A STUDY ON FLEXIBLE EFFECTS OF A SPINNING ROCKET LAUNCHER SYSTEM

In this paper, the coupled vibrating behavior between a spinning rocket with large slenderness ratio and the launcher is studied. Effects of flexibility of rocket and launcher and supporting shoes on the rocket's motion attitude are analyzed. The impact transient response is obtained using a hybrid method when some supporting shoes separate out of the launcher. The approach will provide a useful reference to the design for the new type of rocket-launcher system.