Abstract
A computational method and a mathematical model have been developed to describe the spatial motion of an axisymmetric body of revolution—such as a rocket or a missile—with centering thickenings and a radial drive pin on the body, within a rigidly fixed tubular guide equipped with a screw groove. A comparative calculation analysis of the dynamic characteristics of the interaction between the body of revolution and the guide is conducted, focusing on reaction forces and moments, as well as their corresponding total impulses, varying screw groove parameters. The influence of the these parameters on angular disturbances in pitch and yaw during the missile’s exit from the guide is examined. Using an unguided missile as a case research, the relationship between calculated lateral deviations of the flight trajectory and the disturbances occurring at the exit from the guide is analyzed. The fourth-order Runge-Kutta method is used for the numerical integration of the differential equations of missile motion. The proposed computational method and mathematical motion model can serve as a component of a comprehensive simulation framework for the launch of rockets and missiles from mobile units equipped with packages of tubular guides, with appropriate consideration of the transmitted motion dynamics.
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