摘要
按稳定尾旋的条件对飞机运动方程组作了简化。提出一种计算图解法和尾旋中侧滑角计算式,并用于J—7飞机稳定尾旋特性研究和验证。
In this paper, the non—linear differential equations of aircraft motion are simplified by the condition of steady spin. Put forward a calculative—graphical method and calculative equation of sideslip angle. The method and equ(?)ation of sideslip angle are used to the research of characteristics of stead spin of aircraft J—7. The method and equation of sideslip angle are testified to avaiable.
出处
《飞行力学》
CSCD
北大核心
1993年第4期21-30,共10页
Flight Dynamics
关键词
稳定尾旋
侧滑角
计算图解法
飞机
Steady spin Sideslip angle Calculative—graphical method
