An integrally detachable clamping and releasing mechanism and an in-orbit integral disassembly method

Abstract

The present invention relates to an integrally detachable compression and release mechanism and an on-orbit integral disassembly method, belonging to the field of compression and release of spacecraft mechanisms; the mechanism comprises a small head cover, a first screw, a cover, a nut, an aluminum honeycomb, a hexagon socket bolt, a loading nut, a load-bearing bowl, a slider, a long screw, a long spring, a compression cap, a fastening device, a second screw, a head cover shell, a compression head cover, a compressed part and an explosive nut assembly; at this time, the compression and release mechanism is in a compression state and the spacecraft is in a launch phase; after the spacecraft enters orbit, it enters a release phase and an on-orbit integral disassembly phase in sequence; the integrally detachable compression and release mechanism of the present invention has the characteristics of being integrally detachable and maintainable on-orbit.

Description

Technical Field

[0001] The invention belongs to the field of compression and release of spacecraft mechanisms, and relates to an integrally detachable compression and release mechanism and an on-orbit integral disassembly method. Background Art

[0002] Large-area solar panels are used to meet the high power requirements of large spacecraft on-orbit. The compression and release mechanism is a core component of large-area solar panels on large spacecraft, ensuring their secure retention after repeated deployment and retraction in orbit. To accommodate the long-term in-orbit operation of large spacecraft and the multiple deployment and retraction of solar panels on-orbit, the compression and release mechanism must exhibit high functional reliability and, when necessary, be manually disassembled by astronauts on-orbit.

[0003] Due to the large size and low rigidity of the solar panels, they may malfunction after entering orbit due to the impact and vibration during launch. Astronauts have to manually disassemble them in orbit, which is difficult, has high mission costs, low mission reliability, and short spacecraft life. Summary of the Invention

[0004] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and propose an integrally detachable clamping and releasing mechanism and an on-track integral disassembly method. The integrally detachable clamping and releasing mechanism has the characteristics of being integrally detachable and maintainable on-track.

[0005] The solution of the present invention is:

[0006] An integrally detachable compression and release mechanism, comprising a small head cover, a first screw, a cover, a nut, an aluminum honeycomb, a hexagon socket bolt, a loading nut, a bearing bowl, a slider, a long screw, a long spring, a compression cap, a fastening device, a second screw, a head cover shell, a compression head cover, a pressed part, and an explosive nut assembly;

[0007] The small head cover is installed on the slider through 4 hexagonal bolts; the cover is installed on the top of the clamping cap through 4 first screws; the aluminum honeycomb is installed on the head of the clamping cap; in the clamping state, one end of the long screw is screwed into the thread of the explosive bolt assembly, and the other end cooperates with the loading nut through the thread to press the load-bearing bowl and the slider on the head cover shell; the double nut anti-loosening is achieved by the nut above the loading nut; the slider compresses the long spring; the long spring is sleeved on the middle cylinder of the head cover shell; the head cover shell and the clamping cap are combined into a whole through a nested structure, and are installed on the clamping head cover together through 4 second screws; the shells of the two captive screws are installed on the mounting flange of the clamping cap through screws, and the M8 hexagonal screws in the captive screws are fixed to the clamping head cover through the clamping head cover.

[0008] In the above-mentioned integrally detachable compression and release mechanism, during the launch phase of the spacecraft, the compression and release mechanism is in a compressed state.

[0009] In the above-mentioned integrally detachable clamping and releasing mechanism, after the spacecraft enters orbit, it enters the release phase and the in-orbit integral disassembly phase in sequence.

[0010] In the above-mentioned integrally detachable compression and release mechanism, the specific process of the release stage is as follows:

[0011] After the explosive nut assembly is detonated, the long screw is released. After the constraint of the long screw is released, under the action of the long spring, the slider, load-bearing bowl, loading nut, nut, long screw, small head cover, and first screw are all bounced upward; during the upward popping process, the slider slides along the inner wall of the clamping cap until the head of the first screw on the small head cover hits the aluminum honeycomb; the aluminum honeycomb deforms to consume the energy generated by the impact, completing the release action.

