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Research on model reference sliding mode control in roll stabilization of aerocraft

机译：飞机侧倾稳定中模型参考滑模控制的研究

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Aimed at aerospace roll stabilization, control arithmetic based on model reference sliding mode variable structure theory and chattering reduction arithmetic are formulated. Correctness and validity of arithmetic are analyzed. With flight dynamics, the roll-loop mathematic model and reference model are established. Sliding hyperplane is deduced based on model reference sliding mode variable structure theory. Combing with reaching law, control law is derived, and stability of roll-loop is analyzed. Chattering of aileron instructions is alleviate by using boundary layer approach. Digital flying simulation result shows that variable structure control arithmetic realized roll stabilization control, the roll angle is less than 5.3° under powered flight, and that of unpowered flight is less than 0.5°, respectively. The command fin angle is less than 1.5°. High frequency chattering of fin command nearby the minimum velocity was trailed off by chattering reduction arithmetic. The sliding mode control arithmetic show good performance when aerodynamic coefficients varies 20%. The control arithmetic is easy to be implemented for its simplicity.
机译：针对航空侧倾稳定，提出了基于模型参考滑模变结构理论的控制算法和抖振减小算法。分析了算术的正确性和有效性。利用飞行动力学，建立了侧滚环数学模型和参考模型。基于模型参考滑模变结构理论推导了滑模超平面。结合到达定律，推导了控制律，并分析了滚动回路的稳定性。通过使用边界层方法可以缓解副翼指令的抖动。数字飞行仿真结果表明，变结构控制算法实现了侧倾稳定控制，动力飞行下的侧倾角小于5.3°，无动力飞行下的侧倾角小于0.5°。指令鳍角小于1.5°。最小指令速度附近的鳍命令的高频颤振通过颤振归约算法被消除。当空气动力系数变化20％时，滑模控制算法显示出良好的性能。由于其简单性，易于实现控制算法。

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