CN114852370A - Take-over functional atomic satellite and chemical molecular satellite with latch mechanism - Google Patents

Abstract

The invention discloses a pipe connection function atomic satellite and a chemical molecular satellite with a latch mechanism. The adapter function atomic satellite has a truncated octahedron geometric configuration, the outer surface of the adapter function atomic satellite comprises eight first areas and six second areas, each first area comprises a first main function area and a first auxiliary function area, the latching mechanism comprises a plurality of latching claws, the latching claws can be accommodated in the first auxiliary function areas, the latching claws can also rotate to the plane where the first main function areas are located, and the latching claws in the three first auxiliary function areas adjacent to the first main function areas jointly form the latching mechanism. Therefore, the latch mechanism can ensure the truncated octahedral geometric configuration of the take-over functional atomic satellite in a folded state, effectively improve the space utilization efficiency of the take-over functional atomic satellite in a carrying and storing state, and assist the take-over functional atomic satellite in butt joint and latch target satellite and satellite butt joint rings with different diameters.

Description

Takeover function atomic satellite and chemical molecular satellite with latch mechanism

technical field

The invention relates to the technical field of satellite overall design, in particular to an atomic satellite and a chemical molecular satellite with a latching mechanism that have a takeover function.

Background technique

Artificial satellites are spacecraft that follow the laws of orbital mechanics to fly around the earth or other planets for a long time and perform on-orbit missions. Artificial satellites can achieve a variety of functions including earth monitoring, astronomical observation, communication relay and scientific research. During long-term in-orbit missions, satellites can malfunction and terminate missions due to various threats and challenges within the space environment. In order to restore the mission execution capability of the faulty artificial satellite and prolong the on-orbit operation life of the artificial satellite, the on-orbit service spacecraft is required to capture, dock and repair the faulty artificial satellite. This process requires the formation of a stable combination of the target satellite and the in-orbit service spacecraft by means of a latching mechanism.

Artificial satellites generally need to be carried into orbit by a launch vehicle. During the flight of the launch vehicle, in order to stably connect the satellite to the launch vehicle, the satellite is often designed and installed with a star-arrow docking ring. The structure is also the preferred target on-star structure for in-orbit service spacecraft to capture, dock, lock to target satellites and form assemblies. The in-orbit service spacecraft needs to use the latch mechanism to achieve stable docking with the target satellite. Common latching mechanisms are based on motors, guide rails, screw transmission mechanisms, etc. During the connection process, the rotational motion of the motor can be converted into linear motion of the latching mechanism, so that the latching mechanism can be connected to the star-arrow docking ring. However, although this type of latch mechanism has high strength, its structure and volume are too large, and it will occupy a large space and weight in the control satellite. At the same time, this type of structure is usually an exposed fixed structure, which is only suitable for conventional configurations. In-orbit service spacecraft is not conducive to the flexible assembly and deformation of chemical and molecular satellites with modular and deformable characteristics.

SUMMARY OF THE INVENTION

In order to at least partially solve the above-mentioned technical problems in the prior art, the present invention provides an atomic satellite and a chemical molecular satellite with a latching mechanism that take over the function.

The technical scheme of the present invention is as follows:

An atomic satellite with a takeover function with a latching mechanism, characterized in that the latching mechanism can be connected to a star-arrow docking ring of a target star, the latching mechanism includes a plurality of latching claws, and the takeover function atomic satellite is constructed In a truncated octahedron configuration, the geometric outer surface of the functional atomic satellite includes eight first regions configured as regular hexagons and six second regions configured as squares, wherein the first regions include the first regions. A main functional area and a first secondary functional area, the first main functional area and the first secondary functional area are adjacent to each other through a first adjacent edge, and the latch claw is embedded in the first secondary functional area , and the latch pawl is rotatable with a first axis of rotation parallel to the first adjacent side and can be rotated to the plane where the first main functional area is located, and the first main functional area is adjacent to three the first secondary functional area, three of the first secondary functional areas are all provided with the latching claws, and the latching claws of the three first secondary functional areas together constitute the latching mechanism;

