An on-orbit detachable large solar array clamping and releasing mechanism

Abstract

The present invention relates to a large solar wing compression and release mechanism that is detachable on track, and belongs to the technical field of compression and release mechanisms; the mechanism includes an outer sleeve, an inner sleeve, a top cover, a slider, a load-bearing bowl, a non-slip fastening device, a compression rod assembly, a small head cover, a spring sleeve, a compression spring, etc.; the compression and release mechanism realizes the compression and locking of the solar wing by connecting the compression rod device and the pyrotechnic separation nut before entering the track, and the compression force can be adjusted by loading the nut with preload force. After entering the track, the solar wing is unlocked by power to release and unfold. When the solar wing needs to be repaired, the screws of the non-slip fastening device are unscrewed, and the small head cover is pulled out to pull out the compression rod assembly, so that the solar wing can be refolded. The mechanism of the present invention is smart, compact, and highly reliable, and can realize the compression and release function and realize the on-track maintenance of large solar wing by disassembling the compression rod; the mechanism of the present invention is smart, highly reliable, and can realize the traditional compression and release function and realize the on-track maintenance of large solar wing by disassembling the compression rod.

Description

Technical Field

[0001] The present invention belongs to the technical field of compression and release mechanisms, and relates to an on-orbit detachable large solar wing compression and release mechanism. Background Art

[0002] With the rapid development of aerospace technology, maintainability technology is crucial for extending spacecraft lifespan and reducing manufacturing costs. On-orbit maintainability is becoming a key indicator for evaluating spacecraft performance. Solar panels, the primary energy source for spacecraft, are folded at launch. Once in orbit, a release mechanism unlocks the panels, allowing them to unfold and aim toward the sun, providing energy for the spacecraft.

[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. For traditional compression and release mechanisms, once the solar panels are unlocked, they cannot be folded again, resulting in 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 shortcomings of the existing technology and propose an on-orbit detachable large solar wing compression and release mechanism. The mechanism of the present invention is flexible and highly reliable, and can realize the traditional compression and release functions and realize on-orbit maintenance of large solar wings through disassembly of the compression rod.

[0005] The solution of the present invention is:

[0006] An on-orbit detachable large solar wing compression and release mechanism includes an outer sleeve, an inner sleeve, an outer shell, a screw, a pop-up spring, a compression sleeve, a solar wing, a compression rod, an explosive device separation nut, a compression spring, a spring sleeve, a slider, a load-bearing bowl, a loading nut, a small head cover, a honeycomb plate, a top cover, and a locking leaf spring;

[0007] The compression sleeve is fixedly connected to the last solar wing, the pyrotechnic device separation nut is fixedly connected to the spacecraft body, the compression cap outer sleeve is fixedly connected to the last solar wing, the inner sleeve is placed in the outer sleeve, and the protruding sections on both sides extend from the hollow part of the outer sleeve. The inner sleeve can slide freely in the outer sleeve;

[0008] The top cover and locking leaf spring limit the inner sleeve. After the inner sleeve is installed on the outer sleeve, the top cover is fixed to the top of the outer sleeve by 4 screws, and the locking leaf spring is installed on the outer sleeve by 2 screws. The outer shell of the disengagement fastening device is fixed to the inner sleeve by fastening screws. The screws pass through the inner sleeve and fix the fastening device to the outer sleeve without disassembly. The pop-up spring is sleeved on the outer wall of the screw. The outer sleeve is fixed to the compression sleeve by 4 screws, and the compression sleeve is fixed to the solar wing.

[0009] The lower end of the pressing rod is fixed on the pyrotechnic separation nut. After the spacecraft enters orbit, it can be detonated and separated for release. The upper end of the pressing rod passes through the load-bearing bowl, and the load-bearing bowl is placed in the mating groove of the slider and is pressed tightly by the loading nut above. The slider is fixedly connected to the small head sleeve; the honeycomb panel is located above the small head sleeve; the compression spring is sleeved on the spring sleeve and is pressed tightly by the slider above, and the lower end of the spring sleeve is placed in the pressing sleeve.

