Solar wing root hinge and satellite

Abstract

The utility model relates to a solar wing root hinge and a satellite. The solar wing root hinge comprises a hinge seat; the hinge arm is rotationally connected with the hinge seat; the at least two groups of driving assemblies are provided with hinge seats, one group of driving assemblies is arranged on one side of the hinge arm, the other group of driving assemblies is arranged on the other side of the hinge arm, and the at least two groups of driving assemblies are used for driving the hinge arm to rotate; and the linkage wheel is arranged on the hinge seat and located on one side of the hinge arm, and the linkage wheel is used for being connected with a linkage rope. According to the solar wing root hinge, the driving assemblies are arranged on the two sides of the solar wing root hinge, the single-side envelope size of the solar wing root hinge is reduced, and the problem that assembly is difficult due to driving force single-side offset is at least partially solved.

Description

Technical Field

[0001] This application relates to the field of aerospace equipment, and more particularly to a solar panel root hinge and a satellite. Background Technology

[0002] The solar array root hinge is used to connect the satellite body and the solar array assembly, facilitating the deployment of the solar array assembly after the satellite is launched. The solar array root hinge typically adopts a structure with a linkage wheel on one side and a drive spring on the other side. With multiple drive springs located on the same side of the solar array root hinge, the single-sided envelope size of the solar array root hinge is large, and it may also cause unidirectional bias of the driving force, which is not conducive to the assembly of the solar array root hinge. Utility Model Content

[0003] To address the aforementioned issues, this application provides a solar root hinge and a satellite, which helps to reduce the unilateral envelope size of the solar root hinge and solve the problem of unilateral bias of the driving force.

[0004] Embodiments of this application provide a solar wing root hinge, comprising:

[0005] Hinge seat;

[0006] The hinge arm includes: a first hinge arm and a second hinge arm, wherein the first hinge arm and the second hinge arm are respectively rotatably connected to the hinge seat;

[0007] At least two sets of drive components are disposed on the hinge seat, wherein one set of drive components is located on one side of the hinge arm and the other set of drive components is located on the other side of the hinge arm, and the at least two sets of drive components are used to drive the first hinge arm and the second hinge arm to rotate.

[0008] A linkage wheel is disposed on the hinge seat and located on one side of the hinge arm. The linkage wheel is used to connect the linkage rope.

[0009] According to some embodiments of this application, each group of driving components includes:

[0010] The drive wheel is mounted on the hinge seat;

[0011] An elastic element is disposed on the drive wheel for driving the hinge arm to rotate.

[0012] According to some embodiments of this application, the solar wing root hinge further includes:

[0013] A first stop lever is disposed on the first hinge arm, and the first stop lever abuts against the elastic element corresponding to the first hinge arm;

[0014] A second stop is provided on the second hinge arm, and the second stop abuts against the elastic element corresponding to the second hinge arm.

[0015] According to some embodiments of this application, the elastic element includes an S-shaped spring.

[0016] According to some embodiments of this application, at least two drive wheels located on the same side of the hinge arm are integrally formed.

[0017] According to some embodiments of this application, the linkage wheel and the drive wheel located on the same side of the hinge arm are integrally formed.

[0018] According to some embodiments of this application, the solar wing root hinge further includes: a limiting structure disposed on the hinge seat or the hinge arm, wherein after the hinge arm is deployed into position, the limiting structure is used to restrict the hinge arm from continuing to rotate.

[0019] According to some embodiments of this application, the solar wing root hinge further includes a locking structure disposed on the hinge seat, wherein the locking structure is used to lock the hinge arm after the hinge arm is deployed into position.

[0020] According to some embodiments of this application, the solar wing root hinge further includes a position sensor for detecting whether the hinge arm is fully extended.

[0021] Embodiments of this application also provide a satellite, comprising:

[0022] Satellite body;

[0023] As described above, the solar wing root hinge connects to the satellite body;

[0024] Solar array assembly, wherein the hinge arm connects the solar array assembly.

[0025] This application provides drive components on both sides of the solar root hinge, reducing the single-sided envelope size of the solar root hinge, and at least partially solving the assembly difficulties caused by the single-sided offset of the drive force. Attached Figure Description

[0026] To more clearly illustrate the technical solutions of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without exceeding the scope of protection claimed by this application.

