摘要
主要分析了载人飞船再入大气层时主要参数对气动加热率的影响。首先,建立了飞船再入飞行的数学模型,基于再入轨迹的最优化,广泛地研究了大范围的再入速度RV(7～10.8km/s)和再入角RA在不同组合下对加热率的影响,以及在指定加热率峰值的情况下,不同的再入速度对应的极限再入角。经过大量数值仿真和分析得出了相关特性图和再入走廊。
The influence of major parameters on aerodynamic heating ratio （AHR） is mainly analyzed in phase of reentry for manned space vehicle. Firstly, the mathematical model of the manned spacecraft has been established. The influence of reentry velocity （RV） （7 -10.8 krn/s） and reentry angle （RA） on AHR is extensively studied in the condition of different groups based on the optimal reentry trajectories, as well as the limit of RA varied with different RV when the maximum value of AHR is given. Reentry corridor and related characteristic diagrams are got according to a number of numerical simulations and analyses.
出处
《导弹与航天运载技术》
北大核心
2009年第5期31-34,45,共5页
Missiles and Space Vehicles
关键词
载人飞船
气动加热率
再入速度
再入角
数值仿真
Manned Spacecraft
Aerodynamic heating rate
Reentry velocity
Reentry Angle
Numerical Simulation
