摘要
对航天飞机标准轨道法进行改进,在更新部分D-V剖面、更新整个D-V剖面的基础上,提出第3种剖面更新的方法,以下简称修正标准飞行剖面参数法。该方法在考虑当前飞行时刻的瞬间,平移整个标准飞行剖面,以满足航程要求;采用轨道跟踪控制技术跟踪标准飞行剖面,使得实际航程逼近标准航程;该方法不更新D-V剖面,降低了算法的复杂性,减少计算量并具有较高的制导精度。基于该方法对NASA马歇尔空间飞行中心研究的空天飞行器模型进行再入轨迹设计,仿真结果表明,该方法获得的轨迹不仅能满足过载、热流和动压等过程约束及终端约束,并且轨迹光滑,无跳跃,具备一定的工程应用价值。
This paper is mainly to improve the nominal trajectory method of space shuttle. On basis of updating partial D-V profile and updating whole D-V profile, a new method for updating profile is presented, which is also called modified nominal flight profile parameter method. This method takes current flight time line into account to translate whole nominal flight profile to meet range requirement. Trajectory tracking control technology is adopted to track nominal flight profile, making actual range approach nominal range. This method does not update D-V profile, reducing complexity and computation of algorithm with higher guidance precision. This method is used to design reentry trajectory for aerospace vehicle of NASA Marshall Space Flight Center. The simulation result shows that the trajectory not only meets terminal constraint and process constraint such as overload, heat flux and dynamic pressure, but also the trajectory is smooth with certain engineering application value.
出处
《导弹与航天运载技术》
北大核心
2014年第5期6-9,13,共5页
Missiles and Space Vehicles
关键词
标准轨道法
可重复使用运载器
再入
制导律设计
Nominal trajectory method
Reusable launch vehicle
Reentry
Guidance law design
