Satellite solar wing auxiliary supporting device

Abstract

The utility model provides a satellite solar wing auxiliary supporting device which comprises a supporting component and a top cap connected with the supporting component in a sliding mode and further comprises a limiting component connected with the supporting component, and the limiting component is also connected with the top cap in a sliding mode for limiting. The supporting component comprises a base, a spring and a connecting piece connected with the base, the connecting piece is in sliding connection with the top cap, the spring is arranged between the base and the top cap through the connecting piece, and the limiting component is connected with the connecting piece. When the spring is compressed, the spring is compressed to provide certain supporting force, and the spring can also play a role in buffering. The solar wing multi-point pressing device has the advantages of being capable of solving the problem of solar wing multi-point pressing, simple in structure, small in envelope, light in weight and low in machining cost.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of space technology, especially relates to a satellite solar wing auxiliary support device. BACKGROUND

[0002] Solar energy is an important energy source for micro-satellite in-orbit operation of a spacecraft, and is an indispensable part of a solar sail in the design of a micro-satellite; as a main carrier and structural support of the solar sail, the solar wing is limited by the envelope space of a launch fairing, and needs to be tightly packed on one side of the satellite, and whether it can be smoothly packed and supported and buffered during the satellite launch stage plays an important role in the success of the satellite launch.

[0003] In the prior art, the solar wing is designed in a multi-point packing manner, although the reliability of the multi-point packing is high, the overall structure contains dozens of components, the structure is relatively complex, the envelope is large, the weight is heavy, and the cost is high, which cannot meet the needs of the current commercial space market. UTILITY MODEL CONTENTS

[0004] To solve the above technical problems, the utility model provides a satellite solar wing auxiliary support device, which is especially suitable for low-cost manufacturing, and can realize light weight, small envelope, and meet the reliable packing requirements of the solar wing.

[0005] The technical scheme adopted by the utility model is: a satellite solar wing auxiliary support device, comprising a support component and a top hat in sliding connection with the support component, further comprising a limiting component connected with the support component, and the limiting component is also in sliding connection with the top hat for limiting.

[0006] Further, the support component comprises a connecting piece, a base and a spring, the connecting piece is connected with the base, the top hat is in sliding connection with the connecting piece through the spring, and the spring is arranged between the top hat and the base, and the limiting component is connected with the connecting piece.

[0007] Further, the support component further comprises a fixing assembly and a baffle, the baffle is connected with the connecting piece and arranged between the spring and the base, the connecting piece is arranged in the base and connected with the fixing assembly for fastening.

[0008] Further, the base is provided with a groove for accommodating the fixing assembly.

[0009] Further, the fixing assembly comprises a nut in threaded connection with the connecting piece, and the connecting piece can be embedded with the base to prevent the connecting piece from rotating.

[0010] Further, the fixing assembly further comprises at least one gasket, and the gasket is connected with the connecting piece and arranged between the base and the nut or the base and the baffle.

[0011] Further, the limiting component comprises a limiting piece connected with the supporting component, and the limiting piece is movably inserted into the top cap.

[0012] Further, the limiting component further comprises a positioning piece, the limiting piece is inserted into the supporting component, and the positioning piece is arranged in the supporting component to fix the limiting piece.

[0013] The utility model has the advantages and positive effects that: due to the above technical scheme, the solar wing multi-point compression problem can be solved; the utility model has the advantages of simple structure, small envelope, light weight and low processing cost. BRIEF DESCRIPTION OF DRAWINGS

[0014] Fig. 1 is the explosion map of an embodiment of the utility model;

[0015] Fig. 2 is the structural schematic view of an embodiment of the utility model when being compressed;

[0016] Fig. 3 is the structural schematic view of an embodiment of the utility model when not being compressed;

[0017] Fig. 4 is the structural schematic view of the back surface of the base in an embodiment of the utility model;

[0018] In the drawing:

[0019] 1, top cap 2, base 3, spring

[0020] 4, connecting piece 5, baffle 6, nut

[0021] 7, limiting piece 8, positioning piece 11, limiting groove

[0022] 21, connecting hole 22, boss 23, recess

[0023] 41, insertion hole 91, large pad 92, small pad

[0024] 93, elastic pad DETAILED DESCRIPTION

[0025] The embodiments of the utility model will be described below in conjunction with the drawings, and the described embodiments are only a part of the embodiments of the utility model, not all the embodiments.

