CN220948563U - Locking and unlocking mechanism of rigid solar wing - Google Patents

Abstract

The application relates to the technical field of rigid solar wings and provides a locking and unlocking mechanism of a rigid solar wing, which comprises a clamping hook arranged on the rigid solar wing, a clamping groove arranged on a satellite main body for clamping the clamping hook and a hinge arranged between the rigid solar wing and the satellite main body, wherein an unlocking piece for separating the clamping hook from the clamping groove is arranged in the clamping groove; the hinge comprises a fixed plate arranged on the satellite main body, a rotating plate arranged on the rigid solar wing and rotationally connected with the fixed plate, a rotating piece arranged on the rotating plate and rotationally opened and closed relative to the fixed plate, and a buffer piece arranged between the fixed plate and the rotating plate. The application has the beneficial effects of reducing the possibility of larger impact at the end of opening the solar wing span, and further reducing the damage to the solar wing.

Description

Locking and unlocking mechanism of rigid solar wing

Technical Field

The application relates to the technical field of rigid solar wings, in particular to a locking and unlocking mechanism of a rigid solar wing.

Background

Solar wings, also known as solar panels, are devices that collect solar energy and are commonly used in satellites and spacecraft to provide the necessary energy for their operation. In the satellite launching stage, the solar wings are folded on the satellite surface and unfolded after entering orbit, and the solar wings are possibly damaged due to tremble environment in the launching process, so that the solar wings are required to be locked on the satellite surface in the launching section so as to prevent damage caused by vibration.

In the prior art, the currently commonly used solar wing locking and unlocking mechanism mainly comprises a pre-tightening rope combined hot knife mode, a compression nut compression mode, a miniature hinge combined pin puller mode and the like, so that the solar wing is folded on the surface of a satellite, and is unfolded after entering an orbit. The hinges are divided into spiral spring type, torsion spring type and band spring type according to the type of the energy storage component. And selecting a hinge of a corresponding energy storage type according to the rigidity requirements of different satellites on the solar wing.

The torsion of the torsion spring type hinge is moderate, so that the torsion spring type hinge is commonly used for a microsatellite solar wing, the solar wing is mainly unfolded under the influence of the elasticity of the torsion spring, but the hinge has larger impact at the end of opening of the solar wing span, and the solar wing is damaged to a certain extent, so that further improvement is needed.

Disclosure of utility model

In order to reduce the possibility of larger impact at the end of the opening of the solar wing span and further reduce damage to the solar wing, the application provides a locking and unlocking mechanism of a rigid solar wing.

The application provides a locking and unlocking mechanism of a rigid solar wing, which adopts the following technical scheme:

The locking and unlocking mechanism of the rigid solar wing comprises a clamping hook arranged on the rigid solar wing, a clamping groove arranged on the satellite main body for clamping and embedding the clamping hook, and a hinge arranged between the rigid solar wing and the satellite main body, wherein an unlocking piece for separating the clamping hook from the clamping groove is arranged in the clamping groove; the hinge comprises a fixed plate arranged on the satellite main body, a rotating plate arranged on the rigid solar wing and rotationally connected with the fixed plate, a rotating piece arranged on the rotating plate and rotationally opened and closed relative to the fixed plate, and a buffer piece arranged between the fixed plate and the rotating plate.

Through adopting above-mentioned technical scheme, after satellite main part 2 goes into orbit, through release 41 with make pothook 3 break away from in draw-in groove 4, and then make the solar wing expand under hinge 5's effect, at this moment through being provided with buffer 54 between fixed plate 51 and rotor plate 52, can be to receiving rotor 53 so that rotor plate 52 can alleviate certain impact force when opening and shutting ground rotation for fixed plate 51 to reduce rigid solar wing end-of-span and open the possibility that has great impact, and then with the damage to rigid solar wing.

Preferably, the fixed plate protrusion is provided with first installation piece, the rotation plate protrusion is provided with the second installation piece of butt in first installation piece, the pivot of locating first installation piece and second installation piece and the hinge spring of coaxial cover locating the pivot are worn to locate in the rotation, the both ends of hinge spring set up respectively in the surface that fixed plate and rotation plate are close to each other, the hinge spring forces the rotation plate to keep away from in the installation piece one towards the direction of keeping away from the fixed plate and remove.

Through adopting above-mentioned technical scheme, after the pothook breaks away from in the draw-in groove, the torsion of pivoted spring self is passed through to the pivoted plate to realize the relative rotation between fixed plate and the pivoted plate, thereby in order to realize the expansion of solar wing.

