CN213776049U - Hinge structure for satellite - Google Patents
Hinge structure for satellite Download PDFInfo
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- CN213776049U CN213776049U CN202022595769.6U CN202022595769U CN213776049U CN 213776049 U CN213776049 U CN 213776049U CN 202022595769 U CN202022595769 U CN 202022595769U CN 213776049 U CN213776049 U CN 213776049U
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- hinge
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- torsion spring
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Abstract
The utility model relates to the technical field of satellites, in particular to a hinge structure for satellites, which comprises a female hinge, a male hinge, a main shaft, a first torsion spring and a second torsion spring, wherein the female hinge is provided with a first mounting hole and a second mounting hole in parallel at intervals, and the first mounting hole and the second mounting hole are arranged coaxially; a spindle hole is formed in the male hinge, is arranged between the first mounting hole and the second mounting hole and is coaxial with the first mounting hole; the main shaft penetrates through the first mounting hole, the main shaft hole and the second mounting hole; the first torsion spring and the second torsion spring are sleeved on the main shaft, one end of the first torsion spring is connected with the position of the female hinge, which is provided with the first mounting hole, the other end of the first torsion spring is connected with the male hinge, the second torsion spring is connected with the position of the female hinge, which is provided with the second mounting hole, and the other end of the second torsion spring is connected with the male hinge. The utility model discloses an expansion of the moment drive hinge of first torsional spring and second torsional spring can make the expansion power that public hinge and female hinge received unanimous, can not incline to one side.
Description
Technical Field
The utility model relates to a satellite technology field especially relates to a hinge structure for satellite.
Background
For the existing solar wing unfolding mechanism, a pin locking groove type hinge is usually used, a volute spiral spring is used in the hinge structure, the volute spiral spring is arranged on one side of the hinge and used for driving the hinge to rotate so as to enable the solar wing to unfold, although the structure can ensure the moment for driving the solar wing to unfold, when the volute spiral spring is used for driving the solar wing to unfold, the forces applied to two sides of the hinge are not completely consistent, and therefore the male hinge end and the female hinge end of the hinge cannot be unfolded completely.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a hinge structure for satellite to when solving "pin locking slot type" hinge drive solar wing and expandes, the power that the both sides of hinge received is not completely unanimous, the unable problem that expandes completely of public hinge end and female hinge end of hinge.
To achieve the purpose, the utility model adopts the following technical proposal:
a hinge structure for a satellite, comprising:
the hinge comprises a female hinge, a first mounting hole and a second mounting hole are arranged on the female hinge in parallel at intervals, and the first mounting hole and the second mounting hole are arranged coaxially;
the male hinge is provided with a spindle hole, and the spindle hole is arranged between the first mounting hole and the second mounting hole and is coaxial with the first mounting hole;
the main shaft penetrates through the first mounting hole, the main shaft hole and the second mounting hole;
first torsional spring and second torsional spring, first torsional spring with the second torsional spring is all established on the main shaft, the one end of first torsional spring with female hinge has been seted up the position of first mounting hole is connected, the other end with public hinge joint, the second torsional spring with female hinge has been seted up the position of second mounting hole is connected, the other end with public hinge joint.
As preferred, female hinge includes first fixed plate and parallel interval and sets up first mounting panel and second mounting panel on first fixed plate, first mounting hole is seted up on the first mounting panel, the second mounting hole is seted up on the second mounting panel, the one end of first torsional spring is connected on the first mounting panel, the one end of second torsional spring is connected on the second mounting panel.
Preferably, the male hinge comprises a main body piece and a connecting assembly, the connecting assembly comprises a first connecting piece and a second connecting piece, one end of the first connecting piece is rotatably connected with the end part of the main shaft, the other end of the first connecting piece is connected with the main body piece, one end of the second connecting piece is rotatably connected with the main shaft away from the end part of the first connecting piece, and the other end of the second connecting piece is connected with the main body piece.
Preferably, the first connecting member includes a first spindle connecting portion and a first body connecting portion connected to each other, the first spindle connecting portion is connected to an end portion of the spindle, an end of the first torsion spring away from the second mounting plate is connected to the first spindle connecting portion, and the first body connecting portion is connected to the body.
