Hinge for multiple folding and unfolding of spacecraft

Abstract

The invention discloses a hinge for multiple folding and unfolding of a spacecraft, and relates to the technical field of hinges, the hinge comprises a male hinge, two ends of the male hinge are respectively provided with a first fixed unfolding hinge mechanism and a second fixed unfolding hinge mechanism, and the middle part of the male hinge is provided with a linkage mechanism. Through the installation of the first fixed unfolding hinge mechanism and the second fixed unfolding hinge mechanism, after a spacecraft enters an orbit, the pressing and releasing device releases the antenna plate, as one end of an inner ring of a volute spiral spring is fixed on a pin shaft, and one end of an outer ring is fixed on a coil spring sleeve, a first female hinge is driven to rotate around the pin shaft; in the process that the first female hinge rotates from the folded state to the unfolded state, the torsion spring presses the lock hook through the torque of the torsion spring till the lock hook finally slides to the lock shaft groove of the male hinge, locking of the first fixed unfolding hinge mechanism is achieved, locking of the second fixed unfolding hinge mechanism is achieved in a similar way, and then the antenna plate is stably fixed after being unfolded. Therefore, the problem of cross-plate unfolding of the multi-folding antenna structure can be solved.

Description

Technical Field

[0001] The present invention relates to the technical field of hinges, and in particular to a hinge for multi-fold deployment of a spacecraft. Background Art

[0002] Deployable mechanisms are commonly used in the mechanical systems of spacecraft, effectively solving problems such as limited launch envelopes. With the demand for large space structures, multi-fold deployment mechanisms are being applied more and more widely. However, multiple folding requires the deployment mechanism to be able to compact and deploy in sequence, facing the problem of cross-panel deployment. Traditional deployment drive sources cannot meet the requirements, so researchers have designed different deployment mechanisms to achieve cross-panel deployment.

[0003] Chinese Patent No. 201520469866 discloses a virtual-axis deployment hinge for solving the problem of seamless splicing of flat-panel deployable antennas. This virtual-axis hinge can ensure that there are no protrusions on the radiation surface of the antenna after deployment through two four-bar linkages, and there is no gap between two antenna modules.

[0004] However, compared with the above-mentioned prior art, based on the multi-fold structure of deployable antennas, a new cross-panel deployment mechanism has become the key to its deployment. Therefore, we propose a hinge for multi-fold deployment of a spacecraft to solve the above-mentioned problems. Summary of the Invention

[0005] The purpose of this part is to outline some aspects of the embodiments of the present invention and briefly introduce some preferred embodiments. Some simplifications or omissions may be made in this part, as well as in the abstract and title of the present invention, to avoid obscuring the purpose of this part, the abstract, and the title. However, such simplifications or omissions cannot be used to limit the scope of the present invention.

[0006] Therefore, the purpose of the present invention is to provide a hinge for multi-fold deployment of a spacecraft, which can solve the problem of cross-panel deployment of multi-fold antenna structures.

[0007] To solve the above technical problems, the present invention provides a hinge for multi-fold deployment of a spacecraft, adopting the following technical scheme: including a male hinge, with a first fixed deployment hinge mechanism and a second fixed deployment hinge mechanism respectively arranged at both ends of the male hinge, and a linkage mechanism arranged in the middle of the male hinge; The first fixed unfolding hinge mechanism includes a first female hinge, a locking hook, a torsion spring, an eccentric shaft, a pin shaft and a volute spring. The pin shaft is rotatably arranged at one end of the male hinge. The first female hinge is fixedly arranged on the outer circle of the pin shaft. A first mounting plate is fixedly arranged at the end of the first female hinge. A first connection hole is fixedly formed on the first mounting plate. The eccentric shaft is arranged on the first female hinge. The locking hook is hinged to the eccentric shaft in a hole-shaft fit mode. The axis of the torsion spring is coaxially installed with the eccentric shaft. The tail of the torsion spring rests on the center of the locking hook. A stop shaft and a spring coil sleeve are arranged on the first female hinge. The head of the torsion spring is restricted from rotating by the stop shaft. One end of the inner circle of the volute spring is fixed on the pin shaft, and one end of the outer circle of the volute spring is fixed on the spring coil sleeve.

