PANELS

作品数：129被引量：158H指数：5
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Experimental and numerical studies on buckling and post-buckling behavior of T-stiffened variable stiffness panels
《Chinese Journal of Aeronautics》2024年第10期459-470,共12页Yan HUANG Yahui ZHANG Bin KONG Jiefei GU Zhe WANG Puhui CHEN 
Supported by the National Natural Science Foundation of China(No.11902124).
Currently,experimental research on variable stiffness design mainly focuses on laminates.To ensure adaptability in practical application,it is imperative to conduct a systematic study on stiffened variable stiffness s...
关键词：Variable stiffness composite BUCKLING POST-BUCKLING Finite element method Stiffened panels 
Collaborative force and shape control for large composite fuselage panels assembly被引量：2
《Chinese Journal of Aeronautics》2023年第7期213-225,共13页Zhanghao WANG Dongsheng LI Liheng SHEN Yi SUI Yunong ZHAI 
supported by National Natural Science Foundation of China(No.52105502);Fund of National Engineering and Research Center for Commercial Aircraft Manufacturing(Nos.COMAC-SFGS-2019-263 and COMAC-SFGS-2019-3731);the Fundamental Research Funds for the Central Universities(No.3042021601).
This study proposed a force and shape collaborative control method that combined method of influence coefficients(MIC)and the elitist nondominated sorting genetic algorithm(NSGA-II)to reduce the shape deviation caused...
关键词：ASSEMBLY Collaborative force and shape control Composite panel Hexapod parallel robots Method of influence coefficients 
Suppressing nonlinear aeroelastic response of laminated composite panels in supersonic airflows using a nonlinear energy sink被引量：1
《Chinese Journal of Aeronautics》2021年第2期376-385,共10页Jian ZHOU Minglong XU Zhichun YANG Yingsong GU 
co-supported by the National Natural Science Foundation of China (Nos. 11702204, 11872050 and11672240);the Chinese Postdoctoral Science Foundation(No. 2019M653585);the Natural Science Basic Research Plan in Shanxi Province of China (No. 2018JQ1041)。
This paper proposes using a Nonlinear Energy Sink(NES) to suppress the nonlinear aeroelastic response of laminated composite panels in supersonic airflows. Relevant aeroelastic equations are established using Hamilton...
关键词：Aeroelasticity Laminated composite panel Nonlinear dynamics Nonlinear energy sink Panel flutter Passive suppression 
A model-based prognostics method for fatigue crack growth in fuselage panels被引量：3
《Chinese Journal of Aeronautics》2019年第2期396-408,共13页Yiwei WANG Christian GOGU Nicolas BINAUD Christian BES Jian FU 
partially funded by the National Natural Science Foundation of China (No.51805262)
This paper proposes a model-based prognostics method that couples the Extended Kalman Filter(EKF) and a new developed linearization method. The proposed prognostics method is developed in the context of fatigue crack ...
关键词：Aircraft FUSELAGE PANELS Extended Kalman filter Fatigue crack propagation LINEARIZATION METHOD MODEL-BASED PROGNOSTICS 
Aeroelastic effect on aerothermoacoustic response of metallic panels in supersonic flow被引量：3
《Chinese Journal of Aeronautics》2016年第6期1635-1648,共14页Wang Xiaochen Yang Zhichun Zhou Jian Hu Wei 
supported by the National Natural Science Foundation of China (No. 11472216);support from China Scholarship Council (CSC);German Aerospace Center (DLR)
A finite element formulation is presented for the analysis of the aeroelastic effect on the aerothermoacoustic response of metallic panels in supersonic flow. The first-order shear deformation theory(FSDT) and the von...
关键词：Aeroelastic effect Aerothermoacoustic response Metallic panels Nonlinear frequencyamplitude response Sonic fatigue 
Investigations on damage resistance of carbon fiber composite panels toughened using veils被引量：2
《Chinese Journal of Aeronautics》2013年第3期807-813,共7页Zhu Lingang 
This research focused on how to improve damage resistance of carbon fiber laminates. It was carried out at Cranfield University Composites Centre, Milton Keynes, UK as an MSc by research thesis project. A series of lo...
关键词：CAI Carbon fiber COMPOSITE Compression Damage resistance Impact Vacuum infusion VEIL 
Solution to Boundary-value Problems in Fabrication of High-precision Reflector Panels
《Chinese Journal of Aeronautics》2009年第1期97-104,共8页郝长岭 周贤宾 李小强 
National Natural Science Foundation of China (10477001, 60673056)
The fabrication of high-precision panels for the compact antenna test range (CATR) with a sandwich construction of two aluminum skin-plates and one aluminum middle plate,which are bonded to two aluminum honeycomb core...
关键词：boundary-value problems Fourier series finite element method numerical methods weighted residual method 
Residual Strength of Stiffened LY12CZ Aluminum Alloy Panels with Widespread Fatigue Damage被引量：2
《Chinese Journal of Aeronautics》2008年第1期48-52,共5页李仲 葛森 吕国志 陈莉 丁惠良 
Experimental and analytical investigations on the residual strength of the stiffened LY12CZ aluminum alloy panels with widespread fatigue damage （WFD） are conducted. Nine stiffened LY12CZ aluminum alloy panels with ...
关键词：stiffened panel widespread fatigue damage （WFD） residual strength stress intensity factor plastic zone linkup criterion 
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