%0 Journal Article
%T 导弹撞击角度与飞行时间两阶段控制制导律
%A &lt
%A /br&gt
%A LI Xinsan
%A WANG Lixin
%A FAN Xiaohu
%A DING Bangping
%A XUE Liang
%A WANG Mingjian
%J 国防科技大学学报
%D 2017
%R 10.11887/j.cn.201706002
%X 为了实施饱和攻击，需要对撞击角度与飞行时间同时进行控制。通过一种导弹撞击角度与飞行时间两阶段控制制导策略实现导弹撞击角度与飞行时间控制。第一阶段：基于切换滑模思想在纵向通道内对导弹飞行时间进行精确控制，侧向通道制导指令采用传统的纯比例导引律。第二阶段：切换到含重力补偿轨迹调节最优制导律对撞击角度进行精确控制，与显式制导不同，该制导律显式包含重力补偿项。设计数值仿真验证撞击角度与飞行时间两阶段控制制导方法的有效性，仿真结果表明，所给出的撞击角度与飞行时间两阶段控制制导方法能够实现撞击角度与飞行时间的同时控制。</br>The impact angle and the flight time were needed to be controlled simultaneously for a saturation attack. A two-stage guidance strategy with impact angle and flight time was proposed for impact angle and flight time control. In the first stage, the impact time high-precision control guidance law was derived by using a switching surface in pitch channel. The traditional proportional guidance law was used in yaw channel. Then in the second stage, the trajectory shaping optimal guidance with gravity compensation was used for impact angle control, which was an extension of explicit guidance in that gravity compensation was incorporated. The effectiveness of the impact angle and impact time two-stage guidance was validated by simulation. Simulation results show that the proposed two-stage control guidance with impact angle and flight time can achieve the simultaneous control of the impact angle and flight time.
%K 制导 撞击角度控制 飞行时间控制 重力补偿&lt
%K /br&gt
%K guidance impact angle control flight time control gravity compensation
%U http://journal.nudt.edu.cn/gfkjdxxb/ch/reader/view_abstract.aspx?file_no=201706002&flag=1