An on-orbit foldable solar wing deployment and locking mechanism

Abstract

The present invention provides an on-orbit foldable solar wing deployment locking mechanism, comprising a folding female hinge, an deploying female hinge, a deploying male hinge, a folding mechanism, and a deploying mechanism. The folding female hinge is fixed to a first solar panel, the deploying male hinge is fixed to a second solar panel, the folding female hinge and the deploying female hinge are connected by the folding mechanism, the deploying male hinge and the deploying female hinge are connected by the deploying mechanism, the deploying mechanism is configured to be lockable and self-rotatable, and the folding mechanism is configured to be self-rotatable. The present invention can complete the folding action of the deployment locking mechanism, achieving on-orbit folding of the solar wing.

Description

Technical Field

[0001] The present invention relates to the technical field of deployment and locking mechanisms, and in particular to an on-orbit foldable solar wing deployment and locking mechanism. Background Art

[0002] As spacecraft development costs continue to rise, extending the on-orbit lifespan of spacecraft has become increasingly important. The Hubble Space Telescope, launched in 1990, has undergone five on-orbit repairs using the space shuttle, extending its exceptionally long lifespan. With the official completion of my country's space station, spacecraft can be repaired and maintained by astronauts performing extraordinarily long walks through the spacecraft after docking, thereby extending the lifespan of spacecraft. Solar panels are a crucial component of spacecraft. During on-orbit maintenance, they cannot be simply disassembled and discarded. This would create space debris, and their long, extended deployment area poses the risk of rebound collisions with the spacecraft. Therefore, designing a solar panel that can be retracted in orbit is crucial. The key to retracting and locking the solar panels is an in-orbit retractable, deployable, and deployable mechanism. Currently, the technology for this mechanism is lacking.

[0003] To this end, the present invention provides an on-orbit foldable solar wing deployment and locking mechanism to achieve on-orbit folding of the solar wing. Summary of the Invention

[0004] In view of the defects in the prior art, the purpose of the present invention is to provide a deployment and locking mechanism that can realize the folding of solar wings in orbit.

[0005] The on-orbit foldable solar wing deployment locking mechanism provided by the present invention includes a folding female hinge, an deploying female hinge, a deploying male hinge, a folding mechanism, and an deploying mechanism. The folding female hinge is fixed on the first solar panel, and the deploying male hinge is fixed on the second solar panel. The folding female hinge and the deploying female hinge are connected by the folding mechanism, and the deploying male hinge and the deploying female hinge are connected by the deploying mechanism. The deploying mechanism is configured to be able to lock and self-rotate, and the folding mechanism is configured to be able to self-rotate.

[0006] Preferably, the folding female hinge is connected to the first solar panel via bolts, and the unfolding male hinge is connected to the second solar panel via bolts.

[0007] Furthermore, the unfolding mechanism includes an unfolding shaft, a spring fixing shaft, and an unfolding spring, one end of the unfolding shaft is fixedly connected to the unfolding female hinge, one end of the spring fixing shaft is connected to the unfolding male hinge, one end of the unfolding spring is fixed on the unfolding shaft, the unfolding spring is wound on the unfolding shaft, and the other end of the unfolding spring is connected to the spring fixing shaft.

[0008] Preferably, one end of the spring fixing shaft is provided with a thread, and the spring fixing shaft is threadedly connected to the unfolding female hinge.

[0009] Furthermore, the deployment mechanism also includes a locking hook, a locking pin, a torsion spring, and an extending shaft. The locking hook is connected to the deployment mother hinge through the locking pin, the extending shaft is fixed to the head of the locking hook, the torsion spring is sleeved on the locking pin, the short pin of the torsion spring is fixed on the deployment mother hinge, and the long pin of the torsion spring is in contact with the extending shaft.

[0010] Furthermore, a locking groove is provided on the unfolding male hinge, and the extending shaft can cooperate with the locking groove.

[0011] Furthermore, the folding mechanism includes a folding shaft, a folding spring, a spring mounting wheel, and a fixing stud. One end of the folding shaft is connected to the folding mother hinge, one end of the fixing stud is connected to the unfolding mother hinge, the spring mounting wheel is fixed on the folding shaft, one end of the folding spring is connected to the spring mounting wheel, and the other end of the folding spring is connected to the fixing stud.

[0012] Preferably, one end of the fixing stud is provided with a thread, and the fixing stud is threadedly connected to the expansion female hinge.

[0013] Furthermore, the folding mechanism also includes a non-slipping screw, which includes a large screw and a spring. The large screw compresses the spring, and the large screw is screwed into the folding mother hinge. The large screw can pass through the unfolding mother hinge.

