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针对高超声速飞行器严重气动非线性特性给控制系统设计提出的高要求,基于推广的随控布局思想,从控制系统设计角度对高超声速飞行器总体提出气动非线性程度低的优化设计指标。引入高超声速飞行器气动非线性特性度量——非线性度的定义,通过气动工程估算建立非线性度与飞行器总体外形参数关系的表征模型,将非线性度表示为总体外形参数的函数;采用遗传算法求解以总体外形参数为决策变量和以非线性度最小为目标函数的优化问题;最终确定随控优化思想下的高超声速飞行器总体优化策略。算例分析表明,本文提出的总体随控优化方法对于改善高超声速飞行器的气动非线性特性简单有效。
Aiming at the high demand of design of control system for serious aerodynamic nonlinearity of hypersonic vehicle, based on the idea of extended control layout, the optimal design index of low aerodynamic nonlinearity for hypersonic vehicle is proposed from the viewpoint of control system design. The definition of aerodynamic non-linearity of hypersonic vehicle is introduced, the characterization model of the relationship between non-linearity and aircraft overall shape parameters is established by aerodynamic engineering estimation, and the nonlinearity is expressed as a function of overall shape parameters. Genetic algorithm The overall optimization strategy of the hypersonic vehicle with the optimal control strategy is finally determined by solving the optimization problem whose overall shape parameters are the decision variables and the non-linearity is the minimum objective function. The case study shows that the overall random optimization method proposed in this paper is simple and effective to improve the aerodynamic nonlinearity of the hypersonic vehicle.