Horizontal satellite-rocket separation mechanism

A technology of star-arrow separation and separation mechanism, applied in the field of star-arrow separation system, can solve the problems of inability to meet the requirements of 50kg-class satellites, low utilization rate, large space occupation, etc., and achieves reliable unlocking, small separation angular velocity, and reduced impact effects.

Active Publication Date: 2018-09-14
上海中科辰新卫星技术有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The existing horizontal satellite-rocket separation mechanism is mostly used on cubesats less than 5kg, which cannot meet the requirements of 50kg-class satellites
[0004] The traditional vertically installed star-rocket separation mechanism takes up a lot of space, and the utilization rate of the existing rocket space is relatively low

Method used

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  • Horizontal satellite-rocket separation mechanism
  • Horizontal satellite-rocket separation mechanism
  • Horizontal satellite-rocket separation mechanism

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Embodiment Construction

[0027] The technical solutions of the present application will be clearly and completely described below in conjunction with the accompanying drawings and the embodiments of the present application.

[0028] figure 1 It is a schematic diagram of the horizontal star-arrow separation mechanism of this application. Such as figure 1 As shown, the horizontal star-arrow separation mechanism of the present application mainly includes the following components: main frame, 2 sets of connection unlocking devices, 2 shear positioning pins (or taper pins), 3 sets of spring thrust devices, and travel switch brackets.

[0029] Due to the complex shape of the main frame, it can be formed by 3D printing as a whole. After forming, it will be machined to meet the precision requirements. Two taper pins cooperate with the taper holes of the satellite to bear the longitudinal load. The inner rail cooperates with the satellite outer rail. Considering the influence of manufacturing tolerance and...

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Abstract

The invention relates to a horizontal satellite-rocket separation mechanism which comprises a main frame, two connection unlocking devices, two shear-bearing positioning pins, three spring thrust devices and a stroke switch support.

Description

technical field [0001] This application relates to a satellite-rocket separation system, in particular to a horizontal satellite-rocket separation system suitable for 50kg satellites. Background technique [0002] For the micro-nano satellites above 5Kg, most of them are installed vertically on the rocket at present, that is, the separation movement direction of the satellite is parallel to the axis of the rocket. The rocket cone is used to install the main star, and the carrying satellites need to be evenly arranged on the mounts installed outside the cone. The rocket attitude control of this star-rocket separation system is relatively simple, the separation is not easy to collide, and the safety is good. [0003] The existing horizontal satellite-rocket separation mechanism is mostly used on cubesats less than 5kg, which cannot meet the requirements of 50kg-class satellites. [0004] The traditional vertically installed star-rocket separation mechanism takes up a lot of ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/64
CPCB64G1/645
Inventor 诸成郭彤李晓莉赵学聪
Owner 上海中科辰新卫星技术有限公司
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