[0010] In the above-mentioned on-orbit detachable large solar wing pressing and releasing mechanism, the working process of the pressing and releasing mechanism includes a pressing state, an unlocking state, and a state of disassembling the pressing rod.

[0011] In the above-mentioned on-orbit detachable large solar wing pressing and releasing mechanism, when the pressing and releasing mechanism is in the pressing state, the lower end of the pressing rod is fixed on the pyrotechnic separation nut, and the load-bearing bowl, the slider, the compression spring, and the spring sleeve are fixed in the cavity of the pressing sleeve through the loading nut; the pressing sleeve is fixed on the solar wing.

[0012] In the above-mentioned on-orbit detachable large solar wing pressing and releasing mechanism, when the pressing and releasing mechanism is in the unlocking state, the pyrotechnic separation nut on the spacecraft is unlocked by electrolysis, and the cooperation between the pressing rod and the pyrotechnic separation nut fails; under the action of the compression spring, the slider, the loading nut, the load-bearing bowl, and the pressing rod move upward along the inner sleeve until the small head sleeve abuts against the honeycomb panel. The honeycomb panel absorbs the impact energy of the moving parts through deformation. At this time, the spring force is not enough to release the limit of the locking leaf spring; thus, the release process of the pressing rod is completed, and the solar wing then completes the subsequent unfolding action.

[0013] In the above-mentioned on-orbit detachable large solar wing pressing and releasing mechanism, when the pressing and releasing mechanism is in the state of disassembling the pressing rod, the astronaut needs to unscrew the screws of the non-removable fastening device on both sides of the inner sleeve. When the threads of the screws are unscrewed from the threaded holes on the outer sleeve, the screws bounce upward under the action of the spring. Due to the protection of the outer shell, the screws are restricted within the outer shell; thus, the inner sleeve is separated from the outer sleeve, and then a pulling force is applied through the small head sleeve to release the restriction of the locking leaf spring. The locking leaf spring deforms due to the upward movement thrust of the inner sleeve. Driven by the small head sleeve, the inner sleeve, the slider, the load-bearing bowl, the loading nut, and the pressing rod connected thereto all move upward until the two lugs of the inner sleeve abut against the top cover. At this time, the locking leaf spring slides into the wedge-shaped hole at the bottom of the inner sleeve to complete the locking of the inner sleeve; thus, the pressing rod is pulled out from the solar wing pressing sleeve to complete the on-orbit disassembly work of the pressing and releasing mechanism.

[0014] The beneficial effects of the present invention compared with the prior art are as follows:

[0015] (1) The present invention is applied to the large solar wing pressing and releasing mechanism. This mechanism is convenient for disassembly, has a simple and compact structure, conforms to ergonomics, can avoid interference between the pressing rod and the solar wing plate, realizes the folding of the large solar wing, and thus realizes on-orbit maintenance.

[0016] (2) A detachable large solar wing clamping and releasing mechanism of the present invention can avoid interference between the solar wing and the clamping rod by disassembling the clamping rod, realize the secondary folding of the solar wing, and thus enable the solar wing to be repaired in orbit;

[0017] (3) The detachable large solar wing clamping and releasing mechanism of the present invention has a compact structure, conforms to ergonomics, and is easy to operate. The astronaut can unscrew two screws in orbit to disassemble the clamping rod and fold the solar wing;

[0018] (4) The detachable large solar wing clamping and releasing mechanism of the present invention has good reliability. A non-disengaging fastening device is designed, which is convenient for on-orbit operation and there is no risk of losing parts. Brief Description of the Drawings

[0019] Figure 1 is a schematic diagram of the clamping state of the clamping and releasing mechanism of the present invention;

[0020] Figure 2 is a schematic diagram of the unlocking state of the clamping and releasing mechanism of the present invention;

[0021] Figure 3 is a schematic diagram of the state of disassembling the clamping rod of the clamping and releasing mechanism of the present invention;

[0022] Figure 4 is a schematic diagram of the outer sleeve structure of the clamping and releasing mechanism of the present invention;

[0023] Figure 5 is a schematic diagram of the structure of the inner sleeve of the clamping and releasing mechanism of the present invention;

[0024] Figure 6 is a schematic diagram of the full process of on-orbit disassembly of the clamping and releasing mechanism of the present invention. Detailed Description of the Invention

[0025] The present invention will be further described below in conjunction with embodiments.

