CN114852370A - Take-over functional atomic satellite and chemical molecular satellite with latch mechanism - Google Patents
Take-over functional atomic satellite and chemical molecular satellite with latch mechanism Download PDFInfo
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- CN114852370A CN114852370A CN202210414941.4A CN202210414941A CN114852370A CN 114852370 A CN114852370 A CN 114852370A CN 202210414941 A CN202210414941 A CN 202210414941A CN 114852370 A CN114852370 A CN 114852370A
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- 230000007246 mechanism Effects 0.000 title claims abstract description 40
- 210000000078 claw Anatomy 0.000 claims abstract description 32
- 238000003032 molecular docking Methods 0.000 claims description 20
- 230000004308 accommodation Effects 0.000 claims description 14
- 230000004323 axial length Effects 0.000 claims description 3
- 210000001503 joint Anatomy 0.000 abstract description 7
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
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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
Technical Field
The invention relates to the technical field of satellite overall design, in particular to a pipe connection function atomic satellite and a chemical molecular satellite with a latch mechanism.
Background
Satellites are spacecraft that perform in orbit tasks, flying around the earth or other planets for long periods of time, following the laws of orbital mechanics. Satellites can perform a variety of functions including earth monitoring, astronomical observations, communication relays, and scientific research. During long-term performance of in-orbit tasks, satellites can fail and terminate tasks due to various threats and challenges within the spatial environment. In order to recover the task execution capacity of the failed artificial satellite and prolong the in-orbit operation life of the artificial satellite, the in-orbit service spacecraft is required to capture, butt joint and repair the failed artificial satellite. This process requires the formation of a stable combination of the target satellite and the in-orbit service spacecraft with the aid of the latching mechanism.
The artificial satellite is carried into orbit by a carrier rocket, and in order to stably connect the satellite to the carrier rocket during the flight of the carrier rocket, the satellite is usually designed and provided with a satellite-rocket butt joint ring. The structure is also the preferred target satellite-borne structure for the in-orbit service spacecraft to capture, dock, lock and form a combination. The on-orbit service spacecraft needs to realize stable docking with a target satellite by means of a latching mechanism. Common latch mechanisms are all formed based on motors, guide rails, screw transmission mechanisms and the like, and in the connection process, the rotary motion of the motors can be converted into the linear motion of the latch mechanisms, so that the latch mechanisms can be connected to a satellite-rocket docking ring. However, although the latch mechanism is strong, its structure and volume are too large to occupy large space and weight in the control satellite, and at the same time, the structure is usually an exposed fixed structure, which is only suitable for the on-orbit service spacecraft with the conventional configuration, and is not favorable for flexible assembly and deformation among chemical molecular satellites with modularization and deformable characteristics.
Disclosure of Invention
To at least partially solve the technical problems of the prior art as described above, the present invention provides a take-over function atomic satellite and a chemical molecular satellite having a latch mechanism.
The technical scheme of the invention is as follows:
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 is rotatable with respect to the main arm about a second rotation axis parallel to the first rotation axis by means of the hinge post and to a position at an angle of 180 ° to the main arm, and is movable into the accommodation space along the first and second chutes to adjust the docking radius after being rotated to the position at an angle of 180 ° to the main arm.
Optionally, the first sliding groove extends along a length direction of the first support arm, the second sliding groove extends along a length direction of the second support arm, and the first sliding groove and the second sliding groove are disposed opposite to each other and both face the accommodating space.
Optionally, the hinge post is provided with a connecting groove extending along an axial length direction of the hinge post, the connecting groove having an opening facing a radial direction of the hinge post, and 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 an angle of 180 ° with respect to the main arm.
Optionally, the hinge post has first spacing face, butt face and the spacing face of second that connects gradually, first spacing face with the spacing face of second is parallel to each other and is located the same one side of butt face, first spacing face, butt face with the spacing face of second forms jointly at least partially the spread groove, wherein, the notch width of first spout with the notch width of second spout is the same, simultaneously first spacing face with distance between the spacing face of second with the notch width of first spout is the same.
