CN216233082U - Satellite unfolding and locking mechanism - Google Patents
Satellite unfolding and locking mechanism Download PDFInfo
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- CN216233082U CN216233082U CN202122970192.7U CN202122970192U CN216233082U CN 216233082 U CN216233082 U CN 216233082U CN 202122970192 U CN202122970192 U CN 202122970192U CN 216233082 U CN216233082 U CN 216233082U
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Abstract
The utility model relates to the technical field of spacecrafts, in particular to a satellite unfolding and locking mechanism which comprises a female hinge, wherein the female hinge comprises a first transverse plate and two first side plates connected to two ends of the first transverse plate; the male hinge is hinged with the female hinge; the locking assembly comprises a fixing piece and a locking pin, the fixing piece is connected to the first transverse plate, a guide cavity is formed in the direction parallel to the first side plate, the locking pin can move along the guide cavity and partially extends out of the fixing piece, and the locking pin can selectively enable the female hinge and the male hinge to rotate relatively or to be static relatively. When the female hinge and the male hinge are in the unfolding state, the locking pin in the locking assembly can enable the female hinge and the male hinge to be relatively static and completely unfolded, compared with the existing pin locking type unfolding and locking mechanism, the locking mechanism has the advantages of simpler structure, stable function, accurate positioning and low processing cost, and can completely meet the unfolding and locking functions of 50-100 kg-grade satellite solar wings for microsatellites.
Description
Technical Field
The utility model relates to the technical field of spacecrafts, in particular to a satellite unfolding and locking mechanism.
Background
The satellite solar wing is in a folded state in the launching stage, and the satellite and the arrow are unfolded and locked after being separated, so that the energy supply of the whole satellite is ensured. In the launching stage, the locking mechanism is unfolded to fix the solar wing on the star body, so that high-rigidity connection between the solar wing and the whole star is realized, and accessories such as the solar wing and the like can bear complex environments such as impact, vibration, overload and the like of a launching section without being damaged; after the star and the arrow are separated, the unlocking function is completed according to the program control or remote control instruction, the constraint on the solar cell array is removed, the unfolding and locking of the solar wing are realized by the unfolding and locking mechanism, and a solar wing unfolding and positioning signal is provided.
The existing mini-satellite unfolding and locking mechanism adopts a pin locking type unfolding and locking mechanism which is complex in structure and relatively high in requirements on machining and mounting precision, so that high cost is brought.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a satellite unfolding and locking mechanism which is simple in structure, stable in function and low in processing cost.
In order to achieve the purpose, the utility model adopts the following technical scheme:
a satellite deployment locking mechanism comprising:
the female hinge comprises a first transverse plate and two first side plates connected to two ends of the first transverse plate;
the male hinge is hinged with the female hinge;
the locking assembly comprises a fixing piece and a locking pin, the fixing piece is connected to the first transverse plate, a guide cavity is formed in the direction parallel to the first side plate, the locking pin can move along the guide cavity and partially extends out of the fixing piece, and the locking pin can selectively enable the female hinge and the male hinge to rotate relatively or to be static relatively.
Preferably, the male hinge comprises a second transverse plate and two second side plates connected to two ends of the second transverse plate, and the second side plates are hinged to the first side plates in a one-to-one correspondence manner.
Preferably, the first side plate and the second side plate are hinged through a rotating shaft.
Preferably, the rotating shaft is sleeved with a torsion spring, and the torsion spring can abut against the second side plate.
Preferably, the male hinge further comprises a positioning plate connected to the second transverse plate, and a locking hole is formed in the positioning plate;
the female hinge and the male hinge are in a furled state, and the locking pin can abut against the outer wall of the positioning plate of the male hinge;
the female hinge and the male hinge are in an unfolded state, and the locking pin can penetrate through the locking hole to limit the relative rotation of the female hinge and the male hinge.
Preferably, one end of the locking pin close to the positioning plate is arc-shaped.
Preferably, the fixing piece is provided with a limiting groove, the locking pin is provided with a limiting part, and the limiting part can slide along the limiting groove and can abut against the inner wall of the limiting groove.
Preferably, the locking assembly further comprises an elastic member, and the elastic member is clamped between the locking pin and the fixing member and can drive the locking pin to move along the guide cavity.
Preferably, the outer wall of the fixing piece is provided with a switch, the locking pin penetrates through the locking hole, and the limiting part can abut against the switch to enable the switch to send out a locking signal.
Preferably, the first transverse plate of the female hinge is provided with a mounting through hole for connecting the solar wing substrate.
The utility model has the beneficial effects that: according to the utility model, the locking assembly is arranged on the first transverse plate of the female hinge, when the female hinge and the male hinge are in the unfolding state, the locking pin in the locking assembly can enable the female hinge and the male hinge to be relatively static and completely unfolded, compared with the existing pin locking type unfolding locking mechanism, the locking mechanism has the advantages of simpler structure, stable function, accurate positioning and low processing cost, and can completely meet the function of unfolding and locking the solar wings of a microsatellite.
