新型导弹姿态控制系统二次镇定方法研究

Quadratic Stabilization Model for the Novel Missile Flight Attitude Control System

现代新型导弹由于进行大范围机动飞行,要求飞行姿态控制参数在大范围区间内变化。考虑到传统区间系统数学描述和该类系统控制设计的不足,针对参数依赖区间系统的稳定性分析和二次镇定问题,研究了具有时间连续的参数依赖区间系统的二次镇定问题及在新型导弹姿态控制系统设计中的应用。与传统区间系统的分析和控制设计不同,给出了参数依赖模型的区间系统二次稳定的新充要条件。在二次镇定结构下,提出一种区间不确定参数顶点的控制设计方法,以一簇参数化的线性矩阵不等式(LMI)的形式给出了控制的可解性条件,且所得到的LMI条件采用标准的数值计算软件进行有效求解,所得到的结果有利于控制系统分析与优化设计。最后,将上述方法成功应用于具有区间线性化纵向动力学模型的某型导弹飞行姿态控制系统设计中,验证了所提出方法的有效性。

Taking into account the range of traditional mathematical description of the system deficiencies and drawbacks of such systems control design, this paper is concerned with quadratic stabilization for continuous - time linear parameter - dependent interval systems. Differing from previous results in the analysis and control design of in- terval systems, new necessary and sufficient conditions for the quadratic stability are derived based on parameter- dependent model representation of interval systems. In the quadratic framework, an approach based on a vertex result on interval uncertain parameters is proposed. This allows the solvability conditions to be presented in terms of a set of parameterized linear matrix inequalities which can be efficiently solved by using standard numerical softwares. A line- arized longitudinal dynamic model of the attitude control system of a flight attitude control for the certain missile sys- tem is presented to illustrate the effectiveness and advantage of the proposed methods.