A claw-type on-orbit detachable pressing and releasing mechanism

Abstract

The present invention relates to a claw-type on-orbit detachable pressing and releasing mechanism, belonging to the field of pressing and releasing of spacecraft mechanisms; it includes a non-loosening screw, a first slider, a pressing cap, a claw, a first bracket, a second slider, a compression spring, a spring sleeve, a pressing head sleeve, a locknut, a loading nut, a load-bearing bowl, a tension spring, a long screw, a second bracket and a workpiece to be pressed; the working process of the pressing and releasing mechanism includes three stages: long screw release, claw clamping, and on-orbit disassembly of the pressing and releasing mechanism; finally, the astronaut takes away the whole pressing and releasing mechanism and places it in a storage bag to complete the on-orbit disassembly work of the pressing and releasing mechanism; the present invention can achieve on-orbit disassembly by astronauts. This solution uses a claw-type structure to clamp the internal parts to achieve disassembly and separation without scattering or generating space debris.

Description

Technical Field

[0001] The present invention belongs to the field of clamping and releasing mechanisms of spacecraft mechanisms, and relates to a claw-type on-orbit detachable clamping and releasing mechanism. Background Art

[0002] With the development of large spacecraft missions in China, large-area solar wings have been adopted to meet the requirements of high power on orbit for large spacecraft. The clamping and releasing mechanism is one of the core components of the large-area solar wings of large spacecraft, ensuring reliable fixation of the solar wings after multiple repeated deployment and retraction on orbit. To meet the requirements of long-term on-orbit operation of large spacecraft and multiple deployment and retraction of solar wings on orbit, the clamping and releasing mechanism needs to have a high functional reliability and can be disassembled and assembled manually by astronauts on orbit when necessary. However, when astronauts disassemble on orbit at present, the internal parts will inevitably not scatter due to separation and generate space debris, and there is currently no solution to solve the above technical problems. Summary of the Invention

[0003] The technical problem solved by the present invention is: overcoming the deficiencies of the prior art, a claw-type on-orbit detachable clamping and releasing mechanism is proposed, which can realize on-orbit disassembly by astronauts. This solution uses a claw structure to hold the internal parts to achieve disassembly and separation without scattering and without generating space debris.

[0004] The solution for the present invention to solve the technology is:

[0005] A claw-type on-orbit detachable clamping and releasing mechanism, including a non-loosening screw, a first slider, a compression cap, a claw, a first bracket, a second slider, a compression spring, a spring sleeve, a compression head sleeve, a locknut, a loading nut, a load-bearing bowl, a tension spring, a long screw, a second bracket, and a pressed part;

[0006] In the initial state, one end of the long screw is connected to the loading nut through threads, and double-nut anti-loosening is achieved using the locknut; the load-bearing bowl, the second slider, and the pressed part are pressed together through the loading nut; the compression spring is pressed by the second slider on the spring sleeve, the spring sleeve is installed on the compression head sleeve, and the compression head sleeve is installed on the pressed part through structural adhesive;

[0007] The compression cap is installed on the pressed part through 2 non-loosening screws; the second slider, the compression spring, the spring sleeve, the locknut, the loading nut, the load-bearing bowl, and the long screw are all restricted in the compression head sleeve by the compression cap;

[0008] The first slider is installed on the top cylindrical surface of the pressing cap. Four first brackets are installed on the large cylindrical end face of the pressing cap. The first brackets are connected to the rotating shafts of the grippers through the round holes on them. One end of the gripper is installed in the long strip-shaped round hole on the trapezoidal bracket of the first slider through a cylindrical surface. A non-loosening screw is installed at the head of the first slider. The non-loosening screw is screwed into and passes through the first slider through threads. The first slider is connected to four tension springs through four triangular brackets on it. The other ends of the tension springs are fixed on the second brackets, and the second brackets are welded on the flange surface of the pressing cap.

[0009] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the pressing and releasing mechanism further includes an explosive nut assembly. The other end of the long screw is screwed into the explosive nut assembly.

[0010] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the pressing and releasing mechanism further includes a buffer pad. The buffer pad is installed at the head of the pressing cap to reduce the impact generated when the long screw is ejected by the compression spring and hits the pressing cap after the explosive nut assembly detonates.

