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An Investigation of the Applicability of Linear Optimal Control Theory to Aircraft Control System Design

机译：线性最优控制理论在飞机控制系统设计中的适用性研究

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Using steady-state linear regulator theory a longitudinal feedback control system is found for a hypothetical high-performance aircraft that operates through a wide range of Mach number and dynamic pressure. The aircraft stability derivatives vary statistically and the aircraft measurement sensors are affected by body bending responses. Linear approximations of the optimal feedback law gains are programmed as functions of Mach number and dynamic pressure, and the normal-acceleration elevator-step-response of the closed-loop aircraft is simulated. The simulated step responses are compared to a normal acceleration step response criterion envelope that is specified in the 1970 Joint Automatic Control Conference (JACC) Design Challenge. (Author)

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作者
Sherrard, A. R.;
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年度 1971
页码 p.1-134
总页数 134
原文格式 PDF
正文语种 eng
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关键词
Flight control systems ; Adaptive control systems ; Design ; Mathematical models ; Differential equations ; Matrix algebra ; Stochastic processes ; Aerodynamics ; Gust loads ; Feedback ; Stability ; Computer programs ; Simulation ; Theses;

机译：飞行控制系统;自适应控制系统;设计;数学模型;微分方程;矩阵代数;随机过程;空气动力学;阵风载荷;反馈;稳定性;计算机程序;模拟;论文;

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5. Controllability of switched linear systems and the optimal control of nonlinear systems. [D] . Yang, Ying. 1996

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7. Optimal Control Theory due to Parameter Optimization Method and its Application to The Design of Optimal Control Equipment for Aircraft [O] . Kunihiko ICHIKAWA, Kimio KANAI, Hidenori OSHIMA 1969

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An Investigation of the Applicability of Linear Optimal Control Theory to Aircraft Control System Design

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