[0026] The present invention provides a detachable large solar wing clamping and releasing mechanism, which can realize the clamping and locking of the solar wing before entering orbit, unlock and release the solar wing after entering orbit, and when the solar wing needs to be repaired, the detachable clamping rod can be used to fold the solar wing for the second time for repair.

[0027] The detachable large solar wing clamping and releasing mechanism, as Figure 1 shown, specifically includes an outer sleeve 1, an inner sleeve 2, a housing 3, screws 4, a pop-up spring 5, a compression sleeve 6, a solar wing 7, a clamping rod 8, a pyrotechnic separation nut 9, a compression spring 10, a spring sleeve 11, a slider 12, a bearing bowl 13, a loading nut 14, a small head sleeve 15, a honeycomb panel 16, a top cover 17 and a locking leaf spring 18.

[0028] The specific structure of the on-orbit detachable large solar wing clamping and releasing mechanism of the present invention is as follows: The clamping sleeve 6 is fixedly connected to the last solar wing 7, the pyrotechnic separation nut 9 is fixedly connected to the spacecraft body, the outer sleeve 1 of the clamping cap is fixedly connected to the last solar wing 7, the inner sleeve 2 is placed inside the outer sleeve 1, and the two protruding sections extend out from the hollow part of the outer sleeve 1. The inner sleeve can slide freely inside the outer sleeve. The structure of the outer sleeve 1 is as Figure 4 shown, and the structure of the inner sleeve 2 is as Figure 5 shown. The top cover 17 and the locking leaf spring 18 play a limiting role on the inner sleeve 2. After the inner sleeve 2 is installed on the outer sleeve 1, the top cover 17 fixes the top of the outer sleeve 1 through 4 screws, and the locking leaf spring 18 is installed on the outer sleeve 1 through 2 screws; the shell 3 of the ejection fastening device is fixed on the inner sleeve 2 through fastening screws, and the screw 4 passes through the inner sleeve 2. Without disassembly, the non-ejection fastening device is fixed on the outer sleeve 1; the ejection spring 5 is sleeved on the outer wall of the screw 4; the outer sleeve 1 is fixed on the clamping sleeve 6 through 4 screws, and the clamping sleeve 6 is fixed on the solar wing 7; the lower end of the clamping rod 8 is fixed on the pyrotechnic separation nut 9. After the spacecraft enters the orbit, it can be detonated for separation and release. The upper end of the clamping rod 8 passes through the load-bearing bowl 13, and the load-bearing bowl 13 is placed in the mating groove of the slider 12 and is pressed by the loading nut 14 above. The slider 12 and the small head sleeve 15 are fixedly connected; the honeycomb panel 16 is located above the small head sleeve 15; the compression spring 10 is sleeved on the spring sleeve 11 and is pressed by the slider 12 above, and the lower end of the spring sleeve 11 is placed in the clamping sleeve 6.

[0029] The working process of the clamping and releasing mechanism includes the clamping state, the unlocking state, and the state of disassembling the clamping rod.

[0030] When the clamping and releasing mechanism is in the clamping state, the lower end of the clamping rod 8 is fixed on the pyrotechnic separation nut 9, and the load-bearing bowl 13, the slider 12, the compression spring 10, and the spring sleeve 11 are fixed in the cavity of the clamping sleeve 6 through the loading nut 14; the clamping sleeve 6 is fixed on the solar wing 7.

