Simulation and tests for horizontal throwing separation of satellite cabin shell based on rigid-flexible coupling

GE Yue, WANG Hongbo, GONG Min, LUO Bo, ZHAO Junfeng, GAO Feng

Journal of Vibration and Shock ›› 2021, Vol. 40 ›› Issue (7) : 19-28.

PDF(2348 KB)
PDF(2348 KB)
Journal of Vibration and Shock ›› 2021, Vol. 40 ›› Issue (7) : 19-28.

Simulation and tests for horizontal throwing separation of satellite cabin shell based on rigid-flexible coupling

  • GE Yue, WANG Hongbo, GONG Min, LUO Bo, ZHAO Junfeng, GAO Feng
Author information +
History +

Abstract

Here, aiming at influences of flexible effect on separation process of a satellite cabin shell, a rigid-flexible coupled dynamic model for horizontal throwing separation of a composite satellite cabin shell was established based on the flexible multi-body dynamic method. The thrust-displacement relationship of a thruster was used to realize the thrust equivalence of the thruster from ground tests to arbitrary conditions. Simulation and contrastive analysis for the flexible body model and the rigid body model were performed. The results showed that elastic deformation of the shell is dominated by the second-order “breathing motion” mode to absorb about 15% of work done by the thruster, and the separation speed decreases; the respiratory motion at the lower corner point of the separation surface is the most severe, and the influence of the first time inward breathing movement of the half hood on the inner envelope is the greatest; the flexibility effect can also affect the thrust action time history of the thruster. Satellite cabin separation ground tests were conducted. A high-speed photography was used to measure the half hood’s motion to contrastively verify the correctness of the simulation method. It was shown that the simulation error is less than 13%; the study results are helpful to ensure the effectiveness of the separation scheme, release the design margin of the satellite cabin inner envelope space, and provide a reference for separation optimization design.

Key words

satellite cabin / horizontal throwing separation / thruster / rigid-flexible coupling / breathing deformation

Cite this article

Download Citations
GE Yue, WANG Hongbo, GONG Min, LUO Bo, ZHAO Junfeng, GAO Feng. Simulation and tests for horizontal throwing separation of satellite cabin shell based on rigid-flexible coupling[J]. Journal of Vibration and Shock, 2021, 40(7): 19-28

References

[1]高峰,谭杰,尚辉, 等.“国家队”正式进军商业发射市场:捷龙一号火箭首次商业发射圆满成功[J].国际太空,2019(9):38-41.
GAO Feng,TAN Jie,SHANG Hui, et al.“National Team” officially entered into the commercial launch market:the first commercial launch of the Smart-Dragon 1 rocket has been a complete success[J].Space International,2019(9):38-41.
[2]马忠辉. 大型弹性整流罩分离特点分析[J]. 中国科学(技术科学), 2009(3):482-489.
MA Zhonghui. Separation characteristic analysis of large scale elastic fairing[J]. Scientia Sinica(Technologica), 2009, 39(3): 482-489.
[3]李哲, 范学领, 孙秦, 等. 大型整流罩分离动力学简化建模及仿真分析[J]. 固体火箭技术, 2012, 35(5):583-587. 
LI Zhe, FAN Xueling, SUN Qin, et al. Simplified finite element modeling method and separation dynamics of large scale fairing structure[J]. Journal of Solid Rocket Technology, 2012, 35(5): 583-587.
[4]张大鹏, 雷勇军, 柳海龙, 等. 大型柔性整流罩分离特点仿真分析[J]. 振动与冲击, 2015,34(22):115-120.
ZHANG Dapeng, LEI Yongjun, LIU Hailong, et al. Simulations and analyses on separation characteristics of large scale flexible fairing[J]. Journal of Vibration and Shock, 2015, 34(22): 115-120.
[5]李刚,艾森,唐霄汉,等. Abaqus的CEL算法在整流罩地面分离试验仿真中的应用研究[C]//
2014年中国计算力学大会暨第三届钱令希计算力学奖颁奖大会.贵阳:中国力学学会计算力学专业委员会,2014.
[6]唐霄汉. 新一代运载火箭整流罩关键分离特性研究[D]. 大连: 大连理工大学, 2018.
[7]翟章明, 周一磊, 王旭刚,等. 火箭复杂分离连接结构的动力学仿真方法及应用[J]. 载人航天, 2016, 22(3):328-333.
ZHAI Zhangming,ZHOU Yilei,WANG Xugang, et al. Study and application of dynamic simulation method for complex rocket stage separation and connection structure[J]. Manned Spaceflight, 2016, 22(3):328-333.
[8]LIKINS P W. Finite element appendage equations for hybrid coordinate dynamic analysis[R]. Pasadena:Jet Propulsion Laboratory, California Institute of Technology, 1971.[9]洪嘉振,蒋丽忠. 动力刚化与多体系统刚-柔耦合动力学[J]. 计算力学学报, 1999, 16(3): 295-301.
HONG Jiazhen, JIANG Lizhong. Dynamic stiffening and multibody dynamics with coupled rigid and deformation motions[J]. Chinese Journal of Computational Mechanics, 1999, 16(3): 295-301.
[10]蒋丽忠,洪嘉振.柔性多体系统产生动力刚化原因的研究[J].计算力学学报,1999,16(4):403-409.
JIANG Lizhong, HONG Jiazhen. Study on the cause of dynamic stiffening of flexible multibody system[J]. Chinese Journal of Computational Mechanics,1999,16(4):403-409.
[11]崔奇. 飞行器整流罩分离的动力学模拟及可靠性分析[D]. 哈尔滨: 哈尔滨工业大学,2011.
[12]李大耀.关于弹射筒分离特性测定的几点结论[J]. 中国空间科学技术,1985(6): 13-30.
LI Dayao. Some conclusions of measuring separation charactoristic of ejecting guns[J]. Chinese Space Science and Technology, 1985(6): 13-30.
[13]董寻虎,张修科,韩智超,等.整流罩弹射筒力学特性工程估算[J]. 上海航天, 2006, 23(6): 46-49.
DONG Xunhu, ZHANG Xiuke, HAN Zhichao, et al. Engineering calculation of ejector dynamic characteristic for
fairing[J]. Aerospace Shanghai, 2006, 23(6): 46-49.
PDF(2348 KB)

Accesses

Citation

Detail

Sections
Recommended

/