摘要
通过改造非定常气动力的数学模型,对经典六自由度方程进行改进,提出一种新颖的全量气动力六自由度方程,计算飞机飞行轨迹。以某型飞机大攻角大振幅动态风洞试验结果为样本数据建立数学模型,进行尾旋仿真计算,分析飞机尾旋各阶段的非定常气动力特性。
By transforming the unsteady aerodynamic model to improve the classic six-degree-freedom nonlinear equations, a novel equation with total aerodynamic forces is proposed to calculate the flight path of the aircraft. A mathematical model is built to simulate the spin motion of aircraft, by using the wind tunnel test of the large amplitude motion as the sample data. The simulation illustrates the characteristics of unsteady aerodynamic in each stage of spin.
出处
《大众科技》
2013年第11期87-90,共4页
Popular Science & Technology
关键词
非定常气动力
尾旋
仿真
六自由度方程
Spin
unsteady aerodynamic model
simulation
six-degree-freedom nonlinear equations
