一种进场着陆阶段的模型跟踪控制律设计  

Design of model-following control law for approach and landing

作　　者：张喆[1] 祁圣君[1] 王锋[1] 

机构地区：[1]中国飞行试验研究院飞机所,陕西西安710089

出　　处：《飞行力学》2013年第5期447-449,共3页Flight Dynamics

摘　　要：为进行进场着陆阶段飞机俯仰角速度、航迹、迎角等参数的空中飞行模拟,根据模型相似准则,以经典控制原理进行升降舵控制、直接升力控制和自动油门控制的纵向模型跟踪控制律设计,并在Simlink环境下进行数值仿真。仿真结果表明,所设计的控制律可以满足跟踪模拟的要求。In-flight simulation in the stage of approach and landing focuses on the simulation of some im- portant parameters, such as angle of attack, flight-path angle, pitch rate and so on. According to the similarity criterion, longitudinal control law includes the control of elevator, direct lift and automatic throttle. This paper describes the design of model-following control law in terms of classical control theory. Digital simulation results by Simlink show that the control law could meet the requirements of model- following, which is a feasible attempt for control law design of variable stability aircraft.

关 键 词：变稳飞机 空中飞行模拟 经典控制理论 模型跟踪 

分 类 号：V212.1[航空宇航科学与技术—航空宇航推进理论与工程] V249.1