摘要
舰载机事故主要发生在着舰过程,而其主要原因是由于舰载机低速着舰时航迹控制不稳定引起的,进场动力补偿系统就是为了解决这一不稳定现象而产生的推力自动控制系统.为了克服舰载机低速不稳定问题,提高航迹控制精度,并减轻飞行员在着舰阶段的工作负荷,飞机系统中需要引入速度恒定进场动力补偿系统.采用F/A-18A舰载机参数建立舰载机纵向运动小扰动线性化模型,分析模型飞行品质,并引入飞机姿态控制系统来解决俯仰控制不稳定的现象并使飞机满足一级飞行品质,之后采用衰减曲线法设计PID参数完成对速度恒定进场动力补偿系统的设计,解决航迹角无法跟踪俯仰角这一航迹控制不稳定问题,最后又引入舰尾流的垂直稳态分量验证了系统的抗扰动能力.
Carrier-based aircraft disaster mainly occurs during landing, and the main reason is due to the unstable flight path control when the aircraft has low speed. The approach power compensator system is used to solve this unstable phenomenon. In order to overcome the shortcoming of instability caused by the low speed, improve the precision of flight path control, and reduce the burden of the pilot during landing, the approach Power compensator system with constant speed should be used in the aircraft system. On the basis of parameters of F/A-18A, the linear model of longitudinal motion is established, and the flying quality of model is analyzed and calculated. The instability of pitch control is solved and the flying quality of level one is satisfied by using the attitude control system. Then in order to complete the design of approach power compensator system, the PID controller is applied. By using the approach power compensator, the question that track angle can not follow angle of pitch, ie, .the phenomenon of unstable flight path control is solved.
出处
《应用科技》
CAS
2013年第2期40-43,共4页
Applied Science and Technology
基金
国家自然科学基金资助项目(61104037)
关键词
舰载机
进场动力补偿系统
飞行控制
PID
舰艉流
carrier - based aircraft
approach power compensator system
flight control
PID
carrier aft flow
