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本文采用三阶活塞理论推导超声速机翼的非线性气动力和气动力矩,建立了随机扰动下具有俯仰立方非线性效应的二元机翼运动方程。之后进行稳定性分析得到理论颤振速度,并利用MATLAB仿真验证。研究表明,利用三阶活塞理论能更精确得到定常气动力和气动力矩,可以提高机翼动力学研究的可靠性和安全性。
In this paper, the nonlinear aerodynamic and aerodynamic torques of supersonic winged wing are deduced by the third-order piston theory. The binary wing equation of motion with pitch-cube nonlinearity under random perturbation is established. After stability analysis, the theoretical flutter speed is obtained and verified by MATLAB simulation. The research shows that the steady-state aerodynamic and aerodynamic torques can be obtained more accurately by the third-order piston theory, which can improve the reliability and safety of wing dynamics research.