Gravity-Induced Angular Motion of a Spinning Missile

摘要

The usual analysis of the steady state angular motion of a dynamically stable spinning missile assumes a quasi-steady state calculation of a gravity-induced trim angle. A condition for the validity of this quasi-steady state assumption is derived. When this condition is not satisfied, the gravity-induced angular motion must be described differently for three distinct portions of the trajectory: the upleg, near apogee, and the downleg. The accuracy of this description is checked by comparison with numerical integrations. Finally the influence of cubic static and Magnus moments on the motion is determined and a revised point mass trajectory model is constructed. (Author)