[0026] The embodiments of the utility model will be described in detail below, and the examples of the embodiments are shown in the drawings, wherein the same or similar reference signs represent the same or similar units or units with the same or similar functions throughout. The embodiments described below by referring to the drawings are exemplary and are only used to explain the utility model, and cannot be understood as limiting the utility model.

[0027] In the description of this utility model, it should be understood that terms such as "installation", "connection", and "fixation" should be interpreted broadly, and can refer to direct connection, installation or fixation, or indirect connection, installation or fixation. This utility model does not limit this.

[0028] In the description of this utility model, it should be understood that the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc., indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this utility model and simplifying the description, and are not intended to indicate or imply that the structure or unit referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model.

[0029] like Figs. 1 to 4 As shown in the schematic diagram of an embodiment of the satellite solar panel auxiliary support device of the present invention, it includes a support component and a top cap 1 slidably connected to the support component, and also includes a limiting component connected to the support component, which is also slidably connected to the top cap 1 for limiting.

[0030] In this embodiment, the supporting component includes a connector 4, a base 2, and a spring 3. The connector 4 is connected to the base 2. The top cap 1 is slidably connected to the connector 4 via the spring 4, and the spring 3 is disposed between the base 2 and the top cap 1. A limiting component is connected to the connector 4 to limit movement. In this embodiment, the top cap 1 is movably fitted onto the end of the connector 4 away from the base 2, and its movement range is limited by the limiting component. The spring 3 is fitted onto the outside of the connector 4 to adjust the movement of the top cap 1 through elastic potential energy and to provide support for the top cap 1. The connector 4 can serve as a central axis to connect the top cap 1, the spring 3, and the base 2 into a whole. The end of the top cap 1 is arc-shaped to contact the back of the solar panel. The base 2 has multiple mounting holes for connection and fixation to the satellite.

[0031] In this embodiment, the connector 4 is detachably connected to the base 2. The supporting component also includes a fixing component and a baffle 5. The baffle 5 is connected to the connector 4 and is disposed between the spring 3 and the base 2. The connector 4 passes through the base 2 and is connected to the fixing component for fastening. In this embodiment, the connector 4 is fastened to the base 2 by the cooperation of the baffle 5 and the fixing component. One end of the spring 3 contacts the top cap 1, and the other end contacts the baffle 5.

[0032] In the embodiment, the base 2 is provided with a groove 23 for accommodating the fixing assembly. The fixing assembly is installed in the groove 23 and does not exceed the back plane of the base 2, which can ensure the planar requirement of the base 2 when the base 2 is installed with the satellite body, and can also make full use of the envelope space of the whole device, and the groove can also reduce the structure weight and better realize the small envelope and light weight.

[0033] In the embodiment, the fixing assembly includes a nut 6 threadedly connected with the connecting piece 4, and the connecting piece 4 can be embedded with the base 2 to prevent the connecting piece 4 from rotating.

[0034] In the embodiment, the base 2 is provided with a connecting hole 21, and the connecting piece 4 is inserted into the connecting hole 21 and the connecting piece 4 is adapted to the shape of the connecting hole 21. In order to facilitate the installation of the nut 6 and the connecting piece 4, in the embodiment, the connecting hole 21 is a square hole, and the part of the connecting piece 4 below the baffle 5 is adapted in shape to be embedded with the square hole; in other embodiments, the connecting hole 21 can also be provided as other polygonal holes, which can prevent the connecting piece 4 from rotating when the nut 6 is installed. In the embodiment, the top of the base 2 is provided with a boss, the connecting hole 21 is provided at the boss, and the back of the boss is provided with a groove 23 for accommodating the fixing assembly, that is, the groove 23 at the back of the boss is used for installing the nut 6 to ensure that the nut 6 does not exceed the back plane of the base 2.

