深空再入返回飞行仿真及工程应用分析

Deep Space Entry Flight Simulation and Engineering Application Analysis

深空高速再入对返回技术提出了许多新的挑战.采用传统弹道式返回,将使返回器面临残酷的气动热环境,同时需要解决落点偏差大的问题;采用新的预测制导返回技术需要解决返回过程的航迹规划、制导和姿态控制问题.根据球冠倒锥外形飞行器在大气层内再入飞行时的受力情况建立飞行器的动力学模型,然后对弹道式返回和预测制导返回两种飞行方案进行仿真,最后围绕返回飞行总体特性参数和返回方式的技术要求等进行工程应用分析,为深空返回的工程实践提供指导.

Deep space return entry technique at high speed brings a lot of new challenges to return technique. Traditional ballistic return technique will cause return vehicle to encounter very server aerodynamic heating environment and is required to solve the problem of great impact point error. A new predictive guidance return technique is required to solve issues of flight planning, guidance and attitude control. A flight dynamics model is built on the basis of the air stress analysis of a ball-back tapered spacecraft under aerosphere, and a flight simulation analysis of ballistic return and predictive guidance return is given for the spacecraft. Finally, an analysis of engineering application of different return techniques about the return flight system specification and technical parameter is given, and helps for the deep space engineering projects.