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Wei W.,Xi'an University of Arts and Science | Zhao X.,Aircraft Strength Research Institute of China | Zhao X.,Fatigue Laboratory
International Review on Computers and Software | Year: 2012

An intelligent capacitor and inductor measuring instrument with intelligent AC parameters is developed. The key used technologies are the capacitance (inductance)-voltage conversion principle and STC89C52 MCU. The measuring data is from A/D conversion to STC89C52 MCU, and then being sent to monitor for display. Compared with the traditional measuring instrument, it has the advantages of digital display, simple operation and automatic measurement. In addition, compared with the other digital measuring instrument, the proposed instrument has the advantages of high precision and low cost. © 2012 Praise Worthy Prize S.r.l. - All rights reserved.


Guo B.-H.,Weinan Normal University | Wang Z.-Y.,Aircraft Strength Research Institute of China | Li H.-L.,Weinan Normal University
Journal of Materials Engineering and Performance | Year: 2016

Ni-SiC composite coatings were prepared on TA15 alloy by composite electroplating technology. The friction and wear behavior of TA15 alloy, and the coating were comparatively studied at both room temperature and 600 °C using GCr15 as the counterparts. The results show that the obtained coating is relatively dense and compact, and possesses higher micro-hardness than TA15 alloy. The coating has significant friction reduction effect sliding at 600 °C, but has no obvious friction reduction effect sliding at room temperature. The coating possesses superior wear resistance than TA15 alloy, evidenced by its much lower mass losses than those of TA15 alloy sliding at both room temperature and 600 °C. The TA15 alloy and the coating showed different wear mechanisms under the given sliding conditions. © 2016, ASM International.


Sun X.,Aircraft Strength Research Institute of China | Xiao Y.,Aircraft Strength Research Institute of China
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2014

Aircraft structural health monitoring (SHM) technology has experienced rapid development since its concept emerged. However, it faces the bottleneck in the applications for the aviation engineering now. The purpose of this paper is trying to explain the crux of the problem and provide a clear way for the next development. From the viewpoint of the evolution of aircraft structural integrity program and of the change of aircraft structure design philosophy, the necessity of aircraft structural health monitoring technology is analyzed. Aircraft structure design requirements and safety control system are discussed. The evidence strongly proves that the structural health monitoring technology, with great potential for improving the safety and reliability of aircraft structural level, reducing maintenance costs for future aircraft structures, will bring a revolutionary impact on aircraft structures design. The strategy of aircraft structural health monitoring is also analyzed. The latest progress and the development direction in the research of aircraft structural health monitoring are introduced. ©, 2014, AAAS Press of Chinese Society of Aeronautics and Astronautics. All right reserved.


Wu C.,Aircraft Strength Research Institute of China | Duan S.,Aircraft Strength Research Institute of China | Li X.,Aircraft Strength Research Institute of China
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | Year: 2011

It is of great significance and difficulty to ensure the stability of the composite corrugated panels in the design of aircraft wing structures. The main purpose of this paper is to establish a numerical method for the buckling of composite corrugated panel under shear loads via experiments and computations. The buckling and failure loads are examined by experiments for corrugated panels with three different wave lengths. Then, the buckling loads for eight different wave lengths are explored by the engineering method and the finite element method and are compared with experimental data. Finally the correction factors for the computational buckling loads are proposed. Results reveal that compared with experimental data, the buckling loads are greater than the experimental loads with the engineering method, while smaller with the finite element method. The results also show the longer the wave length is, the bigger the error is for the computational buckling loads. In addition, the results show that the computational buckling loads can be approximated to experimental loads by the proposed correction factors, which means that the correction factors are feasible and efficient.


Zhao H.-J.,Xi'an University of Architecture and Technology | Dong N.-J.,Aircraft Strength Research Institute of China | Liu C.,Xi'an University of Architecture and Technology | Wu M.-Z.,Xi'an University of Architecture and Technology
Gongcheng Lixue/Engineering Mechanics | Year: 2011

Based on the dynamic stability theory of an elastic system, parametric vibration equations of laced and battened lattice columns subject to a periodic load under high temperature (fire) condition were established respectively by adopting the energy method and Hamilton principle. Galerkin's method was used to convert the partial differential equations into second order ordinary differential Mathieu equations, and then the dynamic instability regions surrounded by periodic solutions were obtained. The dynamic stability problems of parametric vibration were discussed about two kinds of axial compression lattice columns. Through analyzing the influences of slenderness ratio, constant load and temperature etc. on the dynamic instability regions of axial compression lattice column, reference basis for the dynamic analysis and design on high temperature (fire) condition in structure engineering is provided.