[0012] In the above-mentioned integrally detachable clamping and releasing mechanism, the specific process of the in-orbit integral disassembly stage is as follows:

[0013] The astronauts walked out of the cabin holding power tools, and with the assistance of the extravehicular robotic arm, removed the M8 screws of the two captive screws on the clamping cap one by one, releasing the connection between the clamping head cover and the pressed part; then the astronauts held the clamping cap and applied outward pulling force to remove the clamping cap, the clamping head cover and all the internal parts, completing the overall disassembly of the clamping release mechanism in orbit.

[0014] A method for integrally disassembling a fully detachable compression release mechanism on track, comprising:

[0015] Make a compression release mechanism;

[0016] During the spacecraft launch phase, the compression release mechanism is in a compressed state;

[0017] After the spacecraft enters orbit, the hold-down release mechanism is in the release phase;

[0018] The clamping and releasing mechanism is disassembled as a whole on track.

[0019] In the above-mentioned method for integrally disassembling a detachable compression release mechanism on track, the compression release mechanism includes a small head cover, a first screw, a cover, a nut, an aluminum honeycomb, a hexagon socket bolt, a loading nut, a bearing bowl, a slider, a long screw, a long spring, a compression cap, a fastening device, a second screw, a head cover shell, a compression head cover, a pressed part and an explosive nut assembly;

[0020] The small head cover is installed on the slider through 4 hexagonal bolts; the cover is installed on the top of the clamping cap through 4 first screws; the aluminum honeycomb is installed on the head of the clamping cap; in the clamping state, one end of the long screw is screwed into the thread of the explosive bolt assembly, and the other end cooperates with the loading nut through the thread to press the load-bearing bowl and the slider on the head cover shell; the double nut anti-loosening is achieved by the nut above the loading nut; the slider compresses the long spring; the long spring is sleeved on the middle cylinder of the head cover shell; the head cover shell and the clamping cap are combined into a whole through a nested structure, and are installed on the clamping head cover together through 4 second screws; the shells of the two captive screws are installed on the mounting flange of the clamping cap through screws, and the M8 hexagonal screws in the captive screws are fixed to the clamping head cover through the clamping head cover.

[0021] In the above-mentioned method for integrally disassembling an integrally detachable clamping and releasing mechanism on track, the clamping and releasing mechanism is in a clamped state.

[0022] In the above-mentioned method for in-orbit disassembly of a wholly detachable clamping and releasing mechanism, the specific process of the clamping and releasing mechanism in the release stage is as follows:

[0023] After the explosive nut assembly is detonated, the long screw is released. After the constraint of the long screw is released, under the action of the long spring, the slider, load-bearing bowl, loading nut, nut, long screw, small head cover, and first screw are all bounced upward; during the upward popping process, the slider slides along the inner wall of the clamping cap until the head of the first screw on the small head cover hits the aluminum honeycomb; the aluminum honeycomb deforms to consume the energy generated by the impact, completing the release action.

[0024] In the above-mentioned method for disassembling the entire detachable clamping and releasing mechanism on-track, the specific process of disassembling the entire detachable clamping and releasing mechanism on-track is as follows:

[0025] The astronauts walked out of the cabin holding power tools, and with the assistance of the extravehicular robotic arm, removed the M8 screws of the two captive screws on the clamping cap one by one, releasing the connection between the clamping head cover and the pressed part; then the astronauts held the clamping cap and applied outward pulling force to remove the clamping cap, the clamping head cover and all the internal parts, completing the overall disassembly of the clamping release mechanism in orbit.

[0026] The beneficial effects of the present invention compared with the prior art are:

[0027] (1) The present invention adopts a head cover shell and a compression cap to be matched into an integral body through a nested structure, and is installed on the compression head cover together by four second screws. The shell of the two captive screws is installed on the mounting flange of the compression cap by screws. The captive screws pass through the compression head cover and are fixed to the compressed part. By adopting an innovative compression method, the compression release mechanism is kept in a reliable compression state during the launch phase of the spacecraft.

