摘要
结合飞行安全和作战效能需求,对过失速战斗机的大迎角/过失速迎角下俯敏捷性指标及纵向控制效能需求进行了研究。为了满足飞行品质和过失速敏捷性指标要求,采用非线性动态逆方法设计了某推力矢量飞机快回路和慢回路飞行控制律。在此基础上,根据过失速下俯敏捷性和滚转敏捷性指标要求,对所需的最小俯仰推力矢量偏角进行了计算分析,所得结果对先进战斗机的设计有一定的参考价值。
Considering the requirement of flight safety and combat efficiency, the pitch down agility metrics and the longitudinal control requirement for advanced post-stall aircraft at high-angle-of-attack/post-stall was discussed in this paper. In order to meet the request of both flying quality and post-stall, agility, a nonlinear dynamic inverse（NDI） method was engaged to design the fast-loop and slow-loop flight control law of a thrust vectoring control aircraft. And then the min deflection of the pitch thrust vectoring that satisfied the requirement of pitch down agility and rolling agility respectively was computed by a trial and error method and a rough analytical estimate method. The results showed in the paper has some reference value to the advanced aircraft design.
出处
《飞行力学》
CSCD
北大核心
2009年第6期10-13,共4页
Flight Dynamics
基金
航空科学基金资助项目(2007ZA52010)
关键词
大迎角/过失速敏捷性
非线性动态逆
推力矢量控制
控制效能
high-angle-of-attack/post-stall agility
nonlinear dynamic inverse
thrust vectoring control
control requirement