Optionally, a first limit block is disposed on an outer periphery of an end portion of the hinge column close to the first support arm, a first limit groove is disposed on an end of the first support arm far from the pivot portion, the first limit block is rotatably received in the first limit groove, and the first limit block can limit the first limit block to enable the sub-arm to rotate between an initial position and a final position, wherein when the first limit block is located at the initial position, the sub-arm is located in the receiving space, and when the first limit block is located at the final position, an included angle between the sub-arm and the main arm is 180 °.
Optionally, a second limit block is disposed on an outer periphery of an end portion of the hinge post close to the second support arm, a second limit groove is disposed at an end of the second support arm far from the pivot portion, the second limit block is rotatably received in the second limit groove, and the second limit groove can limit the second limit block so that the sub-arm can rotate between the initial position and the final position.
Optionally, the latch mechanism further comprises a pulling rope, the hinge pillar is provided with a rope hole, the rope hole extends along the radial direction of the hinge pillar, the axial direction of the rope hole is parallel to the first limiting surface, one end of the pulling rope penetrates through the rope hole to be connected to one end, away from the connecting block, of the sub-arm, and the other end of the pulling rope is connected to a driving motor in the take-over function atomic satellite.
Optionally, the hinge post is further provided with a pulley, the pulley is sleeved on the periphery of the hinge post, the radial length of the pulley is greater than that of the hinge post, and the traction rope is further arranged around the periphery of the pulley before being connected to the driving motor from the rope hole.
According to a second aspect of the present invention, there is also provided a chemical molecular satellite comprising a plurality of modular atomic satellites constructed in a truncated octahedral configuration, the atomic satellites being connectable directly to each other or indirectly via external means, the atomic satellites comprising a takeover-function atomic satellite according to any one of the first aspects of the present invention.
The technical scheme of the invention has the following main advantages:
the adapter function atomic satellite is provided with a latch mechanism which can be used for butting satellite and rocket butting rings of target satellites with different diameters and is in stable rigid connection with the target satellites. Meanwhile, the latch mechanism can be folded and stored in the receiving pipe function atomic satellite, so that the receiving pipe function atomic satellite can keep a truncated-angle octahedron geometric configuration, the space utilization efficiency of the receiving pipe function atomic satellite in a storage and carrying state is effectively improved, and meanwhile, the assembly and connection between the current receiving pipe function atomic satellite and other modularized satellites are facilitated.
Drawings
The accompanying drawings, which are included to provide a further understanding of embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
In the drawings:
FIG. 1 is a schematic diagram of a structure of a take-over function atomic satellite according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of the atomic satellite shown in FIG. 1 for taking over a further view;
FIG. 3 is a schematic diagram of the latching claw in the take-over function atomic satellite of FIG. 1, wherein the sub-arm is in an initial position;
fig. 4 is a schematic view of the structure of a main arm in the latching claw shown in fig. 3;
FIG. 5 is a schematic view of the hinge post in the latch claw of FIG. 3;
FIG. 6 is a schematic view of a sub-arm of the latching claw of FIG. 3;
FIG. 7 is a schematic view of the latch claw of FIG. 3 with the sub-arms extended;
FIG. 8 is a schematic view of the latch claw of FIG. 3 with the sub-arms in an expanded configuration, wherein the sub-arms are in a terminal position;
FIG. 9 is an operational schematic view of the latching pawl of FIG. 3;
fig. 10 is a schematic diagram illustrating the operation of the take-over function atomic satellite in the present embodiment when the satellite and arrow docking rings of the target satellite are latched.
