Design of multiple-input/multiple-output control law for active flutter suppression of flying-wing aircraft
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摘要:
针对飞翼布局飞机刚体模态与弹性模态耦合严重，体自由度颤振问题突出的特点，提出一种基于鲁棒控制理论的飞翼布局飞机体自由度颤振主动抑制控制律设计方法。该控制律设计方法将受控对象所受干扰及建模过程中存在的不确定参数统一视为 “未知扰动”，通过分析其输入/输出关系对其进行状态估计，最后，综合给出反馈控制律。为验证所提控制律的颤振抑制效果，以一飞翼布局无人机标模为分析对象，分别以机身内侧2副翼舵面作为控制输入，飞机刚体俯仰速度和翼尖运动速度为反馈信号来设计控制器。对闭环系统
V -g 曲线、闭环时域状态方程等进行了数值仿真，结果表明：该控制律设计方法能有效提高飞机颤振临界速度。-
关键词:
- 气动弹性 /
- 飞翼布局飞机 /
- 颤振主动抑制 /
- 体自由度颤振 /
- MIMO输出反馈控制器
Abstract:In this paper, a multiple-input/multiple-output control law design method for active flutter suppression of flying-wing aircraft is proposed. The input/output relationship of the plant is used to estimate and adjust the “unknown perturbation” caused by the uncertain factors of the controlled plant. The output feedback control law is then designed. In order to validate the effectiveness of the proposed control law on flutter suppression, a high aspect ratio flying-wing layout aircraft was chosen as the research object of this paper. For the controller synthesis, the inboard ailerons served as the control surfaces, and the rigid-body pitch rate combined with the wing tip motion velocity provided the feedback. A high aspect ratio flying-wing layout aircraft was selected as the research object for this paper in order to verify the efficacy of the suggested control law on flutter suppression. The two aileron rudder surfaces on the inside of the fuselage were used as control inputs, and the rigid body pitch speed and wing tip motion speed were used as feedback signals to design the control input. The relation between velocity and damping of the closed-loop system and the closed-loop time-domain state equation is carried out. The results show that the control law design method can effectively improve the critical flutter velocity of the aircraft.
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表 1 模型主要几何尺寸
Table 1. Principal geometric dimensions of the model
展长b/m 机身长度L/m 展弦比 后掠角λ/(°) 翼根弦长 $ {c}_{\text{root}} $/m 3.05 0.85 10.2 22 0.299 
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表 2 模态参数
Table 2. Modal parameters
模态阶数 频率/Hz 模态振型 7 5.377 一阶对称弯曲 8 9.471 一阶反对称弯曲 9 12.783 一阶反对称扭转 10 14.411 一阶对称扭转 11 19.345 二阶对称弯曲 12 27.260 二阶反对称扭转 13 30.660 二阶反对称弯曲 14 31.654 二阶对称扭转
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表 3 各阶模态对应特征向量
Table 3. Feature vectors corresponding to each mode
模态阶数 频率/Hz 模态振型 特征向量 3 0 刚体沉浮 0.054−0.048i 4 0 刚体俯仰 1.00 7 5.377 一阶对称弯曲 −0.58+0.30i 10 14.411 一阶对称扭转 0.036−0.013i 11 19.345 二阶对称弯曲 0.021−0.004i
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