Preferably, the first mounting block is provided with a mounting groove for mounting the buffer piece, the buffer piece comprises a spring fixedly connected to the inner wall of the mounting groove of the first mounting block and a first limit rod fixedly connected to the spring, and the spring is made of a memory alloy wire; the first limiting rod slides and wears to locate first installation piece, the first spacing hole that supplies first limiting rod to slide and insert is seted up to the second installation piece, the intercommunication groove in intercommunication and first spacing hole has been seted up to the second installation piece, the degree of depth in intercommunication groove is from being close to the direction of rotor plate reduces gradually towards the direction of keeping away from the rotor plate.

By adopting the technical scheme, it is to be noted that when the satellite is not launched into space, the spring is heated to influence the length of the spring to be stretched to some extent, thereby make the first gag lever post slide under the effect of the extension of spring length and insert and locate in the first spacing hole, after the satellite main part is in orbit, after the pothook breaks away from the draw-in groove, at this moment because the spring is made by the memory alloy wire, the spring begins to receive the temperature to warp, will stretch the spring to some extent before, so as to move the first gag lever post towards the direction of keeping away from first spacing hole, because the pivoted plate is influenced by the hinge spring and is rotated, the depth influence at first gag lever post along the intercommunication groove can make the pivoted plate rotate gradually, so that the pivoted plate can slowly rotate, in order to reduce the impact force that appears rotating too soon and make the possibility that the rigid solar wing damaged appears.

Preferably, the first limiting rod is sleeved with an elastic sleeve, and the inner wall of the second mounting block, which is positioned in the communication groove, is provided with anti-skid patterns.

Through adopting above-mentioned technical scheme, through being provided with elastic sleeve and anti-skidding line, can increase the area of contact between the two, increase the frictional force that first gag lever post slides when connecting in the intercommunication groove promptly to make the rotor plate can further slowly rotate, in order to further reduce the possibility that the produced impact force of rotation too fast appears in order to make the damage appear in the rigid solar wing.

Preferably, the fixed plate is further provided with a limiting member for limiting the rotation of the rotating plate.

Through adopting above-mentioned technical scheme, when the pivoted panel rotates to in order to drive the sun wing and expand the back for the satellite main part, through being provided with the locating part in order to carry out spacingly to reduce the pivoted panel and receive external force influence appearance pivoted possibility.

Preferably, the locating part is for the second gag lever post of arranging in the mounting groove, the second gag lever post is located to the spring housing, the one end fixed connection of second gag lever post in first gag lever post, the spout that supplies the second gag lever post to slide to wear to establish is seted up to first installation piece, be provided with the butt in on the fixed plate the stopper of first installation piece, the second spacing hole that supplies the second gag lever post to slide to insert is seted up to the stopper.

Through adopting above-mentioned technical scheme, because the spring is made by memory alloy wire, the spring begins to warp by the temperature, will the spring that the length was stretched before begins to shrink, when moving first gag lever post towards the direction of keeping away from first spacing hole, drive the gag lever post towards the direction that is close to the second spacing hole and slide, rotate to in order to drive the solar wing and expand the back for the satellite main part when the rotor plate, second spacing hole and spout are corresponding this moment for the second gag lever post slides and inserts and locate the second spacing hole in order to carry out the function of auto-lock.

Preferably, an elastic pad is arranged in the second limiting hole.

Through adopting above-mentioned technical scheme, through being provided with the elastic pad to reduce the interval between second spacing hole and the second gag lever post, and also improve the area of contact between the second gag lever post, with the possibility that the second gag lever post slides and breaks away from in the second spacing hole.

Preferably, the rigid solar wings are provided with a plurality of rigid solar wings, hinges are also arranged between the adjacent solar wings, and elastic strips are arranged at the edges of the adjacent solar wings, which are close to each other.

Through adopting above-mentioned technical scheme, be provided with the elastic strip between adjacent solar wing, can carry out certain spacing when rotating same horizontal position to two solar wings on the one hand, and alleviate the impact force that produces when the rigidity solar wing rotates, further reduce the possibility that collision appears damaging between the adjacent rigidity solar wing.

In summary, the utility model has the following beneficial effects:

Through being provided with the bolster between fixed plate and rotor plate, can be to receiving the rotor so that the rotor plate can alleviate certain impact force when rotating for the fixed plate open and shut to reduce rigid solar wing span and open the end and have great impact's possibility, and then with the damage to the rigid solar wing that reduces.

