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Variable structure robust flight control system for the F-14

机译：F-14的可变结构鲁棒飞行控制系统

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摘要

In this paper, a flight control law for a simplified F-14 aircraft model is designed based on variable structure control (VSC) theory. For m-input, q-output linear uncertain systems (q>m), a VSC law is derived. For the derivation of the control law, a choice of a sliding surface is made so that the zero dynamics of the system are stable. The linear lateral and longitudinal dynamics of the F-14 are decoupled. This allows design of lateral and longitudinal flight controllers separately. An application of variable structure system (VSS) theory to control of lateral dynamics is presented. A control law is derived for the control of roll angle, lateral velocity, and yaw rate. The chosen sliding surface for the controller design is a linear function of the tracking error, its derivative, and the integral of the tracking error. Simulation results are presented to show that in the closed-loop system, precise bank angle trajectory tracking and regulation of lateral velocity and yaw rate can be accomplished in spite of aerodynamic parameter uncertainty.
机译：本文基于可变结构控制（VSC）理论，设计了简化的F-14飞机模型的飞行控制律。对于m输入，q输出线性不确定系统（q> m），推导了VSC定律。为了推导控制律，需要选择滑动面，以使系统的零动态稳定。 F-14的线性横向和纵向动力学是解耦的。这样可以分别设计横向和纵向飞行控制器。提出了变结构系统理论在横向动力学控制中的应用。推导了用于控制侧倾角，横向速度和横摆率的控制律。为控制器设计选择的滑动表面是跟踪误差，其导数和跟踪误差积分的线性函数。仿真结果表明，在闭环系统中，尽管存在气动参数不确定性，但仍可以实现精确的倾斜角轨迹跟踪以及横向速度和偏航角速度的调节。

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