetrahedron frames without changing its original geometric definition is inherited in the invention. Comparing to the original single geometric tetrahedron, the mechanism newly developed by two individual geometric arcs is suffering fewer constraints and gaining more work space. If a terminal saddle is equipped onto a terminal frame, the newly developed mechanism can be increased extra payload capability. Therefore, this improvement is substantially extending the utility of twelve axes mechanism for spherical coordinate kinematics. 
         [0006]    The above and other objects, features and advantages of the invention will become apparent from the following detailed description taken with the accompanying drawings. 
       SUMMARY OF THE INVENTION 
       [0007]    It is one objective of the present disclosure to provide a mechanism geometrically constituted with twelve axes configured to be manipulated for spherical coordinate kinematics. 
         [0008]    A twelve axes mechanism includes a base frame, two terminal frame sets, four arc-link sets, and at most two crank sets. The base frame set comprises a base frame including a plurality of brackets and four base rotating modules installed into the base frame. Each terminal frame set comprises a terminal frame and two terminal rotating modules installed into the terminal frame. Each arc-link set comprises a base arc-link, a terminal arc-link and an arc-link rotating module. Each crank set comprises an arc crank and a crank rotating module. There are total twelve axes in the mechanism for pivoting with four base rotating modules, four arc-link rotating modules and four terminal rotating modules individually, and each axis of theses rotating modules is specifically directed into the center of the base frame for concentrically rotating each arc-link set along a specified geometric orbit between the base frame and two terminal frames. Therefore, the final output torque can be integrated via serial linking and parallel cooperating with the twelve rotating modules. 
         [0009]    The “at most two” crank sets is meaningful. It should be emphasized that the quantity of the crank set can be optional, that is zero, one, or two. There are six embodiments for sufficiently introducing the twelve axes mechanism with single crank set or with double crank sets or without crank set. And two independent claims are enumerated, i.e., claim  1  and claim  6 . Except excluding crank sets, claim  6  substantially includes a base frame, two terminal frame sets, and four arc-link sets, and the definitions of these elements are as same as those of claim  1 . 
         [0010]    These and other objectives of the present disclosure will no doubt become obvious to those of ordinary skill in the art after reading the following detailed description of the preferred embodiment that is illustrated in the various figures and drawings. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0011]      FIG. 1A - FIG. 1B  show geometrical and perspective drawings of base frame design type I. 
           [0012]      FIG. 2A - FIG. 2B  show geometrical and perspective drawings of base frame design type II. 
           [0013]      FIG. 3A - FIG. 3B  show geometrical and perspective drawings of base frame design type III. 
           [0014]      FIG. 4A - FIG. 4B  show geometrical and perspective drawings of base frame design type IV. 
           [0015]      FIG. 5A - FIG. 5B  show geometrical and perspective drawings of the orbit specification I 
           [0016]      FIG. 6A - FIG. 6B  show geometrical and perspective drawings of the orbit specification II. 
           [0017]      FIG. 7A - FIG. 7B  show geometrical and perspective drawings of the orbit specification III. 
           [0018]      FIG. 8A - FIG. 8B  show geometrical and perspective drawings of the orbit specification IV. 
           [0019]      FIG. 9A - FIG. 9B  show geometrical and perspective drawings of crank&#39;s pivotal configuration I. 
           [0020]      FIG. 10A - FIG. 10B  show geometrical and perspective drawings of crank&#39;s pivotal configuration II. 
           [0021]      FIG. 11A - FIG. 11C  show the first embodiment&#39;s 3-view drawings for the orbit specification I with single crank set. 
           [0022]      FIG. 12A - FIG. 12C  show the second embodiment&#39;s 3-view drawings for the orbit specification II with single crank set. 
           [0023]      FIG. 13A - FIG. 13C  show the third embodiment&#39;s 3-view drawings for the orbit specification III with double crank sets. 
           [0024]      FIG. 14A - FIG. 14C  show the fourth embodiment&#39;s 3-view drawings for the orbit specification IV with double crank sets. 
           [0025]      FIG. 15A - FIG. 15C  show the fifth embodiment&#39;s 3-view drawings for the orbit specification III without crank set. 
