Adaptive Control of Advanced Fighter Aircraft in Nonlinear Flight Regimes
Adaptive Control of Advanced Fighter Aircraft in Nonlinear Flight Regimes
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DOI：
10.2514/1.30213
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发表时间：
2008-09
影响因子：
2.6
通讯作者：
Y. Shin;A. Calise;Matthew Johnson
中科院分区：
文献类型：
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作者：
Y. Shin;A. Calise;Matthew Johnson
先进战斗机大迎角飞行时，非定常气动力效应、机翼摇摆和气动效应器饱和会导致操纵和机动困难。研究了一种基于动态逆的飞机自适应输出反馈控制器设计方法，该方法适用于高度非线性飞行状态，其中未建模参数变化和未建模动态的不确定性是常见的。设计的稳定性进行了分析和验证与模拟使用修改后的NASA F-15模拟。模拟包括推力矢量和差动稳定器，以提供在大迎角时增加的控制权和放松的静稳定性，以增加俯仰机动性。控制设计包括使用“伪控制对冲”技术，以排除适应控制饱和。
When advanced fighter aircraft fly at high angles of attack, unsteady aerodynamic effects, wing rock, and saturation of aerodynamic effectors can lead to difficulty in control and maneuverability. A novel adaptive output feedback control design based on dynamic inversion is investigated for aircraft which are operated in highly nonlinear flight regimes, where uncertainties in the form of both unmodeled parameter variations and unmodeled dynamics are common. The stability of the design is analyzed and validated with simulations using a modified NASA F-15 simulation. The simulation includes thrust vectoring and a differential stabiliator to provide increased control authority at high angles of attack and relaxed static stability to increase pitch maneuverability. The control designs include the use of "pseudocontrol hedging" techniques to exclude adaptation to control saturation.