Active Vibration Control Design Method Based on Transfer Matrix Method for Multibody Systems

Zhang

Int Journal of Mech Sys Dyn

et al. 2022

Self Cite

116

The multibody system transfer matrix method (MSTMM), a novel dynamics approach developed during the past three decades, has several advantages compared to conventional dynamics methods. Some of these advantages include avoiding global dynamics equations with a system inertia matrix, utilizing low-order matrices independent of system degree of freedom, high computational speed, and simplicity of computer implementation. MSTMM has been widely used in computer modeling, simulations, and performance evaluation of approximately 150 different complex mechanical systems. In this paper, the following aspects regarding MSTMM are reviewed: basic theory, algorithms, simulation and design software, and applications.Future research directions and generalization to more applications in various fields of science, technology, and engineering are discussed.

Section: Controlled Mstmmmentioning

confidence: 99%

Multibody system transfer matrix method: The past, the present, and the future

Zhang

Int Journal of Mech Sys Dyn

et al. 2022

Self Cite

116

“…Let a new state variable be ξ � t 0 e dt [24], then an augmented system is formed along with (21) given as…”

Section: The Design Of the Vibration Controlmentioning

confidence: 99%

“…It has advantages such as no need for global dynamic equations of the system, the lower order of system matrix, high programming, high precision, and suitable for modeling and controller designing for complex multibody systems. Wang et al [21] presented a robust controller using the independent modal space control method for active vibration control of general linear multibody. Chen et al [22] studied the model of the Stewart parallel mechanism and employed LQR control.…”

Section: Introductionmentioning

confidence: 99%

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

et al. 2020

Shock and Vibration

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Multiple Launch Rocket System (MLRS) has been widely used in recent years; vibration control in launching process is an effective way to improve its dispersion characteristics. In this paper, a novel vibration control system applying Annularly Arranged Thrusters (AAT) for MLRS in launching process is introduced and the prototype of the proposed system is built. The dynamic model of the MLRS with the AAT is established based on the Transfer Matrix Method for Multibody Systems (MSTMM). The LQR-PID control law and the management for the AAT are presented. The simulation and experiment of the proposed system are carried out and analyzed. The results show that the vibration of MLRS is effectively attenuated by the proposed control system. The study in this paper provides a new idea to improve the dispersion characteristic by reducing the vibration of MLRS in launching process.

“…[32][33][34][35] The MSTMM has been successfully applied to the analysis and evaluation of vibration characteristics and dynamics response of various mechanical systems. [36][37][38] However, the involved MSTMMs for the above studies on the MLRS dynamics are linear with the hypothesis of local linearization, which require a small enough calculation step to ensure calculation accuracy and stability of the MLRS dynamics.…”

Section: Introductionmentioning

confidence: 99%

On modeling and dynamics of a multiple launch rocket system

Proceedings of the Institution of Mechanical Engineers, Part G:

et al. 2021

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Dynamics analysis is currently a key technique to fully understand the dynamic characteristics of sophisticated mechanical systems because it is a prerequisite for dynamic design and control studies. In this study, a dynamics analysis problem for a multiple launch rocket system (MLRS) is developed. We particularly focus on the deductions of equations governing the motion of the MLRS without rockets by using a transfer matrix method for multibody systems and the motion of rockets via the Newton–Euler method. By combining the two equations, the differential equations of the MLRS are obtained. The complete process of the rockets’ ignition, movement in the barrels, airborne flight, and landing is numerically simulated via the Monte Carlo stochastic method. An experiment is implemented to validate the proposed model and the corresponding numerical results.