           [0026]      FIG. 16A - FIG. 16C  show the sixth embodiment&#39;s 3-view drawings for the orbit specification IV without crank set. 
       
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
       [0027]    The invention is a mechanism which can be manipulated for spherical coordinate kinematics and geometrically constituted by twelve axes. The mechanism comprises a base frame set, two terminal frame sets, four arc-link sets, and at most two crank sets. 
         [0028]    The base frame set comprises a base frame  0   c  including a plurality of brackets and four base rotating module  0   a  installed into the base frame  0   c , the base frame  0   c  is configured with four vertexes which can be used to constitute a base geometrical tetrahedron, each axis of base rotating module  0   a , denoted by unit vector U i , wherein i=1-4, is individually coincided with a vertex-to-center line of the base geometrical tetrahedron, and these four vertex-to-center lines are coincided with the center of the base frame  0   a . An angle between any two vertex-to-center lines of the base geometrical tetrahedron is geometrically represented as            ij =Arc Cos(U i U j ), wherein i≠j. The angle between any two vertex-to-center lines of the base geometrical tetrahedron is greater than 75° and less than 150°, i.e.: 75°&lt;           ij &lt;150°. The geometric definition of base frame set is shown as  FIG. 1A ,  FIG. 2A ,  FIG. 3A , and  FIG. 4A . 
         [0029]    According to our first pre-invention, if the base frame  0   c  is geometrically defined as a regular tetrahedron, the regular tetrahedron frame may be easily designed and simulated due to its simple and symmetry. Thus, six angles defined by each pair of vertex-to-center lines of the base frame  0   c  are equal, approximately 109.5°, i.e.:            12 =           13 =           14 =           23 =           24 =           34 ≈109.5°. But the regular tetrahedron is a configuration most likely to have singularities. This characteristic was clearly introduced and specifically analyzed in our first pre-invention. For the sake of avoiding singularities, it is preferred that the base frame  0   c  is not defined as a regular tetrahedron. 
         [0030]    According to  FIG. 12 - FIG. 15  referring to our first pre-invention, these four figures and related description are introduced for clearly proving that the operating range of an angle between any two vertex-to-center lines of a movable frame defined by flexible geometric tetrahedron which was ever tested and verified or singularity avoid ance can be determined by proper parametric design. Evidently, the mentioned operating range which is proved between 75° and 150° is adapted in the independent claim  1  and claim  6 . After analyzing geometrics and configurations, the sufficient and enable mode is disclosed as expected. 
         [0031]    The base frame  0   c  can be either closed-loop type or open-loop type, and the closed-loop type is designed to enhance rigidity in order to avoid vibration or deformation. The open-loop type is designed for preventing predictable interference caused by arc-link sets. Therefore, there are four design types for base frame  0   c , design type I is shown as  FIG. 1A - FIG. 1B , design type II is shown as  FIG. 2A - FIG. 2B , design type III is shown as  FIG. 3A - FIG. 3B , and design type IV is shown as  FIG. 4A - FIG. 4B . 
         [0032]    In the two terminal frame sets, each terminal frame set comprises an terminal frame  4   c  and two terminal rotating modules  4   a  installed into the terminal frame  4   c,  the terminal frame is geometrically defined by two vertexes which can be used to constitute a terminal geometrical arc, each axis of terminal rotating module  4   a  is individually coincided with a vertex-to-center line of the terminal geometrical arc, and these two vertex-to-center lines are coincided with the center of the base frame for concentrically rotating the terminal frame along specified geometric orbit. The radius of the terminal frame&#39;s geometric orbit is denoted by r 4 . The radius of the base frame&#39;s geometric orbit is denoted by r 0 . 
         [0033]    The two vertex-to-center lines of the first terminal geometrical arc are individually denoted by unit vector V 1  and V 2 . An angle between the two vertex-to-center lines is geometrically represented as λ 12 =Arc Cos (V 1 V 2 ). The two vertex-to-center lines of the second terminal geometrical arc are individually denoted by unit vector V 3  and V 4 . An angle between the two vertex-to-center lines is geometrically represented as λ 34 =Arc Cos (V 3 V 4 ). The angle between the two vertex-to-center lines of the terminal geometrical arc is greater than 75° and less than 150°, i.e.: 75°&lt;λ 12 &lt;150° and 75°&lt;λ 34 &lt;150°. The geometrical definitions of terminal frame are shown in  FIG. 5A ,  FIG. 6A ,  FIG. 7A , and  FIG. 8A . 