[0008] Preferably, the second fixed unfolding hinge mechanism includes a second female hinge. The second female hinge is rotatably arranged at the end of the male hinge far from the first female hinge. The second female hinge and the first female hinge have the same structure, and the second female hinge and the first female hinge are symmetrically distributed about the center line of the male hinge.

[0009] Preferably, two lock shaft grooves symmetrically distributed about the center line of the male hinge are fixedly arranged at the bottom of the male hinge. The end of the locking hook far from the eccentric shaft is stuck on the corresponding lock shaft groove.

[0010] Preferably, a second mounting plate is fixedly arranged at the end of the second female hinge. A second connection hole is fixedly formed on the second mounting plate.

[0011] Preferably, an L-shaped support frame is fixedly arranged on the side of the male hinge. A damper is fixedly arranged on the side of the L-shaped support frame. One end of the pin shaft on the second female hinge is connected to the damper. A connecting rod is fixedly arranged on the outer circle of the pin shaft on the second female hinge, and the other end of the connecting rod is fixedly connected to the second female hinge.

[0012] Preferably, the linkage mechanism includes two gears. Both of the two gears are rotatably arranged in the middle of the male hinge through bearings. The two gears are meshed with each other. Sector gears are fixedly arranged on the surfaces of the second female hinge and the first female hinge, and the mutually adjacent sector gears and gears are meshed with each other.

[0013] Preferably, it further includes two antenna plates, and the two antenna plates are respectively installed on the first mounting plate and the second mounting plate.

[0014] In summary, the present invention includes at least one of the following beneficial effects: 1. After the spacecraft is in orbit, the antenna panel is released by the compression and release device due to the installation of the first fixed deployment hinge mechanism and the second fixed deployment hinge mechanism. Since one end of the inner ring of the volute spring is fixed on the pin shaft and the other end of the outer ring is fixed on the spring coil sleeve, it drives the first female hinge to rotate around the pin shaft. When the first female hinge rotates from the retracted state to the deployed state, the torsion spring presses the locking hook by its torque until it finally slides onto the locking shaft groove of the male hinge, realizing the locking of the first fixed deployment hinge mechanism. Similarly, the locking of the second fixed deployment hinge mechanism is realized, and then the antenna panel is stably fixed after deployment. Therefore, the problem of cross-panel deployment of the multi-fold antenna structure can be solved. 2. Through the installation of the linkage mechanism, during the relative rotation of the first female hinge and the second female hinge, the two sector gears are respectively engaged with the two gears, so that the second female hinge and the first female hinge can rotate relatively synchronously, and then the deployment hinge mechanisms on both sides of the male hinge can be deployed synchronously. 3. Through the installation of the L-shaped support frame, the connecting rod and the damper, the slow-speed movement at the end of the hinge deployment is realized, ensuring the stable deployment of the antenna panel. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can be obtained based on these drawings.

[0016] Figure 1 It is a schematic perspective view of the first angle of a hinge for multi-fold deployment of a spacecraft according to the present invention; Figure 2 It is a schematic perspective view of the second angle of a hinge for multi-fold deployment of a spacecraft according to the present invention; Figure 3 It is a schematic perspective view from below of a hinge for multi-fold deployment of a spacecraft according to the present invention; Figure 4 It is a schematic front view of the rear side of the present invention; Figure 5 It is a schematic front view of the front side of the present invention; Figure 6 It is a schematic view of the structure when the first female hinge of the present invention is in the retracted state; Figure 7 It is a schematic view of the structure of the antenna panel in the retracted state of the present invention; Figure 8 It is a schematic view of the structure of the antenna panel in the deployed state of the present invention.

