摘要
针对再入过程中返回舱体存在严重的气动热问题,提出一种新型再入系统.通过建立减速系统的阻力估算模型和求解动力学方程,分析再入过程的速度特性和驻点热流密度,计算结果与文献算例数据吻合,验证飞行器再入过程的热流特性.采用Euler数值计算与边界层内工程算法相结合的方法计算充气阻力罩表面热流密度,结果表明热流密度在驻点附近较大,远离驻点后迅速减小.
A new reentry system is proposed with the problem that there exists a serious aerothermal problem on recoverable module during the reentry process. The speed characteristics and the heating rate of stagnation point are analyzed by building a resistance estimation model for deceleration system and solving the dynamics equation. The results meet the data of the example in the published article, which verifies the heat flow characteristics of the aircraft reentry process. The heating rate of inflatable resistance cover surface is calculated combing the Euler numerical calculation with engineering algorithm of boundary and the results indicate that the heating rate near the stagnation point is bigger and decreases quickly with the increase of the distance away from the stagnation point.
出处
《计算机辅助工程》
2013年第4期46-50,共5页
Computer Aided Engineering
关键词
返回舱
充气阻力伞
充气阻力罩
热流密度
驻点
边界层
recoverable module
inflatable drag parachute
inflatable resistance cover
heating rate
stagnation point
boundary layer