         [0034]    In the two terminal frame sets, each terminal frame set further comprises a terminal saddle  4   s  which can be equipped onto the terminal frame&#39;s opposite side relative to terminal arc-links  2   c  for carrying a payload. The terminal saddle  4   s  can be functioned as a lifting mechanism having an extendable piston rod as implemented in pneumatic cylinders, hydraulic cylinders or electric actuator. Applications include a robot&#39;s shoulder joint and hip joint. 
         [0035]    In the four arc-link sets, each arc-link set includes an base arc-link  1   c , an terminal arc-link  2   c  and an arc-link rotating module  2   a , an end of the base arc-link  1   c  is pivotally connected with an end of the terminal arc-link  2   c  through an axis of arc-link rotating module  2   a,  the other end of base arc-link  1   c  is pivotally connected with an axis of base rotating module  0   a , and the other end of terminal arc-link  2   c  is pivotally connected with an axis of terminal rotating module  4   a,  each axis of arc-link rotating modules  2   a,  denoted by unit vector W i , wherein i=1-4, is normally directed into the center of the base frame  0   c  for concentrically rotating each arc-link set along specified geometric orbit between the base frame  0   c  and two terminal frames  4   c.  The radius of each base arc-link&#39;s geometric orbit is denoted by r 1  . The radius of each terminal arc-link&#39;s geometric orbit is denoted by r 2 . 
         [0036]    Arc-length of a base arc-link  1   c , geometrically represented by α i =Arc Cos (U i W i ), is defined as an angle between two axes of the base rotating module  0   a  and the arc-link rotating module  2   a  which are individually connected with the same base arc-link  1   c . Arc-length of a terminal arc-link  2   c , geometrically represented by β i =Arc Cos (V i W i ), is defined as an angle between two axes of terminal rotating module  4   a  and the arc-link rotating module  2   a  which are individually connected with the same terminal arc-link  2   c.    
         [0037]    Referring to our first pre-invention, singularities avoidance and geometric limitation were clearly introduced and specifically analyzed. Sum of arc-lengths of any two of the base arc-links is greater than or equal to an angle between their corresponding vertex-to-center lines of the base geometrical tetrahedron, i.e.:            ij ≦α j +α j , wherein i≠j. Sum of arc-lengths of any two of the terminal arc-links is greater than or equal to an angle between their corresponding vertex-to-center lines of the same terminal geometrical arc, i.e.: λ 12 ≦β 1 +β 2  and λ 34 ≦β 3 +β 4 . 
         [0038]    There are total twelve axes in these four arc-link sets for pivoting with four base rotating modules  0   a , four arc-link rotating modules  2   a  and four terminal rotating modules  4   a  individually, therefore the final output torque can be integrated via serial linking and parallel cooperating with the twelve rotating modules. The invention is inherited the same twelve axes geometric configuration from our two pre-inventions. An important issue is how to make a twelve axes mechanism operate smoothly without mutual interference and/or singularity while contemplating practical design and regulating geometric limitation. Therefore, the invention is directed to a new approach regarding to interference and singularity avoidance in comparing to our first pre-invention. 
         [0039]    The most unbeatable problem is four-axle fold singularity for constructing a mechanism with twelve axes. The phenomena of four-axle fold singularity are detail introduced and precisely defined on  FIG. 16 - FIG. 21  referring to our first pre-invention. These six figures are clearly expressed for concerning that “Since four-axle fold singularity always happens when the mechanism is at the notional center, once the mechanism is trapped, it is difficult to escape. Unfortunately, the central position must be passed over because it is the vital part for the processes of both initialization and return.” In advance, for avoiding four-axle fold singularity, three parameter design approaches are developed by our first pre-invention. 