The latch pawl includes:

a main arm, the main arm includes a first support arm, a second support arm and a pivot part, the first support arm and the second support arm are parallel to each other and arranged side by side, the end of the first support arm and the end of the second support arm are fixedly connected by the pivot part, the main arm is connected to the takeover function atomic satellite via the pivot part, the first support arm and the second support An accommodation space is formed between the arms, and the first support arm and the second support arm are further provided with a first chute and a second chute respectively;

a hinge column, two ends of the hinge column are respectively pivotally connected to one end of the first support arm away from the pivot portion and an end of the second support arm away from the pivot portion; and

a sub-arm, the sub-arm can be accommodated in the accommodating space formed between the first support arm and the second support arm, one end of the sub-arm is connected to the hinge post, the sub-arm The other end away from the hinge post is provided with a hook that can connect and lock the star-arrow docking ring of the target star;

Wherein, the sub-arm can be rotated relative to the main arm around a second rotation axis parallel to the first rotation axis by means of the hinge column, and can be rotated to a position at an angle of 180° with the main arm , and when the sub-arm rotates to a position that forms an angle of 180° with the main arm, the sub-arm can move into the accommodating space along the first chute and the second chute to Adjust the docking radius.

Optionally, the first chute extends along the length direction of the first support arm, the second chute extends along the length direction of the second support arm, and the first chute and The second sliding grooves are arranged opposite to each other and face the accommodating space.

Optionally, the hinge column is provided with a connecting groove extending along the axial length direction of the hinge column, the connecting groove has an opening toward the radial direction of the hinge column, and the end of the sub-arm is provided with There is a connecting block, which can be completely accommodated in the connecting slot, wherein when the sub-arm is rotated to an angle of 180° with the main arm, the connecting block can The connecting groove moves into the first sliding groove and the second sliding groove.

Optionally, the hinge column has a first limit surface, an abutment surface and a second limit surface connected in sequence, the first limit surface and the second limit surface are parallel to each other and located in the abutting surface. On the same side of the junction surface, the first limiting surface, the abutting surface and the second limiting surface together at least partially form the connecting groove, wherein the width of the slot of the first chute is the same as the width of the The width of the slot of the second chute is the same, and the distance between the first limiting surface and the second limiting surface is the same as the width of the slot of the first chute.

Optionally, a first limit block is provided on the outer periphery of the end portion of the hinge column close to the first support arm, and a first limit slot is provided at the end of the first support arm away from the pivot portion, so The first limit block is rotatably received in the first limit groove, and the first limit groove can limit the first limit block so that the sub-arm is between the initial position and the end position Rotation, wherein, when the first limit block is in the initial position, the sub-arm is located in the accommodating space, and when the first limit block is in the end position, the sub-arm and The included angle between the main arms is 180°.

Optionally, a second limit block is provided on the outer periphery of the end portion of the hinge column close to the second support arm, and a second limit slot is provided at the end of the second support arm away from the pivot portion, so The second limit block is rotatably received in the second limit slot, and the second limit slot can limit the second limit block so that the sub-arm is in the initial position and the Rotate between end positions.

Optionally, the latching mechanism further includes a traction rope, and the hinge column is provided with a rope hole, the rope hole extends along the radial direction of the hinge column, and the axial direction of the rope hole is parallel to In the first limiting surface, one end of the traction rope is connected to the end of the sub-arm away from the connecting block through the rope hole, and the other end is connected to the drive motor in the atomic satellite that takes over the function.

Optionally, the hinge column is further provided with a pulley, the pulley is sleeved on the outer circumference of the hinge column, the radial length of the pulley is greater than the radial length of the hinge column, and the traction rope is The rope hole is also arranged around the outer circumference of the pulley before being connected to the driving motor.

