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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。
Aiming at the problem that the aerodynamic model of traditional bluff body vehicle FADS system is no longer suitable for the lift body high-speed aircraft, a nonlinear least squares optimization algorithm based on Levenberg-Marquardt algorithm is used to establish the aerodynamic model of the FADS system. According to the established high-order nonlinear model, a method to optimize the nonlinear equations is proposed. The calculation results show that the established aerodynamic model of FADS system can fully reflect the physical laws between the flow parameters and the measured pressure, and the atmospheric parameters can be obtained by solving the higher-order nonlinear equations. The error of Mach number is less than 0.15 and the angle of attack error Less than 0.3 °, the slip angle error is less than 0.5 ° and the static pressure is less than 500 Pa.