Description of reference numerals:
100: take over the functional atomic satellite 111: first region 112: second region
113: the connection device 114: first main functional region 115: first sub-function area
200: latching pawl 210: main arm 211: first support arm
212: second support arm 213: the pivot portion 214: first chute
215: the second chute 220: hinge post 221: connecting groove
222: first stopper 223: the second stopper 224: rope hole
225: pulley 230: the sub-arm 231: clamp hook
232: connecting block 300: satellite and rocket butt joint ring.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, 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 accompanying drawings. It is to be understood that the described embodiments are merely a few embodiments of the invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a take-over function atomic satellite and a chemical molecular satellite with a latch mechanism. The adapter function atomic satellite can be connected with other external devices or target satellites through the latch mechanism, and the latch mechanism can be embedded in the adapter function atomic satellite, so that the adapter function atomic satellite can be formed into a modular satellite in a truncated octahedron configuration, and therefore the adapter function atomic satellite can be conveniently connected with other modular satellites with similar structures to be finally combined into a chemical molecular satellite. It is understood that chemical molecules are generally formed by combining chemical atoms and chemical bonds, and based on similar principles, in the invention, a chemical molecular satellite is a deformable and reconfigurable multifunctional spacecraft which is composed of a plurality of atomic satellites with different functions and chemical bond-like mechanical arms.
The technical scheme provided by the embodiment of the invention is described in detail below with reference to the accompanying drawings.
Specifically, in one embodiment according to the invention, a take-over function atomic satellite is provided, which is a special atomic satellite designed for enabling a chemical molecular satellite to realize the on-orbit service mission function and capturing a target satellite.
As shown in fig. 1 to 10, the adapter function atomic satellite 100 is constructed in a truncated octahedral shape. As known to those skilled in the art, a truncated octahedral shape is formed by a structure of a regular octahedron by cutting its six vertices, and therefore, the geometric outer surface of the truncated octahedral shape includes eight regular hexagonal surfaces, and six square surfaces. Thus, the geometric outer surface of the takeover function atomic satellite 100 in the present embodiment includes eight first regions 111 configured as regular hexagons and six second regions 112 configured as squares, based on a plurality of outer surfaces of different directions and shapes.
In order to be able to interconnect with other structures, at least one of the first region 111 and the second region 112 is further provided with a connecting means 113, by means of which connecting means 113 the takeover function atomic satellite 100 can be interconnected with other modular satellites or robotic arms. Illustratively, the connecting device 113 can be a hermaphroditic docking structure disposed on the first region 111 and/or the second region 112.
In the present embodiment, as shown in fig. 1 and 2, the first region 111 includes a first main functional region 114 and a first sub-functional region 115, the first main functional region 114 and the first sub-functional region 115 are adjacent via a first adjacent edge, the latch claw 200 is embedded in the first sub-functional region 115, and the latch claw 200 is rotatable about a first rotation axis parallel to the first adjacent edge and rotatable to a plane in which the first main functional region 114 is located or a plane in which the first main functional region 114 is located.
Further, as shown in fig. 3, 7, 8 and 9, the latching 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 210 via the hinge post 220. The sub-arm 230 can rotate relative to the main arm 210 under the action of the hinge post 220, and after the sub-arm 230 rotates to a position forming an angle of 180 ° with the main arm 210, the sub-arm 230 can also move towards the other end of the main arm 210 along the length direction 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 213, the first support arm 211 and the second support arm 212 are parallel to each other and are arranged side by side, and an end of the first support arm 211 and an end of the second support arm 212 are fixedly connected by the pivot 213 to form a substantially U-shaped structure. An accommodation space is formed between the first and second support arms 211 and 212, and the first and second support arms 211 and 212 are further provided with first and second slide grooves 214 and 215, respectively. In the present embodiment, the first sliding groove 214 extends along the longitudinal direction of the first support arm 211, the second sliding groove 215 correspondingly extends along the longitudinal direction of the second support arm 212, and the first sliding groove 214 and the second sliding groove 215 are disposed opposite to each other and both face the accommodating space. Preferably, the first sliding slot 214 extends through the first support arm 211 and the second sliding slot 215 extends through the second support arm 212.
As shown in fig. 3 and 5, both ends of the hinge post 220 are pivotably connected to an end of the first support arm 211 remote from the pivot portion 213 and an end of the second support arm 212 remote from the pivot portion 213, respectively. Also, the hinge post 220 can rotate with respect 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 fig. 3 and 6, the sub-arm 230 can be accommodated in an accommodation space formed between the first and second support arms 211 and 212, one end of the sub-arm 230 is connected to the hinge post 220, and the other end of the sub-arm 230, which is away from the hinge post 220, is provided with a hook 231. Preferably, the catching hook 231 may be configured like a hook structure.
