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Predictions of thermal buckling strengths of hypersonic aircraft sandwich panels using minimum potential energy and finite element methods

机译：用最小势能和有限元方法预测高超声速飞机夹芯板的热屈曲强度

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Thermal buckling characteristics of hypersonic aircraft sandwich panels of various aspect ratios were investigated. The panel is fastened at its four edges to the substructures under four different edge conditions and is subjected to uniform temperature loading. Minimum potential energy theory and finite element methods were used to calculate the panel buckling temperatures. The two methods gave fairly close buckling temperatures. However, the finite element method gave slightly lower buckling temperatures than those given by the minimum potential energy theory. The reasons for this slight discrepancy in eigensolutions are discussed in detail. In addition, the effect of eigenshifting on the eigenvalue convergence rate is discussed.

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作者
Ko, William L.;
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年度 1995
页码 1-56
总页数 56
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
AERODYNAMIC HEATING; AERODYNAMIC LOADS; AIRCRAFT DESIGN; APPLICATIONS PROGRAMS (COMPUTERS); ASPECT RATIO; COMPUTER AIDED DESIGN; CRITICAL TEMPERATURE; ENERGY METHODS; FINITE ELEMENT METHOD; HYPERSONIC AIRCRAFT; RAYLEIGH-RITZ METHOD; RECTANGULAR PANELS; SANDWICH STRUCTURES; THERMAL BUCKLING; BENDING MOMENTS; COMPUTERIZED SIMULATION; EIGENVALUES; LOAD TESTS; MATHEMATICAL MODELS; POISSON RATIO; POTENTIAL ENERGY; STIFFNESS MATRIX; TEMPERATURE MEASUREMENT; TITANIUM;

机译：空气动力加热;空气动力负荷;飞机设计;应用程序（计算机）;宽高比;计算机辅助设计;临界温度;能量方法;有限元法;超音速飞机; RaYLEIGH-RITZ方法;矩形面板;三明治结构;热屈曲;弯曲的时刻;计算机模拟;特征值;负荷试验;数学模型; pOIssON比率;潜在能源;刚性矩阵;温度测量;钛;

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1. Material combinations and parametric study of thermal and mechanical performance of pyramidal core sandwich panels used for hypersonic aircrafts [J] . Zhang Ruiping, Zhang Xiaoqing, Lorenzini Giulio, Continuum mechanics and thermodynamics . 2016,第6期

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2. Optimization of multi-sandwich-panel composite structures for minimum weight with strength and buckling considerations [J] . Hai-Tao Fan, Hai Wang, Xiu-Hua Chen Science and Engineering of Composite Materials . 2018,第2期

机译：在考虑强度和屈曲的情况下优化多层夹芯板复合结构以实现最小重量
3. Thermal post-buckling analysis of a laminated composite spherical shell panel embedded with shape memory alloy fibres using non-linear finite element method [J] . S K Panda, B N Singh Proceedings of the Institution of Mechanical Engineers, Part C: Journal of Mechanical Engineering Science . 2010,第4期

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4. A comparison of finite element buckling analysis predictions and experimental results for riveted aircraft fuselage panels [C] . K. Koffi, A. Gibson, M. Price Tenth International Conference on Computational Methods and Experimental Measurements, 10th, 2001, Alicante . 2001

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5. EXPERIMENTAL AND FINITE ELEMENT INVESTIGATION OF THE BUCKLING CHARACTERISTICS OF A BEADED SKIN PANEL FOR A HYPERSONIC AIRCRAFT. [D] . SIEGEL, WILLIAM HARRY. 1978

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6. Modeling of Sensor Placement Strategy for Shape Sensing and Structural Health Monitoring of a Wing-Shaped Sandwich Panel Using Inverse Finite Element Method [O] . Adnan Kefal, Mehmet Yildiz 2017

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Predictions of thermal buckling strengths of hypersonic aircraft sandwich panels using minimum potential energy and finite element methods

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