摘要
针对直接力控制的脉冲发动机非线性量化特性和喷流因子的不确定性,结合直接力/气动力双反馈复合控制方案,为了导弹飞行高速稳定性设计,提出了圆判据的鲁棒稳定性分析方法。首先建立了直接力/气动力复合控制系统数学模型,在完成复合控制系统设计的基础上,采用圆判据稳定性分析特点把非线性复合控制系统简化成一个非线性环节和一个线性环节的典型闭环结构形式,并根据圆判据的结论分析了脉冲发动机喷流因子不确定性和非线性量化特性对导弹自动驾驶仪稳定性影响。最后仿真结果验证了方法的正确性。
Base on the Aerodynamic/Reaction -jet double feedback complex controller,a robustness and stability analysis method of circle criterion for the Aerodynamic/Reaction - jet controller of Missile Autopilot is present in this paper.The reaction - jet of micro - impulse engine nonlinear quantiser characteristic and the quotiety of cascade uncertainty affects the robustness and stability for the autopilot.First,the model of reaction -jet /aerodynamic composite control system is given.Base on the characteristic of circle criterion composite control system predigests a linear system and a nonlinear system.Then the robustness and stability of reaction -jet/aerodynamic composite control system are analyze using circle criterion.Finally the result of simulation shows the method is correct.
出处
《计算机仿真》
CSCD
北大核心
2010年第7期5-9,共5页
Computer Simulation
关键词
直接力/气动力复合控制
喷流因子
非线性量化
鲁棒稳定性
圆判据
Reaction-jet/Aerodynamic Composite Controller
Quotiety of Cascade
Nonlinear Quantiser
Robustness and Stability
Circle Criterion