[0017] Description of the reference numerals: 1. First female hinge; 2. Second female hinge; 3. Lock hook; 4. Torsion spring; 5. Eccentric shaft; 6. Pin shaft; 7. Volute spring; 8. Stop shaft; 9. Male hinge; 10. Spring sleeve; 11. Link; 12. Gear; 13. Bearing; 14. Damper; 15. Sector gear; 16. First mounting plate; 17. Antenna plate. Detailed implementation manners

[0018] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0019] Please refer to Figures 1-6 , an embodiment provided by the present invention: A hinge for multi-fold deployment of a spacecraft includes a male hinge 9. First fixed deployment hinge mechanisms are respectively arranged at both ends of the male hinge 9. The first fixed deployment hinge mechanisms and the second fixed deployment hinge mechanisms have the same structure. The present invention focuses on taking the first fixed deployment hinge mechanism as an example.

[0020] Further, the first fixed deployment hinge mechanism includes a first female hinge 1, a lock hook 3, a torsion spring 4, an eccentric shaft 5, a pin shaft 6 and a volute spring 7. The pin shaft 6 is rotatably arranged at one end of the male hinge 9. The first female hinge 1 is fixedly arranged on the outer circle of the pin shaft 6. The eccentric shaft 5 is arranged on the first female hinge 1. The lock hook 3 is hinged to the eccentric shaft 5 in a hole-shaft fit mode. The axis of the torsion spring 4 is coaxially installed with the eccentric shaft 5. The tail of the torsion spring 4 rests on the center of the lock hook 3. A stop shaft 8 and a spring sleeve 10 are arranged on the first female hinge 1. The head of the torsion spring 4 is restricted from rotating by the stop shaft 8. One end of the inner circle of the volute spring 7 is fixed on the pin shaft 6, and one end of the outer circle of the volute spring 7 is fixed on the spring sleeve 10.

[0021] Further, two lock shaft grooves symmetrically distributed about the center line of the male hinge 9 are fixedly arranged at the bottom of the male hinge 9. The end of the lock hook 3 far from the eccentric shaft 5 is stuck on the corresponding lock shaft grooves.

[0022] Specifically, since one end of the inner circle of the volute spring 7 is fixed on the pin shaft 6 and one end of the outer circle is fixed on the spring sleeve 10, driving the first female hinge 1 to rotate around the pin shaft 6. When the first female hinge 1 rotates from the retracted state ( Figure 5 ) to the deployed state ( Figure 1 ), the torsion spring 4 presses the lock hook 3 by its torque until it finally slides onto the lock shaft grooves of the male hinge 9, realizing the locking of the first fixed deployment hinge mechanism.

[0023] Further, for the second female hinge 2 of the second fixed unfolding hinge mechanism, the second female hinge 2 is rotatably arranged at one end of the male hinge 9 away from the first female hinge 1. The second female hinge 2 has the same structure as the first female hinge 1, and the second female hinge 2 and the first female hinge 1 are symmetrically distributed about the center line of the male hinge 9. Similarly, when the second female hinge 2 rotates from the retracted state to the unfolded state, the torsion spring 4 on the second female hinge 2 presses the corresponding lock hook 3 by virtue of its torque until it finally slides onto another lock shaft groove of the male hinge 9, realizing the locking of the second fixed unfolding hinge mechanism.

[0024] Therefore, through the installation of the first fixed unfolding hinge mechanism and the second fixed unfolding hinge mechanism, the antenna panel 17 can be stably fixed after being successfully unfolded, and the problem of cross-panel unfolding of the multi-folded antenna structure can be solved.

