Abstract
In order to improve the ability of the spacecraft protection system to resisted hypervelocity orbit debris, a composite double-layer honeycomb sandwich structure was proposed in the article. Four sets of models were established, through the method of controlling variables, and the SPH algorithm of the LS-DYNA finite element software was used to analysis the composite honeycomb sandwich structure. The diameter of the aluminum ball was 7mm and the velocity was 5818m/s. The results show that the residual velocity of debris cloud decreases with the increase of the cell diameter of the front-stage honeycomb. and the residual velocity of debris cloud increases with the decreases of the cell diameter of the back-stage honeycomb structure. The energy absorption effect of the composite structure was much higher than that of the traditional honeycomb structure, the remaining speed was reduced by about 64%, and the total energy absorption was increased by 77.6%.
Export citation and abstract BibTeX RIS
Content from this work may be used under the terms of the Creative Commons Attribution 3.0 licence. Any further distribution of this work must maintain attribution to the author(s) and the title of the work, journal citation and DOI.