         [0040]    After analyzing the potential challenge related to the singularity, and for providing useful reference for designing, the fourth parameter design approach is introduced. Assign both base arc-link and terminal arc-link belong to the same arc-link set be concentrically rotated along the same geometric orbit, singularity can be avoided for the sake of disability of fully folding, i.e.: the radius of each base arc-link&#39;s geometric orbit is “equal to” the radius of each terminal arc-link&#39;s geometric orbit. The orbit specification is continually following the two basic orbit specifications described in our second pre-inventions. The first basic orbit specifications, i.e.: the radius of the base frame&#39;s geometric orbit is “greater than” the radius of the terminal frame&#39;s geometric orbit. The second basic orbit specifications, i.e.: the radius of the base frame&#39;s geometric orbit is “less than” the radius of the terminal frame&#39;s geometric orbit. 
         [0041]    After synthesizing our two pre-inventions and the definition just mentioned above, four orbit specifications are classified for the invention. The orbit specification I: The radius of the base frame&#39;s geometric orbit is “greater than” the radius of the terminal frame&#39;s geometric orbit, and the radius of each base arc-link&#39;s geometric orbit is “equal to” the radius of each terminal arc-link&#39;s geometric orbit, i.e.: r 0 &gt;r 1 =r 2 &gt;r 4 , shown as  FIG. 5A - FIG. 5B . The orbit specification II: The radius of the base frame&#39;s geometric orbit is “less than” the radius of each terminal frame&#39;s geometric orbit, and the radius of each base arc-link&#39;s geometric orbit is “equal to” the radius of the terminal arc-link&#39;s geometric orbit, i.e.: r 0 &lt;r 1 =r 2 &lt;r 4 , shown as  FIG. 6A - FIG. 6B . The orbit specification III: The radius of the base frame&#39;s geometric orbit is “greater than” the radius of the terminal frame&#39;s geometric orbit, and the radius of each base arc-link&#39;s geometric orbit is “greater than” the radius of each terminal arc-link&#39;s geometric orbit, i.e.: r 0 &gt;r 1 &gt;r 2 &gt;r 4 , shown as  FIG. 7A - FIG. 7B . The orbit specification IV: The radius of the base frame&#39;s geometric orbit is “less than” the radius of the terminal frame&#39;s geometric orbit, and the radius of each base arc-link&#39;s geometric orbit is “less than” the radius of each terminal arc-link&#39;s geometric orbit, i.e.: r 0 &lt;r 1 &lt;r 2 &lt;r 4 , shown as  FIG. 8A - FIG. 8B . 
         [0042]    In the at most two crank sets, each crank set comprises an arc crank  3   c  and a crank rotating module  3   a.  An end of the arc crank  3   c  is mounted a rod which is concentrically extended opposite side relative to the base frame  0   c , these extending lines of the extended rods are denoted by unit vector N i , wherein i=1-2. The other end of the arc crank  3   c  is pivoted through an axis of base rotating module  0   a  and installed into the crank rotating module  3   a  opposite side relative to the base frame  0   c , and the arc crank  3   c  can be concentrically rotated along a geometric orbit between terminal arc-link  2   c  and terminal frame  4   c . The radius of each arc crank&#39;s geometric orbit is denoted by r 3 . Arc-length of arc crank  3   c,  geometrically represented by δ i =Arc Cos (U i N i ), wherein i=1-2, is defined as an angle between the axis of base rotating module  0   a  and the extended rod mounted onto the same arc crank  3   c.  The arc-length of arc crank  3   c  is less than or equal to 90°, i.e.: δ i 90°, wherein i=1-2. The geometric definitions of crank set are shown as  FIG. 9A - FIG. 9B  and  FIG. 10A - FIG. 10B . 
         [0043]    The crank rotating module  3   a  can be functionally actuated for preventing predictable interference caused by terminal arc-link  2   c  and/or terminal frame  4   c . Each crank set further comprises a crank saddle  3   s  which can be equipped onto the arc crank&#39;s extended rod opposite side relative to the base frame  0   c  for carrying the payload. The crank saddle  3   s  can be a clamp of a lathe to support a shaft of a laser cutter or install a drill as applied in multi-shaft composite machining centers. 