[0035] In the embodiment, the fixing assembly further includes at least one gasket, which is connected with the connecting piece 4 and arranged on the side of the base 2 facing or away from the nut 6, and more specifically, each gasket is arranged between the base 2 and the nut 6 or between the base 2 and the baffle 5. In the embodiment, the number of gaskets is multiple, including a large flat gasket 91, a small flat gasket 92 and a spring gasket 93, the large flat gasket 91 is sleeved outside the connecting piece 4 and arranged between the baffle 5 and the base 2, and more specifically, the large flat gasket 91 is arranged between the boss and the baffle 5; the small flat gasket 92 and the spring gasket 93 are both sleeved outside the connecting piece 4 and arranged between the base 2 and the nut 6, and more specifically, after the connecting piece 4 passes through the boss of the base 2, the small flat gasket 92, the spring gasket 93 and the nut 6 are installed in sequence, and the small flat gasket 92, the spring gasket 93 and the nut 6 are all arranged in the groove 23.

[0036] In the embodiment, the limiting component includes a limiting piece 7 connected with the supporting component, and the limiting piece 7 is movably inserted into the top cap 1. In the embodiment, the limiting piece 7 is connected with the connecting piece 4, and the top cap 1 is provided with a limiting groove 11, and the limiting piece 7 is movably inserted into the limiting groove 11. The limiting device of the spring 3 is formed by the cooperation of the limiting groove 11 and the limiting piece 7, which can limit the compression or extension of the spring 3.

[0037] In the embodiment, the limiting component further comprises a positioning member 8, the limiting member 7 is inserted through the support component, and the positioning member 8 is arranged in the support component to fix the limiting member 7. The top cap 1 is symmetrically provided with two limiting grooves 11, and the two ends of the limiting member 7 are respectively arranged in the corresponding limiting grooves 11. In the embodiment, the connecting member 4 is provided with an insertion hole 41, the limiting member 7 is connected with the connecting member 4 in an interference fit through the insertion hole 41, the positioning member 8 is arranged in the connecting member 4 and is arranged perpendicularly to the limiting member 7, the limiting member 7 can be fixed by the positioning member 8, the limiting member 7 can be better prevented from moving or separating in the insertion hole 41, and the hidden danger that the limiting member 7 is stressed and deformed when the limiting member 7 is in boundary contact with the limiting groove 11 due to the movement of the top cap 1 driven by the spring 3 is reduced.

[0038] When the satellite solar wing auxiliary support device is compressed, the satellite solar wing auxiliary support device has the maximum supporting force, at this time, the spring 3 is in a retracted state, and the limiting member 7 is arranged at the boundary of the limiting groove 11, and the limiting member 7 is in a stroke limit state; when the satellite solar wing auxiliary support device is not compressed, the satellite solar wing auxiliary support device has the minimum supporting force, at this time, the spring 3 is in an extended state, and the limiting member 7 is arranged at the other boundary of the limiting groove 11, and the limiting member 7 is also in a stroke limit state, and the spring 3 cannot continue to extend.

[0039] The working process of the embodiment applied to the micro-satellite solar wing auxiliary support is as follows:

[0040] In the rocket launching phase, the satellite is limited by the envelope space in the rocket, the solar wing needs to be folded on the satellite body side wall and keep a certain folding stiffness, the arc-shaped end of the top cap 1 is in direct contact with the concave embedded part on the back of the solar wing panel, the base 2 is connected and fixed with the satellite body through four counterborescrews, at this time, the spring 3 is in a compressed state due to the pressure of the solar wing panel, the limiting member 7, the insertion hole 41 and the limiting groove 11 provide limiting stroke protection for the spring 3, the spring 3 provides a certain supporting force upward by using the stretching and retracting characteristics, and can also play a certain buffering effect, so as to ensure the folding frequency and stiffness of the solar wing; when the solar wing is unfolded, the spring 3 gradually loses the pressure from the panel, and recovers from the compressed state to the extended state (i.e. the non-compressed state), at this time, the auxiliary support device is separated from the solar wing and does not provide support for the solar wing.

