Debris analysis method of on-orbit satellite collision is presented in this paper. Hypervelocity impact simulation technique and self-developed fragment identification and statistics method are applied to analyzing fragmentation process of Iridium33 and Cosmos2251 collision as an instance. Using a combined method of finite element method (FEM) and smoothed particle hydrodynamics (SPH), large fragments are identified from the debris cloud. Then with binary image conversion and statistics of connectedness regions on the image, the amount, size, position, velocity and mass of each fragment are determined. Simulation results show that most large fragments are generated from Cosmos2251 and the quantity of fragments is in agreement with space surveillance network (SSN) observation data, which shows the effectiveness of the proposed method. Most materials in the normal impact region are converted into small fragments after the impact while the large fragments are from materials far from the normal impact region. To measure the degree of spall, equivalent normal impact mass is defined. The computation results show that the total mass of either large or small fragments is only determined by equivalent normal impact mass despite various impact locations.
ZHANG Xiaotian, JIA Guanghui, HUANG Hai
. Debris Analysis of On-orbit Satellite Collision Based on Hypervelocity Impact Simulation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011
, 32(7)
: 1224
-1230
.
DOI: CNKI:11-1929/V.20110330.1305.004
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