Dynamics design for complex mechanical systems has become an important research field and development direction at present, capturing attentions of an increasing number of engineers and scientists worldwide. Based on many advantages of the transfer matrix method for multibody system in studying multibody system dynamics, a design problem of a multiple launch rocket system is solved in this paper. Particular attention is addressed to model actions of the exhaust flow on the multiple rocket launcher, which are associated with firing order and firing intervals of rockets. Combined with a genetic algorithm, firing order and firing intervals are optimized to achieve optimum impact point dispersion reduction. The results of numerical simulation and verification tests show good agreement, while the dispersion characteristics of rockets have been improved in a low-cost way.

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Abstract. Transfer matrix method for multibody system (MSTMM) is a new and efficient method for multibody system dynamics (MSD) developed in recent 20 years. Based on many advantages of MSTMM in studying MSD, the rapid and accurate computation problem of vibration characteristics of a complex multiple launch rocket system (MLRS) are solved in this paper. The dynamics model, the transfer equations of elements, the overall transfer equation and the eigenfrequency equation are established. The results got by MSTMM were validated by modal tests, and compared with ordinary dynamics method, the computational speed has been increased 65 times.