부산대학교 도서관

Large cracks may occur in the pressured module under the impacts of micro-meteors and space debris during orbit, which may cause rapid instable extension of cracks under the internal pressure load. To reduce the risk, the design criterion of crack stop is put forward, and the mechanism of fracture extension, simulation analysis and test verification method are studied. At the same time, the critical crack length and the influence of different parameters on it are obtained by the analysis and test of a typical integrally stiffened structure. It is proved that the structure design of the integrally stiffened structure for a spacecraft has a good crack stop performance.