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SLIDING MODE CONTROL OF PITCH RATE OF AN F-16 AIRCRAFT

机译：F-16飞机俯仰速度的滑模控制

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The control of the longitudinal flight dynamics of an F-16 aircraft is challenging because the system is highly nonlinear and also nonaffine in the input. We consider a sliding mode control (SMC) design based on linearization of the aircraft, with the altitude h and velocity V (Mach number) as the trim variables. The design further exploits the modal decomposition of the dynamics into its short-period and phugoid approximations. The primary design objective is model-following of the pitch rate q, which is the preferred system for aircraft approach and landing. Regulation of the aircraft velocity V (or the Mach-hold autopilot) is also considered, but as a secondary objective. It is shown that the inherent robustness of the sliding mode control design provides a convenient way to design controllers without gain scheduling, with a steady-state response that is comparable with that of a conventional gain-scheduled approach with integral control, but with improved transient performance. Finally, we apply the recently developed technique of "conditional integrators" to achieve asymptotic regulation with constant exogenous signals, without degrading the transient response. Through extensive simulation on the nonlinear multiple-input/multiple-output (MIMO) longitudinal model of the F-16 aircraft, we show that the conditional integrator design outperforms the one based on the conventional approach, without requiring any scheduling.
机译：F-16飞机的纵向飞行动力学的控制具有挑战性，因为该系统是高度非线性的，并且在输入中也不仿射。我们考虑一种基于飞机线性化的滑模控制（SMC）设计，其中高度h和速度V（马赫数）为微调变量。该设计进一步将动力学的模态分解转化为其短周期和垂线近似。主要设计目标是模型跟随俯仰速率q，这是飞机进近和着陆的首选系统。还考虑了对飞机速度V（或马赫保持自动驾驶仪）的调节，但这是次要目标。结果表明，滑模控制设计的固有鲁棒性为不进行增益调度的控制器设计提供了一种便捷的方法，其稳态响应与具有集成控制的传统增益调度方法相当，但瞬态得到改善性能。最后，我们应用最新开发的“条件积分器”技术，以恒定的外源信号实现渐近调节，而不会降低瞬态响应。通过对F-16飞机的非线性多输入/多输出（MIMO）纵向模型的广泛仿真，我们表明条件积分器设计优于传统方法，而无需任何调度。

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