[0041] The utility model discloses installation safe and reliable: can pass through the arc-shaped end of top cap 1 and solar wing panel back contact, can prevent solar wing panel reciprocating movement, more safe and reliable;

[0042] The utility model discloses height adjustable: different solar wing after folding the internal envelope space is different, the length of limiting groove 11 can be processed according to the space envelope and be adjusted to satisfy the whole star folding volume requirement, the greater the distance between the upper and lower boundaries of limiting groove 11, the greater the deformation of compression spring, the greater the supporting force range provided by compression spring, more can satisfy the use demand of solar wing;

[0043] The utility model discloses low cost: traditional solar wing support mode adopts memory alloy, stretch pole and other components, and the price is expensive, and compared with it, the utility model is mostly metal structural member, and simple composition, processing cost is low, is applicable to the solar wing scheme of microsatellite solar wing " single point compression, multiple point support", and more conforms to the development and application demand of current commercial space market.

[0044] The utility model discloses simple structure: compared with traditional solar wing support mode, the utility model's structure simple, clever design, utilize the compression, stretch performance of spring 3, provide the support force for solar wing sailboard and keep certain gather frequency.

[0045] The utility model discloses be applicable to the gathering auxiliary support of microsatellite solar wing, with simple structure, low in cost, light weight's characteristics, especially applicable to the overall gathering envelope volume rigorous situation, therefore the utility model has very considerable application prospect in the structure of space microsatellite solar wing product.

[0046] The above embodiment of the utility model has been explained in detail, but the content is only the preferred embodiment of the utility model, and can not be considered for limiting the implementation scope of the utility model. All equal changes and improvements in the utility model application scope still belong to the patent coverage of the utility model.

Claims

1. A satellite solar wing auxiliary support device, comprising a support component and a top hat in sliding connection with the support component, characterized in that: The support component is connected with a limiting component, and the limiting component is also connected with the top cap in a sliding mode to limit the top cap.

2. The satellite solar wing auxiliary support device of claim 1, wherein: The support component comprises a connecting piece, a base and a spring, the connecting piece is connected with the base, the top cap is connected with the connecting piece in a sliding mode through the spring, and the spring is arranged between the top cap and the base.

3. The satellite solar wing auxiliary support device of claim 2, wherein: The support component further comprises a fixing assembly and a baffle, the baffle is connected with the connecting piece and arranged between the spring and the base, the connecting piece is arranged through the base and connected with the fixing assembly to be fastened.

4. The satellite solar wing auxiliary support apparatus of claim 3, wherein: The base is provided with a groove to accommodate the fixing assembly.

5. The satellite solar wing auxiliary support apparatus of claim 3, wherein: The fixing assembly comprises a nut connected with the connecting piece in a threaded mode, and the connecting piece can be embedded with the base to prevent the connecting piece from rotating.

6. The satellite solar wing auxiliary support apparatus of claim 5, wherein: The fixing assembly further comprises at least one gasket connected with the connecting piece to be arranged between the base and the nut or between the base and the baffle.

7. The satellite solar wing auxiliary support device according to any one of claims 1-6, characterized in that: The limiting component comprises a limiting piece connected with the support component, and the limiting piece is movably arranged in the top cap.

8. The satellite solar wing auxiliary support apparatus of claim 7, wherein: The limiting component further comprises a positioning piece, the limiting piece is arranged in the support component, and the positioning piece is arranged in the support component to fix the limiting piece.

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