Preferably, the first body connecting portion is provided with a first connecting hole, the body member is provided with a third connecting hole, the first fixing member passes through the first connecting hole, and the third connecting hole connects the first connecting member with the body member.
Preferably, the hinge structure for the satellite further comprises a shaft sleeve, the shaft sleeve is fixedly sleeved on the main shaft, and the male hinge is rotatably sleeved on the shaft sleeve through the main shaft hole.
Preferably, the hinge structure for the satellite further comprises a locking assembly and a clamping assembly, the locking assembly is rotatably arranged on the female hinge, the clamping assembly is arranged on the male hinge, a bayonet is arranged on the clamping assembly, and when the hinge structure for the satellite is in an unfolding state, the locking assembly can be clamped on the bayonet.
As preferred, locking Assembly includes pivot, third torsional spring, dwang and fitting pin, the pivot set up in first mounting panel with between the second mounting panel, the dwang rotates to set up in the pivot, the fitting pin sets up the dwang is kept away from pivot one side, the third torsional spring cover is located the pivot, third torsional spring one end butt is in on the female hinge, other end butt is in on the fitting pin so that the fitting pin with joint subassembly butt, when hinge structure is in the expansion state for the satellite, the fitting pin can the joint in the bayonet socket.
Preferably, the locking pin is an eccentric pin.
Preferably, the clamping component comprises an arc-shaped sliding piece and two second fixing plates arranged in parallel at intervals, the arc-shaped sliding piece is arranged between the two second fixing plates, and the locking pin is arranged along the unfolding process of the hinge structure for the satellite and slides to the bayonet from the upper end arc surface of the arc-shaped sliding piece.
The utility model has the advantages that:
the utility model provides a hinge structure for a satellite, wherein a first mounting hole and a second mounting hole which are coaxially arranged are arranged on a female hinge in parallel at intervals; the male hinge is provided with a main shaft hole, and a main shaft penetrates through the first mounting hole, the main shaft hole and the second mounting hole; the first torsion spring and the second torsion spring are both sleeved on the main shaft, one end of the first torsion spring is connected with the position, provided with the first mounting hole, of the female hinge, the other end of the first torsion spring is connected with the male hinge, the second torsion spring is connected with the position, provided with the second mounting hole, of the female hinge, the other end of the second torsion spring is connected with the male hinge, the specifications of the first torsion spring and the second torsion spring are the same, the first torsion spring and the second torsion spring are both sleeved on the main shaft, in the unfolding process of the hinge structure for the satellite, the moments of the first torsion spring and the second torsion spring driving the hinges to unfold are the same, the forces borne by the male hinge and the female hinge can be consistent, the solar wing cannot incline to one side, and the solar wing can be smoothly unfolded.
Drawings
Fig. 1 is a structural view of the hinge structure for a satellite according to the present invention when it is unfolded;
fig. 2 is a structural view of the hinge structure for satellite of the present invention when folded;
fig. 3 is a structural diagram of a fixing plate in the hinge structure for satellite according to the present invention;
fig. 4 is a connection structure diagram of the first connecting member and the second connecting member of the hinge structure for satellite according to the present invention and the main shaft;
fig. 5 is a structural view of a main body part of a male hinge in the hinge structure for a satellite according to the present invention;
fig. 6 is a structural diagram of a locking assembly in the hinge structure for a satellite according to the present invention;
fig. 7 is a structural diagram of the arc-shaped sliding piece in the hinge structure for satellite according to the present invention.
In the figure:
1. performing female hinging; 11. a first fixing plate; 12. a first mounting plate; 121. a first mounting hole; 13. a second mounting plate; 131. a second mounting hole;
2. male hinging; 21. a main body member; 211. a spindle hole; 212. a third connection hole; 22. a first connecting member; 221. a first main shaft connecting part; 222. a first body connecting portion; 2221. a first connection hole; 23. a second connecting member; 231. a second spindle connecting portion; 232. a second body connecting portion; 2321. a second connection hole;
3. a main shaft;
4. a first torsion spring;
5. a second torsion spring;
6. a shaft sleeve;
7. a locking assembly; 71. a rotating shaft; 72. a third torsion spring; 73. rotating the rod; 74. a locking pin;
8. a clamping assembly; 81. a bayonet; 82. an arc-shaped sliding sheet; 83. and a second fixing plate.
