Multidisciplinary Design and Optimization of Variable Camber Wing with Non-Equal Chord

Since the taper ratio of most wings is not equal to 1, beam-disk trailing edge deflection mechanism originally designed for rectangular wing fully applicable non-equal chord wing. Moreover, it only expected that shape can achieve excellent aerodynamic performance under different flight conditions, but one also needs consider whether flexible skin this deformation. This paper used honeycomb composite structure with zero Poisson’s as variable camber wing, and The configuration was optimized considering deformation capability skin, multidisciplinary design optimization method studied. results show performances were better than before all given conditions. could withstand strain caused by maximum weight reduced 47.1% compared initial when structural stiffness strength satisfied.