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Pressing and releasing mechanism and method thereof

A technology of releasing mechanism and pressing seat, which is used in motor vehicles, aerospace equipment, aerospace aircraft, etc., can solve the problem of how many plates are pressed at a distance, and achieve a smooth extraction process, high rigidity and high strength. Effect

Active Publication Date: 2019-02-05
SHANGHAI AEROSPACE SYST ENG INST +1
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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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  • Pressing and releasing mechanism and method thereof
  • Pressing and releasing mechanism and method thereof

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Embodiment Construction

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

[0029] Due to the limitation of the size of the carrier envelope, the large-front payload on the spacecraft is usually divided into multiple sub-regions. During the launch process, the sub-regions are superimposed on each other, and the sub-regions are expanded after entering the predetermined orbit. The compression release mechanism is used to compress each sub-area during the launch process. After entering the predetermined track, 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, ...

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Abstract

The invention provides a pressing and releasing mechanism and a method thereof. Problems of large plate piece number and large-distance pressing and releasing are solved. The pressing and releasing mechanism comprises a base, a force bearing component, a spring and a spring sleeve; the force bearing component comprises an unlocking end, a main force bearing piece and an adjusting end; the adjusting end comprises an angle fine adjusting component and an adjusting nut; the unlocking end is mounted on the base; the spring sleeve is mounted on a plate piece which is farthest from the base; the adjusting end is placed in the spring sleeve; one end of the main force bearing piece is connected with the unlocking end after penetrating through each plate piece; the angle fine adjusting component and the adjusting nut sleeve the other end of the main force bearing piece in sequence; the angle fine adjusting component is supported on the main force bearing piece; by tightening the adjusting nut to apply a pressing force, the pressing force is transmitted to each plate piece through the angle fine adjusting component; the spring is placed in the spring sleeve; one end of the spring is connected with the spring sleeve; and the other end of the spring is connected with the other end of the main force bearing piece.

Description

Technical field [0001] The invention relates to the design of a mechanism on a spacecraft, in particular to a compression release mechanism and a method thereof. Background technique [0002] With the diversification of functions and functional requirements of military and civilian spacecraft, higher requirements have been put forward on the space scale parameters such as the length and area of ​​the plate-and-frame structure on the spacecraft. However, the limited size of the carrier envelope limits the size of the spacecraft, and it is difficult to directly launch a large-area plate and frame structure. The mainstream approach adopted at this stage is to divide the large-area working front into multiple sub-boards. During the launch phase, the sub-boards are folded to reduce the envelope size, and a corresponding unfolding mechanism is installed between each sub-board. The unfolding mechanism splices each sub-board into a working front. This method effectively weakens the lim...

Claims

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Application Information

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Patent Type & Authority Applications(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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