[0027] Figure 1 This is a schematic diagram of the solar panel root hinge according to an embodiment of this application;

[0028] Figure 2 This is a schematic diagram of the hinge seat according to an embodiment of this application;

[0029] Figure 3 This is a schematic diagram of the hinge arm according to an embodiment of this application;

[0030] Figure 4 This is a schematic diagram of the driving component in an embodiment of this application;

[0031] Figure 5 This is an exploded view of the driving component in an embodiment of this application;

[0032] Figure 6 This is a schematic diagram of the first hinge arm and the second hinge arm in an embodiment of this application;

[0033] Figure 7 This is a schematic diagram of two drive wheels integrally formed according to an embodiment of this application;

[0034] Figure 8 This is a schematic diagram of the limiting structure according to an embodiment of this application;

[0035] Figure 9 This is a schematic diagram of the locking structure in an embodiment of this application;

[0036] Figure 10 This is a schematic diagram of the first hinge arm in an embodiment of this application;

[0037] Figure 11 This is a schematic diagram of a position sensor according to an embodiment of this application;

[0038] Figure 12 This is a schematic diagram of a satellite according to an embodiment of this application. Detailed Implementation

[0039] The technical solutions of this application will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some, not all, of the embodiments of this application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort are within the scope of protection of this application.

[0040] like Figure 1 As shown, an embodiment of this application provides a solar root hinge 100, which includes: a hinge seat 1, a hinge arm 2, at least two sets of drive components 3, and a linkage wheel 4.

[0041] like Figure 2 As shown, the hinge seat 1 is provided with bolt holes 11, and bolts are inserted into the bolt holes 11 to fasten the hinge seat 1 to the satellite body. Optionally, the hinge seat 1 is located on the A-axis SADA (Solar Actuation Device) of the satellite body.

[0042] like Figure 3As shown, the hinge arm 2 is rotatably connected to the hinge base 1. For example, the hinge base 1 is provided with a first pivot hole 12, and a first pivot 13 passes through the first pivot hole 12 to connect one end of the hinge arm 2, so that the hinge arm 2 can rotate relative to the hinge base 1. The other end of the hinge arm 2 is connected to the solar array assembly.

[0043] like Figure 6 As shown, in some embodiments, the hinge arm 2 includes a first hinge arm 21 and a second hinge arm 22, which are located on opposite sides of the hinge base 1. One end of the first hinge arm 21 and one end of the second hinge arm 22 are rotatably connected to the hinge base 1 via a first pivot 13. The other end of the first hinge arm 21 and the other end of the second hinge arm 22 are used to connect to the solar array assembly.

[0044] like Figure 1 As shown, all drive components 3 are mounted on the hinge base 1. At least one set of drive components 3 is located on one side of the hinge arm 2, and at least another set of drive components 3 is located on the other side of the hinge arm 2. The drive components 3 are used to drive the hinge arm 2 to rotate. The number of drive components 3 is set according to requirements; the more drive components 3, the greater the driving force provided to the hinge arm 2. By setting drive components 3 on both sides of the hinge arm 2, the unilateral envelope size of the sun wing root hinge 100 can be reduced, and the problem of unilateral bias of the driving force can be at least partially solved. Optionally, the drive components 3 are mounted on the hinge base 1 via a first pivot 13 on the hinge base 1.

[0045] For example, there are three drive components 3. The first drive component 3a and the second drive component 3b are arranged side by side and are both located on the side of the first hinge arm 21 away from the second hinge arm 22. The third drive component 3c is located on the side of the second hinge arm 22 away from the first hinge arm 21.

[0046] The linkage wheel 4 is mounted on the hinge seat 1 and located on one side of the hinge arm 2. Optionally, the first rotating shaft 13 passes through the linkage wheel 4, and fasteners secure the linkage wheel 4 so that it cannot rotate relative to the hinge seat 1. The linkage wheel 4 is used to connect the linkage rope, which in turn connects other hinges on the solar array assembly, enabling the linkage between the solar array root hinge 100 and other hinges on the solar array assembly. For example, both the linkage wheel 4 and the third drive assembly 3c are located on the side of the second hinge arm 22 away from the first hinge arm 21.

[0047] After the satellite is launched, the device used to lock the solar array components is unlocked, and the drive component 3 drives the hinge arm 2 to rotate, thereby causing the solar array components to deploy.

