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Satellite launching box ejection device

A satellite launch and ejection device technology, applied in the aerospace field, can solve problems such as ejection travel, elastic force size and elastic uniformity limitations, large-sized satellites are not suitable, etc.

Pending Publication Date: 2022-07-12
北京劢亚科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Although this device is relatively simple in structure and light in weight, due to the limitation of the characteristics of the spring itself, the ejection stroke, the size of the elastic force and the uniformity of the elastic force are limited, especially not suitable for large-sized satellites.

Method used

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  • Satellite launching box ejection device
  • Satellite launching box ejection device
  • Satellite launching box ejection device

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Embodiment Construction

[0022] Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. In the following description, numerous specific details are set forth in order to give those skilled in the art a more complete understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention may be practiced without some of these specific details. Furthermore, it is to be understood that the invention is not limited to the specific embodiments described. Rather, the invention is contemplated to be practiced with any combination of the following features and elements, whether or not they relate to different embodiments. Accordingly, the following aspects, features, embodiments, and advantages are for illustration purposes only and should not be regarded as elements or limitations of the claims unless explicitly stated in the claims.

[0023] The meanings of the terms involved in this specificati...

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Abstract

Disclosed is a satellite launch box ejection device (100), comprising: a lower fixing plate (101); an upper fixing plate (102); a central shaft (201); a first boss (202); a second bushing (203); the first end of each first connecting rod (106) and the first end of each second connecting rod (107) are connected to the first shaft sleeve (202) and the second shaft sleeve (203) in a pivoted mode respectively, and the second end of each first connecting rod (106) and the second end of each second connecting rod (107) are connected in a pivoted mode; a pull ring (103); the first end of each tension spring (108) is connected to the pull ring (103), and the second end of each tension spring (108) is connected to the second end of the first connecting rod (106) and the second end of the second connecting rod (107); and the locking and releasing mechanism is used for switching the device (100) from a locking state to a releasing state, so that the first connecting rod group and the second connecting rod group are mutually opened under the recovery action of the tension spring group in the stretching state, the upper fixing plate (102) is driven to be bounced off through the second shaft sleeve (203), and the satellite is ejected and released.

Description

technical field [0001] The invention relates to the field of aerospace technology, in particular to a satellite launch box ejection device. Background technique [0002] With the rapid development of aerospace technology, the frequency of satellite launches in my country is getting higher and higher, and the number of satellite launches is increasing. The ejection device of the satellite launch box is an indispensable part of the satellite launch. After the satellite is launched into space by a rocket, it needs to complete the separation of the star and arrow. . Therefore, the design of the ejection device must strictly control the weight of the mechanism, and ensure that the system has the characteristics of high reliability, high performance, and high operability. [0003] At present, most of the mechanisms used to realize the satellite ejection function rely on the recovery after the compression of the compression spring to realize the ejection of the satellite from the...

Claims

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Application Information

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IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 崔鸿斌孙文明
Owner 北京劢亚科技有限公司
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