CN116039966A - Satellite solar wing and minisatellite - Google Patents

Abstract

The application relates to a satellite solar wing and a minisatellite, wherein the satellite solar wing comprises: the solar wing sailboard is connected to the star body and comprises an inner side sailboard and an outer side sailboard, a hinge is arranged among the star body, the inner side sailboard and the outer side sailboard, the solar wing sailboard is compressed or released on the star body through a compression and release device, and the released solar wing sailboard is unfolded and locked through the hinge. According to the satellite solar wing and the small satellite, the compression state of the solar wing sailboard can be kept before orbit entering, the solar wing sailboard is released relative to the star body after orbit entering, the inner side sailboard and the outer side sailboard are unfolded, and electric energy is stably and reliably provided for the satellite. The hinges arranged among the star body, the inner sailboard and the outer sailboard can enable the inner sailboard to be unfolded relative to the star body and the outer sailboard to be unfolded relative to the inner sailboard in sequence after the solar wing sailboard is released, so that the reliability of the integral unfolding of the solar wing sailboard is guaranteed.

Description

Satellite solar wing and minisatellite

Technical Field

The application relates to the technical field of solar wing devices, in particular to a satellite solar wing and a small satellite.

Background

The solar wing is an indispensable part of the spacecraft, mainly provides electric energy supply for the spacecraft, and because the small satellite is small in size, most of solar wings are folded and pressed on the surface of the satellite before being launched, and whether the solar wings can be smoothly unfolded after the satellite enters the orbit is an important index for success or failure of the launching task of the spacecraft at present.

Disclosure of Invention

The purpose of this application is to provide a satellite solar wing and little satellite, can release the compaction to the solar wing after the little satellite goes into orbit to expand and maintain the state of expanding under the effect of its hinge, provide the electric energy for the satellite steadily and reliably.

To achieve the above object, in a first aspect, the present invention provides a satellite solar wing, comprising: the solar wing sailboard is connected to the star body and comprises an inner side sailboard and an outer side sailboard, a hinge is arranged between the star body, the inner side sailboard and the outer side sailboard, the solar wing sailboard is compressed or released on the star body through a compression release device, and the released solar wing sailboard is unfolded and locked through the hinge.

In an alternative embodiment, the compression release device comprises a compression unit and a release unit, wherein the compression unit is arranged on the star and comprises a pre-tightening assembly, a compression seat, a guide piece and a Kevlar rope;

the solar wing sailboard is provided with a sailboard embedded part, the fixed end of the Kevlar stay rope is bound on the sailboard embedded part, the pre-tightening end sequentially penetrates through the compression seat and the guide part and then is connected to the pre-tightening assembly, the pre-tightening assembly comprises a pre-tightening base, a pre-tightening nut and a pre-tightening screw, and a guide post is arranged in the pre-tightening base.

In an optional embodiment, the sailboard embedded part includes an inner sailboard embedded part and an outer sailboard embedded part which are respectively arranged on the inner sailboard and the outer sailboard, the solar wing sailboard is in a compressed state, the inner sailboard embedded part, the outer sailboard embedded part and the compressing seat are sequentially stacked, and the mutual contact surface is a spherical surface;

the top of inboard sailboard buries is provided with the recess, it has spacing ball to hold to lie in the recess, the stiff end of Kevlar stay cord is connected on the spacing ball.

In an alternative embodiment, the solar wing sailboard is provided with a compression hole for installing the sailboard embedded part, and the compression hole is opposite to the compression seat;

the compression holes and the compression seats are correspondingly arranged, the number of the compression holes is adjustable, and the sailboard embedded parts and the Kevlar stay ropes are in one-to-one correspondence.

In an alternative embodiment, the release unit includes a hot-melting device mounted on the star, and the kev pull ropes pass through the hot-melting device, and the hot-melting device can blow the kev pull ropes to release the solar panel.

In an alternative embodiment, the hinge comprises a root hinge arranged between the star and the inner sailboard and used for folding and unfolding the solar wing sailboard, and an inter-board hinge arranged between the inner sailboard and the outer sailboard and used for folding and unfolding the inner sailboard and the outer sailboard, wherein a trigger device is arranged on the root hinge and used for limiting the outer sailboard to unfold.

In an alternative embodiment, the root hinge comprises a female hinge, a male hinge and a root hinge main torsion spring, wherein the female hinge is connected with the inner sailboard, the male hinge is connected with the star, and the released solar wing sailboard is unfolded relative to the star through the root hinge main torsion spring.