Drawings

FIG. 1 is a schematic diagram of an embodiment of the present application;

FIG. 2 is a schematic cross-sectional view of a hook and a slot according to an embodiment of the present application;

FIG. 3 is a schematic view of the structure of a rigid solar wing and hinge in an embodiment of the application;

FIG. 4 is a schematic view of a hinge in an embodiment of the application;

FIG. 5 is an enlarged schematic view of a portion of FIG. 4 at A;

FIG. 6 is a schematic diagram showing a state that a first stop lever is slidably connected to a communicating groove according to an embodiment of the present application;

fig. 7 is a schematic structural diagram of a second limiting rod slidably inserted into a second limiting hole according to an embodiment of the present application.

Reference numerals illustrate: 1. rigid solar wings; 11. an elastic strip; 2. a satellite body; 3. a clamping hook; 31. a through groove; 4. a clamping groove; 41. an unlocking member; 411. a pin puller; 412. a first PCB board; 413. a memory alloy wire; 414. a second PCB board; 5. a hinge; 51. a fixing plate; 52. a rotating plate; 53. a rotating member; 531. a rotating shaft; 532. a hinge spring; 54. a buffer member; 541. a spring; 542. a first stop lever; 6. a first mounting block; 61. a mounting groove; 62. a chute; 7. a second mounting block; 71. a first limiting hole; 72. a communication groove; 721. anti-skid lines; 8. an elastic sleeve; 9. a second limit rod; 10. a limiting block; 101. a second limiting hole; 102. an elastic pad.

Detailed Description

The present application will be described in further detail with reference to fig. 1-7.

The embodiment of the application discloses a locking and unlocking mechanism of a rigid solar wing.

Examples:

Referring to fig. 1 and 2, the locking and unlocking mechanism of the rigid solar wing comprises a clamping hook 3 arranged on the rigid solar wing 1, a clamping groove 4 arranged on the satellite main body 2 for clamping the clamping hook 3, and a hinge 5 arranged between the rigid solar wing 1 and the satellite main body 2, wherein an unlocking piece 41 for separating the clamping hook 3 from the clamping groove 4 is arranged in the clamping groove 4.

The unlocking piece 41 comprises a pin puller 411 which is slidably connected in the clamping groove 4, a first PCB 412 which is fixedly connected with the pin puller 411, a memory alloy wire 413 which is fixedly connected with the first PCB 412, and a second PCB 414 which is fixedly connected with the other end of the memory alloy wire 413, wherein the second PCB 414 is fixedly connected with the inner side wall of the clamping groove 4. In this embodiment, the memory alloy wire 413 is a titanium-nickel alloy wire, and can automatically restore its own shape at a specific temperature, wherein the hook 3 is provided with a through slot 31 for the pin puller 411 to slide through.

It should be noted that, the memory alloy wire 413 is deformed by current control, and the second PCB 414 moves under the deformation effect thereof, so as to generate a tensile force on the pin puller 411, so that the pin puller 411 is movably clamped with the hook 3, and the rigid solar wing 1 is unfolded.

Referring to fig. 2 and 3, in the present embodiment, the rigid solar wings 1 are disposed on opposite side walls of the satellite main body 2, two rigid solar wings 1 disposed on one side of the satellite main body 2 are disposed, a hinge 5 is also disposed between two adjacent rigid solar wings 1, and two opposite surfaces of each adjacent rigid solar wing 1 are also respectively provided with a hook 3 and a slot 4, so that after the rigid solar wings 1 are folded on the satellite main body 2, when the rigid solar wings are in orbit, the hooks 3 are separated from the slots 4 together by the unlocking member 41, so that the rigid solar wings 1 are unfolded under the action of the hinge 5.

Referring to fig. 4 and 5, in particular, the hinge 5 includes a fixed plate 51, a rotating plate 52 rotatably coupled to the fixed plate 51, a rotating member 53 provided to the rotating plate 52 to be opened and closed with respect to the fixed plate 51, and a buffer member 54 provided between the fixed plate 51 and the rotating plate 52.

When the fixing plate 51 and the rotating plate 52 are mounted between the rigid solar wing 1 and the satellite main body 2, the fixing plate 51 is fixedly connected to the satellite main body 2, and the rotating plate 52 is fixedly connected to the rigid solar wing 1. When the fixed plates are arranged on the adjacent rigid solar wings 1, the rotating plates 52 and the fixed plates 51 are respectively fixedly connected to the side edges of the two rigid solar wings 1, which are close to each other.

