某小型无人机的机体结构及其强度计算
摘要
近年来,国内外掀起了研制无人机的高潮。复合材料在无人机上得到了越来越广泛的应用。本文在参照《无人机强度和刚度规范》以及其他规范的基础上,进行了一种无人机结构的设计和强度的一些初步工作。
在参阅相关文献的基础上,基于无人机总体设计的初步概念设计理念,完成了部分机体结构的初步打样,并在文中做了简要的描述。本文还结合无人机的特点,参照无人机强度和刚度规范,给出了无人机的飞行载荷计算结果,这些结果是进行无人机结构有限元分析的载荷数据。
对玻璃钢泡沫夹芯结构、玻璃钢叠层板结构、铝合金结构这三种结构形式的机翼翼盒在无人机机动俯仰时两种载荷情况下的受载分析,列出了近似等质量和近似等强度两种情形下的对比分析结果。
依据结构模型化准则,建立了无人机的机翼、机身及全机的有限元模型。使用通用有限元分析软件ABAQUS计算了机翼在各主要受载情况下的应力和变形,并作了机翼翼盒的稳定性分析,给出了它们的分析结果;还完成了全机模型的自由模态分析、稳定性分析以及总体应力分析,给出了相应的分析结果。
本文的工作是对某型无人机的结构强度的初步探讨,对于诸如滚转机动,回收撞击等情况下无人机结构强度则有待进一步研究。
More and more academic institutions have the plan to develop an Unmanned Aerial Vehicle (UAV) in recent years. And composite materials have been used to make a UAV more and more. The accidence analysis of the certain UAVs structures strength has been done in this paper, which was based on the goal in the whole and the strength and stiffness criterion of UAV as well as other criterions.
Since some structures have been designed based on initial concept design of the goal in the whole, its component structures was described in the paper. And referring to characteristic of a UAV, the aviation load was given by using the strength and stiffness criterion of UAV. Then the load would be used to do FEM analysis of the structures of the UAV.
The analysis of three structures of wing-box including sandwich structure of GFRP and foam, laminate of GFRP and aluminum alloy structure are compared by equal quality and equal strength under two major load cases.
According as the criterion of modeling structures, the FEM model of the wing, fuselage and its whole body are founded. By using the FEM software ABAQUS, the stress and strain of wing under different load cases is calculated. And stability analysis of wing-box and whole body as is done, too. The analysis of free model and stress and strain of the whole body are obtained in the end. Then the analysis result is gived.
However, the work done in this paper is just initial job about the structures strength of the UAV. More and advanced work such as its strength when the UAV is doing roll-maneuver should be going on.
在参阅相关文献的基础上,基于无人机总体设计的初步概念设计理念,完成了部分机体结构的初步打样,并在文中做了简要的描述。本文还结合无人机的特点,参照无人机强度和刚度规范,给出了无人机的飞行载荷计算结果,这些结果是进行无人机结构有限元分析的载荷数据。
对玻璃钢泡沫夹芯结构、玻璃钢叠层板结构、铝合金结构这三种结构形式的机翼翼盒在无人机机动俯仰时两种载荷情况下的受载分析,列出了近似等质量和近似等强度两种情形下的对比分析结果。
依据结构模型化准则,建立了无人机的机翼、机身及全机的有限元模型。使用通用有限元分析软件ABAQUS计算了机翼在各主要受载情况下的应力和变形,并作了机翼翼盒的稳定性分析,给出了它们的分析结果;还完成了全机模型的自由模态分析、稳定性分析以及总体应力分析,给出了相应的分析结果。
本文的工作是对某型无人机的结构强度的初步探讨,对于诸如滚转机动,回收撞击等情况下无人机结构强度则有待进一步研究。
More and more academic institutions have the plan to develop an Unmanned Aerial Vehicle (UAV) in recent years. And composite materials have been used to make a UAV more and more. The accidence analysis of the certain UAVs structures strength has been done in this paper, which was based on the goal in the whole and the strength and stiffness criterion of UAV as well as other criterions.
Since some structures have been designed based on initial concept design of the goal in the whole, its component structures was described in the paper. And referring to characteristic of a UAV, the aviation load was given by using the strength and stiffness criterion of UAV. Then the load would be used to do FEM analysis of the structures of the UAV.
