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新复合材料结构的发展要求用较精确的计算方法代替过去较粗裢的工程计算法分析结构的应力应变。本文结合 X-X 改型飞机操纵面的改进,针对全高度变厚度 Nomex 纸蜂窝芯、碳纤维面板夹芯翼面与实心碳纤维梁、空心前缘组合结构,讨论了计算原理、分析方法、介绍了计算模型和程序编制方法,并编制了计算程序,按用于微机 IBM-PC 及其兼容机编制,使计算费用大为降低。此程序可广泛应用于复合材料平面或曲率不大的夹芯结构,如翼面、地板、舱盖等。文中以调正片为例进行了计算,与原试验结果对比表明,应力、应变和变形分布正确,精度达到航空工程实用要求。
The development of new composite structures requires the use of more accurate calculation methods instead of the more coarse engineering calculation method of structural stress and strain analysis. In this paper, with the improvement of control plane of XX modified aircraft, the calculation principle and analysis method of Nomex paper honeycomb core, carbon fiber sandwich panel airfoil and solid carbon fiber beam and hollow leading edge are discussed. The calculation model And programming methods, and the preparation of a calculation program, according to computer IBM-PC and compatible with the preparation of the computational costs greatly reduced. This program can be widely used in composite materials flat or curved sandwich structure, such as the airfoil, floor, hatch and so on. In this paper, the correction film is taken as an example to calculate. Compared with the original test results, the stress, strain and deformation distribution are correct, and the accuracy meets the practical requirements of aviation engineering.