[0014] Furthermore, the non-slip screw also includes a shell and a small screw. The shell is connected to the expansion female hinge through the small screw, and the shell can accommodate the large screw.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] The in-orbit foldable solar wing deployment locking mechanism proposed in the present invention is based on a design of double rotating shaft systems and double spring drives. Astronauts use electric tools in orbit to achieve unlocking between the folding mother hinge and the deployment mother hinge. Driven by the folding spring, the folding mother hinge rotates around the folding shaft system to complete the folding action of the deployment locking mechanism, thereby achieving the purpose of folding the solar wing in orbit, realizing the in-orbit folding of the deployment locking mechanism, and achieving the purpose of folding the solar panel in orbit. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Other features, objects and advantages of the present invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following drawings:

[0018] Figure 1Schematic diagram of the initial state of the deployment and locking mechanism of the on-orbit retractable solar wing according to an embodiment of the present invention;

[0019] Figure 2 Schematic diagram of the deployment and locking state of the on-orbit foldable solar wing deployment and locking mechanism according to an embodiment of the present invention;

[0020] Figure 3 A schematic diagram of the folding process of the deployment and locking mechanism of the on-orbit foldable solar wing according to an embodiment of the present invention;

[0021] Figure 4 This is a schematic diagram of the folding end state of the deployment locking mechanism of the on-orbit foldable solar wing according to an embodiment of the present invention;

[0022] Figure 5 This is a schematic diagram of the entire process of the on-orbit retractable solar wing deployment and locking mechanism according to an embodiment of the present invention.

[0023] In the figure, 1-folding female hinge, 2-non-slipping screw, 3-expanding female hinge, 4-locking hook, 5-locking pin, 6-torsion spring, 7-extending shaft, 8-expanding male hinge, 9-connecting bolt, 10-spring fixing shaft, 11-expanding spring, 12-expanding shaft, 13-folding spring, 14-folding shaft, 15-spring mounting wheel, 16-fixing stud. DETAILED DESCRIPTION

[0024] The present invention will be described in detail below with reference to specific embodiments. The following examples will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those skilled in the art, several changes and improvements can be made without departing from the scope of the present invention. These all fall within the scope of protection of the present invention.

[0025] The present invention provides an on-orbit foldable solar wing deployment locking mechanism. The mechanism is based on a dual-rotating shaft system and dual-spring drive design. The astronaut uses an electric tool on-orbit to unlock the folding mother hinge and the deployment mother hinge. Driven by the folding spring, the folding mother hinge rotates around the folding shaft system to complete the folding action of the deployment locking mechanism, thereby achieving the purpose of folding the solar wing on-orbit. In the initial state, the folding mother hinge and the deployment mother hinge are connected together by two non-slip screws to form an integral component. In the initial state, the locking hook is always pressed against the arc of the deployment male hinge by the torsion spring installed on it. During the deployment process, the deployment mother hinge is driven by the deployment spring to rotate 180° and then the deployment mother hinge is in place. The deployment movement is locked by the locking hook on the deployment mother hinge and the locking groove structure on the deployment male hinge, and the deployment movement ends. During the folding process, the astronaut uses an electric tool to loosen the two non-slip screws, and the constraints between the folding mother hinge and the deployment mother hinge are released. Driven by the folding spring, the folding mother hinge rotates, thereby achieving the folding of the solar wing on-orbit.

[0026] like Figures 1 to 5 As shown, the on-orbit foldable solar wing deployment locking mechanism of this embodiment includes a folding female hinge 1, an unfolding female hinge 3, an unfolding male hinge 8, a non-slip screw 2, an unfolding spring 11, an unfolding shaft 12, a folding spring 13, a folding shaft 14, a locking hook 4, and a torsion spring 6.

[0027] The male expansion hinge 8 is mounted on the solar panel via two connecting bolts 9. The rotating axis of the expansion shaft 12 is fixedly connected to the female retraction hinge 3. The spring fixing shaft 10 is screwed into the female expansion hinge 8. One end of the expansion spring 11 is fixed to the rotating axis of the expansion shaft 12, and the other end is fixed to the spring fixing shaft 10. The expansion spring 11 is completely wound around the expansion shaft 12. Driven by the expansion spring 11, the female expansion hinge 8 rotates around the expansion shaft 12 to achieve the expansion action.

[0028] The locking hook 4 is connected to the folding female hinge 3 through the locking pin 5, the extending shaft 7 is fixed to the head of the locking hook 4, the torsion spring 6 passes through the locking pin 5, the short pin of the torsion spring 6 is fixed to the unfolding female hinge 3, and the long pin of the torsion spring 6 is pressed on the extending shaft 7. In the initial state, the locking hook 4 is always pressed against the arc of the unfolding male hinge 8 by the torsion spring 6 installed thereon. After entering the track, the constraint between the solar panels is released, and the unfolding female hinge 3 is driven by the unfolding spring 11 to rotate 180° counterclockwise around the unfolding shaft 12. The extending shaft 7 is locked with the locking groove structure on the unfolding male hinge 8, and the unfolding movement is completed.

