scholarly journals Semi-Analytical Finite Strip Transfer Matrix Method for Buckling Analysis of Rectangular Thin Plates

2015 ◽  
Vol 2015 ◽  
pp. 1-11 ◽  
Author(s):  
Li-Ke Yao ◽  
Bin He ◽  
Yu Zhang ◽  
Wei Zhou

Plates and shells are main components of modern engineering structures, whose buckling analysis has been focused by researchers. In this investigation, rectangular thin plates with loaded edges simply supported can be discretized by semi-analytical finite strip technology. Then the control equations of the strip elements of the buckling plate will be rewritten as the transfer equations by transfer matrix method. A new approach, namely semi-analytical Finite Strip Transfer Matrix Method, is developed for the buckling analysis of plates. This method requires no global stiffness matrix of the system, reduces the system matrix order, and improves the computational efficiency. Comparing with some theoretical results and FEM’s results of two illustrations (the plates and the ribbed plates) under six boundary conditions, the method is proved to be reliable and effective.

Author(s):  
Qicheng Zha ◽  
Xiaoting Rui ◽  
Feifei Liu ◽  
Hailong Yu ◽  
Jianshu Zhang

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.


2014 ◽  
Vol 530-531 ◽  
pp. 1043-1048 ◽  
Author(s):  
Hossam Hendy ◽  
Xiao Ting Rui ◽  
Qin Bo Zhou ◽  
Fu Feng Yang ◽  
Mostafa Khalil

Many real systems such as inertial measurement unit (IMU) in vibration environment, avionic systems in flight tests, half car dynamic model in rid comfortable test and suspension design…etc. can be expressed as Two-inputs-two-outputs (TITO) system for more realistic analysis than single-input-single-output system (SISO); but with more additional complexities. Comparing Transfer Matrix Method for multibody systems (MSTMM) with classical dynamic methods has preferences of modeling flexibility, low order of system matrix, and high computational efficiency, without necessity of deriving the system’s global dynamic equations. The need of combining control strategies with MSTMM becomes an issue of paramount importance due to that a lot of systems are considered as multibody systems, some need control to obtain higher accuracies requirement, vibration isolation treatment, …etc. As a rule of thumb the concept of designing vibration isolator in one field can be applied in many other fields. In this article a generalized TITO model is analyzed using MSTMM to deal with the vibration problem via an active isolator for both vertical translation and pitch responses. Active isolation is applied via Proportional-Integral- Derivative (PID) controller to prove the capability of formulating a relationship between MSTMM and well-known control methodologies to mitigate vibration effects. For verification purpose the analyzed model is verified using data for half car model and standard formulae for road models input excitation test. The achieved results declared that MSTMM can be combined with control techniques without need of special treatments or preconditions for different models with the advantages of MSTMM. This article allows wider developed control applications to use MSTMM simple application for more complex systems models. Dilatation in studying controlled systems using MSTMM provides a possibility for incoming control applications because of the good dealing of MSTMM with the increased complexities of multi-rigid-flexible-body problems.


2010 ◽  
Vol 78 (2) ◽  
Author(s):  
Bao Rong ◽  
Xiaoting Rui ◽  
Guoping Wang

The speedy computation of eigenvalue problems is the key point in structure dynamics. In this paper, by combining transfer matrix method and finite element method, the modified finite element-transfer matrix method and its algorithm for eigenvalue problems are presented. By using this method, the speedy computation of eigenvalue problem of flexible structures can be realized, and the repeated eignvalue problem can be solved simply and conveniently. This method has the low order of system matrix, high computational efficiency, and stability. Formulations of this method, as well as some numerical examples, are given to validate the method.


2010 ◽  
Vol 163-167 ◽  
pp. 279-282
Author(s):  
Jian Peng Sun ◽  
Qing Ning Li

Arch bridge as well as arch frame of building is òne kind of plane-curved-bar system of bearing pressure.When the load of arch carrying reaches some value, the arch will lost the balance stability. Based on the theory of precise transfer matrix method and differential equation of circular arch in plane, a new method for plane-buckling analysis of circular arch under uniform load is derived, by which the critical load of circular arch with two hinge supports is calculated. Compared with the theoretical solution, they anastomosed each other well, that shows the method is right and effective.


Author(s):  
Bao Rong ◽  
Xiaoting Rui ◽  
Hailong Yu ◽  
Guoping Wang

Efficient, precise dynamic analysis for a complex spacecraft has become a research focus in the field of spacecraft dynamics. In this paper, by combining discrete time transfer matrix method of multibody system and finite element method, the transfer equations and transfer matrices of typical elements of spacecrafts are developed, and a high-efficient dynamic modeling method is developed for high-speed computation of spacecraft dynamics. Compared with ordinary dynamic methods, the proposed method does not need the global dynamic equations of system and has the low order of system matrix, high computational efficiency. This method has more advantages for dynamic modeling and real-time control of complex spacecrafts. Formulations of the proposed method as well as a numerical example of a spacecraft with a flexible solar panel are given to validate the method.


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