[0011] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the non-loosening screw at the head of the first slider is screwed into and passes through the head thickness of the first slider through threads, and the end of the screw abuts against the upper surface of the head of the pressing cap.

[0012] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the working process of the pressing and releasing mechanism includes three stages: long screw release, gripper clamping, and on-orbit disassembly of the pressing and releasing mechanism.

[0013] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the specific process of long screw release is as follows:

[0014] After entering the orbit, the explosive nut assembly detonates, and the thread constraint between the long screw and the explosive nut assembly is released. The second slider, the locknut, the loading nut, the load-bearing bowl, and the long screw bounce upward under the action of the compression spring. The long screw stops moving after hitting the buffer pad. The release action of the long screw is completed.

[0015] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the specific process of gripper clamping is as follows:

[0016] The astronaut holds an electric tool to tighten the non-loosening screw, and the length of the screw inserted into the first slider becomes longer; the first slider moves upward along the small cylindrical surface at the end of the pressing cap. The first slider drives the cylindrical surface of the gripper to move outward through 4 trapezoidal brackets, forcing the gripper to rotate around the rotation axis between the gripper and the first bracket. As a result, the other end of the gripper moves towards the inside of the pressing cap until the cylindrical surface of the gripper moves to the outermost end of the long rectangular hole of the trapezoidal bracket of the first slider of the bracket. At this time, the other end of the gripper passes through the spring and moves into the pressing cap, restricting the second slider, compression spring, locknut, loading nut, load-bearing bowl, and long screw within the pressing cap, completing the gripper clamping action.

[0017] In the above-mentioned gripper-type on-orbit detachable pressing and releasing mechanism, the specific process of on-orbit disassembly of the pressing and releasing mechanism is as follows:

[0018] After the gripper is tightened, the astronaut holds an electric tool to sequentially remove the two non-loosening screws between the pressing cap and the pressed part, releasing the constraint between the pressing cap and the pressed part; the astronaut takes the entire pressing and releasing mechanism and places it in the storage bag, completing the on-orbit disassembly of the pressing and releasing mechanism.

[0019] The beneficial effects of the present invention compared with the prior art are as follows:

[0020] (1) After the present invention is in orbit, by detonating the explosive nut assembly, the thread constraint between the long screw and the explosive nut assembly is released; the second slider, locknut, loading nut, load-bearing bowl, and long screw bounce upward under the action of the compression spring and stop moving after hitting the buffer pad; the release action of the long screw is completed, providing a stable and highly reliable release of the long screw for the astronaut to manually perform disassembly and assembly on orbit.

[0021] (2) In the present invention, by the astronaut tightening the non-loosening screw, the other end of the gripper moves towards the inside of the pressing cap until the cylindrical surface of the gripper moves to the outermost end of the long rectangular hole of the trapezoidal bracket of the first slider of the bracket; at this time, the other end of the gripper passes through the spring and moves into the pressing cap, restricting the second slider, compression spring, locknut, loading nut, load-bearing bowl, and long screw within the pressing cap, completing the gripper clamping action and pre-clamping the internal parts in advance, solving the problem that the parts do not scatter and generate space debris due to disassembly and separation.

[0022] (3) In the present invention, the astronaut holds an electric tool to sequentially remove the two non-loosening screws between the pressing cap and the pressed part, releasing the constraint between the pressing cap and the pressed part; the astronaut takes the entire pressing and releasing mechanism and places it in the storage bag, completing the on-orbit disassembly of the pressing and releasing mechanism. Description of the Drawings

[0023] Figure 1 It is the top view of the pressing and releasing mechanism of the present invention;

[0024] Figure 2 Front cross-sectional view before the clamping rod of the clamping and releasing mechanism of the present invention is released and before the gripper clamps.

[0025] Figure 3 Rear cross-sectional view after the clamping rod of the clamping and releasing mechanism of the present invention is released and after the gripper clamps.

[0026] Figure 4 Rear cross-sectional view after the clamping rod of the clamping and releasing mechanism of the present invention is released and after the gripper clamps.

[0027] Figure 5 Rear cross-sectional view after the clamping rod of the clamping and releasing mechanism of the present invention is released and after the gripper clamps.

