Study on test dynamics method of non-full loading firing for multiple launch rocket system

Miao, Yunfei; Wang, Guoping; Rui, Xiaoting; Tu, Tianxiong

doi:10.1016/j.ymssp.2018.12.043

Cited by 11 publications

(3 citation statements)

References 7 publications

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“…After the rocket completely ejects out the muzzle, the exterior ballistic equations of rocket are adopted considering random factors such as dynamic unbalance, thrust eccentricity, mass eccentricity, and random wind. The specific dynamics equations can be found in reference (Miao et al, 2019).…”

Section: Dynamics Equations Of the Rocket-launcher Coupling Systemmentioning

confidence: 99%

Dynamics modelling and influencing factor analysis of a rocket-launcher coupling system considering uncertain parameters

Miao

Wang

Rui

et al. 2023

Journal of Vibration and Control

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Vibration characteristic is an important factor affecting the motion of rocket in the launcher and its firing performance. In this paper, a rocket-launcher coupling dynamics model is proposed by applying the transfer matrix method for multibody systems. Considering manufacturing error and nonlinear contact force, the dynamics equations of the rocket-launcher coupling system during the whole process of firing are deduced. Combined with the dynamics model and equations, a dynamics simulation system is developed with uncertain parameters. The uncertain parameter description scheme and probability sampling scheme are proposed to obtain dynamics characteristic and firing performance of the system. The relevant tests are carried out to verify simulation results. Then, the factors affecting the firing performance are discussed. In view of the analysis results, the influence weight of initial disturbance on firing precision is 85% under the condition of full-loading continuous firing, and the swing angular velocity of rocket at muzzle is the main influence factor.

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Section: Dynamics Equations Of the Rocket-launcher Coupling Systemmentioning

confidence: 99%

Dynamics modelling and influencing factor analysis of a rocket-launcher coupling system considering uncertain parameters

Miao

Wang

Rui

et al. 2023

Journal of Vibration and Control

Self Cite

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“…A number of research publications concerning the system of analogous structure MLRS (multiple launch rocket system) are available as well. In reference [9], MLRS is presented as a multibody system consisting of rigid bodies representing the vehicle and the launcher and elastic bodies in the form of elastic beams representing launching tubes. All bodies are interacting through elastic damping elements.…”

Section: Introductionmentioning

confidence: 99%

Dynamics of the Missile Launch from the Very Short-Range Mobile Firing Unit

Fedaravičius

JASAS

Gaidys

et al. 2023

Shock and Vibration

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In this article, the results of research of dynamical processes during the first stage of a missile launch from very short-range mobile firing unit (MFU) are presented. The determined laws of motion of the system’s components enabled determining characteristic motions that need to be reconstructed by the launcher simulator intended to be developed for personnel training. The half-car approach is applied for modelling the unit which consists of a vehicle and is attached to its missile launcher. The combined system is represented by a lumped-parameter model. The mathematical model is derived by applying the principle of Lagrange differential equations. Motion laws of the components of the system as its response to excitation load generated during missile launch were determined.

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“…The authors have stated the advantages of the MSTMM in several studies (Abbas et al, 2015; Liu et al, 2016; Rui et al, 2007; Tang et al, 2016). Some researchers (Miao et al, 2019) have argued that the multi-rigid-flexible body dynamics model of the MLRS, established by using the MSTMM, is verified by experiments. In order to solve the dynamics of time-varying, nonlinear and large-scale motion multibody systems, Rui et al (2005) proposed and gradually improved the discrete-time MSTMM.…”

Section: Introductionmentioning

confidence: 99%

Simulation and adaptive control of back propagation neural network proportional–integral–derivative for special launcher using new version of transfer matrix method for multibody systems

Miao

Wang

Rui

2019

Journal of Vibration and Control

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Rocket launcher system, as a special launcher placed on tactical vehicles, is a very complex mechanical system with characteristics of strong shock and vibration. In order to improve position accuracy, as well as reduce vibration, this paper creates a nonlinear dynamics model of the launcher system by using a new version of the transfer matrix method for multibody systems. The overall transfer equation of the nonlinear model is deduced. Combining with general kinematics equations of the rocket, the system launch dynamics are simulated and compared with experiments to verify the correctness of the model. On this basis, a backpropagation neural network proportional–integral–derivative adaptive control system is designed to improve servo control of the launcher. Then, the effectiveness of this method is verified by comparing with the traditional proportional–integral–derivative control method. Simulated results show that the backpropagation neural network proportional–integral–derivative control system makes the azimuth and elevation angles reach the target values smoothly and quickly, with higher accuracy. The results prove that the proposed method prominently reduces vibrations of the launcher, by adjusting the control parameters online according to the operation state of the system, presenting a better stability and robustness.

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Study on test dynamics method of non-full loading firing for multiple launch rocket system

Cited by 11 publications

References 7 publications

Dynamics modelling and influencing factor analysis of a rocket-launcher coupling system considering uncertain parameters

Dynamics modelling and influencing factor analysis of a rocket-launcher coupling system considering uncertain parameters

Dynamics of the Missile Launch from the Very Short-Range Mobile Firing Unit

Simulation and adaptive control of back propagation neural network proportional–integral–derivative for special launcher using new version of transfer matrix method for multibody systems

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