摘要
为解决中性速度稳定性控制律切换到正向速度稳定性控制律过程中飞机瞬态大以及飞行员操纵负担重的问题,提出了一种控制律转换过程中保持平尾偏度不变的瞬态抑制方法并进行了仿真。首先分析了控制律转换过程中飞机状态变化大的原因;然后通过存储器使控制律模态转换后平尾偏度不变;最后通过逻辑运算选取飞行员操纵指令。仿真结果表明,所设计的瞬态抑制方法能够明显减小控制律转换过程中的飞机瞬态变化量,同时显著减轻飞行员负担。
In order to solve the problem that large variation of aircraft transient responses and pilot＇s workload during transforming from neutral speed stability control laws to positive speed stability control laws,a method to suppress the transient responses by holding elevator deflection constant during control laws transformation was proposed and simulated as well. Firstly,reasons for large changes of aircraft states due to control laws switch were analyzed. Secondly,elevator deflection was hold by means of a memory after control laws mode switch. Finally,pilot＇s control command was selected based on logic calculation.Simulation results show that the designed transient suppression method in this paper can obviously reduce the aircraft transient responses during control law transformation,at the same time greatly alleviate pilot＇s workload.
作者
赵海
景海峰
刘世民
ZHAO Hai;JING Hai-feng;LIU Shi-min(Flight Control System Design Institute,Xi＇an Aircraft Design Institute,Xi＇an 710089,China)
出处
《飞行力学》
CSCD
北大核心
2018年第5期30-33,38,共5页
Flight Dynamics
关键词
控制律转换
平尾偏度
瞬态抑制
control laws transformation
elevator deflection
transient suppression
