摘要
可充气式太空舱是一种能够提高运载效率和满足大型空间飞行器长期在轨性能的有效结构形式。由于采用柔性结构和复合材料 ,它具有重量和空间上的优势 ,但同时为防护结构的设计带来更高的要求和难度。结合实验、理论等手段对可充气式太空舱防护结构进行方案选择和初步结构设计 ,给出一个防护结构设计模型方案 ,并进行防护性能的验证。为了更好地说明可充气式太空舱的防护性能 ,将其与惠式防护结构作以比较。计算结果显示 ,所给出的可充气式太空舱防护结构设计方案满足防护设计要求 。
Trans Hab is an efficientmethod solving the launch efficiency and the performance re- quirements for large spacecraftwith long operation period.Because of the flexible structure and com- posite materials,ithas the mass and volume advantages.Butin the meantime,itis more difficultfor the shield structure design.In thispaper,the conceptchoice and preliminary design for the Trans Hab shield are described,a shield structure modelisgiven,and the performanceisassessed.Ascomparing with Whipple shielding,the performance of Trans Hab shield is obviously better.The calculation re- sults show thatthe shield structure modeldescribed in thispapercan meetthedesign requirements,so the deeper analysis is worthwhile.
出处
《导弹与航天运载技术》
北大核心
2002年第1期4-10,共7页
Missiles and Space Vehicles