According to a second aspect of the present invention, there is also provided a chemical molecular satellite, the chemical molecular satellite includes a plurality of modular atomic satellites, the atomic satellites are constructed in a truncated octahedral configuration, and the atomic satellites are Capable of being connected directly or indirectly via external means, the atomic satellite comprises a takeover function atomic satellite according to any one of the first aspects of the present invention.

The main advantages of the technical solution of the present invention are as follows:

The atomic satellite with the takeover function of the present invention is provided with a latching mechanism, which is capable of docking the star-arrow docking rings of target satellites of different diameters, and forms a stable rigid connection with the target satellite. At the same time, the latch mechanism can be folded and stored inside the takeover function atomic satellite, ensuring that the takeover function atomic satellite can maintain the truncated octahedral geometry, effectively improving the space utilization efficiency of the takeover function atomic satellite in the storage and carrying state, and at the same time Facilitates the assembly and connection between the current takeover function atomic satellites and other modular satellites.

Description of drawings

The accompanying drawings described herein are used to provide further understanding of the embodiments of the present invention, and constitute a part of the present invention. The schematic embodiments of the present invention and their descriptions are used to explain the present invention, and do not constitute an improper limitation of the present invention.

In the attached image:

1 is a schematic structural diagram of an atomic satellite that takes over a function according to an embodiment of the present invention;

FIG. 2 is a schematic structural diagram of another perspective of the atomic satellite that takes over the function shown in FIG. 1;

Fig. 3 is the structural schematic diagram of the latch claw in the takeover function atomic satellite shown in Fig. 1, wherein, the sub-arm is in the initial position;

FIG. 4 is a schematic structural diagram of the main arm in the latch claw shown in FIG. 3;

5 is a schematic structural diagram of a hinge column in the latch claw shown in FIG. 3;

FIG. 6 is a schematic structural diagram of the sub-arm in the latch claw shown in FIG. 3;

Fig. 7 is the structural schematic diagram when the sub-arm in the latch claw shown in Fig. 3 is unfolded;

FIG. 8 is a schematic structural diagram of the sub-arm in the latch claw shown in FIG. 3 after unfolding, wherein the sub-arm is at the end position;

Fig. 9 is the working schematic diagram of the latch claw shown in Fig. 3;

FIG. 10 is a working schematic diagram of the atomic satellite with the takeover function latching the star-arrow docking ring of the target satellite in this embodiment.

Description of reference numbers:

100: Take over function of atomic satellite 111: First area 112: Second area

113: Connection device 114: The first main functional area 115: The first secondary functional area

200: Latch pawl 210: Main arm 211: First support arm

212: Second support arm 213: Pivot part 214: First chute

215: Second chute 220: Hinge post 221: Connecting groove

222: The first limit block 223: The second limit block 224: Rope hole

225: Pulley 230: Sub-arm 231: Hook

232: Connection block 300: Star arrow docking ring.

Detailed ways

In order to make the objectives, technical solutions and advantages of the present invention clearer, the technical solutions of the present invention will be clearly and completely described below with reference to the specific embodiments of the present invention and the corresponding drawings. Obviously, the described embodiments are only some, but not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

The invention provides an atomic satellite and a chemical molecular satellite with a latching mechanism that take over the function. The takeover function atomic satellite can be interconnected with other external devices or target satellites by means of a latch mechanism, and the latch mechanism can be embedded in the takeover function atomic satellite, so that the takeover function atomic satellite can maintain the configuration of the truncated octahedron It is formed into a modular satellite, so that it can be easily connected with other modular satellites with similar structures to form a chemical molecular satellite in the final combination. It can be understood that chemical molecules are usually composed of chemical atoms and chemical bonds. Based on similar principles, in the present invention, chemical molecular satellites are composed of a variety of atomic satellites with different functions and chemical bond-like mechanical arms, which can be deformed. Reconfigurable multi-purpose spacecraft.

The technical solutions provided by the embodiments of the present invention are described in detail below with reference to the accompanying drawings.

