机身壁板剪切试验方法研究
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摘要
机身壁板剪切试验方法研究是飞机结构强度研究的重要内容,基于机身壁板剪切载荷的承力特性,给出了一种新的剪切试验方法。该方法采用"D"夹具和弓形角盒模拟机身圆筒结构,用合页连接"D"夹具和机身壁板组成单闭室盒段,以扭转单闭室盒段的方式施加剪切载荷。设计加工了机身壁板试验件和试验装置,并完成验证试验。验证试验实测应力分布较为合理,且与理论解基本相符,证明该试验方法是正确的和工程可行的。该方法避免设置与机身壁板尺寸相近的过渡段和加载段,减少装配工作量,节约研究成本,并已应用于民用飞机机身壁板剪切稳定性试验。
The test method of fuselage panel subjected to shear load is an important technique for aircraft structure strength research. A new shear test method is proposed based on the property of aircraft fuselage panel subjected to shear load. "D"jig and arch angle connectors is designed to simulate the circular structure of fuselage,and the shear stress is applied through the torsional form of single closed box structure,consisting of "D"jig and fuselage panel through hinge. A test panel and a set of fixtures were designed and manufactured,and validation test were conducted. Validation test verifies the validity and engineering feasibility of this method,and the stress distribution of panel in test is uniform as well as in a good agreement with theoretical analysis. In addition,this test method avoids to design a transition section and a loading section with the similar length of aircraft fuselage panel,and saves assembly work and test expenses. The stability test of the fuselage panel on civil aircraft adopts this new method at present.
The test method of fuselage panel subjected to shear load is an important technique for aircraft structure strength research. A new shear test method is proposed based on the property of aircraft fuselage panel subjected to shear load. "D"jig and arch angle connectors is designed to simulate the circular structure of fuselage,and the shear stress is applied through the torsional form of single closed box structure,consisting of "D"jig and fuselage panel through hinge. A test panel and a set of fixtures were designed and manufactured,and validation test were conducted. Validation test verifies the validity and engineering feasibility of this method,and the stress distribution of panel in test is uniform as well as in a good agreement with theoretical analysis. In addition,this test method avoids to design a transition section and a loading section with the similar length of aircraft fuselage panel,and saves assembly work and test expenses. The stability test of the fuselage panel on civil aircraft adopts this new method at present.
引文
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[9]臧伟锋,董登科,张海英.机身壁板内压载荷强度试验方法研究[J].机械强度,2015,37(5):972-977.ZANG Weifeng,DONG Dengke,ZHANG Haiying.Research on test method of fuselage panel subjected to internal pressure load[J].Journal of Mechanical Strength,2015,37(5):972-977(In Chinese).
[10]臧伟锋,董登科,王俊安.机身壁板复合载荷强度试验装置及试验方法[P].中国,CN201210528413.8,2013-6-12.ZANG Weifeng,DONG Dengke,WANG Junan.Test Fixture and Method for Fuselage Panel Under Combined Loads[P]China.CN201210528413.8,2013-6-12(In Chinese).
[11]顾松年,尤文洁,诸德培.结构试验基础[M].北京:国防工业出版社,1981:51-56.GU Shong Nian,YOU Wen Hao,ZHU De Pei.Basic structure test[M].Beijing:National Defence Industrial Press,1981:51-56(In Chinese).
[12]蔡怀崇,闵行.材料力学[M].西安:西安交通大学出版社,2004:54-56.CAI Huai Chong,MIN Hang.Materials mechanics[M].Xi’an:Xi’an Jiaotong University Press,2004:54-56(In Chinese).
[2]吉国明,孙刚,张量.承受轴压载荷的加筋板的准静态分析[J].机械强度,2013,35(3):308-311.JI Guo Ming,SUN Gang,ZHANG Liang.Quasi-static analysis of stiffened plate under axial pressure[J].Journal of Mechanical Strength,2013,35(3):308-311(In Chinese).
[3]《飞机设计手册》总编委会编.飞机设计手册第9册:载荷、强度和刚度[M].北京:航空工业出版社,2001:494-503.A handbook of Aircraft Designer Committee.A handbook of aircraft designer the 9rd volume:load,Strength and Rigidity[M].Beijing:Aviation Industrial Press,2001:494-503(In Chinese).
[4]孙为民,童明波,董登科.民机大型加筋曲板在剪切载荷下失效破坏试验[J].南京航空航天大学学报,2008,40(4):521-525.SUN Weimin,TONG Mingbo,DONG Dengke.Failure damage experiments of stiffened panels subjected to shear loading[J].Journal of Nanjing University of Aeronautics&Astronautics,2008,40(4):521-525(In Chinese).
[5]Ambur,D.A.,Rouse,M.,Starnes,J.H.,and Shuart,M.J.Facilities for Combined Loads Testing of Aircraft Structures to Satisfy Structural Technology Development Requirements[R].presented at the 5th Annual Advanced Composites Technology Conference,Seattle.1994:22-36.
[6]Marshall R,Richard D Y.Structural Stability of a Stiffened Aluminum Fuselage Panel Subjected to combined Mechanical and internal pressure Loads[R].AIAA-2003-1423,2003.
[7]Andrew E.Lovejoy.Configuration and Sizing of a Test Fixture for Panels Under Combined Loads[R].NASA/CR-2006-214520.2006:9-13.
[8]Damodar R.Ambur,Jeffrey A Cerro,and John Dickson.Analysis of a D-Box Fixture for Testing Curved Stiffened Aircraft Fuselage Panels in Axial Compression and Internal Pressure[R].AIAA-94-1345-CP.1994:309-319.
[9]臧伟锋,董登科,张海英.机身壁板内压载荷强度试验方法研究[J].机械强度,2015,37(5):972-977.ZANG Weifeng,DONG Dengke,ZHANG Haiying.Research on test method of fuselage panel subjected to internal pressure load[J].Journal of Mechanical Strength,2015,37(5):972-977(In Chinese).
[10]臧伟锋,董登科,王俊安.机身壁板复合载荷强度试验装置及试验方法[P].中国,CN201210528413.8,2013-6-12.ZANG Weifeng,DONG Dengke,WANG Junan.Test Fixture and Method for Fuselage Panel Under Combined Loads[P]China.CN201210528413.8,2013-6-12(In Chinese).
[11]顾松年,尤文洁,诸德培.结构试验基础[M].北京:国防工业出版社,1981:51-56.GU Shong Nian,YOU Wen Hao,ZHU De Pei.Basic structure test[M].Beijing:National Defence Industrial Press,1981:51-56(In Chinese).
[12]蔡怀崇,闵行.材料力学[M].西安:西安交通大学出版社,2004:54-56.CAI Huai Chong,MIN Hang.Materials mechanics[M].Xi’an:Xi’an Jiaotong University Press,2004:54-56(In Chinese).