[0025] To ensure the synchronization of the unfolding of the first fixed unfolding hinge mechanism and the second fixed unfolding hinge mechanism, a linkage mechanism is arranged in the middle of the male hinge 9. The linkage mechanism has two gears 12. Both of the two gears 12 are rotatably arranged in the middle of the male hinge 9 through bearings 13. The two gears 12 mesh with each other. Sector gears 15 are fixedly arranged on the surfaces of the second female hinge 2 and the first female hinge 1. The mutually adjacent sector gears 15 and gears 12 mesh with each other. With such an arrangement, the second female hinge 2 and the first female hinge 1 can rotate relative to each other synchronously, and thus the unfolding hinge mechanisms on both sides of the male hinge 9 can be unfolded synchronously.

[0026] Further, a first mounting plate 16 is fixedly arranged at the end of the first female hinge 1. A first connection hole is fixedly opened on the first mounting plate 16. A second mounting plate is fixedly arranged at the end of the second female hinge 2. A second connection hole is fixedly opened on the second mounting plate. The first mounting plate 16 and the second mounting plate are both fixedly connected to the antenna panel 17. The two antenna panels 17 are respectively connected to the corresponding connection hole positions, and a set of this hinge is installed on each side of the antenna panel 17.

[0027] Further, an L-shaped support frame is fixedly arranged on the side surface of the male hinge 9. A damper 14 is fixedly arranged on the side surface of the L-shaped support frame. One end of a pin shaft 6 on the second female hinge 2 is connected to the damper 14. A connecting rod 11 is fixedly arranged on the outer ring of the pin shaft 6 on the second female hinge 2. The other end of the connecting rod 11 is fixedly connected to the second female hinge 2. Through the connecting rod 11, the damper 14 is used for buffering and decelerating to realize the slow-speed movement at the end of the hinge unfolding.

[0028] To more intuitively reflect the retracted and unfolded states of the antenna panel 17, please refer to Figure 7 , before the spacecraft is launched, the hinge is in the retracted state, the antenna panel 17 is retracted, and it is pressed by the pressing and releasing device of the antenna panel 17 itself.

[0029] Please also refer to Figure 8, after the spacecraft is in orbit, the clamping and releasing device releases the antenna panel 17, and the first female hinge 1 rotates from the retracted state ( Figure 5 ), and rotates to the deployed state ( Figure 1 ), and both the first fixed deployment hinge mechanism and the second fixed deployment hinge mechanism are locked, so that the antenna panel 17 is stably fixed after being deployed.

[0030] Working principle: Connect the two antenna panels 17 to the corresponding connection holes respectively, and install a set of this hinge on each side of the antenna panel 17. Before launch, the hinge is in the retracted state, and the antenna panel 17 is retracted and compressed by the clamping and releasing device of the antenna panel 17 itself. After the spacecraft is in orbit, the clamping and releasing device releases the antenna panel 17. Since one end of the inner ring of the volute spring 7 is fixed on the pin shaft 6 and the other end of the outer ring is fixed on the spring housing 10, it drives the first female hinge 1 to rotate around the pin shaft 6. When the first female hinge 1 rotates from the retracted state ( Figure 5 ), and rotates to the deployed state ( Figure 1 ), the torsion spring 4 presses the locking hook 3 by its torque until it finally slides onto the locking shaft groove of the male hinge 9, realizing the locking of the first fixed deployment hinge mechanism. Similarly, the locking of the second fixed deployment hinge mechanism is realized, so that the antenna panel 17 is stably fixed after being deployed. And during the relative rotation of the first female hinge 1 and the second female hinge 2, the fan-shaped teeth 15 and the gear 12 that are close to each other are engaged with each other, so that the second female hinge 2 and the first female hinge 1 can rotate relatively synchronously, and thus the deployment hinge mechanisms on both sides of the male hinge 9 can be deployed synchronously. In addition, through the connecting rod 11, the damper 14 is used for buffering and decelerating to realize the slow-speed movement at the end of the hinge deployment, ensuring the stable deployment of the antenna panel 17.