In an alternative embodiment, the triggering device comprises a triggering lever, a triggering rod, a triggering screw, a triggering device rotating shaft and a triggering torsion spring, wherein the triggering rod is fixedly connected to the male hinge, the triggering lever is installed on the rotating shaft of the root hinge through the triggering device rotating shaft, and the rotating shaft of the root hinge is fixedly connected with the female hinge;

the trigger torsion spring is sleeved on the trigger device rotating shaft, the trigger screw is connected to the trigger lever, the trigger lever can be abutted to the screw rod of the trigger screw, and the trigger lever can rotate around the trigger device rotating shaft through the trigger torsion spring.

In an alternative embodiment, the inter-plate hinge comprises a female hinge, a male hinge and an inter-plate hinge main torsion spring, wherein the female hinge is connected with the outer sailboard, the male hinge is connected with the inner sailboard, and the triggered solar wing sailboards are relatively unfolded through the inter-plate hinge main torsion spring;

the inter-board hinge and the root hinge are respectively provided with a locking component, and the locking components are used for locking the inner sailboard and the star body and locking the unfolding states of the outer sailboard and the inner sailboard;

the locking assembly comprises a locking rod connected to the female hinge and a locking hole formed in the male hinge, a pressure spring is sleeved on the locking rod, and after the female hinge and the male hinge relatively rotate, the locking rod can be inserted into the locking hole under the action of the pressure spring.

In a second aspect, the present invention provides a minisatellite comprising a star and a satellite solar wing as described in any one of the preceding embodiments.

According to the satellite solar wing and the small satellite, the compression state of the solar wing sailboard can be kept before orbit entering, the solar wing sailboard is released relative to the star body after orbit entering, the inner side sailboard and the outer side sailboard are unfolded, and electric energy is stably and reliably provided for the satellite.

The hinges arranged among the star body, the inner sailboard and the outer sailboard can enable the inner sailboard to be unfolded relative to the star body and the outer sailboard to be unfolded relative to the inner sailboard in sequence after the solar wing sailboard is released, so that the reliability of the integral unfolding of the solar wing sailboard is guaranteed.

Additional features and advantages of the present application will be set forth in the detailed description which follows.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered limiting the scope, and that other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view of the overall structure of a satellite solar wing in the present application;

FIG. 2 is a schematic view of the structure of the compression release device;

FIG. 3 is a schematic view of a solar panel;

FIG. 4 is a schematic view of the mounting structure of the embedded sailboard on the inner sailboard and the outer sailboard;

FIG. 5 is a schematic structural view of a pretensioning assembly;

FIG. 6 is a schematic structural view of a root hinge;

FIG. 7 is a schematic diagram of the trigger device;

FIG. 8 is a schematic view of an inter-plate hinge;

FIG. 9 is a view of the solar panel as a whole in an unfolded state after release;

FIG. 10 is a view of the trigger device in an expanded state upon triggering;

FIG. 11 is a state diagram of the outer windsurfing board versus the inner windsurfing board deployment process;

fig. 12 is a state diagram of the inner and outer sailboards after they are fully unfolded.

Icon:

1-a solar wing sailboard; 11-inner sailboards; 12-outer sailboards; 13-an inner sailboard embedded part; 14-an outer sailboard embedded part; 15-compacting holes; 16-grooves; 17-limiting balls;

a 2-compaction unit; 21-a pretension assembly; 211-pre-tightening the base; 212-pre-tightening the nut; 213-pretension screw; 214-a guide post;

22-a compression seat; 23-a guide; 231-a first guide; 232-a second guide; 24-Kevlar rope;

a 3-release unit;

41-root hinge; 42-inter-plate hinge; 43-female hinge; 44-male hinges; 45-root hinge main torsion spring; 46-an inter-plate hinge main torsion spring;

5-triggering means; 51-trigger lever; 52-a trigger lever; 53-trigger screw; 54-a trigger device rotating shaft; 55-triggering a torsion spring;

6-locking assembly; 61-locking bar; 62-locking holes.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It will be apparent that the embodiments described are some, but not all, of the embodiments of the present application. The components of the embodiments of the present application, which are generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.

In the description of the present application, it should be noted that, the azimuth or positional relationship indicated by the terms "inner", "outer", etc. are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship that is commonly put when the product of the application is used, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.

In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.