[0048] In this embodiment, drive components 3 are respectively provided on opposite sides of the hinge arm 2, which provides a sufficiently large driving force to the hinge arm 2 while reducing the single-sided envelope size of the sun wing root hinge 100. The sun wing root hinge 100 in this embodiment can also at least partially solve the problem of single-sided bias of driving force, which facilitates the assembly of the sun wing root hinge 100.

[0049] like Figure 4 and Figure 5 As shown, in some embodiments, each drive assembly 3 includes a drive wheel 31 and an elastic element 32. A first rotating shaft 13 passes through the drive wheel 31 to mount the drive wheel 31 on the hinge seat 1, and the drive wheel 31 cannot rotate relative to the hinge seat 1. The elastic element 32 is mounted on the drive wheel 31 and is used to drive the hinge arm 2 to rotate.

[0050] The linkage wheel 4 and the drive wheel 31 are coaxially arranged. Each drive wheel 31 is provided with an annular groove 311, and the elastic element 32 is disposed in the annular groove 311. The linkage wheel 4 is provided with a protrusion 41 for connecting the linkage rope.

[0051] The solar wing root hinge 100 further includes: a first stop 51 and a second stop 52. The first stop 51 is disposed on the side wall of the first hinge arm 21 and abuts against the elastic element 32 corresponding to the first hinge arm 21. For example, the elastic elements 32 of the first drive assembly 3a and the second drive assembly 3b both abut against the first stop 51 to drive the first hinge arm 21 to rotate. The second stop 52 is disposed on the side wall of the second hinge arm 22 and abuts against the elastic element 32 corresponding to the second hinge arm 22. For example, the elastic element 32 of the third drive assembly 3c abuts against the second stop 52 to drive the second hinge arm 22 to rotate.

[0052] In some embodiments, the elastic element 32 includes an S-shaped spring. The S-shaped spring is disposed in an annular groove 311, one end of which is connected to the drive wheel 31 by a screw 33, and the other end of which abuts against the corresponding hinge arm. When the solar panel assembly is deployed, the S-shaped spring provides driving force for the rotation of the hinge arm.

[0053] like Figure 7 As shown, in some embodiments, at least two drive wheels 31 located on the same side of the hinge arm 2 are integrally formed. Each drive wheel 31 is provided with an elastic element 32 to facilitate the manufacturing and assembly of the drive assembly 3.

[0054] like Figure 5 As shown, in some embodiments, the linkage wheel 4 and the drive wheel 31 located on the same side of the hinge arm 2 are integrally formed, which is beneficial to improving the production efficiency of the solar wing root hinge 100.

[0055] like Figure 8As shown, in some embodiments, the solar root hinge 100 further includes a limiting structure 6, disposed on the hinge seat 1 or the hinge arm 2. After the hinge arm 2 is fully extended, the limiting structure 6 is used to restrict the hinge arm 2 from continuing to rotate, thereby improving the safety of the solar root hinge 100. For example, the limiting structure 6 includes a limiting screw, which is disposed on the hinge seat 1. After the hinge arm 2 is fully extended, it abuts against the limiting screw. Optionally, there are two limiting structures 6, which are respectively disposed for the first hinge arm 21 and the second hinge arm 22.

[0056] like Figure 9 As shown, in some embodiments, the solar root hinge 100 further includes a locking structure 7, which is disposed on the hinge seat 1. After the hinge arm 2 is extended into place, the locking structure 7 is used to lock the hinge arm 2.

[0057] Optionally, the locking structure 7 includes a locking hook 71 and a torsion spring 72. One end of the locking hook 71 is rotatably connected to the hinge seat 1, and the other end of the locking hook 71 is hook-shaped. The torsion spring 72 is disposed on the hinge seat 1 and is used to apply pressure to the locking hook 71. The hinge arm 2 is provided with a locking pin 23 adapted to the locking hook 71. After the hinge arm 2 is extended into place, the locking hook 71 engages with the locking pin 23, and the torsion spring 72 keeps the locking hook 71 in the locked state to restrict the rotation of the hinge arm 2.

[0058] There are two locking structures 7, corresponding to the first hinge arm 21 and the second hinge arm 22 respectively, and each of the first hinge arm 21 and the second hinge arm 22 is provided with a locking pin 23.

