Calculation techniques for mallaunch of spin-stabilized free rocket due to in-tube rocket bending

Rocket flexibility is modelled for the launch phase. The model accounts for bearing clearances, a variable stiffness motor section and allows for the 3-D motion of a rigid warhead. The phenomenon of whirling is investigated and the bent configuration of the rocket is calculated for synchronous whirling. The resulting mallaunch rates agree with reported range data. A computer program is presented which predicts the mallaunch rate for ANSSR II. Requirements for input data are stated and output is defined. A modification to account for inertia forces acting on the bent rocket is developed and expressions for calculating bearing reactions are given. Listings for both the basic and modified programs are given in appendices and some results of the program are presented.