新一代歼击机建模及仿真研究

Model and Simulation Research of New Generation Flighter

针对新一代歼击机气动外形与传统歼击机的不同及其模型具有非线性、强耦合、不确定性等特点,基于Matlab插值函数和S函数,分别计算和建立新一代歼击机的气动参数及六自由度十二状态微分方程,并利用Trim函数进行飞机配平研究。最后利用非线性动态逆法设计的控制律进行飞行仿真实验,仿真结果表明,所建立的模型和获取的平衡状态可用于新一代歼击机的控制器设计和仿真研究。

Since the new generation flight involves characteristics of nonlinearity,strong coupling,uncertainty,and the particularity in aerodynamic shape,the aerodynamic coefficients are calculated based on interpolation functions,six freedom differential equation is established based on S-functions,and the flight trim points with the trim function are computed.Finally,the simulation studies show the established model is feasible with the designed control laws.