[0031] As Figure 2 shown, when the clamping and releasing mechanism is in the unlocking state, the pyrotechnic separation nut 9 on the spacecraft is unlocked by electrolysis, and the cooperation between the clamping rod 8 and the pyrotechnic separation nut 9 fails; under the action of the compression spring 10, the slider 12, the loading nut 14, the load-bearing bowl 13, and the clamping rod 8 move upward along the inner sleeve 2 until the small head sleeve 15 abuts against the honeycomb panel 16. The honeycomb panel 16 absorbs the impact energy of the moving parts through deformation. At this time, the spring force is not enough to release the limit of the locking leaf spring 18; thus, the release process of the clamping rod is completed, and the solar wing then completes the subsequent unfolding action.

[0032] As Figure 3As shown in the figure, when the compression release mechanism is in the state of disassembling the compression rod, the astronaut needs to unscrew the screws 4 of the non-removable fastening device on both sides of the inner sleeve 2. When the threads of the screws 4 are unscrewed from the threaded holes on the outer sleeve 1, under the action of the spring 5, the screws 4 bounce upward. Due to the protection of the outer shell 3, the screws 4 are restricted within the outer shell 3; thus, the inner sleeve 2 is separated from the outer sleeve 1. Then, by applying a pulling force to the small head sleeve 15, the restriction of the locking leaf spring 18 is released. The locking leaf spring 18 is deformed due to the upward movement thrust of the inner sleeve 2. Driven by the small head sleeve 15, the inner sleeve 2, the slider 12, the load-bearing bowl 13, the loading nut 14, and the compression rod 8 connected thereto all move upward until the two lugs of the inner sleeve 2 abut against the top cover 17. At this time, the locking leaf spring 18 slides into the wedge-shaped hole at the bottom of the inner sleeve 2, completing the locking of the inner sleeve 2; thus, the compression rod 8 is pulled out from the solar array compression sleeve, completing the on-orbit disassembly work of the compression release mechanism.

[0033] The full process of on-orbit disassembly of the compression release mechanism of the present invention is as Figure 6 shown.

[0034] The detachable large solar array compression release mechanism includes an outer sleeve 1, an inner sleeve 2, a non-removable fastening device which includes an outer shell 3, a spring 5, screws 4, a compression sleeve 6, a solar array 7, a compression rod 8, an explosive separation nut 9, a compression spring 10, a spring sleeve 11, a slider 12, a load-bearing bowl 13, a loading nut 14, a small head sleeve 15, a honeycomb panel 16, a top cover 17, and a locking leaf spring 18.

[0035] The compression cap assembly is composed of an outer sleeve 1, an inner sleeve 2, a compression spring 10, a spring sleeve 11, a slider 12, a load-bearing bowl 13, a small head sleeve 15, a honeycomb panel 16, a top cover 17, and a locking leaf spring 18. The compression rod assembly is composed of a compression rod 8 and a loading nut 14. The non-removable fastening device is composed of an outer shell 3, a spring 5, screws 4, and a gasket and a spring washer.

[0036] The compression force of the solar array is adjusted by the loading nut 14; when the spacecraft is in orbit, the explosive separation nut 9 is unlocked by electrolysis. Under the action of the compression spring 10, the slider 12 can slide inside the inner sleeve 2.

[0037] The load-bearing bowl 13 is placed at the center of the slider 12 and is compressed from above by the loading nut 14.

[0038] During the deployment process of the solar array, the load-bearing bowl 13 bears the forces from all directions and can slide on the contact spherical surface with the slider 12, solving the problem of the restriction of the sleeve on the load-bearing rod during the deployment process; after the solar array is released and deployed, the inner sleeve 2 can be prevented from sliding out by the restriction of the locking leaf spring 18.

[0039] When performing on-orbit maintenance, unscrew the screw 4 of the non-removing fastening device, so that the outer sleeve 1 and the inner sleeve 2 are separated, and the housing 3 prevents the screw 4 from coming out; after unscrewing the screws 4 of the non-removing fastening devices on both sides, the astronaut can hold the small head sleeve to release the restriction of the locking leaf spring 18, so as to take out the entire compression rod assembly from the solar wing compression sleeve.

[0040] The outer sleeve 1 and the inner sleeve 2 are hollow structures in four directions, as Figure 4 , Figure 5 shown.

