Test Dynamics Method of Non-Full Loading Firing for Multiple Launch Rocket System Using Transfer Matrix Method for Multibody Systems

2018 ◽  
Author(s):  
Yunfei Miao ◽  
Guoping Wang ◽  
Xiaoting Rui ◽  
Tianxiong Tu ◽  
Lilin Gu
Keyword(s):  
Transfer Matrix Method ◽  
Matrix Method ◽  
Multibody Systems ◽  
Simulation System ◽  
Test Method ◽  
Firing Test ◽  
Rocket System ◽  
Full Loading ◽  
Dynamics Method ◽  
Precision Test

This paper studies test dynamics method of non-full loading firing for multiple launch rocket system (MLRS) and provides a new test method for reducing rocket consumption in MLRS firing precision test. Based on the theories of launch dynamics and Rui method, namely the transfer matrix method for multibody systems (MSTMM), launch dynamics model, characteristic equations and dynamics response equations of MLRS are established. The launch and flight dynamic simulation system for MLRS is developed combining the Monte Carlo simulation technology. The simulated results of vibration characteristics, rocket initial disturbance, and firing precision are verified by modal test, pulse thrust test and firing test, which show the simulation system can more accurately reflect the dynamic characteristics of the actual system and its dynamics computation has sufficient accuracy. The relationship between the initial state of MLRS and the mean value and median error of the impact points are established. Based on the idea of equal initial disturbance, non-full loading firing test dynamics method is presented for reducing the rocket consumption in firing precision test, by optimizing the loading position, firing orders and firing intervals of the rockets. For a practical MLRS, a seven-shot test scheme is designed and tested. The experimental results show that the amount of the rockets in firing precision test is reduce by 61% compared with the conventional test method, which saves a lot of testing costs.

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

2018 ◽  
Author(s):  
Lilin Gu ◽  
Xiaoting Rui ◽  
Guoping Wang ◽  
Bo Li ◽  
Tianxiong Tu
Keyword(s):  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Multibody Systems ◽  
Optimization Design ◽  
Controller Design ◽  
Simulation System ◽  
Parameters Optimization ◽  
Management Scheme ◽  
Rocket System

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.

Study on Response of Launch Vehicle Under Ground Wind Loads Based on Transfer Matrix Method for Multibody Systems

2018 ◽  
Author(s):  
Xun Wang ◽  
Xiaoting Rui ◽  
Fufeng Yang
Keyword(s):  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Transfer Equation ◽  
Matrix Method ◽  
Multibody Systems ◽  
Launch Vehicle ◽  
Wind Loads ◽  
Dynamics Response ◽  
Domain Dynamics ◽  
Dynamics Method

In order to study dynamics response of a launch vehicle under ground wind loads, the dynamics model of a launch vehicle erected on the pad is developed based on transfer matrix method for multibody systems and the theory of structural wind engineering. The overall transfer equation, overall transfer matrix, and characteristics equation of the system are deduced based on the automatic deduction theorem of overall transfer equation of multibody system. The equation governing the motion of the launch vehicle is obtained by using the orthogonality of augmented eigenvector. The vibration characteristics, and frequency domain and time domain dynamics response under ground wind loads of the launch vehicle are simulated. The simulation results show that the eigenfrequencies obtained by the proposed method and ordinary dynamics method have good agreements. The paper provides an effective approach to compute the dynamics response of the launch vehicle under ground wind loads.

Application of the Transfer Matrix Method for Multibody Systems in Dynamics of the Self-Propelled Artillery

2018 ◽  
Author(s):  
Qicheng Zha ◽  
Xiaoting Rui ◽  
Feifei Liu ◽  
Hailong Yu ◽  
Jianshu Zhang
Keyword(s):  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Multibody Systems ◽  
The Self ◽  
System Matrix ◽  
Topological Graph ◽  
Fast Calculation ◽  
Transfer Equations ◽  
Model Transfer

Transfer Matrix Method for Multibody Systems (MSTMM) has the advantages of no need to establish the global system dynamics equations, low order of the system matrix, high programming, and fast calculation speed compared to the ordinary dynamics methods. In this paper, the topological graph of the dynamics model, transfer equations, transfer matrix of overall system and the simulation program of dynamics of the self-propelled artillery system are established by using the new version of the transfer matrix method for multibody systems and the automatic deduction theorem of overall transfer equation of systems. Realize the rapid calculation of the deviation of the pitch angle and the revolution angles of the turret versus time in the self-propelled artillery. It provides a theoretical basis and simulation means for the dynamics analysis of the self-propelled artillery.

scholarly journals Controller Parameters Tuning Based on Transfer Matrix Method for Multibody Systems

2014 ◽  
Vol 6 ◽  
pp. 957684 ◽  
Author(s):  
Hossam Hendy ◽  
Xiaoting Rui ◽  
Qinbo Zhou ◽  
Mostafa Khalil
Keyword(s):  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Matrix Method ◽  
Multibody Systems ◽  
Parameters Tuning

Riccati Transfer Equations for Linear Multibody Systems with Indeterminate In-Span Conditions

2019 ◽  
Vol 86 (6) ◽  
Author(s):  
Jianshu Zhang ◽  
Xiaoting Rui ◽  
Junjie Gu
Keyword(s):  
Transfer Matrix ◽  
Transfer Matrix Method ◽  
Transfer Equation ◽  
Matrix Method ◽  
Multibody Systems ◽  
Internal Force ◽  
State Variables ◽  
Transfer Matrices ◽  
Transfer Equations ◽  
Mechanical Elements

The transfer matrix method for linear multibody systems is capable of providing precise solutions for the dynamics of various mechanical systems, but it may also suffer from numerical instability in some cases, where serial chains with a large number of mechanical elements are involved or high-frequency harmonic responses are computed. Combining such a transfer strategy with the Riccati transformation yields the Riccati transfer matrix method (RTMM), which can help improve the numerical stability. According to the existing method, the conventional transfer matrices of all the mechanical elements should be obtained first; in other words, the existence of conventional transfer matrices is a prerequisite for the application of the RTMM. Thus, it seems that the RTMM is incapable of performing the dynamics analysis of linear multibody systems with indeterminate in-span conditions due to the nonexistence of the corresponding conventional transfer matrices. Observe that, for any state variables with indeterminate input–output relationships, the complementary state variables (the complementary state variable of a displacement is the corresponding internal force and vice versa) are identically equal to zero, and that the dimension of the Riccati transfer equation is only half of that of the conventional transfer equation. It reveals that the Riccati transfer equations for the connection points associated with indeterminate in-span conditions can be formulated directly, and that there is no need to rely on the conventional transfer equation. Two numerical examples are simulated and the computational results are compared with those obtained by the finite element method, which verifies the proposed method.

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