Large amplitude oscillations of cruciform tailed missiles. Part 2: Catastrophic yaw avoidance

摘要

In Part I, the large-angle, roll orientation-dependent and gravity-dependent cubic equations of motion of a spinning cruciform missile were presented. The equilibrium points and their stability characteristics were found numerically and the gravity effects were shown to be negligible in the majority of cases up to large angles of attack. This part shows that, depending on the case, the cubic aerodynamic model or even a simple linear model can be conservatively used to obtain the expression of the minimum fin cant and steady-state spin that assure the low amplitude of the single equilibrium point.