CN214608148U - Satellite solar wing connecting and unlocking device - Google Patents
Satellite solar wing connecting and unlocking device Download PDFInfo
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- CN214608148U CN214608148U CN202120631686.XU CN202120631686U CN214608148U CN 214608148 U CN214608148 U CN 214608148U CN 202120631686 U CN202120631686 U CN 202120631686U CN 214608148 U CN214608148 U CN 214608148U
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- mounting seat
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- solar wing
- fuse
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Abstract
The utility model discloses a satellite solar wing is connected and unlocking device, include: the male mounting seat is provided with a first mounting part for mounting; the female mounting seat is provided with a second mounting part for mounting; the pre-tightening elastic piece is arranged on the female mounting seat; the fusing component is arranged on the female mounting seat; the angle adjusting wheel is rotatably connected to the female mounting seat; one end of the fuse wire is fixedly connected with the pre-tightening elastic piece, the other end of the fuse wire is fixedly connected with the male mounting seat, and the fuse wire penetrates through the fuse component and is wound on the angle adjusting wheel; when the fuse is unlocked, the fuse wire is fused through heating of the fusing assembly, so that the male mounting seat is separated from the female mounting seat. The device can change the connection angle of the fuse wire, so that the adaptability is stronger.
Description
Technical Field
The utility model belongs to the technical field of the space flight, especially, relate to a satellite solar wing is connected and unlocking device.
Background
In recent years, with the increasing maturity of aerospace technology, micro-nano satellites and cubic satellites are carried on the orbit increasingly frequently. Commercialization in the aerospace field is deepened continuously, and the admittance threshold of the micro-nano satellite is further reduced. In order to meet the requirement of continuously improving the loading capacity of the micro-nano satellite, the problem of urgently solving the requirement of improving the energy supply capacity of the micro-nano satellite is solved. One of the main ways of energy expansion of the current micro-nano satellite is to increase the area of a solar wing, and a foldable movable solar wing becomes the only way for increasing the area of the solar wing. The connection unlocking of the folding of the solar wing is one of the key technologies of the design of the solar wing.
At present, the connection and the unlocking of the traditional solar wing and a star body are realized through initiating explosive devices, the micro-nano satellite and the cubic star are restricted by the envelope size and the power supply requirement of the satellite, and a separation release device not only needs to be compact in structure, but also needs to ensure quick release.
At present, a solar wing of a micro-nano satellite is directly connected with a satellite body through a fuse such as a strong force guy wire, and the unlocking is realized by heating and melting the strong force guy wire through a hot knife. The high requirement is provided for the connection layout of the solar wing and the satellite, the installation angle of the strong guy is not controllable, and the solar wing unlocking device is more restricted and has high limitation.
SUMMERY OF THE UTILITY MODEL
In order to solve the above problem, the present invention provides a satellite solar wing connection and unlocking device, which can change the connection angle of the fuse, so that the adaptability is stronger.
In order to achieve the above purpose, the technical scheme of the utility model is that:
a satellite solar wing connection and unlocking device comprising:
the male mounting seat is provided with a first mounting part for mounting;
the female mounting seat is provided with a second mounting part for mounting;
the pre-tightening elastic piece is arranged on the female mounting seat;
the fusing component is arranged on the female mounting seat;
the angle adjusting wheel is rotatably connected to the female mounting seat;
one end of the fuse wire is fixedly connected with the pre-tightening elastic piece, the other end of the fuse wire is fixedly connected with the male mounting seat, and the fuse wire penetrates through the fuse component and is wound on the angle adjusting wheel;
when the fuse is unlocked, the fuse wire is fused through heating of the fusing assembly, so that the male mounting seat is separated from the female mounting seat.
According to the utility model discloses an embodiment, public mount pad be the mounting panel female mount pad is an open-ended mounting box, the mounting panel lid is located mounting box open-ended one side, the angle modulation wheel is located the mounting panel with between the fusing subassembly.
According to the utility model discloses an embodiment, including micro-gap switch, locate the mounting box with between the mounting panel, the mounting panel compresses tightly micro-gap switch's reed, during the unblock the mounting panel leaves the reed is so that micro-gap switch is triggered.
According to the utility model discloses an embodiment, pretension elastic component is the extension spring.
According to the utility model discloses an embodiment, fusing subassembly is the circuit board, be equipped with heating resistor on the circuit board, the circuit board install in on the installation face of female mount pad.
According to the utility model discloses an embodiment, the fuse is big force horse line.
The utility model discloses owing to adopt above technical scheme, make it compare with prior art and have following advantage and positive effect:
(1) the embodiment of the utility model provides an in can change the connection angle of fuse through setting up the angle modulation wheel for adaptability is stronger during the installation, can satisfy different installation angle demands.
