Implementation of Optimal Guidance Laws Using Predicted Missile Velocity Profiles
Implementation of Optimal Guidance Laws Using Predicted Missile Velocity Profiles
复制标题
使用预测的导弹速度剖面实施最优制导律
DOI：
10.2514/2.4420
复制
发表时间：
1999
期刊：
影响因子：
--
通讯作者：
M. Tahk
中科院分区：
文献类型：
--
作者：
Hangju Cho;C. Ryoo;M. Tahk
针对变速导弹，推导了一类加权控制力最小化导引律。作为一种实用的加权函数，我们考虑了空气密度和导弹速度的正实数参数函数。由此产生的最优制导问题可以解释为亚音速或超音速导弹的阻力最小化问题，这取决于所使用的参数。仿真研究表明，该方法易于推广应用于具有任意速度特性和任意阻力特性的典型防空导弹系统的阻力最小化问题。文中还给出了最优律的制导增益随参数值变化的分析结果。由于最优导引律利用的是未来导弹的速度分布，因此如何实施最优导引律是一个关键问题。为了避免导弹速度预测不准确导致制导指令在交战的最后阶段炸毁的困难，我们提出了两种简单的在线速度验证更新方案，大大缓解了这一问题。
A class of weighted control-effort minimizing guidance laws are derived for missiles of varying velocity. As a practical weighting function, we consider a function of air density and missile velocity parameterized by positive real numbers. The resulting optimal guidance problem can be interpreted as the drag minimization problem for subsonic or supersonic missiles, depending on what parameters are used. This approach is extended easily to solve the drag minimization of a typical antiaircraft missile system with an arbitrary velocity proe le and arbitrary drag characteristics, as demonstrated by a simulation study. We also present analytical results on how the guidance gain of the optimal law varies according to the values of the parameters. Because the optimal guidance laws make use of the future missile velocity proe le, one critical issue is how to implement the laws. To avoid the dife culty that an inaccurately predicted missile velocity proe le causes the guidance command to blow up in the last part of the engagement, we suggest two simple on-line velocity-proe le updating schemes, which considerably alleviate the problem.