Specifically, according to an embodiment of the present invention, a takeover function atomic satellite is provided, and the takeover function atomic satellite is a special kind of satellite designed to enable the chemical molecule satellite to realize the on-orbit service mission function and capture the target satellite. Atomic satellite.

As shown in FIGS. 1 to 10 , the takeover function atomic satellite 100 is constructed in the shape of a truncated octahedron. It is known to those skilled in the art that the truncated octahedral shape is formed by the structure of a regular octahedron by truncating its six vertices, therefore, the geometric outer surface of the truncated octahedral shape includes eight regular hexagonal surface, and six square surfaces. Thus, based on a plurality of outer surfaces with different directions and shapes, the geometric outer surface of the functional atomic satellite 100 in this embodiment includes eight first regions 111 configured as regular hexagons and six second regions 111 configured as squares area 112.

In order to be able to connect with other structures, at least one of the first area 111 and the second area 112 is also provided with a connecting device 113 , by means of the connecting device 113 , the atomic satellite 100 that takes over the function can be connected with other modular satellites or robotic arms connected to each other. Illustratively, the connecting device 113 may be a hermaphroditic docking structure disposed on the first region 111 and/or the second region 112 .

In this embodiment, as shown in FIG. 1 and FIG. 2 , the first area 111 includes a first main functional area 114 and a first secondary functional area 115 , and the first main functional area 114 and the first secondary functional area 115 pass through the first Adjacent edges are adjacent, the latching pawl 200 is embedded in the first secondary functional area 115, and the latching pawl 200 can rotate with a first rotation axis parallel to the first adjacent edge, and can rotate to the first main functional area The plane where 114 is located, or parallel to the plane where the first main functional area 114 is located.

Further, as shown in FIGS. 3 , 7 , 8 and 9 , the latch claw 200 includes a main arm 210 , a hinge post 220 and a sub-arm 230 , wherein the sub-arm 230 is rotatably connected to the main arm via the hinge post 220 210. The sub-arm 230 can rotate relative to the main arm 210 under the action of the hinge column 220 . The longitudinal direction moves toward the other end of the main arm 210 .

As shown in FIG. 4 , the main arm 210 includes a first support arm 211 , a second support arm 212 and a pivot portion 213 . The first support arm 211 and the second support arm 212 are parallel to each other and are arranged side by side. The end portion and the end portion of the second support arm 212 are fixedly connected by the pivot portion 213 to form a substantially U-shaped structure. An accommodation space is formed between the first support arm 211 and the second support arm 212 , and the first support arm 211 and the second support arm 212 are further provided with a first chute 214 and a second chute 215 respectively. In this embodiment, the first chute 214 is extended along the length direction of the first support arm 211 , the second chute 215 is correspondingly extended along the length direction of the second support arm 212 , and the first chute 214 and The second sliding grooves 215 are disposed opposite to each other and face the accommodating space. Preferably, the first chute 214 penetrates the first support arm 211 , and the second chute 215 penetrates the second support arm 212 .

As shown in FIGS. 3 and 5 , both ends of the hinge column 220 are pivotally connected to one end of the first support arm 211 away from the pivoting portion 213 and one end of the second support arm 212 away from the pivoting portion 213 , respectively. Also, the hinge post 220 can rotate relative to the main arm 210 about a second rotation axis parallel to the first rotation axis. The second rotation axis is perpendicular to the length direction of the main arm 210 .

As shown in FIGS. 3 and 6 , the sub-arm 230 can be accommodated in the accommodating space formed between the first support arm 211 and the second support arm 212 , one end of the sub-arm 230 is connected to the hinge post 220 , and the sub-arm 230 is away from the hinge The other end of the column 220 is provided with a hook 231 . Preferably, the hook 231 may be configured as a hook-like structure.

In this embodiment, the sub-arm 230 can rotate relative to the main arm 210 around the second rotation axis by means of the hinge 220 , so that the sub-arm 230 can leave the accommodating space, and the sub-arm 230 can be rotated to be between the main arm 210 The included angle is 180°. When the sub-arm 230 is rotated out of the accommodating space and the included angle between the main arms forms 180°, the sub-arm 230 can move into the accommodating space along the first sliding slot 214 and the second sliding slot 215 .