[0028] Figure 6 Schematic diagram of the whole process of on-orbit disassembly of the clamping and releasing mechanism of the present invention. Detailed implementation manners

[0029] The present invention will be further described below in conjunction with embodiments.

[0030] The present invention provides a gripper-type on-orbit detachable clamping and releasing mechanism, which can realize on-orbit disassembly by astronauts. This solution uses a claw-type structure to hold the internal parts to achieve disassembly and separation without scattering and generating space debris.

[0031] The gripper-type on-orbit detachable clamping and releasing mechanism, as Figures 1 to 5 shown, specifically includes a non-loosening screw 1, a first slider 2, a compression cap 4, a gripper 5, a first bracket 6, a second slider 7, a compression spring 8, a spring sleeve 9, a compression head sleeve 10, a locknut 11, a loading nut 12, a load-bearing bowl 13, a tension spring 14, a long screw 15, a second bracket 16, and a workpiece to be pressed 17;

[0032] In the initial state, one end of the long screw 15 is connected to the loading nut 12 by threads, and double-nut locking is achieved using the locknut 11; the load-bearing bowl 13, the second slider 7, and the workpiece to be pressed 17 are pressed together by the loading nut 12; the compression spring 8 is pressed by the second slider 7 on the spring sleeve 9, the spring sleeve 9 is installed on the compression head sleeve 10, and the compression head sleeve 10 is installed on the workpiece to be pressed 17 by structural adhesive; the non-loosening screw 1 at the head of the first slider 2 is screwed in through the head thickness of the first slider 2 by threads, and the end of the screw abuts against the upper surface of the head of the compression cap 4.

[0033] The compression cap 4 is installed on the workpiece to be pressed 17 by 2 non-loosening screws 1; the second slider 7, the compression spring 8, the spring sleeve 9, the locknut 11, the loading nut 12, the load-bearing bowl 13, and the long screw 15 are all restricted in the compression head sleeve 10 by the compression cap 4.

[0034] The first slider 2 is installed on the top cylindrical surface of the pressing cap 4. Four first brackets 6 are installed on the large cylindrical end face of the pressing cap 4. The first brackets 6 are connected to the rotating shafts of the holding claws 5 through the round holes thereon. One end of the holding claw 5 is installed in the long strip-shaped round hole on the trapezoidal bracket of the first slider 2 through a cylindrical surface. A non-loosening screw 1 is installed at the head of the first slider 2. The non-loosening screw 1 is screwed into and passes through the first slider 2 through threads. The first slider 2 is connected to four tension springs 14 through four triangular brackets thereon. The other ends of the tension springs 14 are fixed on the second bracket 16, and the second bracket 16 is welded on the flange surface of the pressing cap 4.

[0035] The pressing and releasing mechanism further includes an explosive nut assembly 18. The other end of the long screw 15 is screwed into the explosive nut assembly 18. The pressing and releasing mechanism further includes a buffer pad 3. The buffer pad 3 is installed at the head of the pressing cap 4 to reduce the impact generated when the long screw 15 is ejected by the compression spring 8 and hits the pressing cap 4 after the explosive nut assembly 18 detonates.

[0036] The working process of the pressing and releasing mechanism includes three stages: the release of the long screw 15, the clamping of the holding claws 5, and the on-orbit disassembly of the pressing and releasing mechanism. As Figure 6 shown, the whole process of on-orbit disassembly of the pressing and releasing mechanism is as follows:

[0037] 1. The specific process of the release of the long screw 15 is as follows:

[0038] After entering the orbit, the explosive nut assembly 18 detonates, and the thread constraint between the long screw 15 and the explosive nut assembly 18 is released. The second slider 7, the locknut 11, the loading nut 12, the load-bearing bowl 13, and the long screw 15 bounce upward under the action of the compression spring 8. The long screw 15 stops moving after hitting the buffer pad 3. The release action of the long screw 15 is completed.

