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Nonlinear adaptive and sliding mode flight path control of F/A-18 model

机译：F / A-18模型的非线性自适应滑模飞行路径控制

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The question of inertial trajectory control of aircraft in the three-dimensional space is discussed. It is assumed that the nonlinear aircraft model has uncertain aerodynamic derivatives. The control system is decomposed into a variable structure outer loop and an adaptive inner loop. The outer-loop feedback control system accomplishes (x,y,z) position trajectory and sideslip angle control using the derivative of thrust and three angular velocity components (p,q,r) as virtual control inputs. Then an adaptive inner feedback loop is designed, which produces the desired angular rotations of aircraft using aileron, elevator, and rudder control surfaces to complete the maneuver. Simplification in the inner-loop design is obtained based on a two-time scale (singular perturbation) design approach by ignoring the derivative of the virtual angular velocity vector, which is a function of slow variables. These results are applied to a simplified F/A-18 model. Simulation results are presented which show that in the closed-loop system asymptotic trajectory control is accomplished in spite of uncertainties in the model at different flight conditions.
机译：讨论了飞机在三维空间中的惯性轨迹控制问题。假定非线性飞机模型具有不确定的空气动力学导数。控制系统被分解为可变结构外环和自适应内环。外环反馈控制系统使用推力和三个角速度分量（p，q，r）的导数作为虚拟控制输入来完成（x，y，z）位置轨迹和侧滑角控制。然后，设计一个自适应内部反馈回路，该回路使用副翼，升降舵和方向舵控制表面产生所需的飞机角旋转，以完成操纵。通过忽略虚拟角速度矢量的导数（这是慢变量的函数），可基于两次尺度（奇异摄动）设计方法获得内环设计的简化。这些结果应用于简化的F / A-18模型。仿真结果表明，尽管模型在不同的飞行条件下存在不确定性，但在闭环系统中仍可实现渐近轨迹控制。

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