         [0044]    The end effect arc-link assembly introduced in our second pre-invention is renamed as crank set in the invention, and more especially, “at least one” end effect arc-link assemblies are improved as “at most two” crank sets. If geometrics and configurations are simply concerned, at most four crank sets are able to install in the base frame  0   c . After simulating and verifying, utility and effectiveness of greater than two crank sets are worthless, because they are unavoidably interfered with base frame  0   c  and/or each arc-link set. Work space of two crank sets is also reduced but acceptable, because they can clamp the payload corporately and stably. Work space of one crank set is gradually increased, and oscillation and vibration are easily accompanied for a single crank hanging alone. 
         [0045]    While our first pre-invention has a greater space for orientating due to no hinder of any crank set, it is capable of directly outputting torque due to eliminating crank set. Although shortage of crank saddle  3   s,  payload still can be carried on equipping terminal saddles  4   s.  The different quantity of crank sets are separately adapted in different suitable domains, therefore, the quantity about “at most two” is adapted in the invention to replace by the quantity about “at least one” in our second pre-invention. After analyzing geometrics and configurations, the sufficient and enable mode is disclosed as expected. 
         [0046]    The base frame  0   c  can be either closed-loop type or open-loop type, and the closed-loop type is designed to enhance rigidity in order to avoid vibration or deformation. The open-loop type is designed for preventing predictable interference caused by arc-link sets and/or crank sets. Therefore, there are four design types for base frame  0   c , design type I is shown as  FIG. 1A - FIG. 1B , design type II is shown as  FIG. 2A - FIG. 2B , design type III is shown as  FIG. 3A - FIG. 3B , design type IV is shown as  FIG. 4A - FIG. 4B . 
         [0047]    There are two pivotal configurations for connecting the at most two crank sets and base frame set. The two pivotal configurations are continually following two basic orbit specifications described in our second pre-inventions. The pivotal configuration I: The arc crank  3   c  can be concentrically rotated along a geometric orbit between each terminal arc-link  2   c  and the terminal frames  4   c  while the radius of each terminal arc-link&#39;s geometric orbit is “greater than” the radius of the terminal frame&#39;s geometric orbit, i.e.: r 2 &gt;r 3 &gt;r 4 , shown as  FIG. 9A - FIG. 9B . The pivotal configuration II: The arc crank  3   c  can be concentrically rotated along a geometric orbit between each terminal arc-link  2   c  and the terminal frames  4   c  while the radius of each terminal arc-link&#39;s geometric orbit is “less than” the radius of the terminal frame&#39;s geometric orbit, i.e.: r 2 &lt;r 3 &lt;r 4 , shown as  FIG. 10A - FIG. 10B . 
         [0048]    The base rotating module  0   a  can be assembled by a torque output device and/or an angle sensor and/or a bearing with an axle. The arc-link rotating module  2   a  can be assembled by a torque output device and/or an angle sensor and/or a bearing with an axle. The terminal rotating module  4   a  can be assembled by a torque output device and/or an angle sensor and/or a bearing with an axle. The crank rotating module  3   a  can be assembled by a torque output device and/or an angle sensor and/or a bearing with an axle. 
         [0049]    There are six embodiments for realizing the invention. The first embodiment is the orbit specification I with single crank set, shown as  FIG. 11A - FIG. 11C . The second embodiment is the orbit specification II with single crank set, shown as  FIG. 12A - FIG. 12C . The third embodiment is the orbit specification III with double crank sets, shown as  FIG. 13A - FIG. 13C . The fourth embodiment is the orbit specification IV with double crank sets, shown as  FIG. 14A - FIG. 14C . The fifth embodiment is the orbit specification III without crank set, shown as  FIG. 15A - FIG. 15C . The sixth embodiment is the orbit specification IV without crank set, shown as  FIG. 16A - FIG. 16C . 
         [0050]    Those skilled in the art will readily observe that numerous modifications and alterations of the device and method may be made while retaining the teachings of the invention. Accordingly, the above disclosure should be construed as limited only by the metes and bounds of the appended claims.