In the present embodiment, the sub-arm 230 can be rotated about the second rotation axis with respect to the main arm 210 by means of the hinge post 220 so that the sub-arm 230 can be separated from the accommodation space, and the sub-arm 230 can be rotated to a position forming an angle of 180 ° with the main arm 210. When the sub-arm 230 is rotated out of the accommodation space and forms an angle of 180 ° between the main arms, the sub-arm 230 can move into the accommodation space along the first and second sliding grooves 214 and 215.
Further, as shown in fig. 1 and 2, the first main functional region 114 is adjoined by three first sub functional regions 115, and each of the first sub functional regions 115 is provided with a latch claw 200. Thus, when the takeover functional atomic satellite 100 needs to be connected to an external device or a target satellite, as shown in fig. 10, the first main functional region 114 of the takeover functional atomic satellite 100 can be made to face the satellite-rocket docking ring 300 of the connected target, and then the three latching claws 200 on the takeover functional atomic satellite 100 are all rotated to the plane where the first main functional region 114 is located, while the sub-arm 230 is gradually rotated away from the accommodating space. After the sub-arm 230 rotates to a position forming an angle of 180 ° with 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 be clamped to the outer circumference of the satellite-rocket docking ring 300, so that the sub-arm 230 can be connected to the satellite-rocket docking ring 300 in a manner similar to a three-jaw chuck, and finally, the takeover functional atomic satellite 100 can be effectively connected to an external device or a target satellite.
Further, in order to ensure that the latch mechanism on the takeover function atomic satellite 100 can be moved normally, in the present embodiment, as shown in fig. 5, the hinge post 220 is provided with a connection groove 221 extending in the axial length direction of the hinge post 220, the connection groove 221 having an opening facing the radial direction of the hinge post 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 matched with the connecting groove 221, the connecting block 232 extends outward along the width direction of the sub-arm 230, and the connecting block 232 can be at least partially accommodated in the connecting groove 221. When the hinge post 220 is rotated with respect to the main arm 210, the sub-arm 230 will follow the rotation of the hinge post 220 with respect to the main arm 210 since the connection block 232 is fitted into the connection groove 221. After the sub-arm 230 rotates to a position forming an angle of 180 ° with the main arm 210, the connecting block 232 can move towards the first sliding slot 214 and the second sliding slot 215 via the opening of the connecting slot 221, so that the sub-arm 230 can move towards the accommodating space of the main arm 210, thereby ensuring that the hook 231 can be effectively connected to the satellite-rocket docking ring of the target satellite.
As one implementation manner, as shown in fig. 5, the hinge post 220 has a first limiting surface, an abutting surface and a second limiting surface which are connected in sequence and formed into a substantially U shape, the first limiting surface and the second limiting surface are parallel to each other and located on the same side of the abutting surface, and the first limiting surface, the abutting surface and the second limiting surface together at least partially form a connection groove 221 on the hinge post 220. Correspondingly, connecting block 232 has relative first face and the second face that sets up, and first face and second face are parallel to each other, and first face can butt joint to first spacing face, and the second face can butt joint to the spacing face of second. Thus, when the connection block 232 is fitted into the connection groove 221, the sub-arm 230 can be synchronously rotated following the hinge post 220.
Preferably, the width of the notch of the first sliding groove 214 is the same as the width of the notch of the second sliding groove 215, and the distance between the first and second stopper surfaces is the same as the width of the notch of the first sliding groove 214. Thus, when the sub-arm 230 is rotated to a position at an angle of 180 ° to the main arm 210, the connecting block 232 can smoothly move from the connecting groove 221 to the first and second sliding grooves 214 and 215.
More preferably, in order to effectively limit the rotation of the hinge post 220 with respect to the main arm 210, in the present embodiment, a stopper is provided on the hinge post 220 to limit the rotation angle thereof with respect to the main arm 210.
