摘要
建立了线性与非线性两种分布式气动力模型,在弹性飞机模型上添加所建立的气动力模型,验证了整个系统的有效性。对所建立的模型进行着陆及突风扰动动力学仿真,对比线性及非线性气动力模型的飞机动力学响应的差异,结果表明非线性气动力模型能够更合理地计算飞机大迎角状态下的气动载荷及动力学响应。
Linear and nonlinear distributed aerodynamic force models are established and applied on flexible-body aircraft models,and the entire system is proved to be reasonable and available.Landing simulation and gust perturbation simulation are run based on the established model.The difference between the dynamic responses of linear and nonlinear aerodynamic force models are compared.The results show that the nonlinear aerodynamic force model is more reasonable for the calculation of aerodynamic force and dynamic response of aircraft at high angle of attack.
出处
《飞行力学》
CSCD
北大核心
2012年第2期110-112,116,共4页
Flight Dynamics
基金
国防基础科研计划资助(A2720060290)
关键词
柔性飞机
非线性
分布式气动力
动力学
flexible-body aircraft
nonlinear
distributed aerodynamic force
dynamics
