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Guo Q.,Dalian University of Technology | Guo X.,Dalian University of Technology | Fan J.,Aircraft Strength Research Institute | Syed R.,Dalian University of Technology | Wu C.,Dalian University of Technology
International Journal of Fatigue | Year: 2015

Abstract The present paper, firstly, establishes a calculation model of intrinsic dissipation, based on the double exponential regression for the one-dimensional distribution of specimen surface temperature variation. Then, an energy method is proposed for rapid evaluation of high-cycle fatigue parameters (i.e., fatigue limit and S-N curve). The energy method takes intrinsic dissipation as the fatigue damage indicator, and eliminates the interference of internal friction causing no damage on fatigue life evaluation. An experimental research on FV520B stainless steel was performed, in order to verify the feasibility and validity of the energy method, as well as the calculation model. © 2015 Elsevier Ltd. Source


Wei W.,Xian University of Arts and Science | Zhao X.Y.,Aircraft Strength Research Institute
Advanced Materials Research | Year: 2013

The point-to-point swing arm test is very important for large arms which have swing arm movement. Traditional point-to-point swing arm controller is relay control mode. The mode has many shortcomings, such as big volume, high power consumption, low stability, and so on. An intelligent point-to-point swing arm controller, using MCU as the control core, was designed for this reason. It was mainly composed of switch signal detecting module, solenoid valve drive module, USB storage interface module and MCU control module. According to the requirements of test, the controller was able to detect the valid signal of limit switch and control commutation operation of solenoid valve, meanwhile it could record the movement time between one point and another point, the time the arm swayed and the moment information, and these above information would be stored in USB memory. It has some advantages of small size, low power consumption, high stability and flexible functions. © (2013) Trans Tech Publications, Switzerland. Source


Zhou K.,Nanjing University of Aeronautics and Astronautics | Chen P.,Nanjing University of Aeronautics and Astronautics | Chai Y.,Aircraft Strength Research Institute
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2012

In an aircraft structure, it is often necessary to runout some of the stiffeners to satisfy detailed design requirements. Depending on the structural design, stiffeners for a wing structure may terminate at a chord-wise splice, at the forward or rear spar, at a rib, or at a structural discontinuity, such as an access hole. But an abrupt stiffener termination can cause highly localized bending gradients due to stiffness discontinuities and load-path centricities. In this paper, both experiment tests and FEM models relating to three different stiffener runout specimens were presented and the failure modes of these specimens were discussed in detail. In tension, the failure is deduced by peel stress and interlaminar shear stress. In compression, the failure is deduced by interlaminar shear stress only. Source


Kong B.,Nanjing University of Aeronautics and Astronautics | Ye Q.,Nanjing University of Aeronautics and Astronautics | Chen P.,Nanjing University of Aeronautics and Astronautics | Chai Y.,Aircraft Strength Research Institute
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2010

The post-buckling induced failure process was simulated by using the cohesive element in the commercial software ABAQUS. The internal forces on the flange/skin interface were extracted from FEM results, and then their features were studied. The flange thickness was considered as a parameter to build a parameterized model for studying the effect of stiffness ratios of the flange to the skin on the interface debonding. The relationship among each component of the internal forces was also investigated. Failure criteria and failure envelops were developed for the flange/skin interface debonding. Finally the design parameters of the thickness ratio and the stiffness ratio between the flange and the skin were suggested for the design. Source


Kong B.,Nanjing University of Aeronautics and Astronautics | Ye Q.,Nanjing University of Aeronautics and Astronautics | Chen P.,Nanjing University of Aeronautics and Astronautics | Chai Y.,Aircraft Strength Research Institute
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2010

The load transfer mechanisms at the post-buckling stage were studied for an integrated stiffened composite panel subjected to uniaxial compression. An FEM model was created for the panel by using the commercial software ABAQUS. The post-buckling process of the panel was simulated under uniaxial compression. The internal resultant forces and the load transfer mechanisms were discussed in detail at different stages (i. e., the local and global post-buckling). The distributions for resultant forces and moments at nodal and anti-nodal lines were obtained. The simulations agree well with experimental data. Finally it is indicated that the nodal and anti-nodal lines are possibly the first debonding locations of the flange/skin interface at the post-buckling stage and the forces crucial for failure are identified as Mxy and My. Source

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