Further, as shown in FIGS. 1 and 2 , the first main functional area 114 is adjacent to three first secondary functional areas 115 , and each of the first secondary functional areas 115 is provided with a latch claw 200 . Therefore, when the takeover function atomic satellite 100 needs to be connected with an external device or a target satellite, as shown in FIG. 10 , the first main functional area 114 of the takeover function atomic satellite 100 can be made to face the star-arrow docking ring 300 of the connected target, After that, the three latching claws 200 on the atomic satellite 100 that take over the function are rotated to the plane where the first main functional area 114 is located, and at the same time, the sub-arm 230 is gradually rotated away from the accommodating space. After the sub-arm 230 is rotated to a position of 180° with the angle between the main arm 210, the sub-arm 230 moves longitudinally toward the accommodating space of the main arm 210, so that the hook 231 at the end of the sub-arm 230 can It is clamped to the outer periphery of the star-arrow docking ring 300, so that the sub-arm 230 can be connected with the star-arrow docking ring 300 in a manner similar to a three-jaw chuck, and finally enables the takeover function of the atomic satellite 100 to be effectively connected to external devices or target satellites .

Further, in order to ensure the normal movement of the latch mechanism on the atomic satellite 100 that takes over the function, in this embodiment, as shown in FIG. 221 , the connecting groove 221 has an opening facing the radial direction of the hinge column 220 . As shown in FIG. 6 , the end of the sub-arm 230 away from the hook 231 is provided with a connecting block 232 that fits with the connecting groove 221 . The connecting block 232 extends outward along the width direction of the sub-arm 230 . Partially accommodated in the connecting groove 221 . When the hinge column 220 rotates relative to the main arm 210 , since the connection block 232 is fitted into the connection slot 221 , the sub-arm 230 will follow the hinge column 220 to rotate relative to the main arm 210 . When the sub-arm 230 is rotated to a position of 180° with the included angle between the main arm 210 , the connecting block 232 can move toward the first chute 214 and the second chute 215 through the opening of the connecting slot 221 , so that the sub-arm The 230 can move into the accommodating space of the main arm 210, thereby ensuring that the hook 231 can be effectively connected to the star and arrow docking ring of the target satellite.

As an implementation, as shown in FIG. 5 , the hinge column 220 has a first limiting surface, an abutting surface, and a second limiting surface that are sequentially connected and formed into a substantially U-shape. The first limiting surface and the second limiting surface are The limiting surfaces are parallel to each other and are located on the same side of the abutting surface. The first limiting surface, the abutting surface and the second limiting surface together at least partially form the connecting groove 221 on the hinge column 220 . Correspondingly, the connecting block 232 has a first surface and a second surface disposed opposite to each other, the first surface and the second surface are parallel to each other, the first surface can abut against the first limiting surface, and the second surface can abut on the first limiting surface. Two limit surfaces. Therefore, when the connecting block 232 is installed in the connecting groove 221 , the sub-arm 230 can rotate synchronously with the hinge column 220 .

Preferably, the slot width of the first chute 214 is the same as the slot width of the second chute 215 , and the distance between the first limiting surface and the second limiting surface is the same as the slot width of the first chute 214 same. Therefore, when the sub-arm 230 rotates to a position of 180° with the included angle between the main arm 210 , the connecting block 232 can smoothly move from the connecting groove 221 to the first sliding groove 214 and the second sliding groove 215 .

More preferably, in order to effectively limit the rotation of the hinge column 220 relative to the main arm 210 , in this embodiment, a limit block is provided on the hinge column 220 to limit the rotation angle of the hinge column 220 relative to the main arm 210 .