Drawings
FIG. 1 is a schematic structural view of a folded satellite unfolding and locking mechanism provided by the present invention;
FIG. 2 is a schematic view of the satellite deployment locking mechanism according to the present invention in a deployed state
FIG. 3 is a cross-sectional view of a locking assembly provided by the present invention;
FIG. 4 is a schematic view of a female hinge structure provided by the present invention;
fig. 5 is a schematic view of a male hinge structure provided by the present invention.
In the figure:
1. performing female hinging; 11. a first transverse plate; 12. a first side plate;
2. male hinging; 21. a second transverse plate; 22. a second side plate; 23. positioning a plate; 231. a locking hole;
3. a locking assembly; 31. a fixing member; 311. a limiting groove; 32. a locking pin; 321. a limiting part; 33. an elastic member;
4. a switch;
5. a torsion spring.
Detailed Description
The technical scheme of the utility model is further explained by combining the attached drawings and the embodiment. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be further noted that, for the convenience of description, only some but not all of the elements associated with the present invention are shown in the drawings.
In the description of the present invention, it should be noted that unless otherwise explicitly stated 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. 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 to 5, the present embodiment provides a satellite unfolding and locking mechanism, which includes a female hinge 1 and a male hinge 2 that are hinged to each other, wherein the female hinge 1 includes a first horizontal plate 11 and two first side plates 12 connected to two ends of the first horizontal plate 11, and planes of the two first side plates 12 are perpendicular to a plane of the first horizontal plate 11; similarly, the male hinge 2 also includes a second horizontal plate 21 and two second side plates 22 connected to two ends of the second horizontal plate 21, the planes of the two second side plates 22 are perpendicular to the plane of the second horizontal plate 21, the male hinge 2 further includes a positioning plate 23 connected to the second horizontal plate 21, wherein the positioning plate 23 is clamped between the two second side plates 22, and the plane of the positioning plate 23 is also perpendicular to the plane of the second horizontal plate 21.
Specifically, the first side plate 12 and the second side plate 22 are hinged in a one-to-one correspondence manner, and in this embodiment, the second side plates 22 are all disposed on the inner side of the first side plate 12. Hinge holes are formed in the first side plate 12, the second side plate 22 and the positioning plate 23, and the rotating shaft sequentially penetrates through the hinge hole of one of the first side plates 12, the hinge hole of one of the second side plates 22, the hinge hole of the positioning plate 23, the hinge hole of the other second side plate 22 and the hinge hole of the other first side plate 12 to complete the hinge connection of the female hinge 1 and the male hinge 2. More specifically, the pivot that this embodiment provided is self-lubricating pivot, and the position that pivot and hinge hole are connected is equipped with the axle sleeve, and wherein the axle sleeve also is self-lubricating axle sleeve, prevents the wearing and tearing between pivot and the hinge hole.
More specifically, the rotating shaft is sleeved with a torsion spring 5, and when the female hinge 1 and the male hinge 2 are in the folded state, the torsion spring 5 is in a compressed state and abuts against the inner wall of the second side plate 22; when the female hinge 1 and the male hinge 2 are in the unfolded state, the torsion spring 5 is in a natural state.
The satellite unfolding locking mechanism provided by the embodiment further comprises a locking assembly 3, wherein the locking assembly 3 comprises a fixing member 31 and a locking pin 32, the fixing member 31 is connected to the first transverse plate 11, a guide cavity is formed in a direction parallel to the first side plate 12, the locking pin 32 can move along the guide cavity and partially extends out of the fixing member 31, and the locking pin 32 can selectively enable the female hinge 1 and the male hinge 2 to rotate relatively or be stationary relatively.
Specifically, a locking hole 231 is formed in the positioning plate 23 of the male hinge, and when the female hinge 1 and the male hinge 2 are in a folded state, the locking pin 32 can abut against the outer wall of the positioning plate 23 of the male hinge 2; when the female hinge 1 and the male hinge 2 are in the unfolded state, the locking pin 32 can pass through the locking hole 231 to limit the relative rotation of the female hinge 1 and the male hinge 2. The end of the locking pin 32 close to the positioning plate 23 is arc-shaped, so that the locking pin 32 can slide along the outer wall of the positioning plate 23 when abutting against the outer wall of the positioning plate 23.
Specifically, the fixing member 31 is provided with a limiting groove 311, the locking pin 32 is provided with a limiting portion 321, the limiting portion 321 can slide along the limiting groove 311 and can abut against the inner wall of the limiting groove 311, and the limiting groove 311 can limit the locking pin 32.
The locking assembly 3 provided by this embodiment further includes an elastic member 33, the elastic member 33 is sandwiched between the locking pin 32 and the fixing member 31, and can drive the locking pin 32 to move along the guiding cavity, when the locking pin 32 abuts against the outer wall of the positioning plate 23, the elastic member 33 is in a compressed state, and along with the continuous expansion of the male hinge 2 and the female hinge 1, when the locking pin 32 moves to the locking hole 231 of the positioning plate 23, under the action of the elastic member 33, the locking pin 32 passes through the locking hole 231, and the locking of the male hinge 2 and the female hinge 1 is completed. The elastic member 33 provided in this embodiment is a spring.
