Vibration Controller Optimization Design for Multiple Launch Rocket System With Pulse Thrusters Based on Transfer Matrix Method for Multibody Systems

Abstract

Vibration control in launching process is an effective way to improve the dispersion characteristics of Multiple Launch Rocket System (MLRS). In this paper, a novel methodology for MLRS vibration controller design with the application of pulse thrusters and its parameters optimization is introduced. Based on the Transfer Matrix Method for Multibody Systems (MSTMM), the dynamic model of the controlled MLRS with pulse thrusters is established and the launch dynamic simulation system of controlled MLRS is developed. To suppress vibrations of the elevation part using the annularly arranged pulse thrusters, a management scheme based on impulse equivalence approach is presented to adapt the continuous force generated by the PID control law to impulse force. Controller optimization is achieved coupling Particle Swarm Optimization-Genetic Algorithm (PSO-GA) with the established simulation system of controlled MLRS. Finally, the simulation results verify the effectiveness of the proposed controller and demonstrate the engineering practicability value of this methodology.

A Novel Vibration Control System Applying Annularly Arranged Thrusters for Multiple Launch Rocket System in Launching Process

“…Zhan et al [15] took a brief attempt to apply the thrusters to control the vibration of MLRS caused by the jet force, only considering the single shot condition. Gu et al [16] discussed the vibration control of MLRS with thrusters in launching process under simple simulated conditions. e Transfer Matrix Method for Multibody Systems (MSTMM) [17][18][19][20] is a new method for multibody system dynamics in recent 20 years, which studies multibody system dynamics through the transfer relationship between the state vectors in multibody system.…”