摘要
本文针对12维非线性飞机动力学模型,利用非线性逆动力学理论和现代最优控制理论设计了一组含有指令静差积分环节的非线性解耦控制规律。这组控制规律使得对状态变量、控制变量以及它们变化率进行加权约束的性能指标极小,并能用平缓的操纵反应和较小的控制能量使飞机达到完全解耦的指定状态。由于这组控制规律计及了飞机动力学模型中的非线性因素,能够弥补飞机机动飞行时非线性特性的恶化影响,在整个飞行包线内都能为飞机提供优良的操纵品质和飞行性能。
Based on 2-state nonlinear aircraft dynaminc model, a nonlinear decoupling control law which contains command static error integral loop is designed by combining nonlinear inverse dynamics theory and modern optimal control theory . This control law could minimize the performance index which contains the weighted state variables, control variables and their varying rates. Using this control law, the aircraft could capture the desired flight state more accurately and decouples the control more completely with smooth control responses and less control energy. As the control law more accurate represents the nonlinear factors that arise in aircraft dynamic model and remedies the degrading of aircraft nonlinear dynamical behavior during maneuvering flight , it offers the potential for providing high levels of handling quality and flight performance in the entire flight envelope of the aircraft.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第10期B485-B494,共10页
Acta Aeronautica et Astronautica Sinica
关键词
非线性
机动飞行
飞行控制
解耦
nonlinear systems, maneuvering flight, flight control, decoupling , inverse systems
