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摘要:
针对固定翼飞行器无法在复杂多变飞行环境中始终处于最优气动构型的缺陷，提出能够根据飞行环境参数自适应变形的机翼设计理念。设计了一款通过刚性翼盒偏转实现变形功能的机翼，通过面元法耦合XFOIL黏性修正器进行气动模型仿真计算，对该机翼的气动特性进行分析；并在此基础上设计变形机翼舵机风洞试验平台，搭建测试采集系统，对航模舵机驱动变形的气动伺服系统进行低速风洞试验，通过子空间辨识法获得了气动伺服系统的数学模型，并通过比例积分微分（PID）控制结合Smith预估控制算法的方式进行舵机补偿控制。最后根据得到的变形机翼气动数据和舵机频响特性，以优化气动性能为目标设计了一款基于舵机补偿的自适应变形机翼反馈控制系统，可以实现在复杂环境中的舵机补偿和自适应变形，对后续变形机翼的设计提供了参考。
Abstract:Aiming at the defect that the fixed-wing aircraft can not always be in the optimal aerodynamic configuration in the complex and changeable flight environment, the wing design concept which can adapt to the deformation according to the flight environment parameters is proposed. A wing is designed in this study to achieve deformation by deflecting the rigid wing box. The aerodynamic characteristics are investigated by the panel method coupling with the XFOIL viscous corrector. A wind tunnel test platform and data acquisition system for the actuators of the morphing wing are built. A low speed wind tunnel test is then carried out on the deformed pneumatic servo system driven by model aircraft actuators, and the mathematical model of the pneumatic servo system is obtained with the subspace identification method. The servo compensation control is carried out by proportion integral differential (PID) control combined with Smith predictive control algorithm. Finally, according to the aerodynamic data of the morphing wing and the frequency response characteristics of these actuators, a feedback control system of the adaptive morphing wing is designed to optimize the aerodynamic performance based on the compensation of actuators. This design could realize the compensation and adaptive deformation of actuators in complex environments, providing a reference for the subsequent design of the morphing wing.
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图 1 刚性分段后缘变弯度结构设计图
Figure 1. Design drawing of variable bending structure for rigid segmental trailing edge
图 2 刚性分段后缘变弯度结构实物图
Figure 2. Picture of variable bending structure for rigid segmental trailing edge
图 7 各构型升力系数随迎角变化曲线
Figure 7. Variation of lift coefficients of each configuration with angle of attack
图 9 各构型升阻比随迎角变化曲线
Figure 9. Variation of lift-drag ratio of each configuration with angle of attack
图 12 舵机频响特性拟合与试验数据对比
Figure 12. Fitting and experimental data of frequency response characteristics
图 15 不同控制方式下舵机阶跃响应
Figure 15. Step response of steering gear under different control modes
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