Launch Tube and Rocket Interaction for an Aerodynamically Neutral Spin- Stabilized Free Rocket
Technical rept. 15 Oct 1972-15 Oct 1973
AUBURN UNIV AL DEPT OF MECHANICAL ENGINEERING
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A linearized model is developed for the dynamics of a spinning, unbalanced, rigid rocket during the tip-off phase of launch. Mallaunch rates for the rocket are obtained for the short time interval from tip-off to end of guidance. The results show that tip-off should not be a major cause of mallaunch for very high spin rates and short tip-off times. 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. Dynamical equations of motion are developed for a multitube launcher assembly for a spin-stabilized rocket. A parametric study is performed to minimize the mallaunch rates affecting missile flight. The results show that prudent selection of specific structural parameters can minimize mallaunch rates.