Detailed Description
The technical solution of the present invention will be further explained with reference to the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements related to the present invention are shown in the drawings.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection or a removable connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
As shown in fig. 1-7, the utility model provides a hinge structure for satellite, including female hinge 1, male hinge 2, main shaft 3, first torsion spring 4 and second torsion spring 5, wherein the female hinge 1 is provided with first mounting hole 121 and second mounting hole 131 at a distance in parallel, and the first mounting hole 121 and the second mounting hole 131 are provided coaxially; a spindle hole 211 is formed in the male hinge 2, and the spindle hole 211 is arranged between the first mounting hole 121 and the second mounting hole 131 and is coaxial with the first mounting hole 121; the spindle 3 is arranged in the first mounting hole 121, the spindle hole 211 and the second mounting hole 131 in a penetrating manner; the first torsion spring 4 and the second torsion spring 5 are sleeved on the main shaft 3, one end of the first torsion spring 4 is connected with the position of the female hinge 1, which is provided with the first mounting hole 121, the other end of the first torsion spring is connected with the male hinge 2, the second torsion spring 5 is connected with the position of the female hinge 1, which is provided with the second mounting hole 131, the other end of the second torsion spring is connected with the male hinge 2, the first torsion spring 4 and the second torsion spring 5 are sleeved on the main shaft 3 in the same specification, in the unfolding process of the hinge structure for the satellite, the moments of the first torsion spring 4 and the second torsion spring 5 drive the unfolding of the hinge, and the forces borne by the male hinge 2 and the female hinge 1 are consistent and cannot deflect to one side.
Specifically, the female hinge 1 includes a first fixing plate 11 and a first mounting plate 12 and a second mounting plate 13 arranged on the first fixing plate 11 in parallel at an interval, the first fixing plate 11 is provided with a plurality of first positioning holes, the male hinge 2 is provided with a plurality of second positioning holes, the satellite can be connected between the star body and the solar wing plate by the hinge structure through the first positioning holes and the second positioning holes, the solar wing plate can be unfolded from the star body, the satellite can be connected between the two solar wing plates by the hinge structure, the two folded solar wing plates can be unfolded, the first mounting hole 121 is arranged on the first mounting plate 12, the second mounting hole 131 is arranged on the second mounting plate 13, one end of the first torsion spring 4 is inserted on the first mounting plate 12, one end of the second torsion spring 5 is inserted on the second mounting plate 13, the first mounting plate 12 and the second mounting plate 13 are plate-shaped, the structure is firm, the moment of the end parts when the first torsion spring 4 and the second torsion spring 5 are compressed can be borne, and the installation and the disassembly are convenient.
Specifically, public hinge 2 includes main part 21 and coupling assembling, coupling assembling includes first connecting piece 22 and second connecting piece 23, the one end of first connecting piece 22 is rotated and is connected in the tip of main shaft 3, the other end is connected in main part 21, the one end of second connecting piece 23 is rotated and is connected in the tip that main shaft 3 kept away from first connecting piece 22, the other end is connected in main part 21, compare in the public hinge structure of integral type, it is more convenient to install and dismantle, and only need change the part that damages when the part of public hinge 2 damages, need not change the whole of public hinge 2 structure.