[0041] The compression sleeve 6 is fixedly connected to the last solar wing 7, the pyrotechnic separation nut 9 is fixedly connected to the spacecraft body, the compression cap outer sleeve 1 is fixedly connected to the last solar wing 7, the inner sleeve 2 is placed inside the outer sleeve 1, and the protruding sections on both sides extend out from the hollow parts of the outer sleeve 1, and the inner sleeve can slide freely inside the outer sleeve.

[0042] The top cover 17 and the locking leaf spring 18 play a limiting role on the inner sleeve 2. After the inner sleeve 2 is installed on the outer sleeve 1, the top cover 17 fixes the top of the outer sleeve 1 through 4 screws, and the locking leaf spring 18 is installed on the outer sleeve 1 through 2 screws. The housing 3 of the removing fastening device is fixed on the inner sleeve 2 through fastening screws, the screw 4 passes through the inner sleeve 2, and the non-removing fastening device is fixed on the outer sleeve 1 without disassembly. The outer sleeve 1 is fixed on the compression sleeve 6 through 4 screws, and the compression sleeve 6 is fixed on the solar wing 7.

[0043] The lower end of the compression rod 8 is fixed on the pyrotechnic separation nut 9. After the spacecraft is in orbit, it can be detonated and separated and released. The upper end of the compression rod 8 passes through the bearing bowl 13. The bearing bowl 13 is placed in the mating groove of the slider 12 and is pressed tightly by the loading nut 14 above. The slider 12 and the small head sleeve 15 are fixedly connected. The compression spring 10 is sleeved on the spring sleeve 11 and is pressed tightly by the slider 12 above. The lower end of the spring sleeve 11 is placed in the compression sleeve 6.

[0044] 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 modifications 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 detachable large solar wing clamping and releasing mechanism in orbit, characterized in that: It includes an outer sleeve (1), an inner sleeve (2), a housing (3), a screw (4), a pop-up spring (5), a compression sleeve (6), a solar panel (7), a compression rod (8), an explosive separation nut (9), a compression spring (10), a spring sleeve (11), a slider (12), a load-bearing bowl (13), a loading nut (14), a small-end sleeve (15), a honeycomb panel (16), a top cover (17), and a locking leaf spring (18); The compression sleeve (6) is fixedly connected to the last solar panel (7), the explosive separation nut (9) is fixedly connected to the spacecraft body, the outer sleeve (1) is fixedly connected to the last solar panel (7), the inner sleeve (2) is placed inside the outer sleeve (1), and the two protruding sections on both sides extend out from the hollow part of the outer sleeve (1), and the inner sleeve can slide freely inside the outer sleeve; The top cover (17) and the locking leaf spring (18) play a limiting role on the inner sleeve (2). After the inner sleeve (2) is installed into the outer sleeve (1), the top cover (17) fixes the top of the outer sleeve (1) through 4 screws, and the locking leaf spring (18) is installed on the outer sleeve (1) through 2 screws; The housing (3) of the non-removable fastening device is fixed to the inner sleeve (2) through fastening screws. The screw (4) passes through the inner sleeve (2) and fixes the non-removable fastening device to the outer sleeve (1) without disassembly; The pop-up spring (5) is sleeved on the outer wall of the screw (4); The outer sleeve (1) is fixed to the compression sleeve (6) through 4 screws, and the compression sleeve (6) is fixed to the solar panel (7); The lower end of the compression rod (8) is fixed to the explosive separation nut (9), and it can be detonated and separated after the spacecraft enters orbit. The upper end of the compression rod (8) passes through the load-bearing bowl (13), and the load-bearing bowl (13) is placed in the mating groove of the slider (12) and is pressed by the loading nut (14) above. The slider (12) and the small-end sleeve (15) are fixedly connected; The honeycomb panel (16) is located above the small-end sleeve (15); The compression spring (10) is sleeved on the spring sleeve (11) and is pressed by the slider (12) above, and the lower end of the spring sleeve (11) is placed in the compression sleeve (6); The working process of the compression and release mechanism includes a compression state, an unlocking state, and a state of disassembling the compression rod; When the compression and release mechanism is in the compression state, the lower end of the compression rod (8) is fixed to the explosive separation nut (9), and the load-bearing bowl (13), the slider (12), the compression spring (10), and the spring sleeve (11) are fixed in the cavity of the compression sleeve (6) through the loading nut (14); The compression sleeve (6) is fixed to the solar panel (7).

