摘要
给出一种适合通用高速飞行器(CAV)的预测校正再入制导方法。首先基于再入高速飞行器三自由度运动模型,研究了再入过程中CAV受到的过程约束。基于准平衡滑翔条件给出了在指定倾侧角下的参考航程的计算方法,并指出当飞行器的初始航程超过参考航程时,可以使用本文给出的方法有效抑制飞行器轨迹在高度上的振荡。为了提高制导精度,不仅给出了精确计算当前倾侧角的方法,也给出了粗略调整终端倾侧角方法。最后仿真验证了制导方法的有效性。
In this paper, a predictor-corrector guidance method for Common Aero Vehicle （CAV） is presented. First of all, the path constraints of reentry guidance is presented based on the three-dimensional equations of motion of a gliding vehicle. Then, a method of calculating initial reference range is proposed on the base of the quasi-equilibrium glide condition. If the reference range is exceeded by the initial range, the fluctuations of height will be suppressed by use of the guidance method proposed. The algorithm of calculating the value of current bank angle and terminal bank angle is proposed. The simulation is used to validate the guidance method in the last.
出处
《导弹与航天运载技术》
北大核心
2016年第4期34-38,共5页
Missiles and Space Vehicles
关键词
通用高速飞行器
准平衡滑翔条件
航程预测
预测校正制导
Common aero vehicle
Quasi-equilibrium glide condition
Prediction of flight range
Predictor-corrector guidance