Specifically, as shown in FIGS. 3 to 5 , a first limiting block 222 is provided on the outer periphery of the end portion of the hinge column 220 close to the first support arm 211 , and an arc-shaped end of the first support arm 211 away from the pivot portion 213 is provided The first limit slot, the first limit block 222 is rotatably accommodated in the first limit slot, and the first limit slot can limit the rotation of the first limit block 222, so that the sub-arm 230 can only be initially Rotate between position and end position. Wherein, when the first limiting block 222 is at the initial position, the sub-arm 230 is located in the accommodating space, and the angle between the sub-arm 230 and the main arm 210 is 0°; when the first limiting block 222 is at the end position When the sub-arm 230 completely leaves the accommodating space, the included angle between the sub-arm 230 and the main arm 210 is 180°.

More preferably, a second limit block 223 is correspondingly provided on the outer periphery of the end portion of the hinge column 220 close to the second support arm 212 , and an arc-shaped second limit slot is provided at the end of the second support arm 212 away from the pivot portion 213 . The second limiting block 223 is rotatably received in the second limiting slot, and the second limiting slot can limit the rotation of the second limiting block 223 by synchronizing the first limiting slot to limit the first limiting block 222 .

After the sub-arm 230 is rotated to a position where the angle between the sub-arm 230 and the main arm 210 is 180°, in order to allow the hook 231 to smoothly connect to the star-arrow docking ring of the target star, it is necessary to drive the sub-arm 230 to accommodate the main arm 210 To move in space, in this embodiment, the atomic satellite 100 that takes over the function is also provided with a drive motor and a traction rope to drive the sub-arm 230 to move.

Specifically, in this embodiment, as shown in FIG. 3 and FIG. 5 , the latch mechanism further includes a traction rope, and the hinge column 220 is provided with a rope hole 224 , and the rope hole 224 extends along the radial direction of the hinge column 220 , The axial direction of the rope hole 224 is perpendicular to the abutting surface, and the rope hole 224 is located between the plane where the first limiting surface is located and the plane where the second limiting surface is located. One end of the traction rope is connected to the end of the sub-arm 230 away from the connecting block 232 through the rope hole 224 , and the other end of the traction rope can be connected to the drive motor in the atomic satellite 100 that takes over the function. Therefore, as shown in FIG. 8 and FIG. 9 , when the sub-arm 230 rotates to a position where the angle between the sub-arm 230 and the main arm 210 is 180°, that is, after the sub-arm 230 is at the end position, the driving motor rotates, which can pull the traction The rope is retracted toward the takeover function atomic satellite 100 , so that the sub-arm 230 can move into the accommodation space of the main arm 210 .

Further, in order to allow the sub-arm 230 to rotate from the initial position to the end position, the sub-arm 230 can also be pulled to rotate relative to the main arm 210 by means of a traction rope.

Specifically, as shown in FIGS. 5 and 7 , the hinge column 220 in this embodiment is further provided with a pulley 225 , the pulley 225 is installed on the outer circumference of the hinge column 220 , and the radial length of the pulley 225 is greater than the radial length of the hinge column 220 , and the rotation center axis of the pulley 225 is collinear with the rotation axis of the hinge column 220 . Preferably, the pulley 225 is located between the first limiting block 222 and the second limiting block 223, which can be arranged in the accommodating space. During installation, one end of the traction rope is connected to one end of the sub-arm 230 away from the connecting block 232, and the other end is connected to the drive motor, wherein, before the traction rope leaves the rope hole and reaches the drive motor, it can pass through the The wiring hole is arranged around the outer circumference of the pulley 225 and then extends toward the pivot portion 213 , and is finally connected to the drive motor in the atomic satellite 100 that takes over the function.

Thus, when the sub-arm 230 is required to rotate from the initial position away from the accommodation space of the main arm 210 to the final position, the driving motor can be controlled to rotate, thereby pulling the traction rope. Since the traction rope is connected to the outer circumference of the pulley 225, the traction rope will be pulled The hinge column 220 rotates, so that the sub-arm 230 rotates synchronously and leaves the accommodating space.