[0039] 2. The specific process of the clamping of the holding claws 5 is as follows:

[0040] The astronaut holds an electric tool to tighten the non-loosening screw 1, and the length of the screw screwed into the first slider 2 becomes longer. The first slider 2 moves upward along the small cylindrical surface at the end of the pressing cap. The first slider 2 drives the cylindrical surface of the holding claw 5 to move outward through four trapezoidal brackets, forcing the holding claw 5 to rotate around the rotating shaft between the first bracket 6. Then, the other end of the holding claw 5 moves into the pressing cap 4 until the cylindrical surface of the holding claw 5 moves to the outermost end of the long strip-shaped round hole of the trapezoidal bracket of the first slider 2. At this time, the other end of the holding claw 5 passes through the spring and moves into the pressing cap 4, restricting the second slider 7, the compression spring 8, the locknut 11, the loading nut 12, the load-bearing bowl 13, and the long screw 15 in the pressing cap 4. The clamping action of the holding claw 5 is completed.

[0041] 3. The specific process of the on-orbit disassembly of the pressing and releasing mechanism is as follows:

[0042] After the gripper 5 tightly holds, the astronaut holds an electric tool and sequentially removes the two non-loosening screws 1 between the compression cap 4 and the pressed part 17, releasing the constraint between the compression cap 4 and the pressed part 17; the astronaut takes away the entire compression release mechanism and places it in a storage bag, completing the on-orbit disassembly of the compression release mechanism.

[0043] After the present invention is in orbit, the explosive nut assembly 18 detonates, and the threaded constraint between the long screw 15 and the explosive nut assembly 18 is released; the second slider 7, the locknut 11, the loading nut 12, the load-bearing bowl 13, and the long screw 15 bounce upward under the action of the compression spring 8, and the long screw 15 stops moving after hitting the buffer pad 3; the release action of the long screw 15 is completed, providing a stable and highly reliable release of the long screw for the astronaut to manually disassemble and assemble on orbit.

[0044] In the present invention, the astronaut holds an electric tool to tighten the non-loosening screw 1, and the length of the screw inserted into the first slider 2 becomes longer; the first slider 2 moves upward along the small cylindrical surface at the end of the compression cap, and the first slider 2 drives the cylindrical surface of the gripper 5 to move outward through 4 trapezoidal brackets, forcing the gripper 5 to rotate around the rotation axis with the first bracket 6, and then making the other end gripper of the gripper 5 move into the compression cap 4 until the cylindrical surface of the gripper 5 moves to the outermost end of the long rectangular hole of the trapezoidal bracket of the first slider 2 of the bracket; at this time, the other end gripper of the gripper 5 passes through the spring and moves into the compression cap 4, restricting the second slider 7, the compression spring 8, the locknut 11, the loading nut 12, the load-bearing bowl 13, and the long screw 15 in the compression cap 4, completing the gripping action of the gripper 5, pre-gripping the internal parts in advance, and solving the problem that the parts do not scatter and generate space debris due to disassembly and separation.

[0045] In the present invention, the astronaut holds an electric tool and sequentially removes the two non-loosening screws 1 between the compression cap 4 and the pressed part 17, releasing the constraint between the compression cap 4 and the pressed part 17; the astronaut takes away the entire compression release mechanism and places it in a storage bag, completing the on-orbit disassembly of the compression release mechanism.

[0046] Although the present invention has been disclosed above with preferred embodiments, it is not used to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes, and decorations made to the above embodiments based on the technical essence of the present invention without departing from the technical solution of the present invention all belong to the protection scope of the technical solution of the present invention.