Specifically, as shown in fig. 3 to 5, the hinge post 220 is provided with a first stopper 222 at an end periphery thereof near the first support arm 211, an arc-shaped first stopper groove is provided at an end of the first support arm 211 far from the pivot part 213, the first stopper 222 is rotatably received in the first stopper groove, and the first stopper groove can restrict rotation of the first stopper 222, so that the sub-arm 230 can only rotate between the initial position and the final position. When the first stopper 222 is located at the initial position, the sub-arm 230 is located in the accommodating space, and an included angle between the sub-arm 230 and the main arm 210 is 0 degree; when the first stopper 222 is at the end position, the sub-arm 230 is completely separated from the accommodation space, and the angle between the sub-arm 230 and the main arm 210 is 180 °.
More preferably, the hinge post 220 is correspondingly provided with a second stopper 223 at the periphery of the end portion close to the second support arm 212, an arc-shaped second stopper groove is provided at the end of the second support arm 212 far from the pivot portion 213, the second stopper 223 is rotatably accommodated in the second stopper groove, and the second stopper groove can limit the first stopper 222 to limit the rotation of the second stopper 223 synchronously with the first stopper groove.
After the sub-arm 230 rotates to a position forming an angle of 180 ° with the main arm 210, in order to enable the hook 231 to smoothly connect with the satellite-rocket docking ring of the target satellite, the sub-arm 230 needs to be driven to move into the accommodating space of the main arm 210.
Specifically, in the present embodiment, as shown in fig. 3 and 5, the latch mechanism further includes a pulling rope, and the hinge post 220 is provided with a rope hole 224, the rope hole 224 extends in a radial direction of the hinge post 220, an axial direction of the rope hole 224 is perpendicular to the abutment surface, and the rope hole 224 is located between a plane where the first stopper surface is located and a plane where the second stopper surface is located. One end of the pulling rope is connected to one end of the sub-arm 230 away from the connection block 232 through the rope hole 224, and the other end of the pulling rope can be connected to the driving motor in the take-over function atomic satellite 100. Thus, as shown in fig. 8 and 9, when the sub-arm 230 is rotated to a position 180 ° away from the main arm 210, that is, when the sub-arm 230 is at the end position, the driving motor is rotated, and the pulling rope is pulled to be retracted toward the nozzle 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 final position, the sub-arm 230 may be pulled to rotate relative to the main arm 210 by means of a pulling rope.
Specifically, as shown in fig. 5 and 7, the hinge post 220 in the present embodiment is further provided with a pulley 225, the pulley 225 is installed at the outer circumference of the hinge post 220, the radial length of the pulley 225 is greater than that of the hinge post 220, and the rotational center axis of the pulley 225 is collinear with the rotational axis of the hinge post 220. Preferably, the pulley 225 is located between the first stopper 222 and the second stopper 223, which may be disposed in the receiving space. When installed, one end of the pulling rope is connected to one end of the sub-arm 230 away from the connection block 232, and the other end thereof is connected to the driving motor, wherein the pulling rope may extend toward the pivot 213 after being wound around the outer circumference of the pulley 225 via a wire hole provided in the hinge post 220 before exiting the rope hole to the driving motor, and finally connected to the driving motor in the takeover function atomic satellite 100.
Thus, when it is desired to rotate the sub-arm 230 from the initial position to the final position out of the accommodation space of the main arm 210, the driving motor may be controlled to rotate, thereby pulling the pulling rope, which, due to the connection of the pulling rope to the outer circumference of the pulley 225, will pull the hinge post 220 to rotate, thereby causing the sub-arm 230 to rotate synchronously out of the accommodation space.
