| 自抗扰控制在推力矢量飞机大迎角机动中的应用 |
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| 作者姓名： | 刘俊杰 陈增强 孙明玮 孙青林 |
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| 作者单位： | 1.南开大学人工智能学院, 天津 300350 |
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| 基金项目： | 国家自然科学基金面上资助项目61573199国家自然科学基金面上资助项目61573197 |
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| 摘 要： | 为实现推力矢量飞机的大迎角机动控制，提出一种基于自抗扰控制的三通道解耦控制策略.以第三代战机F16公开数据为基础，添加推力矢量模型，利用双发推力矢量喷管组合偏转产生大迎角机动的期望三轴力矩.在纵向、横向和航向通道分别独立设计自抗扰控制器，将系统中未建模动态、不确定性以及通道间的强耦合视作总扰动进行估计并补偿，并在纵向和航向通道引入角速度阻尼反馈项，使原始飞行器开环动力学闭环近似为一个广义对象，降低了自抗扰控制器的设计阶次.选取眼镜蛇机动和赫伯斯特机动两种典型的过失速机动动作进行控制策略验证，数值仿真结果表明，所设计的三通道独立自抗扰控制器能够消除通道间的强耦合，完成推力矢量飞机的大迎角机动控制.蒙特卡罗仿真测试表明，所提控制策略具有较强的鲁棒性.
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| 关 键 词： | 推力矢量飞机 大迎角 过失速机动 自抗扰控制 解耦控制 |
| 收稿时间： | 2018-12-02 |
Application of active disturbance rejection control in high-angle-of-attack maneuver for aircraft with thrust vector |
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| Affiliation: | 1.College of Artificial Intelligence, Nankai University, Tianjin 300350, China2.Key Lab of Intelligent Robotics of Tianjin, Tianjin 300350, China |
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| Abstract: | The super maneuverability of aircraft is a key factor determining its success or defeat in air combat. The analysis and control of aircraft post stall maneuvering at a high angle of attack can greatly improve the aircraft maneuverability. When the aircraft performs a high-angle-of-attack maneuver, the aircraft's attack angle far exceeds the stall angle; thus, the aerodynamic and aerodynamic moment characteristics are not only strongly nonlinear but also have delay effects and strong coupling characteristics. Moreover, the linear control method based on the linearization of small disturbance hardly satisfies the control requirement because there is no typical leveling state. Traditional nonlinear control methods include nonlinear dynamic inverse, sliding mode control, and robust control for high-angle-of-attack maneuvering of aircraft. However, these methods rely on the accurate model of the aircraft and are greatly affected by modeling errors. To realize the high-angle-of-attack maneuver control for an aircraft with thrust vector, a three-channel decoupling control strategy based on active disturbance rejection control was proposed herein. Based on the public data of the third-generation fighter F16, a thrust vector model was developed. The desired triaxial moments were generated by the thrust vector nozzle combination. Active disturbance rejection controllers were independently designed in longitudinal, lateral, and heading channels. The unmodeled dynamics, uncertainty, and strong coupling between the channels were regarded as total disturbance, which was estimated and compensated online. The angular rate damping feedback term made the closed-loop dynamics of the original aircraft approximate a generalized object, which reduced the design order of the active disturbance rejection controller. As two typical post-stall maneuvers, Cobra maneuver and Herbst maneuver were selected for control strategy verification. The numerical simulation results show that the designed three-channel independent active disturbance rejection controllers can eliminate the strong coupling among channels and realize a high-angle-of attack maneuver for the aircraft with thrust vector. The Monte Carlo simulation results show that the control strategy has good robustness. |
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