Abstract: The deployment process of missile folding-wing during launching is studied. The real launching processes of test missiles are simulated, two kinds of folding-wings with different stiffness are tested, and some images and trajectory data of the test missiles are obtained. A dynamic model of deployment process of folding-wings, including the angle of attack and the velocity of test missile, is established, in which the change in angle of attack of test missile is due to launching disturbance. The comparison of the proposed dynamic model and CFD method shows a good agreement for the large rotating angle of airfoil surface. In the test, the deployments of the little stiffness folding-wings are unsynchronized, the deployments of the lower wings are lagged obviously. The proposed dynamic model gives the results of the deployment process by using the measured velocity and angle of attack. Key

Key words: missilefolding-wing, deploymenttest, launchenvironment, dynamicsimulation, angleofattack