[0059] like Figure 10 As shown, the first hinge arm 21 and the second hinge arm 22 have the same structure. Taking the first hinge arm 21 as an example, one end of the first hinge arm 21 is provided with a shaft hole 211, which is used to connect the first rotating shaft 13 for rotatable connection with the hinge seat 1. The other end of the first hinge arm 21 is provided with a connecting hole 214, which is used to connect the solar panel assembly. The bottom of the side wall of the first hinge arm 21 is provided with a stop hole 212, and the first stop 51 is provided in the stop hole 212. The top surface of the first hinge arm 21 is provided with a support ear 213, and the locking pin 23 is provided in the support ear 213. Optionally, there are two support ears 213, which are parallel to each other, and the two ends of the locking pin 23 are respectively connected to the two support ears 213.

[0060] like Figure 11 As shown, in some embodiments, the solar wing root hinge 100 further includes a position sensor 8, which is used to detect whether the hinge arm 2 is fully extended. For example, the position sensor 8 includes a push switch 81 and a push rod 82. When the hinge arm 2 is fully extended, the push rod 82 abuts against the spring of the push switch 81, and the push switch 81 sends a signal to the satellite controller. The controller determines that the hinge arm 2 is fully extended based on the signal from the push switch 81.

[0061] like Figure 12 As shown, an embodiment of this application provides a satellite, which includes a solar array root hinge 100, a satellite body 200, and a solar array assembly 300 as described above. The hinge seat 1 of the solar array root hinge 100 is disposed on the satellite body 200. The hinge arm 2 connects to the connecting rod 301 of the solar array assembly 300, and the linkage rope 302 connects to the linkage wheel 4 and other hinges 303 on the solar array assembly 300, respectively.

[0062] The hinge arm 2 rotates relative to the hinge seat 1 in the direction of the unfolding of the solar wing assembly 300, so that the solar wing assembly 300 unfolds. The linkage rope 302 is used to link the solar wing root hinge 100 with other hinges 303 on the solar wing assembly 300.

[0063] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the technical solutions and core ideas of this application. Therefore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. In summary, the content of this specification should not be construed as a limitation of this application.

Claims

1. A solar wing root hinge, characterized in that, include: Hinge seat; The hinge arm includes: a first hinge arm and a second hinge arm, wherein the first hinge arm and the second hinge arm are respectively rotatably connected to the hinge seat; At least two sets of drive components are disposed on the hinge seat, wherein one set of drive components is located on one side of the hinge arm and the other set of drive components is located on the other side of the hinge arm, and the at least two sets of drive components are used to drive the first hinge arm and the second hinge arm to rotate. A linkage wheel is disposed on the hinge seat and located on one side of the hinge arm. The linkage wheel is used to connect the linkage rope.

2. The solar wing root hinge according to claim 1, characterized in that, Each group of driving components includes: The drive wheel is mounted on the hinge seat; An elastic element is disposed on the drive wheel for driving the hinge arm to rotate.

3. The solar wing root hinge according to claim 2, characterized in that, The solar wing root hinge also includes: A first stop is disposed on the first hinge arm, and the first stop abuts against the elastic element corresponding to the first hinge arm; A second stop is provided on the second hinge arm, and the second stop abuts against the elastic element corresponding to the second hinge arm.

4. The solar wing root hinge according to claim 2, characterized in that, The elastic element includes an S-shaped spring.

5. The solar wing root hinge according to claim 2, characterized in that, At least two of the drive wheels located on the same side of the hinge arm are integrally formed.

6. The solar wing root hinge according to claim 2, characterized in that, The linkage wheel and the drive wheel, located on the same side of the hinge arm, are integrally formed.

7. The solar wing root hinge according to claim 1, characterized in that, Also includes: A limiting structure is provided on the hinge seat or the hinge arm. After the hinge arm is fully extended, the limiting structure is used to restrict the hinge arm from continuing to rotate.

8. The solar wing root hinge according to claim 1, characterized in that, Also includes: A locking structure is provided on the hinge seat, and the locking structure is used to lock the hinge arm after the hinge arm is extended into place.

9. The solar wing root hinge according to claim 1, characterized in that, Also includes: A position sensor is used to detect whether the hinge arm is fully extended.

10. A satellite, characterized in that, include: Satellite body; The solar wing root hinge as described in any one of claims 1 to 9, wherein the hinge seat is connected to the satellite body; Solar array assembly, wherein the hinge arm connects the solar array assembly.

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