Compared with the existing pin locking type unfolding and locking mechanism, the satellite unfolding and locking mechanism provided by the embodiment has the advantages of simpler structure, stable function, accurate positioning and low processing cost, and can completely meet the function of unfolding and locking the sun wing of a 50 kg-100 kg-class satellite for a microsatellite.
The satellite unfolding and locking mechanism provided by the embodiment further comprises a switch 4, the switch is arranged on the outer wall of the fixing member 31, when the locking pin 32 passes through the locking hole 231 under the driving of the elastic member 33, the limiting part 321 of the locking pin 32 can abut against the switch 4, so that the switch 4 sends out a locking signal, which indicates that the female hinge 1 and the male hinge 2 are unfolded in place and locked. The satellite unfolding and locking mechanism provided by the embodiment integrates the switch 4 and the locking component 3, so that the structure is simpler and more compact, and the stability after unfolding is higher.
It should be noted that, in this embodiment, two installation through holes with a diameter of 3.5mm are formed in the first transverse plate 11 of the female hinge 1, and are used for installation and positioning with the solar wing, and three polyimide insulation sleeves are further provided on the first transverse plate 11, and are used for insulation between the installation screws and the solar wing substrate.
It should be understood that the above-described embodiments of the present invention are merely 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 satellite deployment locking mechanism, comprising:
the female hinge (1) comprises a first transverse plate (11) and two first side plates (12) connected to two ends of the first transverse plate (11);
the male hinge (2) is hinged with the female hinge (1);
the locking assembly (3), the locking assembly (3) includes mounting (31) and locking pin (32), mounting (31) connect in first diaphragm (11), and along being on a parallel with the direction of first curb plate (12) has seted up the direction chamber, locking pin (32) can be followed the chamber motion that leads, and partially stretch out mounting (31), locking pin (32) can make selectively female hinge (1) and male hinge (2) relative rotation or relative stillness.
2. The satellite deployment locking mechanism according to claim 1, characterized in that the male hinge (2) comprises a second transverse plate (21) and two second side plates (22) connected to the second transverse plate (21), the second side plates (22) being hinged to the first side plates (12) in a one-to-one correspondence.
3. The satellite deployment locking mechanism of claim 2, wherein the first side plate (12) and the second side plate (22) are hinged by a pivot.
4. The satellite deployment locking mechanism according to claim 3, characterized in that a torsion spring (5) is sleeved on the rotating shaft, and the torsion spring (5) can abut against the second side plate (22).
5. The satellite deployment locking mechanism according to claim 2, wherein the male hinge (2) further comprises a positioning plate (23) connected to the second cross plate (21), the positioning plate (23) having a locking hole (231) formed therein;
the female hinge (1) and the male hinge (2) are in a furled state, and the locking pin (32) can abut against the outer wall of the positioning plate (23) of the male hinge (2);
the female hinge (1) and the male hinge (2) are in an unfolded state, and the locking pin (32) can pass through the locking hole (231) to limit the relative rotation of the female hinge (1) and the male hinge (2).
6. The satellite deployment locking mechanism of claim 5 wherein the locking pin (32) has a rounded end proximate the positioning plate (23).
7. The satellite unfolding and locking mechanism according to claim 5, wherein the fixing member (31) is provided with a limiting groove (311), the locking pin (32) is provided with a limiting portion (321), and the limiting portion (321) can slide along the limiting groove (311) and can abut against the inner wall of the limiting groove (311).
8. Satellite deployment locking mechanism according to claim 7, characterized in that said locking assembly (3) further comprises an elastic element (33), said elastic element (33) being interposed between said locking pin (32) and said fixed element (31) and being able to drive said locking pin (32) along said guiding cavity.
9. The satellite deployment locking mechanism according to claim 7, wherein the outer wall of the fixed member (31) is provided with a switch (4), the locking pin (32) passes through the locking hole (231), and the limiting portion (321) can abut against the switch (4) to enable the switch (4) to send a locking signal.
10. The satellite unfolding and locking mechanism according to any one of claims 1 to 9, wherein the first transverse plate (11) of the female hinge (1) is provided with a mounting through hole for connecting a solar wing substrate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122970192.7U CN216233082U (en) | 2021-11-30 | 2021-11-30 | Satellite unfolding and locking mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122970192.7U CN216233082U (en) | 2021-11-30 | 2021-11-30 | Satellite unfolding and locking mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN216233082U true CN216233082U (en) | 2022-04-08 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122970192.7U Active CN216233082U (en) | 2021-11-30 | 2021-11-30 | Satellite unfolding and locking mechanism |
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| CN (1) | CN216233082U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117508640A (en) * | 2024-01-02 | 2024-02-06 | 银河航天(北京)网络技术有限公司 | Cross plate hinge and satellite wing array |
-
2021
- 2021-11-30 CN CN202122970192.7U patent/CN216233082U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117508640A (en) * | 2024-01-02 | 2024-02-06 | 银河航天(北京)网络技术有限公司 | Cross plate hinge and satellite wing array |
| CN117508640B (en) * | 2024-01-02 | 2024-03-29 | 银河航天(北京)网络技术有限公司 | Cross plate hinge and satellite wing array |
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