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借助PATRAN、NASTRAN有限元分析工具,着重研究机翼结构重量因气动载荷压心变化而产生的影响。气动载荷的压心变化通过在飞机巡航状态中某一个载荷情况下真实的气动载荷基础上叠加一个微小量的分布载荷来实现,保证新得到的气动载荷与原始的气动载荷总载保持一致,从而使得气动载荷的压心位置发生变化。通过理论分析和简单的有限元分析验证,得到了气动载荷压心变化下机翼蒙皮、长桁等单元的应力分布和增长规律,进而得到气动载荷压心变化与机翼结构增重之间的函数关系:气动载荷压心向翼尖方向移动1%,机翼结构重量增重2.46%。该结论可以为其他型号的民机机翼设计提供参考依据。
With PATRAN, the NASTRAN finite element analysis tool focuses on the effect of the structural weight of the wing due to the change in the pressure center of the aerodynamic load. The change of the pressure center of aerodynamic load is realized by adding a small amount of distributed load on the basis of the real aerodynamic load in the case of a certain cruising condition of the aircraft to ensure that the newly obtained aerodynamic load is consistent with the original total aerodynamic load Making the pneumatic load pressure center position change. Through the theoretical analysis and simple finite element analysis, the stress distribution and growth law of the wing skin and stringer are obtained under the changes of the pressure heart of the aerodynamic load, and the relationship between the pressure variation of the aerodynamic load and the weight gain of the wing structure is obtained : The pneumatic load moves 1% to the wingtip and 2.46% to the weight of the wing structure. This conclusion can provide reference for other types of civil aircraft wing design.