Claims

1. A gripper-type on-orbit detachable pressing and releasing mechanism, characterized in that: It includes a non-loosening screw (1), a first slider (2), a pressing cap (4), a clamping jaw (5), a first bracket (6), a second slider (7), a compression spring (8), a spring sleeve (9), a pressing head sleeve (10), a locknut (11), a loading nut (12), a load-bearing bowl (13), a tension spring (14), a long screw rod (15), a second bracket (16), and a pressed part (17); In the initial state, one end of the long screw rod (15) is connected to the loading nut (12) by threads, and double-nut loosening prevention is achieved using the locknut (11); the load-bearing bowl (13), the second slider (7), and the pressed part (17) are pressed together through the loading nut (12); the compression spring (8) is pressed by the second slider (7) against the spring sleeve (9), the spring sleeve (9) is installed on the pressing head sleeve (10), and the pressing head sleeve (10) is installed on the pressed part (17) through structural adhesive; The pressing cap (4) is installed on the pressed part (17) by 2 non-loosening screws (1); the second slider (7), the compression spring (8), the spring sleeve (9), the locknut (11), the loading nut (12), the load-bearing bowl (13), and the long screw rod (15) are all restricted by the pressing cap (4) in the pressing head sleeve (10); The first slider (2) is installed on the top cylindrical surface of the pressing cap (4), and 4 first brackets (6) are installed on the large cylindrical end face of the pressing cap (4); the first brackets (6) are connected to the rotation axis of the clamping jaw (5) through the round holes thereon; one end of the clamping jaw (5) is installed in the long strip-shaped round hole on the trapezoidal bracket of the first slider (2) through a cylindrical surface; a non-loosening screw (1) is installed at the head of the first slider (2), and the non-loosening screw (1) is screwed in through the thread and passes through the first slider (2); the first slider (2) is connected to 4 tension springs (14) through 4 triangular brackets thereon; the other ends of the tension springs (14) are fixed on the second bracket (16), and the second bracket (16) is welded on the flange surface of the pressing cap (4); The working process of the pressing and releasing mechanism includes 3 stages: the release of the long screw rod (15), the clamping of the clamping jaw (5), and the on-orbit disassembly of the pressing and releasing mechanism; The specific process of the release of the long screw rod (15) is as follows: After entering the orbit, the explosive nut assembly (18) detonates, and the thread constraint between the long screw rod (15) and the explosive nut assembly (18) is released; the second slider (7), the locknut (11), the loading nut (12), the load-bearing bowl (13), and the long screw rod (15) bounce upward under the action of the compression spring (8), and the long screw rod (15) stops moving after hitting the buffer pad (3); the release action of the long screw rod (15) is completed.

2. The gripper-type on-orbit detachable clamping and releasing mechanism according to claim 1, characterized in that: The pressing and releasing mechanism further includes an explosive nut assembly (18); the other end of the long screw rod (15) is screwed into the explosive nut assembly (18).

3. The gripper - type on - orbit detachable clamping and releasing mechanism according to claim 2, wherein: The pressing and releasing mechanism further includes a buffer pad (3); the buffer pad (3) is installed at the head of the pressing cap (4) to reduce the impact generated when the long screw rod (15) is ejected by the compression spring (8) after the detonation of the explosive nut assembly (18) and hits the pressing cap (4).

4. A claw-type on-orbit detachable pressing and releasing mechanism according to claim 1, characterized in that: The non-loosening screw (1) at the head of the first slider (2) is screwed in through the head thickness of the first slider (2) by threads, and the end of the screw abuts against the upper surface of the head of the pressing cap (4).

5. The detachable on-orbit clamping and releasing mechanism with clamping claws according to claim 1, characterized in that: The specific process of the gripper (5) clamping is as follows: The astronaut holds a power tool to tighten the non-loosening screw (1), and the length of the screw screwed into the first slider (2) becomes longer; the first slider (2) moves upward along the small cylindrical surface at the end of the pressing cap, and the first slider (2) drives the cylindrical surface of the gripper (5) to move outward through 4 trapezoidal brackets, forcing the gripper (5) to rotate around the rotation axis with the first bracket (6), and then the other end of the gripper (5) moves into the pressing cap (4) until the cylindrical surface of the gripper (5) moves to the outermost end of the long strip circular hole of the trapezoidal bracket of the first slider (2) of the bracket; at this time, the other end of the gripper (5) passes through the spring and moves into the pressing cap (4), restricting the second slider (7), the compression spring (8), the locknut (11), the loading nut (12), the load-bearing bowl (13), and the long screw (15) in the pressing cap (4), completing the clamping action of the gripper (5).

6. The gripper-type on-orbit detachable clamping and releasing mechanism according to claim 5, characterized in that: The specific process of the on-orbit disassembly of the pressing and releasing mechanism is as follows: After the gripper (5) clamps, the astronaut holds a power tool to sequentially disassemble the two non-loosening screws (1) between the pressing cap (4) and the pressed part (17), releasing the constraint between the pressing cap (4) and the pressed part (17); the astronaut takes the whole pressing and releasing mechanism away and places it in the storage bag, completing the on-orbit disassembly work of the pressing and releasing mechanism.

Images