民用飞机球面框的优化和方案设计
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摘要
机身球面框是民用飞机机身增压舱的端框,是飞机的主要结构部件。球面框复杂的结构形式和装配要求,极大地增加了设计难度。在某型号飞机的概念设计阶段,基于先进的Opti Struct优化技术,对球面框初始构型进行了拓扑优化。参照优化后的密度云图,调整经向加筋的结构位置,给出3种满足强度要求和刚度要求的初始设计方案。使用MSC.Patran建立细节有限元模型模拟3种方案,计算每个球面框方案在增压载荷工况下的应力分布,为后续详细结构设计提供数据支持。
The spherical frame is the bulkhead of pressure cabin at civil aircraft,which is a major part of fuselage structure. The complicated configuration and assembly requirement of spherical frame remarkably increase the difficulty in design. The initial configuration of spherical frame was topologically optimized based on the advanced Opti Struct technique in the initial stage of structural concept design. According to the density plots,the structural locations of meridian stiffeners were adjusted,and three initial project designs were proposed to meet the requirements about strength and rigidity. Detailed finite element model was built to simulate the spherical frame of fuselage using MSC. Patran through the three designs,and the stress distribution under the pressurized load was respectively calculated for the designs,which provides the data support for detailed structure design in the future.
The spherical frame is the bulkhead of pressure cabin at civil aircraft,which is a major part of fuselage structure. The complicated configuration and assembly requirement of spherical frame remarkably increase the difficulty in design. The initial configuration of spherical frame was topologically optimized based on the advanced Opti Struct technique in the initial stage of structural concept design. According to the density plots,the structural locations of meridian stiffeners were adjusted,and three initial project designs were proposed to meet the requirements about strength and rigidity. Detailed finite element model was built to simulate the spherical frame of fuselage using MSC. Patran through the three designs,and the stress distribution under the pressurized load was respectively calculated for the designs,which provides the data support for detailed structure design in the future.
引文
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[2]BLACHUT J.Buckling of multilayered metal domes[J].Thin-Walled Structures,2009,47:1429-1438.
[3]CAO Z G,FAN F,SHEN S J.Elasto-plastic stability of single-layer reticulated domes[J].China Civil Engineering Journal,2006,39(10):6-10.
[4]FAN F,YAN J C,CAO Z G.Elasto-plastic stability of single-layer reticulated domes with initial curvature of members[J].Thin-Walled Structures,2012,60:239-246.
[5]TENG T L,YU C M,WU Y Y.Optimal design of filament-w ound composite pressure vessels[J].Mechanics of Composite Materials,2005,41(4):333-340.
[6]SHALLAN O,ERAKY A.Optimum design of space tensegrity dome[J].International Journal of Engineering and Innovative Technology,2014,3(9):47-54.
[7]RIBERT J M.Structural engineering analysis by finite element[M].New Jersey:Prentice Hall,1990.
[8]EUGENIO O.Structural analysis with the finite element method[M].Springer,2013.
[9]SURANAK S,REDDY J N.The finite element method for boundary value problems:mathematics and computaion[M].CRC press,2016.
[10]朱菊芬.非线性有限元及其在飞机结构设计中的应用[M].上海:上海交通大学出版社,2011.
[11]张胜兰,郑冬黎,等.基于Hyper Works的结构优化设计技术[M].北京:机械工业出版社,2007.
[12]李楚琳,张胜兰,等.Hyper Works分析应用实例[M].北京:机械工业出版社,2008.
[13]赵俊辉,孙为民,童明波.气密载荷下机身球面框的强度分析[J].飞机设计,2009,29(2):21-24.
[14]刘昌沅,郭伟毅,等.气密座舱球面框的非线性有限元结构设计[J].航空精密制造技术,2004,40(5):22-25.
[15]牛春匀.实用飞机结构应力分析及尺寸设计[M].北京:航空工业出版社,2009.