Wherein, fixed plate 51 protrusion is fixed with first installation piece 6, and first installation piece 6 is along the length direction interval setting of fixed plate 51, and the rotation plate 52 protrusion is fixed with the second installation piece 7 of butt in first installation piece 6, and second installation piece 7 is along the length direction interval setting of rotation plate 52. The rotating member 53 includes a rotating shaft 531 penetrating through the first mounting block 6 and the second mounting block 7, and a hinge spring 532 coaxially sleeved on the rotating shaft 531, where two ends of the hinge spring 532 are respectively disposed on surfaces of the fixed plate 51 and the rotating plate 52, and the hinge spring 532 forces the rotating plate 52 to move away from one of the mounting blocks in a direction away from the fixed plate 51 in a normal state.

The angle of rotation between the fixed plate 51 and the rotating plate 52 provided between the rigid solar wing 1 and the satellite main body 2 can be controlled to be 90 degrees. And for the fixed plate 51 provided to the adjacent rigid solar wing 1 and the rotation, the angle rotated therebetween is 180 degrees, so that the rigid solar wing 1 is unfolded.

Referring to fig. 4 and 5, specifically, the surface of the first mounting block 6 far from the fixing plate 51 is provided with a mounting groove 61 for mounting the buffer member 54, and the buffer member 54 includes a spring 541 fixedly connected to the first mounting block 6 and located on the inner wall of the mounting groove 61, and a first stop lever 542 fixedly connected to the spring 541, and in this embodiment, the spring 541 is also made of a memory alloy wire.

The first limiting rod 542 slides through the first mounting block 6, the second mounting block 7 is provided with a first limiting hole 71, the first limiting rod 542 slides and is inserted into the first limiting hole 71, the second mounting block 7 is provided with a communicating groove 72 communicated with the first limiting hole 71, it is to be noted that the depth of the communicating groove 72 gradually decreases from the direction close to the rotating plate 52 to the direction far away from the rotating plate 52, and at this moment, the length of the spring 541 is already elongated before the spring 541 enters the rail, so that the first limiting rod 542 slides and is inserted into the first limiting hole 71.

When the satellite main body 2 is in orbit, the temperature in the space is low at this time, the spring 541 is deformed, so that the spring 541 is shortened, and the first limiting rod 542 is driven to move in a direction away from the first limiting hole 71, and the rotating plate 52 rotates relative to the fixed plate 51 due to the torsion of the hinge spring 532, so that the first limiting rod 542 is slidably connected to the communicating groove 72, as shown in fig. 6.

Referring to fig. 6, further, in order to enable the rotating plate 52 to rotate slowly, the elastic sleeve 8 is sleeved outside the first limiting rod 542, the anti-skid patterns 721 are provided on the inner wall of the second mounting block 7 located in the communication groove 72, and the friction force of the first limiting rod 542 when being slidingly connected to the communication groove 72 can be increased during contact due to the characteristics of the elastic sleeve 8 and the anti-skid patterns 721.

Referring to fig. 6 and 7, the fixed plate 51 is further provided with a limiting member for limiting the rotation of the rotating plate 52, in this embodiment, the limiting member is a second limiting rod 9 disposed in the mounting groove 61, the spring 541 is sleeved on the second limiting rod 9, one end of the second limiting rod 9 is fixedly connected to one end of the first limiting rod 542, which is far away from the first limiting hole 71, the first mounting block 6 is provided with a sliding groove 62 along the axis thereof for sliding and penetrating the second limiting rod 9, and the sliding groove 62 is communicated with the mounting groove 61. The fixed plate 51 is provided with a limiting block 10 abutted against the first mounting block 6, and the limiting block 10 is provided with a second limiting hole 101 for sliding and inserting the second limiting rod 9. In this embodiment, an elastic pad 102 is disposed in the second limiting hole 101.

Returning to fig. 1, further, the edges of adjacent solar wings close to each other are provided with elastic strips 11 to relieve impact force generated when the rigid solar wings 1 rotate, so as to further reduce the possibility of damage caused by collision between the adjacent rigid solar wings 1.

