[1] WILLIAMSEN J, MAHRER K, BOHL W, et al. Meteoroid/orbital debris risk assessment for reusable launch vehicles using metallic TPS:AIAA-2003-1553[R]. Reston:AIAA, 2003.
[2] 姚草根, 吕宏军, 贾新潮, 等. 金属热防护系统材料与结构研究进展[J]. 宇航材料工艺, 2005, 35(2):10-13. YAO C G, LU H J, JIA X C, et al. Development of metallic thermal protection system[J]. Aerospace Materials & Technology, 2005, 35(2):10-13(in Chinese).
[3] BLOSSER M L, CHEN R R, SCHMIDT I H, et al. Advanced metallic thermal protection system development:AIAA-2002-0504[R]. Reston:AIAA, 2002.
[4] 解维华, 张博明, 杜善义. 重复使用飞行器金属热防护系统的有限元分析与设计[J]. 航空学报, 2006, 27(4):650-656. XIE W H, ZHANG B M, DU S Y. Analysis and design of metallic thermal protection systems for reusable launch vehicle[J]. Acta Aeronautica et Astronautica Sinica, 2006, 27(4):650-656(in Chinese).
[5] 陈战辉, 万小朋, 何林涛, 等. ARMOR热防护系统蜂窝夹层板结构参数设计[J]. 上海航天, 2009, 26(5):56-60. CHEN Z H, WAN X P, HE L T, et al. Design of structural parameters about honeybomb sandwich on ARMOR thermal protection systems[J]. Aerospace Shanghai, 2009, 26(5):56-60(in Chinese).
[6] 南京航空学院. 传热学[M]. 北京:国防工业出版社, 1982:45-80. Nanjing University of Aeronautics and Astronautics. Heat transfer[M]. Beijing:National Defense Industry Press, 1982:45-80(in Chinese).
[7] POTEET C C, ABU-KHAJEEL H, HSU S Y. Preliminary thermal mechanical sizing of metallic TPS process development and sensitivity studies:AIAA-2002-0505[R]. Reston:AIAA, 2002. |