dynamic analysis and validation for rotating separation of lm-5's large-scale payload fairing
- Paper number
IAC-13,C2,1,7,x17548
- Author
Dr. He Wei, China Academy of Launch Vehicle Technology, China
- Coauthor
Prof. Dong Li, China Academy of Launch Vehicle Technology, China
- Coauthor
Dr. Yu Luan, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Tang Xiao-han, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Liu Hai-long, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Yuan Shui-lin, China Academy of Launch Vehicle Technology, China
- Coauthor
Mr. Lei Yong-jun, Dept. Engineering Mechanics, Dalian University of Technology, China
- Coauthor
Mr. Li Gang, Dept. Astronautical Science and Engineering, National University of Defense Technology, China
- Coauthor
Mr. Huang Bin, China Academy of Launch Vehicle Technology, China
- Year
2013
- Abstract
Separation strategy and structural design for payload fairing are key technologies during development of launch vehicle. In this paper, present strategy of fairing separation and simulation technique is reviewed. Then, rotating separation of LM-5's large-scale payload fairing is simulated through both multi-body dynamics and explicit structural dynamics, based on which, influence of elastic deformation and vibration responses on separation characteristic, enveloping space, and structural strength of the fairing are discussed. Furthermore, to estimate effects of atmosphere during separation experiment of the fairing, coupled Euler Lagrange method is employed. LM-5's fairing separation experiment results are introduced. Finally validity and accuracy for the analysis strategy are evaluated by the experiment results.
- Abstract document
- Manuscript document
IAC-13,C2,1,7,x17548.pdf (🔒 authorized access only).
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