[0028] (2) The present invention uses an explosive nut assembly to detonate and release the long screw. Under the action of the long spring, the slider, the load-bearing bowl, the loading nut, the nut, the long screw, the small head cover, the first screw and other parts are all bounced upward, and the slider slides along the inner wall of the clamping cap until the first screw head on the small head cover hits the aluminum honeycomb, and the aluminum honeycomb deforms to consume the energy generated by the impact. By adopting an innovative unlocking method and the stroke design of each part, the reliable release action of the clamping release mechanism after the spacecraft enters orbit is achieved;

[0029] (3) The present invention first removes the two captive screws on the clamping cap to release the connection between the clamping head cover and the pressed part. Then the astronaut holds the clamping cap and applies a pulling force outward to remove the clamping cap, the clamping head cover and all the internal parts. This innovatively solves the problem of low reliability of the overall disassembly work of the clamping release mechanism on orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] Figure 1 It is a side view of the integrally detachable compression and release mechanism of the present invention;

[0031] Figure 2 It is a cross-sectional view of the initial compression state of the integrally detachable compression and release mechanism of the present invention;

[0032] Figure 3 It is a cross-sectional view of the pyrotechnic device release state of the integrally detachable compression release mechanism of the present invention;

[0033] Figure 4 It is a cross-sectional view of the integrally detachable pressing and releasing mechanism of the present invention after being integrally disassembled on track;

[0034] Figure 5 It is a schematic diagram of the entire process of on-track disassembly of the integrally detachable clamping and releasing mechanism of the present invention. DETAILED DESCRIPTION

[0035] The present invention will be further described below in conjunction with the embodiments.

[0036] The present invention provides an integrally detachable pressing and releasing mechanism and an on-track integrally detachable method. The integrally detachable pressing and releasing mechanism has the characteristics of being integrally detachable and maintainable on-track.

[0037] Integrally detachable compression release mechanism, such as Figure 1 As shown, it specifically includes a small head cover 1, a first screw 2, a cover 3, a nut 4, an aluminum honeycomb 5, a hexagon socket bolt 6, a loading nut 7, a load-bearing bowl 8, a slider 9, a long screw 10, a long spring 11, a clamping cap 12, a fastening device, a second screw 14, a head cover shell 15, a clamping head cover 16, a pressed part 17 and an explosive nut assembly 18; the fastening device is a captive screw 13.

[0038] The small head cover 1 is installed on the slider 9 through 4 hexagon socket bolts 6; the cover 3 is installed on the top of the clamping cap 12 through 4 first screws 2; the aluminum honeycomb 5 is installed on the head of the clamping cap 12; in the clamping state, one end of the long screw 10 is screwed into the thread of the explosive bolt assembly 18, and the other end cooperates with the loading nut 7 through the thread to press the load-bearing bowl 8 and the slider 9 on the head cover shell 15; the double nut anti-loosening is achieved by the nut 4 on the top of the loading nut 7; the slider 9 compresses the long spring 11; the long spring 11 is sleeved on the middle cylinder of the head cover shell 15; the head cover shell 15 and the clamping cap 12 are matched into a whole through a nested structure, and are installed on the clamping head cover 16 together through 4 second screws 14; the shell of the two captive screws 13 is installed on the mounting flange of the clamping cap 12 by screws, and the M8 hexagon socket screw in the captive screw 13 passes through the clamping head cover 16 and is fixed to the pressed part 17.

[0039] During the launch phase of the spacecraft, the compression release mechanism is in a compressed state, such as Figure 2 shown.

[0040] After the spacecraft enters orbit, it enters the release phase and the in-orbit overall disassembly phase in sequence.

[0041] like Figure 3 As shown in Figure 2, the specific process of the release phase is as follows:

[0042] After the explosive nut assembly 18 is detonated, the long screw 10 is released. After the constraint of the long screw 10 is released, under the action of the long spring 11, the slider 9, the load-bearing bowl 8, the loading nut 7, the nut 4, the long screw 10, the small head cover 1, and the first screw 2 are all bounced upward; during the upward popping process, the slider 9 slides along the inner wall of the clamping cap 12 until the first screw 2 on the small head cover 1 hits the aluminum honeycomb 5; the aluminum honeycomb 5 deforms to consume the energy generated by the impact, completing the release action.

