固体火箭的鲁棒自适应耗尽关机制导方法研究

A Robust and Adaptive Depleted Shutdown Guidance Method of Solid Rocket

针对固体火箭的耗尽关机制导问题,提出了一种基于闭路制导和零射程线相结合的自适应耗尽关机制导方法,该方法首先利用闭路制导技术,使待增速度快速收敛;随后基于零射程线理论,设计了对关机时间变化不敏感的零射程线能量耗散管理导引律和末速精调导引律,提高了耗尽关机方法在推力、秒耗、关机时间随机摄动条件下的鲁棒性和自适应性以及制导精度,从而拓展了耗尽关机显示制导方法的工程化应用。

In order to solve the problem of depleted shutdown guidance of solid rocket, a robust and adaptive method based on close-loop guidance and zero-range orientation is proposed. Firstly, the close-loop guidance law is designed to converge the required velocity increment quickly. Then, based on the zero-range orientation theory, an energy management arithmetic that is insensitive to the variety of shutdown time and a precise guidance law of terminal velocity correction are developed, which effectively improve the robust, a- daptability and accuracy of depleted shutdown guidance under the random perturbation of thrust, fuel consumption and shutdown time. The method proposed extends the engineering application of depleted shutdown explicit guidance.