2. The on-orbit detachable large solar array clamping and releasing mechanism according to claim 1, wherein: When the compression release mechanism is in the unlocked state, the pyrotechnic separation nut (9) on the spacecraft is unlocked by electrolysis, and the cooperation between the compression rod (8) and the pyrotechnic separation nut (9) fails. Under the action of the compression spring (10), the slider (12), the loading nut (14), the load-bearing bowl (13), and the compression rod (8) move upward along the inner sleeve (2) until the small head sleeve (15) abuts against the honeycomb panel (16). The honeycomb panel (16) absorbs the impact energy of the moving parts through deformation. At this time, the spring force is not sufficient to release the limit of the locking leaf spring (18). Thus, the release process of the compression rod is completed, and the solar wing then completes the subsequent deployment action.

3. The on-orbit detachable large solar wing clamping and releasing mechanism according to claim 2, characterized in that: When the compression release mechanism is in the state of disassembling the compression rod, the astronaut needs to unscrew the screws (4) of the non-removable fastening device on both sides of the inner sleeve (2). When the threads of the screws (4) are unscrewed from the threaded holes on the outer sleeve (1), the screws (4) bounce upward under the action of the pop-up spring (5). Due to the protection of the outer shell (3), the screws (4) are restricted within the outer shell (3). Thus, the inner sleeve (2) is separated from the outer sleeve (1). Then, by applying a pulling force through the small head sleeve (15), the restriction of the locking leaf spring (18) is released. The locking leaf spring (18) deforms due to the upward movement thrust of the inner sleeve (2). Driven by the small head sleeve (15), the inner sleeve (2), the slider (12), the load-bearing bowl (13), the loading nut (14), and the compression rod (8) connected thereto all move upward until the two lugs of the inner sleeve (2) abut against the top cover (17). At this time, the locking leaf spring (18) slides into the wedge-shaped hole at the bottom of the inner sleeve (2) to complete the locking of the inner sleeve (2). Thus, the compression rod (8) is withdrawn from the solar wing compression sleeve to complete the on-orbit disassembly work of the compression release mechanism.

4. The on-orbit detachable large solar wing clamping and releasing mechanism according to claim 3, characterized in that:

5. The on-orbit detachable large solar array clamping and releasing mechanism according to claim 4, characterized in that: The compression force of the solar wing is adjusted through the loading nut (14). When the spacecraft is in orbit, the pyrotechnic separation nut (9) is unlocked by electrolysis. Under the action of the compression spring (10), the slider (12) can slide inside the inner sleeve (2).

6. The on-orbit detachable large solar wing clamping and releasing mechanism according to claim 5, characterized in that: The load-bearing bowl (13) is placed at the center of the slider (12) and is compressed from above by the loading nut (14).

7. A on-orbit detachable large solar array clamping and releasing mechanism according to claim 6, characterized in that: During the deployment process of the solar wing, the load-bearing bowl (13) bears the forces from all directions and can slide on the contact spherical surface with the slider (12). After the solar wing is released and deployed, the restriction of the locking leaf spring (18) can prevent the inner sleeve (2) from slipping out.

8. A detachable large solar wing clamping and releasing mechanism in orbit according to claim 1, characterized in that: During on-orbit maintenance, unscrew the screws (4) of the non-removable fastening device to separate the outer sleeve (1) from the inner sleeve (2). The outer shell (3) prevents the screws (4) from coming out. After unscrewing the screws (4) of the non-removable fastening device on both sides, the astronaut can hold the small head sleeve to release the restriction of the locking leaf spring (18), thereby removing the entire compression rod assembly from the solar wing compression sleeve. The outer sleeve (1) and the inner sleeve (2) are hollow structures in four directions.

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