(2) The embodiment of the utility model provides an in whether separate expansion through setting up micro-gap switch automated inspection public mount pad and female mount pad.
Drawings
The following detailed description of embodiments of the present invention is provided with reference to the accompanying drawings, in which:
fig. 1 is a cross-sectional view of a satellite solar wing connecting and unlocking device of the present invention;
fig. 2 is an axial view of the satellite solar wing connecting and unlocking device of the present invention;
fig. 3 is a top view of the satellite solar wing connecting and unlocking device of the present invention;
fig. 4 is an exploded view of the satellite solar wing connecting and unlocking device of the present invention.
Description of reference numerals:
1: mounting a plate; 2: mounting a box; 3: an angle adjustment wheel; 4: fusing; 5: a microswitch; 6: a reed; 7: a tension spring; 8: a circuit board.
Detailed Description
The present invention will be described in further detail with reference to the following drawings and specific embodiments. The advantages and features of the present invention will become more fully apparent from the following description and appended claims. It is to be noted that the drawings are in a very simplified form and are not to be construed as precise ratios as are merely intended to facilitate and distinctly illustrate the embodiments of the present invention.
It should be noted that all the directional indicators (such as upper, lower, left, right, front and rear … …) in the embodiment of the present invention are only used to explain the relative position relationship between the components, the motion situation, etc. in a specific posture (as shown in the drawings), and if the specific posture is changed, the directional indicator is changed accordingly.
Referring to fig. 1 to 4, the core of the utility model is to provide a satellite solar wing connects and unlocking device, including public mount pad, female mount pad, pretension elastic component, fusing subassembly, angle modulation wheel 3 and fuse 4. The male mounting seat is provided with a first mounting part for mounting; the female mounting seat is provided with a second mounting part for mounting; the pre-tightening elastic piece is arranged on the female mounting seat; the fusing component is arranged on the female mounting seat; the angle adjusting wheel 3 is rotationally connected with the female mounting seat; fuse 4 one end links firmly in pretension elastic component, the other end links firmly in public mount pad, and fuse 4 wears to locate the fuse subassembly and locate angle accommodate wheel 3.
When unlocking, fuse 4 is fused by heating the fusing component so as to separate the male mounting seat from the female mounting seat.
The connection angle of the fuse wire 4 can be changed by arranging the angle adjusting wheel 3, so that the installation adaptability is stronger, and different installation angle requirements can be met.
The satellite solar wing connecting and unlocking device of the present invention is described in further detail below:
the public mount pad is installed in sun wing one side through first installation department, and first installation department is two mounting holes. The female mounting base is mounted on the star structure through a second mounting portion, and the second mounting portion is four mounting holes.
Public mount pad is mounting panel 1, female mount pad for one side open-ended mounting box 2 in this embodiment, and 2 open-ended one sides of mounting box are located to 1 lid of mounting panel, and are equipped with the installation step on the lateral wall of 2 open-ended sides of mounting box, and on this installation step was located to mounting panel 1 for public mount pad and female mount pad had anti shear effect after connecting.
The angle adjustment wheel 3 is arranged between the mounting plate 1 and the fusing assembly. In this embodiment, the fusing subassembly is circuit board 8, is equipped with heating resistor on the circuit board 8, and heating resistor heating fuses fuse 4, and fuse 4 is big power horse line, and in the different embodiments, the line footpath of fuse 4 can increase or diminish according to actual conditions to rigidity when improving the sun wing and compressing tightly the state. The circuit board 8 is mounted on the mounting surface of the mounting case 2. In addition, in this embodiment, the pre-tightening elastic element is a tension spring 7, and the tension spring 7 is disposed on a side wall of the mounting box 2, which is far away from the mounting plate 1.
4 one end of fusible link links firmly in extension spring 7, then through circuit board 8, winds again and locates angle adjustment wheel 3, and its other end links firmly in mounting panel 1 at last, and is the state of straining at installation status fusible link 4, and extension spring 7 is tensile state, and extension spring 7 gives 4 pretightning forces of fusible link for mounting panel 1 is connected with mounting box 2, so that the sun wing compresses tightly and installs on the star is structural. In different embodiments, the wire diameter of the tension spring 7 can be increased or decreased according to actual conditions so as to adjust the pretightening force when the solar wing is in a compression state.
