Design and Analysis of a Deployment Mechanism with Clearance Compensation for High Stiffness Missile Wings

The deployment performance of the unfolded wing determines whether winged missiles can fly normally after being launched, infecting attack missiles. paper proposes a new mechanism with clearance eliminator. Based on slider-crank principle, proposed achieves fast and low-impact wings. eliminator shape memory alloy (SMA) effectively eliminates sliding pair improves support stiffness stability deployed wing. collision characteristics elimination are studied for mechanism. influence force motion state during is analyzed. static under deformation dynamic catapult modeled based fractal geometry contact stress theory. relationship between locking revealed. kinetic simulation used to analyze response action Modal analysis, harmonic random vibration analysis were conducted whole A prototype was developed verify ejection according input load characteristics. wings tested by fundamental frequency experiments assembly. experimental results show that designed compensation high retention missile