Modeling and verification of firing dynamics of a multiple launch rocket system

Abstract

Multiple rocket launcher systems have great strategic importance in today's defense systems. Therefore, the development and the quality of these strategically important systems are among the priorities of defense industry companies. The quality of the multiple launcher rocket systems is twofold. 1) Firing the ammunition with the appropriate time interval within the correct trajectories, 2) leaving the firing location quickly after completing the mission. In this study, stabilizer support legs were not used to increase vehicle mobility. The dynamics of a multiple rocket launch vehicle are modeled using rigid bodies and elastic elements with eight degrees of freedom in total. Since a 90-degree firing was performed relative to the longitudinal direction, half-vehicle modeling has been developed in the lateral direction of the vehicle. Firing tests had been executed without a support leg over a Multiple Launch Rocket System. During the firing, measurements were taken with a 3-axis accelerometer and gyroscope over the elevation and azimuth platforms. In addition, LPTs in vertical and lateral directions are placed on the superstructure. With these LPTs, the data obtained from the 3-axis accelerometer and gyroscope on the azimuth platform have been confirmed. The model parameters, stiffness/damping parameters of tires, suspensions, and hydraulic actuator, have been obtained using initial test results with MATLAB (TM) Parameter Estimator toolbox. The model's accuracy has been verified with a second firing test result.