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| Design and Verification of Pyrotechnic Shock Reduction Scheme of Spacecraft |
| Received:February 13, 2015 Revised:June 15, 2015 |
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| DOI：10.7643/issn.1672-9242.2015.03.006 |
| KeyWord:pyrotechnic shock environment protection FEA spacecraft shock reduction schemes |
| Author | Institution |
| ZHANG Huan |
Beijing Institute of Spacecraft System Engineering， Beijing ， China |
| LIU Hai-ping |
Beijing Institute of Spacecraft System Engineering， Beijing ， China |
| LIU Tian-xiong |
Beijing Institute of Spacecraft System Engineering， Beijing ， China |
| XIANG Shu-hong |
Beijing Institute of Spacecraft Environment Engineering， Beijing ， China |
| ZHANG Qing-ming |
State Key Laboratory of Explosion Science and Technology， Beijing Institute of Technology， Beijing ， China |
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| Abstract: |
| Objective To study pyrotechnic shock reduction schemes for the spacecraft, and reduce the influence of pyrotechnic shock on the devices mounted in the spacecraft. Methods Three pyrotechnic shock reduction schemes were designed based on the principles of pyrotechnic shock reduction, prediction of shock response was made by NASTRAN software, and validation and model modification were conducted using the separation test data of local joint structure of satellite and launch vehicle. Results The maximum decrease of acceleration response was 62% by increasing the interfaces between satellite and launch vehicle, 86% by inserting a complex structure between satellite and launch vehicle, and 60% by decreasing the contact area. Conclusion Certain pyrotechnic shock reduce effect can be achieved by increasing the interfaces, inserting a complex structure or decreasing the contact area between satellite and launch vehicle. Mass, stiffness of joint structure, pyrotechnic shock reduction effect, and the satellite and launch vehicle status restrictions are factors to be considered when designing the system pyrotechnic shock reducing schemes. |
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