Debris Protection Capability Numerical Simulation of Multi-layer Insulation
Multi-layer insulation (MLI) is one kind of important spacecraft thermal protection structures, arranged outside surface of satellite. In this paper, based on the LS-DYNA software, the shell-type finite-element method was used to establish MLI impact model and two aspects were carried out: First, in condition of constant impact velocity, impact models of six configurations were established and simulated (2 mm aluminum plate, one stacking of MLI, two stackings of MLI, one stacking of MLI covered 2 mm aluminum plate, two stackings of MLI covered 2mm aluminum plate, one stacking of MLI placed 10 mm in front of 2 mm aluminum plate). The ballistic limit energies of those six configurations were obtained, and the debris protection capability of MLI was also evaluated by being equivalent to aluminum plate in impact kinetic energy. Second, for three kinds of structures (2 mm aluminum plate, one stacking of MLI covered 2 mm aluminum plate, one stacking of MLI placed 10 mm in the front of 2 mm aluminum plate), ballist ic limit diameters under different velocities were obtained and the ballistic limit curves of those structures were given. The results show that the debris protection capability can be improved by increasing the space between the MLI and the aluminum plate or increase the number of stacking of MLL
MLI hypervelocity impact space debris ballistic limit curve Numerical simulation
Zhou Guangdong Jia Guanghui
School of Astronautics, Beijing University of Aeronautics and Astronautics,Beijing,100191, China School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing, 100191, China
国际会议
2010 Asia-Pacific International Symposium on Aerospace Technology(2010 亚太航空航天技术研讨会 APISAT 2010)
西安
英文
765-768
2010-09-01（万方平台首次上网日期，不代表论文的发表时间）