Specifically, the first connecting member 22 includes a first main shaft connecting portion 221 and a first main body connecting portion 222 which are connected to each other, the first main shaft connecting portion 221 is rotatably connected to an end portion of the main shaft 3, an end of the first torsion spring 4 away from the second mounting plate 13 is connected to the first main shaft connecting portion 221, the second connecting member 23 includes a second main shaft connecting portion 231 and a second main body connecting portion 232 which are connected to each other, the second main shaft connecting portion 231 is rotatably connected to another end portion of the main shaft 3, an end of the second torsion spring 5 away from the second mounting plate 13 is connected to the second main shaft connecting portion 231, the first main body connecting portion 222 is connected to the main body member 21, the second main body connecting portion 232 is connected to the main body member 21, when the hinge structure for a satellite is in a folded state, the first main shaft connecting portion 221 receives a moment of the first torsion spring 4, the second main shaft connecting portion 231 receives a moment of the second torsion spring 5, during an unfolding of the hinge structure for a satellite, the first torsion spring 4 releases torque to drive the first connecting piece 22 through the first main shaft connecting part 221 so as to drive the main body piece 21, the second torsion spring 5 releases torque to drive the second connecting piece 23 through the second main shaft connecting part 231 so as to drive the main body piece 21 from the other side, the same torque on two sides of the main body piece 21 is ensured, and the male hinge 2 and the female hinge 1 of the hinge structure for the satellite are completely unfolded.
Specifically, the first body connecting portion 222 is provided with a first connecting hole 2221, the second body connecting portion 232 is provided with a second connecting hole 2321, the body member 21 is provided with a third connecting hole 212, the first fixing member passes through the first connecting hole 2221, the third connecting hole 212 and the second connecting hole 2321 to connect the body member 21 between the first connecting member 22 and the second connecting member 23, the first fixing member is a bolt, so that the mounting and dismounting are convenient, the locking effect is good, in other embodiments, the first fixing member may also use a pin, and thus, no limitation is made.
Specifically, the hinge structure for the satellite further comprises a shaft sleeve 6, the shaft sleeve 6 is fixedly sleeved on the main shaft 3, the male hinge 2 is rotatably sleeved on the shaft sleeve 6 through a main shaft hole 211, a clamp spring is arranged in the main shaft hole 211 of the male hinge 2 and used for limiting the position of the shaft sleeve 6 on the main shaft 3, the male hinge 2 is rotatably sleeved on the outer surface of the shaft sleeve 6, rotating friction of the male hinge 2 is reduced, and abrasion of the main shaft hole 211 on the main shaft 3 in the process of repeated unfolding of the hinge structure for the satellite is prevented.
Specifically, hinge structure for satellite still includes locking Assembly 7 and joint subassembly 8, and locking Assembly 7 rotates to be set up on female hinge 1, and joint subassembly 8 sets up on public hinge 2, is provided with bayonet 81 on the joint subassembly 8, and when hinge structure for satellite was in the expansion state, locking Assembly 7 can the joint in bayonet 81, prevents that hinge structure for satellite from expanding excessively to lead to the unable abundant sunlight irradiation of receiving of solar wing panel face.
Furthermore, the locking assembly 7 includes a rotating shaft 71, a third torsion spring 72, a rotating rod 73 and a locking pin 74, the rotating shaft 71 is disposed between the first mounting plate 12 and the second mounting plate 13, the first mounting plate 12 is provided with a third mounting hole, the second mounting plate 13 is provided with a fourth mounting hole, the rotating shaft 71 is disposed through the third mounting hole and the fourth mounting hole and fixed by bolts, the mounting and dismounting are convenient, the rotating rod 73 is rotatably disposed on the rotating shaft 71, the locking pin 74 is disposed at an end of the rotating rod 73 far from the rotating shaft 71, the third torsion spring 72 is sleeved on the rotating shaft 71, one end of the rotating shaft is abutted against the female hinge 1, the other end of the rotating shaft is abutted against the locking pin 74 to make the locking pin 74 abut against the clamping assembly 8, in the process of unfolding the hinge structure for the satellite, the locking pin 74 can abut against an upper surface of the clamping assembly under the action of the moment of the third torsion spring 72, when the hinge structure for the satellite is in the unfolded state, the locking pin 74 can be clamped to the bayonet 81 under the action of the torque of the third torsion spring 72, so that the hinge structure for the satellite is prevented from being excessively unfolded.
Specifically, the locking pin 74 is an eccentric pin, and when the hinge structure for a satellite is unfolded, the eccentric pin can be rotated by an adjusting portion at one end of the eccentric pin, and the relative position of the unfolded male hinge 2 and the unfolded female hinge 1 can be finely adjusted by abutting different positions of the eccentric pin against the bayonet 81.