[0043] like Figure 4 As shown in the figure, the specific process of the on-orbit overall disassembly stage is as follows:

[0044] The astronauts walked out of the cabin holding power tools, and with the assistance of the extravehicular robotic arm, removed the M8 screws of the two captive screws 13 on the clamping cap 12 one by one, releasing the connection between the clamping head cover 16 and the pressed part 17; then the astronauts held the clamping cap 12 and applied outward pulling force to remove the clamping cap 12, the clamping head cover 16 and all the internal parts, completing the overall disassembly of the clamping release mechanism on orbit.

[0045] like Figure 5 As shown, the method for disassembling the integrally detachable clamping and releasing mechanism on track specifically includes the following steps:

[0046] Make a clamping and releasing mechanism; the clamping and releasing mechanism includes a small head cover 1, a first screw 2, a cover 3, a nut 4, an aluminum honeycomb 5, a hexagon socket bolt 6, a loading nut 7, a load-bearing bowl 8, a slider 9, a long screw 10, a long spring 11, a clamping cap 12, a fastening device, a second screw 14, a head cover shell 15, a clamping head cover 16, a pressed part 17 and an explosive nut assembly 18.

[0047] The small head cover 1 is installed on the slider 9 through 4 hexagon socket bolts 6; the cover 3 is installed on the top of the clamping cap 12 through 4 first screws 2; the aluminum honeycomb 5 is installed on the head of the clamping cap 12; in the clamping state, one end of the long screw 10 is screwed into the thread of the explosive bolt assembly 18, and the other end cooperates with the loading nut 7 through the thread to press the load-bearing bowl 8 and the slider 9 on the head cover shell 15; the double nut anti-loosening is achieved by the nut 4 on the top of the loading nut 7; the slider 9 compresses the long spring 11; the long spring 11 is sleeved on the middle cylinder of the head cover shell 15; the head cover shell 15 and the clamping cap 12 are matched into a whole through a nested structure, and are installed on the clamping head cover 16 together through 4 second screws 14; the shell of the two captive screws 13 is installed on the mounting flange of the clamping cap 12 by screws, and the M8 hexagon socket screw in the captive screw 13 passes through the clamping head cover 16 and is fixed to the pressed part 17.

[0048] During the spacecraft launch phase, the compression release mechanism is in a compressed state; at this time, the compression release mechanism is in a compressed state.

[0049] After the spacecraft enters orbit, the compression release mechanism is in the release stage. The specific process of the compression release mechanism in the release stage is as follows:

[0050] After the explosive nut assembly 18 is detonated, the long screw 10 is released. After the constraint of the long screw 10 is released, under the action of the long spring 11, the slider 9, the load-bearing bowl 8, the loading nut 7, the nut 4, the long screw 10, the small head cover 1, and the first screw 2 are all bounced upward; during the upward popping process, the slider 9 slides along the inner wall of the clamping cap 12 until the first screw 2 on the small head cover 1 hits the aluminum honeycomb 5; the aluminum honeycomb 5 deforms to consume the energy generated by the impact, completing the release action.

[0051] The specific process of disassembling the clamping and releasing mechanism as a whole on track is as follows:

[0052] The astronauts walked out of the cabin holding power tools, and with the assistance of the extravehicular robotic arm, removed the M8 screws of the two captive screws 13 on the clamping cap 12 one by one, releasing the connection between the clamping head cover 16 and the pressed part 17; then the astronauts held the clamping cap 12 and applied outward pulling force to remove the clamping cap 12, the clamping head cover 16 and all the internal parts, completing the overall disassembly of the clamping release mechanism on orbit.

[0053] The present invention adopts a head cover shell and a compression cap to be matched into an integral body through a nested structure, and is installed on the compression head cover together by four second screws. The housing of the two captive screws is installed on the mounting flange of the compression cap by screws. The captive screws pass through the compression head cover and are fixed to the compressed part. By adopting an innovative compression method, the compression release mechanism is kept in a reliable compression state during the spacecraft launch phase.