The solar wing of the satellite in the application mainly compresses and releases the solar wing sailboard 1 before and after the satellite enters the orbit, and the compression state of the solar wing sailboard 1 before the satellite enters the orbit is kept through the compression and release device, and the relative release after the satellite enters the orbit is controlled.

By means of the hinges between the star, the inner sailboard 11 and the outer sailboard 12, the solar-wing sailboard 1 is released, and after that, the solar-wing sailboard 1 in the folded state is unfolded in sequence with respect to the star, and the outer sailboard 12 is unfolded with respect to the inner sailboard 11, so that the complete unfolding of the solar-wing sailboard 1 is achieved.

Referring to fig. 1, the satellite solar wing of the present invention includes: the solar-wing sailboard 1 is connected to a star (not shown in the figure), the solar-wing sailboard 1 comprises an inner sailboard 11 and an outer sailboard 12, and a hinge is arranged among the star, the inner sailboard 11 and the outer sailboard 12, specifically, the star is connected with the inner sailboard 11 through the hinge, and the outer sailboard 12 is connected with the inner sailboard 11 through the hinge.

The compression of the solar panel 1 before the entry and the release after the entry are performed by compression release means arranged between the star and the solar panel 1.

Before the satellite enters orbit, the inner sailboard 11 and the outer sailboard 12 are folded and pressed on the star body of the satellite, and the folded inner sailboard 11 battery piece is positioned on the surface of the star body, so that the satellite emission failure caused by insufficient electric quantity after the satellite enters orbit is avoided. In the compressed state, the solar wing sailboard 1 is tensioned through the Kevlar stay rope 24 and compresses the inner sailboard 11 and the outer sailboard 12 on the surface of the star, and the compressed form is simple and reliable.

After the satellite enters orbit, the compression release device controls the solar wing sailboard 1 to release, and the released solar wing sailboard 1 is unfolded, locked and maintained in an unfolded state under the action of the hinge to provide electric energy for the satellite.

Referring to fig. 2-5, in one specific embodiment, the compression release device includes a compression unit 2 and a release unit 3, where the compression unit 2 is mounted on a star and includes a pre-tightening assembly 21, a compression seat 22, a guide 23, and a kevlar rope 24, and the pre-tightening assembly 21, the compression seat 22, and the guide 23 are all connected to the star.

Specifically, the solar-wing sailboard 1 is kept in a compressed state by tensioning the kev pull ropes 24, and sailboard embedded parts are arranged on the solar-wing sailboard 1, wherein the kev pull ropes 24 comprise a plurality of independent pieces, and the number of the kev pull ropes corresponds to that of the sailboard embedded parts.

Each kevlar rope 24 comprises a fixed end and a pre-tightening end, the fixed end of the kevlar rope 24 is bound on the embedded part of the sailboard, and the compressing seat 22 on the star is opposite to the embedded part of the sailboard on the solar-wing sailboard 1 in the folded state of the solar-wing sailboard 1.

The pretension end passes through the compression seat 22 and the guide piece 23 in sequence and then is connected to the pretension assembly 21, the pretension assembly 21 comprises a pretension base 211, a pretension nut 212 and a pretension screw 213, the pretension end of the kev pull rope 24 is connected to the pretension screw 213, the pretension screw 213 is rotated to enable the redundant kev pull rope 24 to be wound on the pretension screw 213, tensioning of the kev pull rope 24 can be achieved, the pretension screw 213 and the pretension base 211 are in threaded connection, and reverse rotation of the pretension screw 213 can be achieved through fastening the pretension nut 212 after the kev pull rope 24 is tensioned.

The guide member 23 in this embodiment includes a first guide member 231 and a second guide member 232, where the first guide member 231 and the second guide member 232 are disposed at the middle parts of the pressing bases 22, preferably, the first guide member 231, the second guide member 232 and the pre-tightening base 211 are located on the same line, so that the guide member 23 plays a guiding role, and at the same time, the stress concentration of the binding force applied by the kevlar rope 24 is formed, so as to ensure the pressing effect.

Two transverse guide posts 214 for guiding the Kevlar rope 24 are arranged in the pre-tightening base 211, and the Kevlar rope 24 is connected between the guide posts 214 in an S-shaped penetrating manner, so that the rope is prevented from being cut off due to contact with edges of the pre-tightening base 211 after being stressed.

