飞船舱间连接部件的烧蚀分析与试验(英文)  

Ablation Analysis and Test for the Lug of Manned Spaceship

作　　者：吴国庭[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2007年第1期74-79,共6页Spacecraft Engineering

摘　　要：突起在神舟飞船防热层表面的舱间连接部件要求在再入时尽早烧去,同时又要求具有足够的厚度,这在设计上造成较大困难,为此研制了一套地面试验和分析计算相互配合、反复迭代的设计方法,从而确定了该连接部件的材料与尺寸,并准确地预示了实际飞行的烧蚀现象。神舟飞船的历次飞行结果表明,该部件的性能与设计要求完全相符,从而为所用方法做了飞行验证。The difficulty in the design of linker between returnable module （RM） and propulsion module （PM） which will leave several lugs on the thermal-protection surface is analyzed. The lugs must be not only burned out as earlier as tx3ssible during the returnable module （R_M） atmospherical re-entry, to avoid the over- heating caused by lugs＇ flow disturbing, but also thick enough to be used as a linker. A set of design proceeding is developed by using analysis and tests repetitively, with which the material and dimensions of the lugs of the linkers are determined, and the ablative behavior of the lug is predicated. The performance of the linkers has been verified by the successful flights of SZ-1 to SZ-6, therefore the technique of the ablative analyses and test of the lugs is also verified.

关 键 词：载人飞船 突起部件 烧蚀 分析 试验 

分 类 号：V423[航空宇航科学与技术—飞行器设计]