刚柔混合变弯度机翼控制方法研究

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.