充气式防热罩再入轨道设计  

Re-entry Trajectory Design of Inflatable Thermal Shield

作　　者：夏刚[1] 程文科[1] 秦子增[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2002年第3期4-8,共5页Journal of National University of Defense Technology

摘　　要：充气式防热罩是最近几年才出现的新型航天回收技术 ,为各种轨道航天器的回收提供了简单、可靠、经济的途径 ,有望逐渐取代降落伞在回收系统中的地位。合理选择防热罩外形 ,用CFD方法计算了防热罩以亚、跨、超声速飞行时的阻力特性 ,并与工程估算方法作对比。分别采用单次和二次充气方案 ,完成了 90kg货舱安全着陆的再入轨道设计。在对两种充气减速方案的再入轨道进行比较分析之后指出 :对于回收同样重量的货舱 ,二次充气方案在保证减速效果的前提下大幅度减轻了防热系统设计的负担 。The newly developed Inflatable Thermal Shield(ITS) technology offers a simple, reliable and economical way to recover various vehicles from orbits and is therefore possible to be a substitute for parachute systems in the future. The selection of the aeroshell shape for the ITS recovery system is discussed. CFD methods are used to predict the subsonic, transonic and supersonic aerodynamics of the selected shape and compared with the Newtonian hypersonic estimation. The single stage and two stage inflation schemes are examined with the calculation of a 90kg cargos re entry trajectory, the latter is shown to possess better combination of deceleration and thermal protection and is therefore the ideal ITS re entry scheme.

关 键 词：充气式防热罩 设计 航天结构 航天回收系统 气动减速 再入轨道 ITS 

分 类 号：V445.4[航空宇航科学与技术—飞行器设计] V412.