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Ground zero-gravity separation test equipment for large spacecraft

A separation test and spacecraft technology, applied in the direction of aircraft component testing, etc., can solve the problems of not meeting the test requirements, unable to obtain accurate separation speed, etc., and achieve the effect of safe and reliable separation process, wide quality range, and adjustable separation stroke

Inactive Publication Date: 2018-07-20
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0013] 4) The effectiveness of the test: if the satellite tape unlocking separation test method is used, the accurate separation speed cannot be obtained, which does not meet the test requirements

Method used

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  • Ground zero-gravity separation test equipment for large spacecraft
  • Ground zero-gravity separation test equipment for large spacecraft
  • Ground zero-gravity separation test equipment for large spacecraft

Examples

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Embodiment Construction

[0040] The large-scale spacecraft ground zero-gravity separation test equipment of the present invention will be further described below in conjunction with the accompanying drawings. This description is only exemplary and is not intended to limit the protection scope of the present invention.

[0041] figure 1It is a structural schematic diagram of the large-scale spacecraft ground zero-gravity separation test equipment of the present invention. Ground zero-gravity separation test equipment for large spacecraft, including test bracket 9, pulley assembly (pulley mechanism 8), buffer mechanism 7, locking mechanism 3, connecting rope 6, counterweight and lifting mechanism 2, tension recorder 5 and test spreader 4. The test bracket 9 is a cubic frame structure, and the three sides of the frame structure are respectively provided with rice-shaped reinforcing support rods, and the angles between the four columns constituting the frame structure and the beams connecting the columns ...

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Abstract

The invention discloses ground zero-gravity separation test equipment for a large spacecraft. The ground zero-gravity separation test equipment comprises a test bracket, pulley assemblies, a buffer mechanism, a locking mechanism, a connecting rope, a weight balancing and lifting mechanism, a tension recorder and a test sling, wherein the test bracket is a cubic frame structure; a pulley mechanism I is arranged on one side surface of a frame in a suspension manner; the test sling is connected to the lower end of the connecting rope, and the weight balancing and lifting mechanism is connected to the other end, going around a pulley mechanism II, of the connecting rope; the two pulley assemblies are respectively arranged on a top cross beam of the frame structure so as to support the connecting rope which goes around the pulley assemblies; the buffer mechanism comprises a buffer and a buffering stop block; and the connecting rope drives the buffering stop block to move together at a uniform speed until the buffering stop block impacts the buffer to enable the kinetic energy to be dissipated.

Description

technical field [0001] The invention belongs to the technical field of spacecraft ground tests, and in particular relates to a separation test equipment that uses a counterweight scheme to meet the ground test requirements for vertical zero-gravity separation of large spacecraft cabin sections. Background technique [0002] At present, there are some known ground zero-gravity separation test methods for large spacecraft at home and abroad, which are mainly divided into three types: counterweight type, free fall type, and horizontal separation type. The more authoritative test standard in China is GJB2203A. For example, the test principle of the separation test of the CZ-2F return capsule and the escape vehicle adopts the free fall method. Among them, in order to ensure the safety of the astronauts, the Shenzhou is equipped with an escape system. If there is an abnormality within a certain period of time after launch, the escape tower will lift off with half of the fairing, ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/60
Inventor 郑圣余易旺民鲍晓萍王晖冯伟崔俊峰郭大宝祁广明陈启威唐赖颖
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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