In the present embodiment, the takeover function atomic satellite is provided with three latching claws 200, and in order to facilitate control while ensuring that the three latching claws 200 can move synchronously, the pulling ropes of the three latching claws 200 may all be connected to the same driving motor. Therefore, when the adapter function atomic satellite needs to be connected with a target satellite, the main arm 210 can be rotated to be parallel to the satellite-rocket docking ring of the target satellite by the pivot 213, and then the driving motor is controlled to rotate, so that the sub-arms 230 in the three latching claws 200 can synchronously rotate relative to the respective main arms 210 and leave the accommodating space, and after the sub-arms 230 rotate to a position forming an included angle of 180 degrees with the main arms 210, the sub-arms 230 in the three latching claws 200 can synchronously move towards the accommodating space formed by the respective main arms 210, and finally, the hooks 231 on the sub-arms 230 can be synchronously connected to the satellite-rocket docking ring of the target satellite, and the stress is relatively balanced.
The technical scheme in the embodiment has the following main advantages:
the adapter function atomic satellite of the embodiment is provided with the latch mechanism which can be adapted to satellite and rocket docking rings with different diameters, and can realize stable rigid connection with the satellite and rocket docking ring of a target satellite. Meanwhile, the latch mechanism can be folded and stored in the receiving pipe function atomic satellite, the truncated octahedron geometric configuration of the receiving pipe function atomic satellite is ensured, the space utilization rate of the receiving pipe function atomic satellite in the storage and carrying states is effectively improved, and meanwhile, the latch mechanism is also beneficial to assembly and connection between the current receiving pipe function atomic satellite and other modularized satellites.
According to another aspect of the present invention, there is also provided a chemical molecular satellite comprising a plurality of modular atomic satellites each constructed in a truncated octahedral configuration, the atomic satellites being connectable to each other via a hermaphroditic docking structure directly or via an external device such as a robotic arm, the atomic satellites including the takeover function atomic satellite according to the above embodiment.
It is noted that, in this document, relational terms such as "first" and "second," and the like, may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. In addition, "front", "rear", "left", "right", "upper" and "lower" in this document are referred to the placement states shown in the drawings.
Finally, it should be noted that: the above examples are only for illustrating the technical solutions of the present invention, and not for limiting the same; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding 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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210414941.4A CN114852370B (en) | 2022-04-20 | 2022-04-20 | Atomic satellite and chemical molecular satellite with latch mechanism for connecting pipe function |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210414941.4A CN114852370B (en) | 2022-04-20 | 2022-04-20 | Atomic satellite and chemical molecular satellite with latch mechanism for connecting pipe function |
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| CN114852370A true CN114852370A (en) | 2022-08-05 |
| CN114852370B CN114852370B (en) | 2024-07-26 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4646994A (en) * | 1985-05-17 | 1987-03-03 | Rca Corporation | Spacecraft support and separation system |
| US5125601A (en) * | 1991-12-26 | 1992-06-30 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Payload retention device |
| US20070250267A1 (en) * | 2006-04-25 | 2007-10-25 | Northrop Grumman Corporation | Delta-V-free satellite cloud cluster flying |
| CN111361768A (en) * | 2020-03-23 | 2020-07-03 | 上海宇航系统工程研究所 | Star arrow butts ring latch mechanism |
| CN113895662A (en) * | 2021-10-11 | 2022-01-07 | 北京空间飞行器总体设计部 | Invalid satellite capturing and docking device and method |
-
2022
- 2022-04-20 CN CN202210414941.4A patent/CN114852370B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4646994A (en) * | 1985-05-17 | 1987-03-03 | Rca Corporation | Spacecraft support and separation system |
| US5125601A (en) * | 1991-12-26 | 1992-06-30 | The United States Of America As Represented By The Administrator, National Aeronautics And Space Administration | Payload retention device |
| US20070250267A1 (en) * | 2006-04-25 | 2007-10-25 | Northrop Grumman Corporation | Delta-V-free satellite cloud cluster flying |
| CN111361768A (en) * | 2020-03-23 | 2020-07-03 | 上海宇航系统工程研究所 | Star arrow butts ring latch mechanism |
| CN113895662A (en) * | 2021-10-11 | 2022-01-07 | 北京空间飞行器总体设计部 | Invalid satellite capturing and docking device and method |
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| Publication number | Publication date |
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| CN114852370B (en) | 2024-07-26 |
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