Aircraft Strength Research Institute of China

Fengcheng, China

Aircraft Strength Research Institute of China

Fengcheng, China
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Qin J.,Aircraft Strength Research Institute of China | Wang B.,Aircraft Strength Research Institute of China
30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016 | Year: 2016

As engine speed increase, centrifugal stiffening causes a blade's natural frequencies to increase. Because the frequencies of bending modes tend to increase at a faster rate than those of torsion mode, the frequencies of bending and torsion modes are disposed to cross. Aimed at the configuration and operation characteristics of the blades of the aero engine, based on sheet bending theory, considering the centrifugal load, the frequency and mode shape of the blades are studied by the beam function combination method. Considering the different engine speed, aero elastic differential integration method for differential equation are researched. The theoretical foundation of the frequency and mode shape research on cantilever sheet are obtained. The new methods of investigation on frequencies and mode shape have been studied. The given frequency and mode shape solutions are rather practical for the blade fatigue detecting, what's more, the theoretical base of flutter designing for engine blade are supplied.


Zhao H.,Aircraft Strength Research Institute of China | Duan S.,Aircraft Strength Research Institute of China | Feng J.,Aircraft Strength Research Institute of China
30th Congress of the International Council of the Aeronautical Sciences, ICAS 2016 | Year: 2016

A proportion-integration-differentiation (PID) controller is a generic control loop feedback mechanism widely used in multi-channel aircraft structural fatigue test. The PID parameter is obtained by test setup method in which PID is tuned after the test setup is actually performed, so that the tuning period becomes overlong. And the dynamic characteristic of mechanical and hydraulic equipment isn't considered as a crucial factor to decrease working capability of loading equipment. at the same time, there is coupling effect among channels, which lower control accuracy. For this, based on multi-channel fatigue test of cantilever beam, the coupling mathematics model of testing system is presented and linearized reasonably. The basic procedure of a multi-channel fatigue test is analyzed systematically. The PID parameter of every channel is simulated by stability margin and bandwidth analysis. The dynamic characteristic of hydraulic equipment and test article are analyzed. Finally, a double channel fatigue test of cantilever beam is implemented. The results of simulation and test show that the new method is effective. This method not only has the ability to predict PID parameter rapidly and the dynamic characteristic of test equipment, but it can also reduce effectively the control errors.


Tang H.,Beihang University | Chang S.,Beihang University | Cheng Z.,Aircraft Strength Research Institute of China
23rd AIAA Computational Fluid Dynamics Conference, 2017 | Year: 2017

Based on the requirements of simulating the flow around spray bar installed in ground based icing test facilities, the accuracy of three Detached Eddy Simulation (DES) turbulence models, including Spalart-Allmaras DES, Realizable k-ε DES, and Shear Stress Transport k-ω DES, were examined through the comparison and analysis of instantaneous flow characteristics and flow statistic parameters obtained from a three-dimensional subcritical flow around circular cylinder at ReD=3900. It is found that: (a) from the point of instantaneous flow characterization, the k-ω RANS (Reynolds Averaged Navier-Stokes) branch also has remarkable influence on the accuracy of SST k-ω DES except k-ε RANS branch, (b) from the point of error range of flow statistic parameters, the size of recirculation region Lrec and mimimum streamwise velocity umin are the key parameters which can reflect the accuracy of numerical simulation on flow around circular cylinder to some extend, (c) compared comprehensively, the predicted values from SST k-ω DES among three DES models give a relatively closer agreement with experimental data, which indicate that it has the potential of applying to the calculation of wake turbulence generated from spray bar system installed in ground based icing test facilities. © 2017, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.


Li Y.,Aircraft Strength Research Institute of China | Dong D.,Aircraft Strength Research Institute of China | Gong Y.,Aircraft Strength Research Institute of China
Jixie Qiangdu/Journal of Mechanical Strength | Year: 2017

First of all, stress analysis of lug under different loading angles was carried out. For the fatigue life analysis of lug under tension-compression loads, the compression load was treated equivalently, and the effective equivalent load factor λ was obtained. The fatigue load spectrum was equivalent to Pmax~λPmin, and then the fatigue life of lug structure was obtained by the Detail Fatigue Rating (DFR) method. Finally, the method was proved by the fatigue test of lug in 45° angles load, which proves that the method is practical in engineering. © 2017, Editorial Department of JOURNAL OF MECHANICAL STRENGTH. All right reserved.


Yang J.-B.,Aircraft Strength Research Institute of China | Ren J.,Aircraft Strength Research Institute of China | Xue Y.-F.,Aircraft Strength Research Institute of China
Proceedings of the 29th Chinese Control and Decision Conference, CCDC 2017 | Year: 2017

Traditional manufacturing processes of 3D force platform (three-dimensional force platform) are purchasing of three dimensional force sensor, calibrating of sensor in specialized agencies and building up with platform table and base. However, due to processing accuracy and installation error, the method of calibration before building up cannot guarantee the global accuracy of 3D force platform, and it is difficult to meet the requirements in practice. An improved method is proposed in this article that calibrating force sensors first, then dynamic monitoring the installation process, and global calibrating the 3D platform, verifying the calibration results at last. This article design a global calibrating system based on the global calibrating method which achieve the function of data extraction, classification, data evaluation and parameter optimization. The 3D force platform is calibrated again using the optimized parameters, and the result shows that the optimized calibration results are in coincide with the calculated results. At the same time, the method of sensitivity optimization based on global calibrating avoids the low efficiency caused by trial-and-error method and repeatedly loaded, and then improves the calibration efficiency and accuracy. © 2017 IEEE.


Yang J.,Aircraft Strength Research Institute of China | Ren J.,Aircraft Strength Research Institute of China
Yingyong Lixue Xuebao/Chinese Journal of Applied Mechanics | Year: 2017

It is known that comparing the energy between released energy and measured energy in the landing gear drop test can verify whether the measuring system works properly or not. However, the traditional method to calculate the released energy neglected a fact that the supporting elastic displacement and inelastic displacement is not inconsistent, which causes some errors in the calculation. The current study makes adjustment to the method of calculating released energy and compares the errors of landing gears with different weight in the traditional method and correction method. Results obtained show that the difference before and after the correction method is about 0.15% to 1.28% and there is great difference between the error of micro landing gears in the traditional method and correction method. Meanwhile, considering the waste of subsidence velocity caused by the delay of released lock and friction between the impeller and pillar, the subsidence velocity in the landing gear drop test is monitored and an experiment method for monitoring and correcting subsidence velocity is proposed. The comparison of the errors between the test by traditional method and proposed method shows that the method can effectively reduce the error and improve the accuracy. © 2017, Editorial Department of CJAM. All right 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.


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.


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.

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