In this embodiment, the atomic satellite that takes over the function is provided with three latching claws 200. In order to facilitate control and ensure that the three latching claws 200 can move synchronously, the traction ropes of the three latching claws 200 can all be connected to the same drive motor. Therefore, when the atomic satellite with the takeover function needs to be connected with the target satellite, the main arm 210 can be rotated to be parallel to the star-arrow docking ring of the target satellite by means of the pivot portion 213, and then the driving motor is controlled to rotate, so that the three latches The sub-arms 230 in the locking pawl 200 can rotate synchronously with respect to the respective main arms 210 and leave the accommodating space. When the sub-arms 230 are rotated to a position of 180° with the included angle between the main arms 210, the three latches The sub-arms 230 in the claw 200 can move synchronously to the accommodation spaces formed by the respective main arms 210, finally ensuring that the hooks 231 on the sub-arms 230 can be synchronously connected to the star-arrow docking ring of the target satellite, and the force is relatively balanced.

The main advantages of the technical solution in this embodiment are as follows:

The atomic satellite with the takeover function of this embodiment is provided with a latching mechanism, which can be adapted to the star-arrow docking ring of different diameters, and can achieve stable and rigid connection with the star-arrow docking ring of the target satellite. At the same time, the latch mechanism can be folded and stored inside the takeover function atomic satellite, ensuring the truncated octahedral geometry of the takeover function atomic satellite, effectively improving the space utilization of the takeover function atomic satellite in the storage and carrying state, and at the same time. May facilitate the assembly and connection between the current takeover function atomic satellites and other modular satellites.

According to another aspect of the present invention, a chemical molecular satellite is also provided, the chemical molecular satellite includes a plurality of modular atomic satellites. The hermaphroditic docking structures are directly connected or connected to each other via external means such as robotic arms, these atomic satellites include including the takeover function atomic satellites of the above-described embodiments.

It should be noted that, in this document, relational terms such as "first" and "second" etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply these There is no such actual relationship or sequence between entities or operations. Moreover, the terms "comprising", "comprising" or any other variation thereof are intended to encompass a non-exclusive inclusion such that a process, method, article or device that includes a list of elements includes not only those elements, but also includes not explicitly listed or other elements inherent to such a process, method, article or apparatus. In addition, "front", "rear", "left", "right", "upper" and "lower" in this document are all referred to the placement state shown in the accompanying drawings.

Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it can still be The technical solutions described in the foregoing embodiments are modified, or some technical features thereof are equivalently replaced; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims (9)

1. A nozzle functional atomic satellite having a latch mechanism capable of connecting a satellite-rocket docking ring of a target satellite, the latch mechanism comprising a plurality of latch claws, the nozzle functional atomic satellite being configured in a truncated octahedral configuration, a geometric outer surface of the nozzle functional atomic satellite comprising eight first regions configured as regular hexagons and six second regions configured as squares, wherein the first regions comprise a first main functional region and a first secondary functional region, the first main functional region and the first secondary functional region being adjoined via a first adjacent edge, the latch claws being embedded in the first secondary functional region, and the latch claws being rotatable about a first axis of rotation parallel to the first adjacent edge and rotatable into a plane in which the first main functional region lies, the first main functional region being adjoined by three of the first secondary functional regions, the three first secondary functional areas are provided with the latching claws, and the latching claws of the three first secondary functional areas jointly form the latching mechanism;

the latch claw includes:

the main arm comprises a first supporting arm, a second supporting arm and a pivoting part, the first supporting arm and the second supporting arm are parallel to each other and are arranged side by side, the end part of the first supporting arm and the end part of the second supporting arm are fixedly connected through the pivoting part, the main arm is connected to the adapter function atomic satellite through the pivoting part, an accommodating space is formed between the first supporting arm and the second supporting arm, and the first supporting arm and the second supporting arm are further provided with a first sliding groove and a second sliding groove respectively;

the two ends of the hinge column are respectively and pivotally connected to one end, away from the pivot part, of the first supporting arm and one end, away from the pivot part, of the second supporting arm; and

