刚柔混合变弯度机翼控制方法研究  

Study on control method of rigid-flexible variable camber wing

作　　者：辛涛 李斌[1] 高鹏 XIN Tao;LI Bin;GAO Peng(School of Aeronautic,Northwestern Polytechnical University,710072 Xi'an,China)

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《应用力学学报》2022年第3期468-475,共8页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金资助项目(No.11872312)。

摘　　要：为实现机翼在驱动控制下弦向连续弯度变化,提出了一种刚柔混合式变后缘机翼。其中,机翼柔顺段结构采用柔性气动肌腱作为驱动装置。首先,推导了气动肌腱驱动力模型;其次,将柔顺结构等效为单关节机械臂结构,建立了其动力学模型;继而建立了基于名义模型的滑模变结构PI控制模型,并对比例系数、积分系数及滑模面参数进行了整定。在此基础上,搭建了翼肋柔顺段变弯度控制试验平台及典型机翼盒段综合偏转控制平台。验证了柔顺段结构在弹性变形范围内达到目标弯度的能力,翼肋实际变形曲线与目标变形曲线误差仅为8%;同时,对控制方法及参数的动态性能进行了测试,其作动响应时间为5.5 s,超调量为0,稳态误差为6%,表明了控制系统的合理性和有效性。最后,对翼盒进行了目标角度的综合控制试验,测试了整体系统的变结构性能。A rigid-flexible hybrid variable trailing edge wing is proposed to realize the continuous chord wise camber change of the wing under drive control. Among them, flexible pneumatic muscle is used as the driving device for the flexible section structure of the wing. In the study on the controlling method, first, the pneumatic muscle drive force model is derived. Then, the pseudo-rigid body modeling method is used to approximate the flexible structure as a single-joint robotic arm structure and establish its dynamics model. In the next step, the PI control model of the sliding mode variable structure based on the nominal model is established, and the proportional coefficients, integral coefficients and sliding mode surface parameters are rectified. On this basis, the test platform of variable camber control of the flexible section of the wing rib and the integrated deflection control platform of the typical wing box section are built. Through the tests, the ability of the flexible section structure to achieve the target camber in the elastic deformation range is verified. The error between the actual deformation curve of wing rib and the target deformation curve is only 8%. The dynamic performance of the control method and parameters are tested. The actuation response time is 5.5 s, the overshoot is 0, and the steady-state error is 6%. The test results verify the reasonableness and effectiveness of the control system. Finally, a comprehensive control test of the target angle is conducted for the wing box to test the variable structure performance of the overall system.

关 键 词：弦向变弯度机翼 柔顺结构 气动肌腱 滑模变结构控制 

分 类 号：V224.5[航空宇航科学与技术—飞行器设计]