Compression release mechanism and method thereof

A technology of releasing mechanism and pressing seat, which is used in motor vehicles, space navigation equipment, space navigation equipment, etc., can solve the problem of how many plates are pressed at a distance, so as to ease the extraction process, avoid large-angle inclination, reduce The effect of small impact

Active Publication Date: 2021-12-21
SHANGHAI AEROSPACE SYST ENG INST +1
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  • Description
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Problems solved by technology

[0005] The purpose of the present invention is to provide a pressing and releasing mechanism and its method to solve the problem of large number of boards and large distance pressing and releasing

Method used

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  • Compression release mechanism and method thereof
  • Compression release mechanism and method thereof

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Embodiment Construction

[0028] The following will combine Figure 1 ~ Figure 2 The compression release mechanism and its method of the present invention will be further described in detail.

[0029] Restricted by the size of the launch envelope, the large array payload on the spacecraft is usually divided into multiple sub-areas. During the launch process, the sub-areas are superimposed on each other, and each sub-area is expanded after entering the predetermined orbit. The compression release mechanism is used to compress each sub-area during the launching process. After entering the predetermined orbit, the compression release mechanism releases the compression effect on each sub-area, and the release process should not affect the expansion of each sub-area.

[0030] figure 1 The above is a schematic diagram of the compression release mechanism of the preferred embodiment of the present invention.

[0031] see figure 1 , the compression release mechanism of this embodiment includes a base 1, a f...

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Abstract

The pressing and releasing mechanism and method thereof of the present invention solve the problems of large number of boards and large distances of pressing and releasing. The compression release mechanism includes a base, a load-bearing component, a spring and a spring sleeve. The load-bearing component includes an unlocking end, a main load-bearing member and an adjusting end. The adjusting end includes an angle fine-tuning component and an adjusting nut; the unlocking end is installed on the base; The spring sleeve is installed on the plate farthest from the base; the adjustment end is placed in the spring sleeve; the main bearing part runs through the rear end of each plate and is connected to the unlocking end; the angle fine-tuning assembly and the adjustment nut are sequentially set on the main bearing On the other end of the power piece, the angle fine-tuning assembly is supported on the main load-bearing piece, and the pressing force is applied by tightening the adjusting nut, and the pressing force is transmitted to each plate through the angle fine-tuning assembly; the spring is placed in the spring sleeve, and one end It is connected with the spring sleeve, and the other end is connected with the other end of the main bearing member.

Description

technical field [0001] The invention relates to the design of mechanisms on spacecraft, in particular to a pressing and releasing mechanism and a method thereof. Background technique [0002] With the diversification of functions and the increasing functional requirements of military and civilian spacecraft, higher requirements are put forward for the space scale parameters such as the length and area of ​​the plate-frame structure on the spacecraft. However, the limited size of the launch envelope limits the size of the spacecraft, and it is difficult to achieve direct launch of a large-area plate-and-frame structure. The mainstream method adopted at this stage is to divide the large-area working front into multiple sub-boards, fold the sub-boards during the launch stage to reduce the envelope size, install corresponding unfolding mechanisms between each sub-board, and pass through the The unfolding mechanism splices each sub-board into a working front. This method effect...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64G1/22B64G1/66
CPCB64G1/222B64G1/66
Inventor 李明孙世超钟汉田李向华周鑫崔琦峰朱雪龙沈勤
Owner SHANGHAI AEROSPACE SYST ENG INST
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