Impact Envrionment Analysis of Spacecraft-rocket Separation for New Generation Manned Spacecraft
- Paper number
IAC-21,C2,3,3,x65173
- Author
Mr. Zhao Yin, China, Beijing Institute of Spacecraft System Engineering, China Academy of Space Technology (CAST)
- Coauthor
Mr. Lai Songbai, China, Beijing Institute of Spacecraft System Engineering, China Academy of Space Technology (CAST)
- Coauthor
Mr. Liang Lu, China, Beijing Institute of Spacecraft System Engineering, China Academy of Space Technology (CAST)
- Year
2021
- Abstract
Due to the fact that the new launch vehicle adopts a new linear separation device, spacecraft-rocket separation will produce a greater impact response. In order to ensure the safety and envriomental adaptability of spacecraft structure and the equipments on it, it is necessary to obtain the real impact environment data of the critical stages such as the spacecraft-rocket separation in the ascent phase. For this reason, the sensor array needs to be arranged on the spacecraft-rocket separation Interface, which can monitor the impact mechanical environment of the spacecraft at the moment of spacecraft -rocket separation. In this paper, the measurement scheme of spacecraft-rocket separation impact is designed, and the impact load data generated by spacecraft-rocket separation in the ascending section of the new generation of spacecraft is processed. The shock response spectrum of interface between sapacecraft and launch vehicle is obtained and the reason for the difference of impact magnitude and attenuation degree in different quadrants is analysed. The research results can provide reference for the optimization of ground mechanical test conditions.
- Abstract document
- Manuscript document
IAC-21,C2,3,3,x65173.pdf (🔒 authorized access only).
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