LI Hui， WU Huai-shuai， WEI Sha， LI Zheng-ze. Natural Characteristics of Fiber-Reinforced Cantilever Composite Thin Plate Under Thermal Vibration Environment[J]. Journal of Northeastern University Natural Science, 2018, 39(1): 87-92.
[1]Vinson J R，Sierakowski R L.The behavior of structures composed of composite materials［M］.Heidelberg:Springer Science & Business Media，2006. [2]Reddy J N.Mechanics of laminated composite plates and shells:theory and analysis［M］.Boca Raton:CRC Press，2004. [3]Jones R M.Mechanics of composite materials［M］.Washington D C:Scripta Book Company，1975. [4]Liu C F，Huang C H.Free vibration of composite laminated plates subjected to temperature changes［J］.Computers & Structures，1996，60(1):95-101. [5]Jeyaraj P，Ganesan N，Padmanabhan C.Vibration and acoustic response of a composite plate with inherent material damping in a thermal environment［J］.Journal of Sound and Vibration，2009，320(1):322-338. [6]Wang Z X，Shen H S.Nonlinear vibration of nanotube-reinforced composite plates in thermal environments［J］.Computational Materials Science，2011，50(8):2319-2330. [7]Fakhari V，Ohadi A，Yousefian P.Nonlinear free and forced vibration behavior of functionally graded plate with piezoelectric layers in thermal environment［J］.Composite Structures，2011，93(9):2310-2321. [8]Shooshtari A，Rafiee M.Vibration characteristics of nanocomposite plates under thermal conditions including nonlinear effects［J］.International Journal of Applied Mechanics，2011，1(1):60-69. [9]Lei Z X，Liew K M，Yu J L.Free vibration analysis of functionally graded carbon nanotube-reinforced composite plates using the element-free kp-Ritz method in thermal environment［J］.Composite Structures，2013，106:128-138. [10]Nejati M，Fard K M，Eslampanah A.Effects of fiber orientation and temperature on natural frequencies of a functionally graded beam reinforced with fiber［J］.Journal of Mechanical Science and Technology，2015，29(8):3363-3371. [11]吴大方，王岳武，蒲颖，等.高超声速飞行器复合材料翼面结构 1100℃高温环境下的热模态试验［J］.复合材料学报，2015，32(2):323-331.(Wu Da-fang，Wang Yue-wu，Pu Ying，et al.Thermal modal test of composite wing structure in high-temperature environments up to 1100℃ for hypersonic flight vehicles ［J］.Acta Materiae Compositae Sinica，2015，32(2):323-331.)