The inner sailboard 11 and the outer sailboard 12 are folded and attached through a preset sailboard embedded part, and are compressed on the star body under the action of the kev pull rope 24, the sailboard embedded part in the embodiment comprises an inner sailboard embedded part 13 and an outer sailboard embedded part 14 which are respectively arranged on the inner sailboard 11 and the outer sailboard 12, the solar panel 1 is in a compressed state, the inner sailboard embedded part 13, the outer sailboard embedded part 14 and the compressing seat 22 are sequentially stacked under the constraint compressing action of the kev pull rope 24, and the mutual contact surface is a spherical surface.

The middle parts of the sailboard embedded part and the compression seat 22 are hollow structures and are used for threading the Kevlar stay rope 24; based on the fact that the inner sailboard 11 is located on the surface of the star body in the folded and compressed state, the groove 16 is formed in the top of the inner sailboard embedded part 13, the limiting ball 17 is contained in the groove 16, the fixed end of the Kevlar pull rope 24 is connected and bound with the limiting ball 17, the limiting ball 17 is pulled into the groove 16 of the inner sailboard embedded part 13 after the Kevlar pull rope 24 is pre-tightened, and the binding force applied by the Kevlar pull rope 24 is combined, so that the inner sailboard embedded part 13 can be prevented from being separated from the inner sailboard 11 during vibration.

In the embodiment, the solar wing sailboard 1 is a main body structure of a satellite solar wing and consists of a PCB (printed circuit board), a battery piece, a sailboard embedded part of a compression point and a frame, wherein the PCB is a base plate of the sailboard, and the solar wing battery piece is attached to the surface of the PCB; the solar wing sailboard comprises a solar wing sailboard body, a plurality of compaction holes 15, a sailboard embedded part, a solar wing sailboard body and a solar wing sailboard body, wherein the compaction holes 15 are preset on the plate and are used for installing sailboard embedded parts of compaction points, the compaction holes 15 on the solar wing sailboard body are opposite to compaction seats 22 on the star body, and the solar wing sailboard body corresponds to each other up and down in a compaction state.

To provide rigidity to the solar panel 1, a bezel is mounted around the PCB.

It should be noted that the number of the solar wing pressing points can be flexibly selected according to the carrying vibration condition, and the pressing points in the present embodiment are substantially composed of a sailboard embedded part disposed in the pressing hole 15 and a kevlar rope 24 connected to the sailboard embedded part in a penetrating manner.

The compaction holes 15 and the compaction seats 22 are correspondingly arranged, preferably in a one-to-one correspondence, and the number of the compaction holes is adjustable to form a structural foundation of a required compaction point, the compaction point can be selected from a plurality of paired compaction holes 15 and compaction seats 22 according to carrying vibration conditions, sailboard embedded parts are installed in the selected compaction holes 15, compaction operation is completed through the Schiff pull ropes, and the sailboard embedded parts are in one-to-one correspondence with the Keff pull ropes 24 to form the compaction point for exerting compaction and binding effects.

The pressing holes 15 of the remaining non-installed sailboard embedded parts can be opposite to the pressing seats 22 in position in a folded state to form reserved pressing points, the folding of the whole solar wing sailboard 1 is not affected, meanwhile, the structural basis of a plurality of pressing points reserved on the solar wing sailboard 1 is realized, and different carrying requirements can be met through the number of the pressing points, and the method is described herein.

Under the compression state, the Kevlar stay 24 sequentially passes through the inner sailboard 11 and the outer sailboard 12 of the solar wing sailboard 1, the ropes are tensioned through the pre-tightening assembly 21, the two sailboards are compressed on the compression seat 22 of the star body, after the satellite enters the orbit, the Kevlar stay 24 is burned through the releasing unit 3, the restraint on the sailboards is released, and the unlocking release of the solar wing is realized.

Specifically, the releasing unit 3 includes a hot melting device installed on the star, all independent kev pulling ropes 24 pass through the hot melting device, and after the satellite enters the orbit, the hot melting device is electrified and blows the kev pulling ropes 24, so that the solar panel 1 is released.

Referring to fig. 6-8, after the solar-wing sailboard 1 is released, the solar-wing sailboard is further unfolded and locked by a hinge, the hinge comprises a root hinge 41 arranged between the star body and the inner-side sailboard 11 and used for folding and unfolding the solar-wing sailboard 1, and an inter-board hinge 42 arranged between the inner-side sailboard 11 and the outer-side sailboard 12 and used for folding and unfolding the two, the root hinge 41 is provided with a triggering device 5, and the triggering device 5 is used for unfolding the outer-side sailboard 12.