[0031] The above are all the preferred embodiments of the present invention, and the protection scope of the present invention is not limited accordingly. Therefore, all equivalent changes made according to the structure, shape, and principle of the present invention should be covered within the protection scope of the present invention.

Claims

1. A hinge for multiple folding and unfolding of a spacecraft, comprising a male hinge (9), characterized in that: Both ends of the male hinge (9) are respectively provided with a first fixed unfolding hinge mechanism and a second fixed unfolding hinge mechanism, and a linkage mechanism is arranged in the middle of the male hinge (9). The first fixed unfolding hinge mechanism includes a first female hinge (1), a locking hook (3), a torsion spring (4), an eccentric shaft (5), a pin shaft (6) and a volute spring (7). The pin shaft (6) is rotatably arranged at one end of the male hinge (9), the first female hinge (1) is fixedly arranged on the outer ring of the pin shaft (6), a first mounting plate (16) is fixedly arranged at the end of the first female hinge (1), a first connection hole is fixedly formed in the first mounting plate (16), the eccentric shaft (5) is arranged on the first female hinge (1), the locking hook (3) is hinged to the eccentric shaft (5) in a hole-shaft fit mode, the axis of the torsion spring (4) is coaxially installed with the eccentric shaft (5), the tail of the torsion spring (4) is placed on the center of the locking hook (3), a stop shaft (8) and a spring coiling sleeve (10) are arranged on the first female hinge (1), the head of the torsion spring (4) is restricted from rotating by the stop shaft (8), one end of the inner ring of the volute spring (7) is fixed on the pin shaft (6), and one end of the outer ring of the volute spring (7) is fixed on the spring coiling sleeve (10).

2. The hinge for multiple folding and unfolding of a spacecraft according to claim 1, characterized in that: The second fixed unfolding hinge mechanism is a second female hinge (2), and the second female hinge (2) is rotatably arranged at the end of the male hinge (9) far from the first female hinge (1). The second female hinge (2) has the same structure as the first female hinge (1), and the second female hinge (2) and the first female hinge (1) are symmetrically distributed about the center line of the male hinge (9).

3. A hinge for multiple folding and unfolding of a spacecraft, as claimed in claim 2, wherein: Two lock shaft grooves symmetrically distributed about the center line of the male hinge (9) are fixedly arranged at the bottom of the male hinge (9), and the end of the locking hook (3) far from the eccentric shaft (5) is stuck on the corresponding lock shaft groove.

4. A hinge for multiple folding and unfolding of a spacecraft, as claimed in claim 2, wherein: A second mounting plate is fixedly arranged at the end of the second female hinge (2), and a second connection hole is fixedly formed in the second mounting plate.

5. A hinge for multiple folding and unfolding of a spacecraft, as claimed in claim 4, wherein: An L-shaped support frame is fixedly arranged on the side surface of the male hinge (9), a damper (14) is fixedly arranged on the side surface of the L-shaped support frame, one end of the pin shaft (6) on the second female hinge (2) is connected with the damper (14), a connecting rod (11) is fixedly arranged on the outer ring of the pin shaft (6) on the second female hinge (2), and the other end of the connecting rod (11) is fixedly connected with the second female hinge (2).

6. A hinge for multiple folding and unfolding of a spacecraft, as claimed in claim 5, wherein: The linkage mechanism includes two gears (12), both of the two gears (12) are rotatably arranged in the middle of the male hinge (9) through bearings (13), the two gears (12) are meshed with each other, sector gears (15) are fixedly arranged on the surfaces of the second female hinge (2) and the first female hinge (1), and the mutually adjacent sector gears (15) and gears (12) are meshed with each other.

7. A hinge for multiple folding and unfolding of a spacecraft, as claimed in claim 4, wherein: Two antenna plates (17) are further included, and the two antenna plates (17) are respectively installed on the first mounting plate (16) and the second mounting plate.

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