Qin J.,Aircraft Strength Research Institute of China | Qi P.,Aircraft Strength Research Institute of China
Zhongguo Jixie Gongcheng/China Mechanical Engineering | Year: 2014

Based on sheet bending theory, the dynamic characteristics of a cantilever sheet were studied by the beam function combination method. Considering the centrifugal force, the obtained analytical solutions of frequency and mode shape might be applied to cantilever sheet. The theoretical foundation of the frequency and mode shape research on cantilever sheet were obtained. A new method of investigation of frequencies veering was presented. The obtained frequency and mode shape solutions are rather practical for the blade fatigue detection.


Zhang A.,Aircraft Strength Research Institute of China | Qiu X.,Chengdu Aircraft Design Research Institute
Yingyong Lixue Xuebao/Chinese Journal of Applied Mechanics | Year: 2015

In order to investigate the mechanism of composite failure so as to provide analysis basis for strength designing, structure failure simulation is necessary. In the process of static general failure analysis, material decay often causes severe convergence problems. Dynamic explicit analysis can well model material breakage. In this paper, the mechanical response of multi-wall box under bending load case is simulated using dynamic explicit analysis method. Panel and wall are modeled with shell element. A solid geometry is introduced to the half-thickness of the up-panel to simulate inter-laminar damage. The VUMAT subroutine is adopted to degrade material stiffness consecutively while damage occurred. It is shown that dynamic explicit analysis can well simulate the damage process of the box. Analysis results including strain, buckling load, failure load and collapse mode are in good agreement with test results. The errors of predicted buckling load and failure load are within 7%, which shows the method is satisfactory to engineering design. ©, 2015, Xi'an Jiaotong University. All right reserved.


Zhang A.,Aircraft Strength Research Institute of China | Chai Y.,Aircraft Strength Research Institute of China | Guan D.,Aircraft Strength Research Institute of China
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2012

A numerical simulation for bending-twisting coupling deformation of unsymmetrical and unbalanced composite laminates under bending load was conducted. The parameters such as laminate width and thickness were also studied. Based on the simulation results, a flexible support device for the four-point-bending test was developed. The flexible four-point-bending tests for unsymmetrical and unbalanced composite laminates were conducted. The test results show that the developed flexible four-point-bending support device does not constrain the twisting deformation of laminates while applying bending load to it. The flexible four-point-bending support device is capable of measuring bending-twisting coupling coefficient of unsymmetrical and unbalanced composite laminates.


Ye Q.,Nanjing University of Aeronautics and Astronautics | Wang R.,Nanjing University of Aeronautics and Astronautics | Chen P.,Nanjing University of Aeronautics and Astronautics | Shen Z.,Aircraft Strength Research Institute of China
Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica | Year: 2012

A method was developed to predict numerically the dent depth of composite laminates subjected to quasi-static indentation. A progressive damage analysis was conducted for composite laminates under quasi-static transverse compressive loading by using a strain based Hashin and Yeh failure criteria as well as the FEM, and a series of degraded elastic constants of the damaged zone were drawn from the numerical results. The effective elastic constants of the damaged zone of the laminates were evaluated according to Sun's explicit expression. Finally, the dent depth vs. indentation force curve was predicted based on Turner's contact theory. The numerical results indicate that the dent initiation is induced by the matrix cracking and delamination, and the transition to rapid increase in dent depth is due to the fiber breakages. The numerical results agree well with the test data for the delamination onset load, the maximum contact force and the corresponding dent depth.


Zhang A.,Aircraft Strength Research Institute of China | Xu H.,Shenyang Engine Design Research Institute | Chen H.,Aircraft Strength Research Institute of China
Jixie Qiangdu/Journal of Mechanical Strength | Year: 2016

Fastened joint repair is a main repair method for composite structure with advantages of easy disassembling, high load transferring capacity. It is important to evaluate the residual strength in repair design process. In this paper, the tensile load bearing capacity of metal riveted repair laminates were evaluated by numerical simulation using progressive failure analysis method. Laminate was modeled using shell element whereas the fasteners were modeled by beam elements. MPC technique was adopt to simulate the constraint between fastener and hole. The USDFLD subroutine was used to degrade material stiffness by multi-lever manner while damage occurred. The failure analysis results including failure mode, failure load are in good agreement with test results. The errors of predicted failure loads are with 6%, which shows the proposed method is helpful to composite fastened joint repair design. © 2016, Journal of Mechanical Strength. All right reserved.

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