摘要
在简要分析飞机侧向控制系统运动模态基础上,对飞机γ角姿态控制系统结构方案进行设计并进行仿真验证。仿真结果显示,所设计的飞机γ角姿态控制系统结构方案及其控制规律具有良好抗干扰能力,是合理有效的,从而提出对飞行状态变化剧烈的飞机,应采用控制规律调参措施。
On the basis of synopsis analysis airplane the sport molds of the lateral side control system, the structure control project of aero angle attitude control system was designed and verified by simulation was done. Simulation results show that designed aero angle attitude control system structure project and it＇s control law had good anti-interference ability, and were feasible. Lastly, it was put forward the control law should adopt adjusting parameters measures with flying state violent variety airplane.
出处
《海军航空工程学院学报》
2012年第4期451-455,458,共6页
Journal of Naval Aeronautical and Astronautical University
基金
国家自然科学基金资助项目(60774016)
关键词
侧向运动模态
γ角姿态控制系统
控制规律传动比
调参
lateral side sport mold
angle attitude control system
transmission ratio of control law
adjusting parameters
simulation