Specifically, the clamping component 8 comprises an arc-shaped sliding piece 82 and two second fixing plates 83 arranged in parallel at intervals, the arc-shaped sliding piece 82 is arranged between the two second fixing plates 83, a fifth mounting hole is formed in the second fixing plate 83, a sixth mounting hole aligned with the fifth mounting hole is formed in the arc-shaped sliding piece 82, the second mounting piece penetrates through the fifth mounting hole and the sixth mounting hole to fix the arc-shaped sliding piece 82 between the two second fixing plates 83, the second mounting piece is a bolt, when the hinge structure for the satellite is in a folded state, the locking pin 74 abuts against the upper end of the arc-shaped sliding piece 82, the locking pin 74 slides to the bayonet 81 along the upper end face of the arc-shaped sliding piece 82 in the unfolding process of the hinge structure for the satellite, the arc-shaped upper end face of the arc-shaped sliding piece 82 in the unfolding process plays a guiding role, and the stable and undulation-free unfolding process of the hinge structure for the satellite is ensured.
It is obvious that the above embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. A hinge structure for a satellite, comprising:
the hinge comprises a female hinge (1), wherein a first mounting hole (121) and a second mounting hole (131) are formed in the female hinge (1) in parallel at intervals, and the first mounting hole (121) and the second mounting hole (131) are arranged coaxially;
the male hinge (2) is provided with a spindle hole (211), and the spindle hole (211) is arranged between the first mounting hole (121) and the second mounting hole (131) and is coaxial with the first mounting hole (121);
the main shaft (3) penetrates through the first mounting hole (121), the main shaft hole (211) and the second mounting hole (131);
first torsional spring (4) and second torsional spring (5), first torsional spring (4) with second torsional spring (5) are all established main shaft (3) are last, the one end of first torsional spring (4) with female hinge (1) has been seted up the position of first mounting hole (121) is connected, the other end with public hinge (2) are connected, second torsional spring (5) with female hinge (1) has been seted up the position of second mounting hole (131) is connected, the other end with public hinge (2) are connected.
2. The hinge structure for satellite according to claim 1, wherein the female hinge (1) comprises a first fixing plate (11) and a first mounting plate (12) and a second mounting plate (13) which are arranged on the first fixing plate (11) in parallel at an interval, the first mounting hole (121) is opened on the first mounting plate (12), the second mounting hole (131) is opened on the second mounting plate (13), one end of the first torsion spring (4) is connected on the first mounting plate (12), and one end of the second torsion spring (5) is connected on the second mounting plate (13).
3. The hinge structure for satellite according to claim 2, wherein the male hinge (2) comprises a main body member (21) and a connecting assembly, the connecting assembly comprising a first connecting member (22) and a second connecting member (23), one end of the first connecting member (22) is rotatably connected to the end of the main shaft (3), the other end is connected to the main body member (21), one end of the second connecting member (23) is rotatably connected to the end of the main shaft (3) away from the first connecting member (22), and the other end is connected to the main body member (21).
4. The hinge structure for satellite according to claim 3, wherein the first connecting member (22) includes a first main shaft connecting portion (221) and a first body connecting portion (222) connected to each other, the first main shaft connecting portion (221) is connected to an end of the main shaft (3), one end of the first torsion spring (4) remote from the second mounting plate (13) is connected to the first main shaft connecting portion (221), and the first body connecting portion (222) is connected to the body member (21).
5. The hinge structure for satellite according to claim 4, wherein the first body connecting portion (222) is provided with a first connecting hole (2221), the main body member (21) is provided with a third connecting hole (212), the first fixing member passes through the first connecting hole (2221), and the third connecting hole (212) connects the first connecting member (22) and the main body member (21).
6. The hinge structure for satellite according to claim 1, further comprising a shaft sleeve (6), wherein the shaft sleeve (6) is fixedly sleeved on the main shaft (3), and the male hinge (2) is rotatably sleeved on the shaft sleeve (6) through the main shaft hole (211).