[0029] The folding female hinge 1 and the unfolding female hinge 3 are connected by a folding shaft 14 and are connected together by two captive screws 2 to form an integral component. The captive screw 2 consists of a housing, a large screw, a spring, and a small screw. The large screw compresses the spring and is simultaneously screwed into the folding female hinge 1. The housing is mounted on the unfolding female hinge 3 via the small screw. The rotating axis of the folding shaft 14 is fixedly connected to the folding female hinge 1. The spring mounting wheel 15 is screwed onto the rotating axis of the folding shaft 14. The fixing stud 16 is threaded into the unfolding female hinge 3. One end of the folding spring 13 is fixed to the spring mounting wheel 15, and the other end is fixed to the fixing stud 16. The two spring mounting wheels 15 are respectively mounted at both ends of the rotating axis of the folding shaft 14. The folding female hinge 1 is mounted on another solar panel via two connecting bolts 9. The unfolding female hinge 3 forms an integral unit with the unfolding male hinge 8 via the folding shaft 12 and the locking hook 4.

[0030] During the retraction process, astronauts use a power tool to loosen the two captive screws 2. The large screws spring upward under the action of the springs, while being restrained within the shell. The constraints on the retraction and deployment hinges 1 and 3 are released. Driven by the retraction spring 13, the retraction hinge 1 rotates 180° clockwise around the retraction axis 14, thus completing the in-orbit retraction of the solar array.

[0031] The above describes specific embodiments of the present invention. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art may make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. The embodiments of this application and the features in the embodiments may be combined with each other in any manner unless there is a conflict.

Claims

1. An on-orbit foldable solar wing deployment and locking mechanism, characterized in that: It includes a folding female hinge, an unfolding female hinge, an unfolding male hinge, a folding mechanism, and an unfolding mechanism. The folding female hinge is fixed on the first battery panel, the unfolding male hinge is fixed on the second battery panel, the folding female hinge and the unfolding female hinge are connected by the folding mechanism, the unfolding male hinge and the unfolding female hinge are connected by the unfolding mechanism, the unfolding mechanism is configured to be lockable and self-rotatable, and the folding mechanism is configured to be self-rotatable; The deployment mechanism includes a deployment shaft, a spring fixing shaft, a deployment spring, a locking hook, a locking pin, a torsion spring, and an extension shaft, one end of the deployment shaft is fixedly connected to the deployment female hinge, one end of the spring fixing shaft is connected to the deployment male hinge, one end of the deployment spring is fixedly provided on the deployment shaft, the deployment spring is wound on the deployment shaft, the other end of the deployment spring is connected to the spring fixing shaft, the locking hook is connected to the deployment female hinge through the locking pin, the extension shaft is fixedly provided on the head of the locking hook, the torsion spring is sleeved on the locking pin, the short pin of the torsion spring is fixedly provided on the deployment female hinge, and the long pin of the torsion spring is in contact with the extension shaft; The folding mechanism includes a folding shaft, a folding spring, a spring mounting wheel, a fixing stud, and a non-slipping screw. One end of the folding shaft is connected to the folding mother hinge, one end of the fixing stud is connected to the unfolding mother hinge, the spring mounting wheel is fixed on the folding shaft, one end of the folding spring is connected to the spring mounting wheel, and the other end of the folding spring is connected to the fixing stud. The non-slipping screw includes a large screw and a spring. The large screw compresses the spring, and the large screw is screwed into the folding mother hinge. The large screw can pass through the unfolding mother hinge.

2. The on-orbit foldable solar wing deployment locking mechanism according to claim 1, characterized in that: The folding female hinge is connected to the first solar panel via bolts, and the unfolding male hinge is connected to the second solar panel via bolts.

3. The on-orbit foldable solar wing deployment locking mechanism according to claim 1, characterized in that: One end of the spring fixing shaft is provided with a thread, and the spring fixing shaft is threadedly connected to the expansion female hinge.

4. The on-orbit foldable solar wing deployment locking mechanism according to claim 3, characterized in that: The unfolding male hinge is provided with a locking groove, and the extending shaft can cooperate with the locking groove.

5. The on-orbit foldable solar wing deployment locking mechanism according to claim 1, characterized in that: One end of the fixing stud is provided with a thread, and the fixing stud is threadedly connected to the expansion female hinge.

6. The on-orbit foldable solar wing deployment and locking mechanism according to claim 1, characterized in that: The non-slip screw further comprises a shell and a small screw. The shell is connected to the expansion female hinge via the small screw, and the shell can accommodate the large screw.

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