基于预测控制的导弹俯仰通道制导控制一体化设计  

Integrated Guidance and Control for the Missiles Pitch Plane Based on Predictive Control

作　　者：水尊师[1] 魏东辉[1] 徐骋[1] 

机构地区：[1]北京机电工程研究所,北京100074

出　　处：《导航定位与授时》2014年第1期35-39,共5页Navigation Positioning and Timing

摘　　要：考虑制导和控制之间固有的时间尺度差异,提出基于预测控制设计制导控制一体化策略,通过对动态调节过程的合理预测,更加真实的反应控制量对系统状态的影响。利用连续时间非线性预测控制,以输出跟踪误差和控制能量的组合为性能指标,在线滚动优化得到控制指令,分析了控制律的参数选取,最后通过数值仿真验证了制导控制一体化策略的有效性。A new integrated guidance and control law was proposed based on continue predictive control, which exploit the inherent time scale separation existing in the missile dynamic between rotational and translational motions. The missile states were predicted by appropriate expansions in a reasonable time span to capture the actual missile physics. The optimal receding horizon control law was obtained through minimizing the predicted errors in the actual response, the desired re- sponse and current control expenditure. The influence of control law parameters was also analyzed. Simulations results show the effectiveness and accuracy of the proposed integrated design scheme.

关 键 词：制导控制一体化 俯仰通道 预测控制 角度约束 

分 类 号：TJ765.3[兵器科学与技术—武器系统与运用工程]