The implementation principle of the locking and unlocking mechanism of the rigid solar wing provided by the embodiment of the application is as follows: after the satellite main body 2 enters the orbit, the unlocking piece 41 is used for enabling the clamping hook 3 to be separated from the clamping groove 4, so that the solar wing is unfolded under the action of the hinge 5, at the moment, the buffer piece 54 is arranged between the fixed plate 51 and the rotating plate 52, and a certain impact force can be relieved when the rotating piece 53 is rotated so that the rotating plate 52 rotates in an opening and closing manner relative to the fixed plate 51, so that the possibility that larger impact is generated at the end of unfolding the rigid solar wing 1 is reduced, and the damage to the rigid solar wing 1 is reduced.

The above embodiments are not intended to limit the scope of the present application, so: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.

Claims (8)

1. The locking and unlocking mechanism of the rigid solar wing comprises a clamping hook (3) arranged on the rigid solar wing (1), a clamping groove (4) arranged on a satellite main body (2) for clamping the clamping hook (3) and a hinge (5) arranged between the rigid solar wing (1) and the satellite main body (2), wherein an unlocking piece (41) for separating the clamping hook (3) from the clamping groove (4) is arranged in the clamping groove (4); the method is characterized in that: the hinge (5) comprises a fixed plate (51) arranged on the satellite main body (2), a rotating plate (52) arranged on the rigid solar wing (1) to be rotatably connected with the fixed plate (51), a rotating piece (53) arranged on the rotating plate (52) to rotate in an opening and closing manner relative to the fixed plate (51), and a buffer piece (54) arranged between the fixed plate (51) and the rotating plate (52).

2. The locking and unlocking mechanism for a rigid solar wing according to claim 1, wherein: the utility model discloses a fixed plate (51) protrusion is provided with first installation piece (6), rotation board (52) protrusion is provided with second installation piece (7) of butt in first installation piece (6), rotate piece (53) including rotating pivot (531) and the coaxial cover of wearing to locate first installation piece (6) and second installation piece (7) and locate pivot (531) hinge spring (532), the both ends of hinge spring (532) set up respectively in the surface that fixed plate (51) and rotation board (52) are close to each other, hinge spring (532) force one of rotation board (52) and keep away from the installation piece and move towards the direction of keeping away from fixed plate (51).

3. A rigid solar wing locking and unlocking mechanism according to claim 2, wherein: the first mounting block (6) is provided with a mounting groove (61) for mounting the buffer piece (54), the buffer piece (54) comprises a spring (541) fixedly connected to the inner wall of the mounting groove (61) of the first mounting block (6) and a first limit rod (542) fixedly connected to the spring (541), and the spring (541) is made of a memory alloy wire; the first limiting rod (542) slides and wears to locate first installation piece (6), first limiting hole (71) that supplies first limiting rod (542) to slide and insert is seted up to second installation piece (7), intercommunication and intercommunication groove (72) of first limiting hole (71) are seted up to second installation piece (7), the degree of depth of intercommunication groove (72) is from being close to the direction of rotor plate (52) reduces gradually in the direction of rotor plate (52) in keeping away from.

4. A rigid solar wing locking and unlocking mechanism according to claim 3, wherein: the first limiting rod (542) is sleeved with an elastic sleeve (8), and the second mounting block (7) is positioned on the inner wall of the communication groove (72) and is provided with anti-skid patterns (721).

5. A rigid solar wing locking and unlocking mechanism according to claim 3, wherein: and a limiting piece for limiting the rotation of the rotating plate (52) is further arranged on the fixed plate (51).

6. The locking and unlocking mechanism for a rigid solar wing as defined in claim 5, wherein: the locating part is second gag lever post (9) of built-in mounting groove (61), second gag lever post (9) are located to spring (541) cover, one end fixed connection of second gag lever post (9) in first gag lever post (542), spout (62) that supply second gag lever post (9) to slide to wear to establish are seted up to first installation piece (6), be provided with on fixed plate (51) butt in stopper (10) of first installation piece (6), second spacing hole (101) that supply second gag lever post (9) to slide to insert are seted up to stopper (10).

7. The locking and unlocking mechanism for a rigid solar wing as defined in claim 6, wherein: an elastic pad (102) is arranged in the second limiting hole (101).

8. The locking and unlocking mechanism for a rigid solar wing according to claim 1, wherein: the rigid solar wings (1) are provided with a plurality of rigid solar wings, hinges (5) are also arranged between the adjacent solar wings, and elastic strips (11) are arranged at the edges of the adjacent solar wings, which are close to each other.