a sub arm capable of being accommodated in the accommodation space formed between the first support arm and the second support arm, one end of the sub arm being connected to the hinge post, and the other end of the sub arm away from the hinge post being provided with a hook capable of connecting and locking a satellite-rocket docking ring of a target satellite;

wherein the sub arm can rotate relative to the main arm about a second rotation axis parallel to the first rotation axis by means of the hinge post and can rotate to a position at an angle of 180 ° to the main arm, and after the sub arm rotates to a position at an angle of 180 ° to the main arm, the sub arm can move along the first sliding groove and the second sliding groove into the accommodation space to adjust the docking radius.

2. The takeover function atomic satellite with the latch mechanism of claim 1, wherein the first sliding groove is provided extending in a length direction of the first support arm, the second sliding groove is provided extending in a length direction of the second support arm, and the first sliding groove and the second sliding groove are provided opposite to each other and both face the accommodation space.

3. The takeover function atomic satellite having the latch mechanism according to any one of claims 1 to 2, wherein the hinge column is provided with a connecting groove extending in an axial length direction of the hinge column, the connecting groove having an opening toward a radial direction of the hinge column, an end of the sub-arm is provided with a connecting block, the connecting block being completely receivable in the connecting groove, wherein the connecting block is movable from the connecting groove into the first and second sliding grooves when the sub-arm is rotated to make an angle of 180 ° with the main arm.

4. A nozzle function atomic satellite with a latch mechanism according to claim 3, wherein the hinge post has a first limit surface, an abutting surface and a second limit surface connected in sequence, the first limit surface and the second limit surface are parallel to each other and located on the same side of the abutting surface, the first limit surface, the abutting surface and the second limit surface together at least partially form the connecting groove, wherein the width of the notch of the first sliding groove is the same as the width of the notch of the second sliding groove, and the distance between the first limit surface and the second limit surface is the same as the width of the notch of the first sliding groove.

5. The takeover function atomic satellite having the latch mechanism of claim 3, wherein the hinge post is provided with a first stopper at an outer periphery of an end portion thereof adjacent to the first support arm, an end of the first support arm remote from the pivot portion is provided with a first stopper groove in which the first stopper is rotatably received, and the first stopper groove is capable of restricting the first stopper so that the sub-arm is rotatable between an initial position and an end position, wherein when the first stopper is located at the initial position, the sub-arm is located in the receiving space, and when the first stopper is located at the end position, an included angle of 180 ° is formed between the sub-arm and the main arm.

6. A takeover function atomic satellite with a latch mechanism according to claim 5, wherein the hinge post is provided with a second stopper on an outer periphery of an end portion thereof near the second support arm, an end of the second support arm remote from the pivot portion is provided with a second stopper groove, the second stopper is rotatably received in the second stopper groove, and the second stopper groove can restrict the second stopper so that the sub-arm can rotate between the initial position and the final position.

7. The nozzle function atomic satellite with the latch mechanism according to claim 5, wherein the latch mechanism further comprises a pulling rope, and wherein the hinge post is provided with a rope hole extending in a radial direction of the hinge post, an axial direction of the rope hole is parallel to the first stopper surface, one end of the pulling rope passes through the rope hole to be connected to one end of the sub-arm away from the connecting block, and the other end of the pulling rope is connected to a driving motor in the nozzle function atomic satellite.

8. The takeover function atomic satellite having the latch mechanism of claim 7, wherein the hinge post is further provided with a pulley that is fitted around an outer periphery of the hinge post, the pulley having a radial length greater than that of the hinge post, and the traction rope is further provided around the outer periphery of the pulley before being connected to the driving motor from the rope hole.

9. A chemical molecular satellite comprising a plurality of modular atomic satellites configured in a truncated octahedral configuration, said atomic satellites being directly connectable or indirectly connectable via an external device, said atomic satellites comprising a takeover function atomic satellite according to any one of claims 1-8.

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