A system for simulating satellite separation experiments in a microgravity environment

Abstract

The invention provides a system for simulating a satellite separation test in a microgravity environment, comprising: a platform satellite structure; a release device structure installed in the platform satellite structure; a small satellite installed in the release device structure A structural member, the release device structural member ejects the small satellite structural member after receiving the release command; a windshield installed at the exit of the release device structural member. The invention effectively reduces the wind resistance in the satellite separation process, and has the characteristics of simple structure, economical and practical, convenient use and high reliability.

Description

technical field The invention relates to a payload windage reduction test device for a separation test system in a simulated microgravity environment, which can effectively reduce the windage of the payload of a separation test system in a simulated microgravity environment during the separation process, making the ground test The separation environment for the payload in the process is closer to a vacuum environment. Background technique On-orbit separation of small satellites involves separation and release of small satellites from the release device inside the platform satellite. The separation and release process takes place in the vacuum and weightlessness of outer space. The process of separating and releasing the small satellite includes unlocking the explosive bolt → pushing the small satellite out by spring action → sliding out the small satellite along the guide rail → free flying of the small satellite. Small satellites and platform satellites are installed ecce...

AI Technical Summary

Problems solved by technology

After analyzing the angular velocity of the separation attitude obtained from the test, it was found that the wind resistance during the falling process has a particularly large impact on the angular velocity of the separation attitude of the small satellite structural parts, which will amplify some initial disturbances several times, causing great trouble to the processing of the test data

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