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| Pyrotechnic Shock Environment in Pyro-shock Separation of Different Rocket-Satellite Separation Manners |
| Received:March 02, 2017 Revised:August 15, 2017 |
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| DOI：10.7643/issn.1672-9242.2017.08.014 |
| KeyWord:pyro-shock, rocket-satellite separation, satellite, response feature. |
| Author | Institution |
| YANG Yan-jing |
Beijing Institute of Spacecraft Environment Engineering, Beijing , China |
| XIANG Shu-hong |
Beijing Institute of Spacecraft Environment Engineering, Beijing , China |
| FENG Guo-song |
Beijing Institute of Spacecraft Environment Engineering, Beijing , China |
| HAN Xiao-jian |
Beijing Institute of Spacecraft Environment Engineering, Beijing , China |
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| Abstract: |
| Objective To study the pyrotechnic shock environment of different pyro-shock separation manners. Methods Pyro-shock accelerations measured at different locations on satellites with different separation pyrotechnic devices, including point source devices, line source devices and combined source devices, were analyzed. Time domain, frequency domain and shock response spectrum of the measured accelerations were studied and the features of different satellites pyro-shock environment were summarized. Results The satellite SRS peak value attenuation ratio in three different separation manners was between 60%~70%. The power spectrum of the shock response induced by point source devices was richer than that of the other two devices. The Power spectrum distribution of line source devices and combined source devices was relatively concentrated. Conclusion The satellite pyro-shock environment of different separation manual is different to a certain extent. The separation manners should be taken into consideration in anti-shock design of the satellite. |
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