Chinese Journal of Theoretical and Applied Mechani ›› 2010, Vol. 42 ›› Issue (3): 583-590.DOI: 10.6052/0459-1879-2010-3-2009-431

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Vibration control for launcher of multiple launch rocket system based on transfer matrix method of multibody system

Zhihuan Zhan Xiaoting Rui Guoping Wang Fufeng Yang Junyi He   

  1. Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China Institute of Launch Dynamics, Nanjing University of Science and Technology, Nanjing 210094, China
  • Received:2009-07-13 Revised:2009-10-23 Online:2010-05-18 Published:2010-05-18

Abstract: High fire accuracy is one of performance goals of Multiple Launch Rocket System (MLRS). One of effective methods to improve the fire accuracy with low cost is the vibration control of launcher in MLRS. In this paper, transfer matrix method of multibody system (MSTMM) is used to develop dynamical model of MLRS. Active vibration control law is designed for pulse thruster using quadratic performance index as cost function. In the law, the pulse thruster is taken as an actuator for launcher vibration control. Vibration control system of MLRS launcher is established under the impact of gas jet from rocket motor. A numerical simulation example on vibration controlling of MLRS launcher is given to obtain optimum amplitude of pulse control force and working times of pulse thruster. Numerical results of controlled and uncontrolled vibration response of launcher show that control law in this paper is efficient to reduce launcher vibration. Furthermore, the present method in this paper is easy to realize in practical engineering, and it is important to be used to control launcher vibration so as to improve fire accuracy of MLRS.

Key words: multiple launch rocket system, transfer matrix method of multibody system, vibration control, pulse thruster