Investigation of Factors Which Contribute to Mallaunch of Free Rockets
AUBURN UNIV AL DEPT OF AEROSPACE ENGINEERING
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The simulation of the motion of a single-round launcherrocket system during launch, transition to free flight, and free flight of the rocket is considered. A simple physical model for the system is described. The model consists of an arbitrary rigid-body launcher, with 3 deg of rotational freedom, and an arbitrary rigid-body rocket, which is attached to the launcher during the spin-up if applicable, detent, and guidance phases by springs. These springs are intended to model the flexibility and damping characteristics of the rockets shoes or the interface between the rocket and the tube of a tube-type launcher. The model also includes the effects of thrust malalignment, tipoff, variable thrust, and spin torque programs and friction. Using modern vector matrix algebra, the vector equations are converted to matrix equations, amenable to digital programming and solution. Results of preliminary simulation runs made using a computer code written to perform the required numerical integration are presented and discussed.