导弹俯仰通道带有落角约束的制导与控制一体化设计

对导弹带有落角约束的制导与控制一体化进行了研究.首先建立了俯仰通道的制导控制一体化状态模型.然后利用特征结构配置方法,设计了制导与控制一体化状态反馈控制律.所设计的控制器一方面保证导弹打击精度,另一方面保证导弹进行垂直打击.最后,进行了导弹非线性数值仿真,验证了所提的制导控制一体化策略的有效性,从仿真结果上看,垂直打击精度是很高的.

Integrated Guidance and Control with Terminal Angular Constraint for the Missile's Pitch Plane

The problem of integrated guidance and control with terminal angular constraint for missiles is studied.Firstly,the integrated guidance and control model of the pitch plane is formulated.Then based on eigenstructure assignment approach,the guidance and autopilot law is designed.This feedback law can not only hit the target accuracy,but also satisfy terminal impact angular.Finally,a nonlinear missile simulation is used to demonstrate the effectiveness and rightness of the integrated design scheme.The simulation results have shown that high accuracy of hitting target can be got.