7. The hinge structure for the satellite according to claim 2, further comprising a locking assembly (7) and a clamping assembly (8), wherein the locking assembly (7) is rotatably arranged on the female hinge (1), the clamping assembly (8) is arranged on the male hinge (2), a bayonet (81) is arranged on the clamping assembly (8), and when the hinge structure for the satellite is in the unfolded state, the locking assembly (7) can be clamped in the bayonet (81).
8. The hinge structure for satellite according to claim 7, wherein the locking assembly (7) comprises a rotation shaft (71), a third torsion spring (72), a rotation lever (73), and a locking pin (74), the rotating shaft (71) is arranged between the first mounting plate (12) and the second mounting plate (13), the rotating rod (73) is rotatably arranged on the rotating shaft (71), the locking pin (74) is arranged on one side of the rotating rod (73) far away from the rotating shaft (71), the rotating shaft (71) is sleeved with the third torsion spring (72), one end of the third torsion spring (72) is abutted against the female hinge (1), the other end of the third torsion spring (72) is abutted against the locking pin (74) so that the locking pin (74) is abutted against the clamping component (8), when the hinge structure for the satellite is in a unfolding state, the locking pin (74) can be clamped in the bayonet (81).
9. The hinge structure for satellite according to claim 8, wherein the locking pin (74) is an eccentric pin.
10. The hinge structure for satellite according to claim 8, wherein the clamping assembly (8) comprises an arc-shaped sliding piece (82) and two second fixing plates (83) arranged in parallel and spaced, the arc-shaped sliding piece (82) is arranged between the two second fixing plates (83), and the locking pin (74) can slide to the bayonet (81) along the upper end arc surface of the arc-shaped sliding piece (82) in the unfolding process of the hinge structure for satellite.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022595769.6U CN213776049U (en) | 2020-11-11 | 2020-11-11 | Hinge structure for satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022595769.6U CN213776049U (en) | 2020-11-11 | 2020-11-11 | Hinge structure for satellite |
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| Publication Number | Publication Date |
|---|---|
| CN213776049U true CN213776049U (en) | 2021-07-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022595769.6U Active CN213776049U (en) | 2020-11-11 | 2020-11-11 | Hinge structure for satellite |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113915230A (en) * | 2021-11-29 | 2022-01-11 | 北京微纳星空科技有限公司 | Anti-backlash locking hinge |
| CN114001086A (en) * | 2021-12-31 | 2022-02-01 | 北京微纳星空科技有限公司 | Low-impact energy-storage pre-tightening hinge |
| CN113958597B (en) * | 2021-10-18 | 2022-08-23 | 北京微纳星空科技有限公司 | Triggering locking hinge device |
| CN115637903A (en) * | 2022-11-11 | 2023-01-24 | 苏州馥昶空间技术有限公司 | Cubic star solar wing chain and cubic star sailboard |
| US20230063114A1 (en) * | 2021-08-26 | 2023-03-02 | Commscope Technologies Llc | Mounting device and clamping device for base station antenna |
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2020
- 2020-11-11 CN CN202022595769.6U patent/CN213776049U/en active Active
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230063114A1 (en) * | 2021-08-26 | 2023-03-02 | Commscope Technologies Llc | Mounting device and clamping device for base station antenna |
| CN113958597B (en) * | 2021-10-18 | 2022-08-23 | 北京微纳星空科技有限公司 | Triggering locking hinge device |
| CN113915230A (en) * | 2021-11-29 | 2022-01-11 | 北京微纳星空科技有限公司 | Anti-backlash locking hinge |
| CN113915230B (en) * | 2021-11-29 | 2022-09-13 | 北京微纳星空科技有限公司 | Anti-backlash locking hinge |
| CN114001086A (en) * | 2021-12-31 | 2022-02-01 | 北京微纳星空科技有限公司 | Low-impact energy-storage pre-tightening hinge |
| CN115637903A (en) * | 2022-11-11 | 2023-01-24 | 苏州馥昶空间技术有限公司 | Cubic star solar wing chain and cubic star sailboard |
| CN115637903B (en) * | 2022-11-11 | 2023-09-19 | 苏州馥昶空间技术有限公司 | Cube star solar wing chain and cube star sailboard |
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