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Nonlinear Flight Control Design for Longitudinal Dynamics

机译：纵向动力学的非线性飞行控制设计

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This paper investigates a state space exact linearization methodology for flight path angle control corresponding to the longitudinal dynamics of a high performance aircraft simulation model. The main challenge of this approach is explicit determination of the Lie derivatives of lift force with respect to flight path angle and pitch angle. These derivatives are not directly available in function format table look-up data. These derivatives, specifically the first and second partial derivatives of lift force as a function of the flight path angle and pitch angle are synthesized by combined use of the drag polar equation and consideration of the short period constant speed approximation. With this methodology, the state space exact linearization design approach transforms the original nonlinear dynamic system into Brunovsky canonical form with new input via state feedback and coordinate transformations. The new input of the obtained system is designed by using the linear backstepping based approach. Control of the single output flight path angle variable, expressed in the velocity axes motion equations, using the single input horizontal tail deflection signal is considered. Algorithms are tested and evaluated with nonlinear closed-loop simulation. Results indicate the state space exact linearization control strategy is effective for longitudinal flight augmentation.
机译：本文研究了一种状态空间精确线性化方法，用于控制与高性能飞机仿真模型的纵向动力学相对应的航迹角。这种方法的主要挑战是明确确定升力的Lie导数相对于飞行路径角和俯仰角的关系。这些导数在函数格式表查找数据中不直接可用。这些导数，特别是升力的一阶和二阶偏导随飞行路径角和俯仰角的函数，是通过组合使用阻力极式方程式并考虑短周期恒速近似而合成的。通过这种方法，状态空间精确线性化设计方法通过状态反馈和坐标变换将原始的非线性动力学系统转换为具有新输入的Brunovsky规范形式。通过使用基于线性反步的方法来设计所获得系统的新输入。考虑使用单个输入水平尾翼偏转信号控制以速度轴运动方程式表示的单个输出飞行路径角度变量。使用非线性闭环仿真对算法进行测试和评估。结果表明，状态空间精确的线性化控制策略对于纵向飞行增强是有效的。

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