论文部分内容阅读
在研究飞机结冰机翼和平尾失速机理的基础上,以飞机迎角作为关键参数,飞机俯仰指令作为指令参数,提出一种基于飞机自驾仪的结冰后边界保护方法.通过引入铰链力矩检测模块,提前告警飞机失速,为边界保护提供了裕度.建立飞机纵向动力学方程,针对俯仰姿态保持(PAH)模式下机翼失速进行了仿真计算.结果表明:结冰条件下,通过铰链力矩的检测,飞机能在失速迎角为2°之前,进入边界保护模式,增加飞行安全的裕度.通过控制指令的限制,自动驾驶模式下飞机迎角能保持在失速迎角之内.
On the basis of studying the mechanism of aircraft icing wing and tail-tail stall, aiming at the angle of attack of the aircraft as the key parameter and the aircraft pitch command as the command parameters, a method of post-icing boundary protection based on the autopilot is proposed. By introducing the hinge torque detection Module, the aircraft is informed of the stall in advance to provide the margin for the boundary protection. The longitudinal dynamics equation of the aircraft is established, and the wing stall in pitch attitude maintaining (PAH) mode is simulated. The results show that under the icing condition, , The aircraft can enter the boundary protection mode before the attack angle of stall is 2 ° to increase the margin of flight safety.The aircraft’s angle of attack in automatic pilot mode can be kept within the stall angle of attack by the limitation of control commands.