Design and Verification of Multi-Mode Variable Camber Wing Trailing Edge

By changing the aerodynamic shape of the trailing edge of its wing, an aircraft can achieve lift and drag reduction during takeoff and landing and continuously achieve better aerodynamic efficiency while cruising, which plays an important role in the whole flight process and has always been a research hotspot in the field of aviation structure. Firstly, the principle scheme of wing trailing edge deformation based on a two-stage multi-link mechanism was designed and realized, and then the mechanical structure was designed in a way that ensured the machining feasibility of the prototype. Secondly, a control system scheme was designed to realize synchronous and differential deformation movement of single and double mechanisms. Finally, power drive device selection and prototype manufacturing verification were carried out. The experiments show that the designed and manufactured variable camber wing trailing edge prototype can achieve two modes of wing trailing edge deformation, namely the overall deflection of the variable camber wing trailing edge +5°~−20° and the wing tip deflection +10°~−10°. The deformation error is measured within 5%.