Referring to fig. 9-12, after the solar-wing sailboard 1 is released, the inner sailboard 11 and the outer sailboard 12 are first unfolded as a whole with respect to the star in a folded state, and when the whole is unfolded at a certain angle, preferably 90 °, with respect to the star, the triggering device 5 on the root hinge 41 triggers to release the constraint on the outer sailboard 12, and under the action of the inter-board hinge 42, the outer sailboard 12 is unfolded and locked with respect to the inner sailboard 11, thereby realizing the complete unfolding of the solar-wing sailboard 1.

The root hinge 41 comprises a female hinge 43, a male hinge 44 and a root hinge main torsion spring 45, the female hinge 43 is connected with the inner sailboard 11, the male hinge 44 is connected with the star, and the whole released solar wing sailboard 1 before being triggered is unfolded relative to the star through the root hinge main torsion spring 45.

After the solar-wing sailboard 1 is unfolded at a certain angle, the triggering device 5 causes the outer sailboard 12 to be unfolded relative to the inner sailboard 11.

Specifically, the triggering device 5 includes a triggering lever 51, a triggering lever 52, a triggering screw 53, a triggering device rotating shaft 54 and a triggering torsion spring 55, the triggering lever 52 is fixedly connected to the male hinge 44, the triggering lever 51 is mounted on the rotating shaft of the root hinge 41 through the triggering device rotating shaft 54, and the rotating shaft of the root hinge 41 is fixedly connected to the female hinge 43;

the trigger torsion spring 55 is sleeved on the trigger device rotating shaft 54, the trigger screw 53 is connected to the rear end of the trigger lever 51, the trigger lever 51 is in a zigzag structure, the trigger screw 53 is connected to the rear end of the top of the trigger lever 51, under the action of the trigger torsion spring 55, the front end of the trigger lever 51 is attached to the outer sailboard 12 in a compressed state, when the root hinge 41 is unfolded by a certain angle, namely after the male hinge 44 and the female hinge 43 are unfolded relatively, the trigger lever 52 connected to the male hinge 44 collides against the bottom of the screw of the trigger screw 53, and meanwhile the trigger lever 51 rotates around the trigger device rotating shaft 54 through the trigger torsion spring 55, and after a certain angle of rotation, the front end of the trigger lever 51 and the outer sailboard 12 are separated and are unfolded in sequence.

The triggered outer sailboard 12 is secondarily unfolded through the inter-board hinge 42 due to the fact that the triggered outer sailboard 12 is released, specifically, the inter-board hinge 42 comprises a female hinge 43, a male hinge 44 and an inter-board hinge main torsion spring 46, the female hinge 43 is connected with the outer sailboard 12, the male hinge 44 is connected with the inner sailboard 11, the triggered solar wing sailboard 1 is relatively unfolded through the inter-board hinge main torsion spring 46, and the outer sailboard 12 is unfolded 180 degrees relative to the inner sailboard 11 through the inter-board hinge 42 based on the state that the inner sailboard 11 is unfolded 90 degrees relative to the star body.

In order to lock the state of the solar panel 1 after two expansions, the inter-panel hinge 42 and the root hinge 41 are provided with locking assemblies 6 for locking the expansion state between the inner panel 11 and the star and locking the expansion state between the outer panel 12 and the inner panel 11, respectively.

The locking assembly 6 comprises a locking rod 61 connected to the female hinge 43 and a locking hole 62 arranged on the male hinge 44, the locking rod 61 is sleeved with a pressure spring, and after the female hinge 43 and the male hinge 44 rotate relatively, the locking rod 61 can be inserted into the locking hole 62 under the action of the pressure spring so as to lock the unfolded solar panel 1 in place, so that the solar panel 1 can be reliably kept in an unfolded state.

Through the satellite solar wing, the solar wing sailboard 1 can be stably folded and pressed on the surface of the star before entering the orbit, and the solar wing sailboard 1 can be reliably unfolded after entering the orbit, so that the technical purpose of stably and reliably providing electric energy for the satellite is achieved.

The invention also provides a small satellite, which comprises a satellite body and the satellite solar wing, wherein the satellite solar wing which is folded, compressed and released to be unfolded can be more suitable for the application of the small satellite with smaller volume, and the stable reliability of electric energy supply is ensured.

It should be noted that, without conflict, features in the embodiments of the present application may be combined with each other.

