摘要
针对飞机设计过程中,操纵面铰链力矩确定问题,进行具有操纵面偏转速率限制的电传飞机实时铰链力矩计算方法研究。这里依据飞机动力学特性、具有最大速率限制的舵面动力学特性以及舵面部件气动特性,确定飞机飞行过程中舵面的实时铰链力矩。利用MATLAB/simulink工具建立了舵面动力学模型和飞机动力学模型。以纵向操纵面升降舵为例,仿真研究了某飞机定直平飞以及机动飞行中舵面实时铰链力矩特性,给出了对应状态的舵面偏转速率,对比分析了静平衡法和本方法确定的操纵面总力矩特性的差异,结果表明本方法适合飞机详细设计阶段。
The computation method of the modern fly-by-wire aircraft hinge moments was studied. The real time hinge moments of the control surfaces were determined according to the flight dynamics characteristics of the aircraft, the control surface dynamics and aerodynamics characteristics. The aircraft six Dof dynamic model and control surface dynamic model were established. The online hinge moment characteristics of the control surfaces were simulated through the MATLAB/simulink tools aiming at the straight and maneuver flight. Simultaneity the elevator deflecting rate and the maximum hinge moment were given. The differences of the control surface overall moment were compared between the results of two methods. The results show that the method is suitable for the aircraft to the detailed design stage.
出处
《系统仿真技术》
2014年第1期58-62,共5页
System Simulation Technology
关键词
飞行力学
民用飞机
速率限制
操纵面
铰链力矩
flight dynamics
civil aircraft
rate limiting
control surface
hinge moment