[0054] At the same time, an explosive nut assembly is used to detonate and release the long screw. Under the action of the long spring, the slider, load-bearing bowl, loading nut, nut, long screw, small head cover, first screw and other parts are all bounced upwards. The slider slides along the inner wall of the clamping cap until the head of the first screw on the small head cover hits the aluminum honeycomb, which deforms to dissipate the energy generated by the impact. By adopting an innovative unlocking method and the stroke design of each component, the clamping release mechanism is released reliably after the spacecraft enters orbit.

[0055] The present invention first removes the two captive screws on the clamping cap to release the connection between the clamping head cover and the pressed part. Then the astronaut holds the clamping cap and applies outward pulling force to remove the clamping cap, the clamping head cover and all the internal parts. This innovatively solves the problem of low reliability of the overall disassembly work of the clamping release mechanism on orbit.

[0056] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions 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 modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A completely detachable compression release mechanism, characterized in that: The invention comprises a small head cover (1), a first screw (2), a cover (3), a nut (4), an aluminum honeycomb (5), a hexagon socket bolt (6), a loading nut (7), a load-bearing bowl (8), a slider (9), a long screw (10), a long spring (11), a pressing cap (12), a fastening device, a second screw (14), a head cover shell (15), a pressing head cover (16), a pressed part (17) and an explosive nut assembly (18); the fastening device is a captive screw (13); The small head cover (1) is mounted on the slider (9) through four hexagon socket bolts (6); the cover (3) is mounted on the top of the clamping cap (12) through four first screws (2); the aluminum honeycomb (5) is mounted on the head of the clamping cap (12); when the integrally detachable clamping release mechanism is in a clamping state, one end of the long screw (10) is screwed into the thread of the explosive nut assembly (18), and the other end is engaged with the loading nut (7) through the thread, so as to press the bearing bowl (8) and the slider (9) onto the head cover shell (15); the upper side of the loading nut (7) is screwed through the nut (4 ) realizes double nut anti-loosening; the slider (9) compresses the long spring (11); the long spring (11) is sleeved on the middle cylinder of the head cover shell (15); the head cover shell (15) and the pressing cap (12) are matched into a whole through a nested structure, and are installed together on the pressing head cover (16) through four second screws (14); the housings of the two captive screws (13) are installed on the mounting flange of the pressing cap (12) through screws, and the M8 hexagon socket screw in the captive screw (13) passes through the pressing head cover (16) and is fixed to the pressed part (17); After the spacecraft enters orbit, it enters the release phase and the on-orbit overall disassembly phase in sequence; The specific process of the release phase is: After the explosive nut assembly (18) is detonated, the long screw (10) is released. After the constraint of the long screw (10) is released, under the action of the long spring (11), the slider (9), the load-bearing bowl (8), the loading nut (7), the nut (4), the long screw (10), and the small head cover (1) are all ejected upwards; during the upward ejection process, the slider (9) slides along the inner wall of the pressing cap (12) until the small head cover (1) hits the aluminum honeycomb (5); the aluminum honeycomb (5) deforms to consume the energy generated by the impact; and the release action is completed; The specific process of the on-orbit overall disassembly stage is as follows: The astronaut walks out of the cabin holding an electric tool, and with the assistance of the extravehicular robotic arm, removes the M8 screws of the two captive screws (13) on the clamping cap (12) in turn, and releases the connection between the clamping head cover (16) and the pressed part (17); then the astronaut holds the clamping cap (12) and applies a pulling force outward to remove the clamping cap (12), the clamping head cover (16) and all the parts inside the clamping cap (12) and the clamping head cover (16), thus completing the overall disassembly of the integrally detachable clamping release mechanism on orbit.

2. A method for in-orbit disassembly of a fully detachable clamping and releasing mechanism, comprising the fully detachable clamping and releasing mechanism according to claim 1, characterized in that: The steps of the on-orbit integral disassembly method include: Produce a fully detachable compression and release mechanism; During the launch phase of the spacecraft, the integrally detachable compression and release mechanism is in a compressed state; After the spacecraft enters orbit, the integrally detachable compression release mechanism is in the release stage; The integrally detachable clamping and releasing mechanism is disassembled in its entirety on track.

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