The foregoing description is only of the preferred embodiments of the present application and is not intended to limit the same, but rather, various modifications and variations may be made by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application should be included in the protection scope of the present application.

Claims (10)

1. A satellite solar wing, comprising: the solar wing sailboard is connected to the star body and comprises an inner side sailboard and an outer side sailboard, a hinge is arranged between the star body, the inner side sailboard and the outer side sailboard, the solar wing sailboard is compressed or released on the star body through a compression release device, and the released solar wing sailboard is unfolded and locked through the hinge.

2. The satellite solar wing according to claim 1, wherein the compression release device comprises a compression unit and a release unit, the compression unit being mounted on the star and comprising a pre-compression assembly, a compression seat, a guide and a kevlar pulling rope;

the solar wing sailboard is provided with a sailboard embedded part, the fixed end of the Kevlar stay rope is bound on the sailboard embedded part, the pre-tightening end sequentially penetrates through the compression seat and the guide part and then is connected to the pre-tightening assembly, the pre-tightening assembly comprises a pre-tightening base, a pre-tightening nut and a pre-tightening screw, and a guide post is arranged in the pre-tightening base.

3. The satellite solar wing according to claim 2, wherein the sailboard embedded part comprises an inner sailboard embedded part and an outer sailboard embedded part which are respectively arranged on the inner sailboard and the outer sailboard, the solar wing sailboards are sequentially stacked with the inner sailboard embedded part, the outer sailboard embedded part and the compressing seat in a compressing state, and the mutual contact surface is a spherical surface;

the top of inboard sailboard buries is provided with the recess, it has spacing ball to hold to lie in the recess, the stiff end of Kevlar stay cord is connected on the spacing ball.

4. The satellite solar wing according to claim 2, wherein the solar wing sailboard is provided with a pressing hole for installing the sailboard embedded part, and the pressing hole is opposite to the pressing seat;

the compression holes and the compression seats are correspondingly arranged, the number of the compression holes is adjustable, and the sailboard embedded parts and the Kevlar stay ropes are in one-to-one correspondence.

5. The satellite solar wing according to claim 4, wherein the release unit comprises a hot melt device mounted on the star, the kev pull ropes all pass through the hot melt device, and the hot melt device is capable of blowing the kev pull ropes to release the solar wing sailboard.

6. The satellite solar wing according to claim 4, wherein the hinge comprises a root hinge for folding and unfolding the solar wing sailboard arranged between the star and the inner sailboard, and an inter-board hinge for folding and unfolding the inner sailboard and the outer sailboard arranged between them, wherein a triggering device is arranged on the root hinge and used for unfolding the outer sailboard.

7. The satellite solar wing according to claim 6, wherein the root hinge includes a female hinge, a male hinge, and a root hinge main torsion spring, the female hinge being connected to the inner sailboard, the male hinge being connected to the star, the released solar sail board being unfolded relative to the star by the root hinge main torsion spring.

8. The satellite solar wing according to claim 7, wherein the trigger device comprises a trigger lever, a trigger rod, a trigger screw, a trigger device rotating shaft and a trigger torsion spring, the trigger rod is fixedly connected to the male hinge, the trigger lever is mounted on the rotating shaft of the root hinge through the trigger device rotating shaft, and the rotating shaft of the root hinge is fixedly connected with the female hinge;

the trigger torsion spring is sleeved on the trigger device rotating shaft, the trigger screw is connected to the trigger lever, the trigger lever can be abutted to the screw rod of the trigger screw, and the trigger lever can rotate around the trigger device rotating shaft through the trigger torsion spring.

9. The satellite solar wing according to claim 6, wherein the inter-panel hinge comprises a female hinge, a male hinge and an inter-panel hinge main torsion spring, the female hinge being connected to the outer sailboard, the male hinge being connected to the inner sailboard, the triggered solar wing sailboards being relatively unfolded by the inter-panel hinge main torsion spring;

the inter-board hinge and the root hinge are respectively provided with a locking component, and the locking components are used for locking the inner sailboard and the star body and locking the unfolding states of the outer sailboard and the inner sailboard;

the locking assembly comprises a locking rod connected to the female hinge and a locking hole formed in the male hinge, a pressure spring is sleeved on the locking rod, and after the female hinge and the male hinge relatively rotate, the locking rod can be inserted into the locking hole under the action of the pressure spring.

10. A minisatellite comprising a star and a satellite solar wing according to any one of claims 1-9.

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