摘要
针对传统钝头体飞行器FADS系统空气动力学模型不再适用于升力体高速飞行器的问题,采用基于Levenberg-Marquardt算法的非线性最小二乘优化算法建立升力体高速飞行器FADS系统空气动力学模型,然后根据建立的高阶非线性模型,提出一种优化求解非线性方程组的方法。计算结果表明:建立的FADS系统空气动力学模型能够充分反映来流参数与测量压力间的物理规律,通过求解高阶非线性方程能够获得来流大气参数,其中马赫数误差小于0.15、攻角误差小于0.3°、侧滑角误差小于0.5°、静压小于500 Pa。
Traditional blunt body aircraft FADS system aerodynamics model is no longer applicable to lifting body high- speed aircraft. Lifting body high-speed aircraft FADS aerodynamics model is established by utilizing nonlinear least squares minimization algorithm based on Levenberg- Marquardt algorithm.Then the method of solving nonlinear equations optimization is proposed according to the established higher order nonlinear model. The results show that FADS system aerodynamic model can fully reflect the physics laws between flow parameters and the measured pressure. The flow atmospheric parameters can be obtained by solving nonlinear equations： Mach error is less than 0. 15,the attack angle error is less than 0. 5 degrees,slip angle error is less than 0. 5 degrees,the static pressure error is less than 500 Pa.
出处
《战术导弹技术》
北大核心
2015年第6期27-31,52,共6页
Tactical Missile Technology