Referring to fig. 1, in the present embodiment, an included angle between the mounting surface of the circuit board 8 on the mounting box 2 and the mounting plate 1 is 0 degree, and an angle of the fuse 4 adjusted by the angle adjusting wheel 3 is 90 degrees, that is, the fuse 4 is changed by 90 degrees by the angle adjusting wheel 3. In practical application, the position and the angle of the mounting surface of the mounting box 2 can be adjusted according to the actual allowable envelope space of the satellite, so that the angle 4 of the angle adjusting wheel 3 can be dynamically adjusted.
The mounting box further comprises a microswitch 5 which is arranged between the mounting box 2 and the mounting plate 1 and is directly arranged on the circuit board 8 in the embodiment. The mounting plate 1 compresses the reed 6 of the micro switch 5, the mounting plate 1 leaves the reed 6 during unlocking so that the micro switch 5 is triggered, and the micro switch 5 triggers to send a feedback signal that the mounting plate 1 is released.
The working process of the present invention is further explained as follows:
after receiving the unlocking signal, the circuit board 8 works, the heating resistor heats and fuses the fuse wire 4, at the moment, the male mounting seat and the female mounting seat are unlocked and separated, and the solar wing is unfolded under the driving of the hinge. At this point, the microswitch 5 triggers the signal that deployment has been unlocked.
The utility model discloses a satellite solar wing is connected and unlocking device realizes the change of 4 connection angles of fuse through the angle directive wheel, can make solar wing and different stars or the connection when different angles have more adaptability with the unblock, improves the applicable scene and the application range of connecting and unlocking device greatly.
The utility model discloses the 7 rigidity of extension spring that in use can suitably change according to solar wing battery battle array size, improve the applicable scene and the application range of connecting and unlocking device greatly.
The utility model discloses in integrated connection, unblock, signal acquisition in an organic whole, realize modularization, simple structure reliable, installation and convenient to use.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, the changes are still within the scope of the present invention if they fall within the scope of the claims and their equivalents.
Claims (6)
1. A satellite solar wing connecting and unlocking device is characterized by comprising:
the male mounting seat is provided with a first mounting part for mounting;
the female mounting seat is provided with a second mounting part for mounting;
the pre-tightening elastic piece is arranged on the female mounting seat;
the fusing component is arranged on the female mounting seat;
the angle adjusting wheel is rotatably connected to the female mounting seat;
one end of the fuse wire is fixedly connected with the pre-tightening elastic piece, the other end of the fuse wire is fixedly connected with the male mounting seat, and the fuse wire penetrates through the fuse component and is wound on the angle adjusting wheel;
when the fuse is unlocked, the fuse wire is fused through heating of the fusing assembly, so that the male mounting seat is separated from the female mounting seat.
2. The satellite solar wing connecting and unlocking device as claimed in claim 1, wherein the male mounting seat is a mounting plate, the female mounting seat is a mounting box with an opening on one side, the mounting plate is covered on the opening side of the mounting box, and the angle adjusting wheel is arranged between the mounting plate and the fusing assembly.
3. The satellite solar wing connecting and unlocking device according to claim 2, comprising a microswitch arranged between the mounting box and the mounting plate, wherein the mounting plate presses a reed of the microswitch, and when unlocking, the mounting plate leaves the reed to trigger the microswitch.
4. The satellite solar wing connecting and unlocking device according to claim 1, wherein the pre-tightening elastic member is a tension spring.
5. The satellite solar wing connecting and unlocking device as claimed in claim 1, wherein the fusing component is a circuit board, a heating resistor is arranged on the circuit board, and the circuit board is mounted on the mounting surface of the female mounting seat.
6. The satellite solar wing connection and release device of claim 1, wherein the fusible link is a maraca line.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120631686.XU CN214608148U (en) | 2021-03-29 | 2021-03-29 | Satellite solar wing connecting and unlocking device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120631686.XU CN214608148U (en) | 2021-03-29 | 2021-03-29 | Satellite solar wing connecting and unlocking device |
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| Publication Number | Publication Date |
|---|---|
| CN214608148U true CN214608148U (en) | 2021-11-05 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202120631686.XU Active CN214608148U (en) | 2021-03-29 | 2021-03-29 | Satellite solar wing connecting and unlocking device |
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| CN (1) | CN214608148U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115848646A (en) * | 2022-12-16 | 2023-03-28 | 苏州馥昶空间技术有限公司 | Supporting mechanism of space camera |
-
2021
- 2021-03-29 CN CN202120631686.XU patent/CN214608148U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115848646A (en) * | 2022-12-16 | 2023-03-28 | 苏州馥昶空间技术有限公司 | Supporting mechanism of space camera |
| CN115848646B (en) * | 2022-12-16 | 2023-10-27 | 苏州馥昶空间技术有限公司 | Supporting mechanism of space camera |
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