It is widely known that the hypervelocity impact of orbital debris can cause serious damage to spacecraft,and enhancing the impact resistance is the great concern of spacecraft shield design.This paper provides a comp...It is widely known that the hypervelocity impact of orbital debris can cause serious damage to spacecraft,and enhancing the impact resistance is the great concern of spacecraft shield design.This paper provides a comprehensive overview of advances in the development of bumper materials for spacecraft shield applications.In particular,the protective mechanism and process of the bumper using different materials against hypervelocity impact are reviewed and discussed.The advantages and disadvantages of each material used in shield were discussed,and the performance under hypervelocity impact was given according to the specific configuration.This review provides the useful reference and basis for researchers and engineers to create bumper materials for spacecraft shield applications,and the contemporary challenges and future directions for bumper materials for spacecraft shield were presented.展开更多
A corrugation stuffed shield system protecting spacecrafts against meteoroid and orbital debris （M/ OD） is presented. The semi-empirical ballistic limit equations （BLEs）defining the protection capability of the sh...A corrugation stuffed shield system protecting spacecrafts against meteoroid and orbital debris （M/ OD） is presented. The semi-empirical ballistic limit equations （BLEs）defining the protection capability of the shield system are given, and the shielding performance is also discussed. The corrugation stuffed shield （CKS） is more effective than stuffed Whipple shield for M/OD protection, and its shielding performance will be improved significantly as increasing the impact angle. Orbital debris up to 1 cm in diameter can be shielded effectively as increasing the impact angle to 25° at the corrugated angle of 30°. The results are significant to spacecraft design.展开更多
Tests of hypervelocity projectile impact on double-wall structure were performed with the front wall ranging from 0.5 mm to 2.0 mm thick and different impact velocities. Smooth particle hydrodynamics (SPH) code in LS-...Tests of hypervelocity projectile impact on double-wall structure were performed with the front wall ranging from 0.5 mm to 2.0 mm thick and different impact velocities. Smooth particle hydrodynamics (SPH) code in LS-DYNA was employed for the simulation of hypervelocity impact on the double-wall structure. By using elementary shock wave theory, the experimental results above are analyzed. The analysis can provide an explanation for the penetration mechanism of hypervelocity projectile impact on double-wall structure about the effect of front wall thickness and impact velocity..展开更多
In a wide strain rate range from 10^-5 to 10^3s^-1, the deformation behavior of an Al-based nanocrystalline alloy was investigated. After fracture, the debris collected was used for statistical analysis, which is expe...In a wide strain rate range from 10^-5 to 10^3s^-1, the deformation behavior of an Al-based nanocrystalline alloy was investigated. After fracture, the debris collected was used for statistical analysis, which is expected to reflect the profile of the fracture behavior of the alloy. The energy absorption of alloy at different strain rates was elucidated on account of mass distribution of debris. Based on the parameters obtained by the compression experiment at different strain rates, the numerical simulation experiment was carried out to evaluate the performance of Al-based nanocrystalline alloy as spacecraft shielding. The results suggest that Al-based nanocrystalline alloys have better shield performance than alu- minum alloy under the identical areal density at velocity of 1-7 km/s. The better shield performance is attributed to high fracture strength, high hardness and low toughness of Al-based nanocrystalline alloy as compared with those of aluminum alloy.展开更多
基金supported by National Natural Science Foundation of China(Grant Nos.12202068,12202087)China National Space Administration Preliminary Research Project(Grant Nos.KJSP2023020201,KJSP2020010402).
文摘It is widely known that the hypervelocity impact of orbital debris can cause serious damage to spacecraft,and enhancing the impact resistance is the great concern of spacecraft shield design.This paper provides a comprehensive overview of advances in the development of bumper materials for spacecraft shield applications.In particular,the protective mechanism and process of the bumper using different materials against hypervelocity impact are reviewed and discussed.The advantages and disadvantages of each material used in shield were discussed,and the performance under hypervelocity impact was given according to the specific configuration.This review provides the useful reference and basis for researchers and engineers to create bumper materials for spacecraft shield applications,and the contemporary challenges and future directions for bumper materials for spacecraft shield were presented.
文摘A corrugation stuffed shield system protecting spacecrafts against meteoroid and orbital debris （M/ OD） is presented. The semi-empirical ballistic limit equations （BLEs）defining the protection capability of the shield system are given, and the shielding performance is also discussed. The corrugation stuffed shield （CKS） is more effective than stuffed Whipple shield for M/OD protection, and its shielding performance will be improved significantly as increasing the impact angle. Orbital debris up to 1 cm in diameter can be shielded effectively as increasing the impact angle to 25° at the corrugated angle of 30°. The results are significant to spacecraft design.
文摘Tests of hypervelocity projectile impact on double-wall structure were performed with the front wall ranging from 0.5 mm to 2.0 mm thick and different impact velocities. Smooth particle hydrodynamics (SPH) code in LS-DYNA was employed for the simulation of hypervelocity impact on the double-wall structure. By using elementary shock wave theory, the experimental results above are analyzed. The analysis can provide an explanation for the penetration mechanism of hypervelocity projectile impact on double-wall structure about the effect of front wall thickness and impact velocity..
基金financially supported by the National Natural Science Foundation of China (No.51674093)the Natural Science Foundation of Heilongjiang Province (No.E201425)+1 种基金the Fundamental Research Funds for the Central Universities (No.HIT.MKSTISP.2016019)the Postdoctoral Scientific Research Development Fund of Heilongjiang Province (No.LBH-Q15040)
文摘In a wide strain rate range from 10^-5 to 10^3s^-1, the deformation behavior of an Al-based nanocrystalline alloy was investigated. After fracture, the debris collected was used for statistical analysis, which is expected to reflect the profile of the fracture behavior of the alloy. The energy absorption of alloy at different strain rates was elucidated on account of mass distribution of debris. Based on the parameters obtained by the compression experiment at different strain rates, the numerical simulation experiment was carried out to evaluate the performance of Al-based nanocrystalline alloy as spacecraft shielding. The results suggest that Al-based nanocrystalline alloys have better shield performance than alu- minum alloy under the identical areal density at velocity of 1-7 km/s. The better shield performance is attributed to high fracture strength, high hardness and low toughness of Al-based nanocrystalline alloy as compared with those of aluminum alloy.