The analysis of three structures of wing-box including sandwich structure of GFRP and foam, laminate of GFRP and aluminum alloy structure are compared by equal quality and equal strength under two major load cases.
According as the criterion of modeling structures, the FEM model of the wing, fuselage and its whole body are founded. By using the FEM software ABAQUS, the stress and strain of wing under different load cases is calculated. And stability analysis of wing-box and whole body as is done, too. The analysis of free model and stress and strain of the whole body are obtained in the end. Then the analysis result is gived.
However, the work done in this paper is just initial job about the structures strength of the UAV. More and advanced work such as its strength when the UAV is doing roll-maneuver should be going on.
引文
[1]法斯多姆(Fahlstrom,P.G)等著.无人机系统导论(吴汉平等译)[M].北京:电子工业出版社,2003.9,第二版.
[2]朱宝鎏编著.无人飞机空气动力学[M].北京:航空工业出版社,2006.10
[3]强岁红.无人机发展的启示[J].飞机工程,2007,(3):5-8.
[4]王文雅摘编.各国无人机状况简介[J].信息广角,2006,(2):53-56.
[5]周军,徐文.无人机的发展趋势和前景[J].飞航导弹,2003,(7):32-40.
[6]丁红杰.复合材料在无人机上的应用[J].电光系统,2004,(1):62-64.
[7]陈绍介.无人机上复合材料的应用与研究[J].飞机设计,2003,(3):26-30.
[8]Barry Berenberg.Unmanned Composite Aircraft Patrol the Skies[J].High-performance Composite.2002,(5):18-22.
[9]王荣国等.复合材料概论[M].哈尔滨:哈尔滨工业大学出版社,1999.8.
[10]王震鸣编著.复合材料力学和复合材料结构力学[M].北京:机械工业出版社,1991.3.
[11]沈观林,胡更开编著.复合材料力学[M].北京:清华大学出版社,2006.9.
[12]陈建桥编著.复合材料力学概论[M].北京:科学出版社,2006.8.
[13]王兴业等编著.复合材料力学分析与设计[M].长沙:国防科技大学出版社,1 999.11.
[14]吕恩林编著.复合材料力学[M].重庆:重庆大学出版社,1992.1.
[15]李曙林编著.飞机与发动机强度[M].北京:国防工业出版社,2007.6.
[16]Kwon O J,Sankar L N.Viscous Flow Simulation of a Fighter Aircraft[J].J.Aircraft,1992,29(5):886-891.
[17]张元明,赵鹏飞.低速小型无人机中的复合材料结构及分析[J].玻璃钢/复合材料,2003,(6):36-40.
[18]冯密荣.世界无人机大全[M].北京:航空工业出版社,2004.
[19]何景武,范曼华,张晓鸥.关于无人机结构设计技术的讨论[J].无人机, 2005,[5):23-27.
[20]中国航空研究所.GJB67.2-1985,军用飞机强度和刚度规范使用说明(S).北京:国防工业出版社,1986.2.
[21]中国人民解放军总装备部.GJB5435-2005,无人机强度和刚度规范(S).北京:总装备部军标出版发行部,2005.9
[22]杨乃宾等编著.复合材料飞机结构设计[M].北京:航空工业出版社,2002.
[23]石一平,周玉蓉.ABAQUS有限元分析实例详解[M].北京:机械工业出版社,2006.6.
[24]庄茁.ABAQUS非线性有限元分析与实例[M].北京:科学出版社,2005.
[25]Hu HT.Buckling analysis of fiber-composite laminate plates with material non-linearity[J].Finite Elements in Analysis and Design,1995(19):169-178.
[26]郭乙木,陶伟明,庄茁编著.线性与非线性有限元及其应用[M].北京:机械工业出版社,2003.10.
[27]Jinsoo Cho,Younhyuck Chang.Supersonic flutter analysis of wings using an unsteady 3D panel method[J].Computers & Fluids,2001,30:237-256.
[28]O'Connor C.Chan T H Dynamic wheel loads from bridge strains[J].Structural Engineering ASCE,1988(114):1703-1723.
[29]王志瑾,姚卫星编著.飞机结构设计[M].北京:国防工业出版社,2007.8.
[30]王肇荣,姚全珠编著.FORTRAN语言程序设计[M].西安:西安电子科技大学出版社,2005.1,第二版.
[31]《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,2001.12.
[32]《飞机设计手册》总编委会编.飞机设计手册,第10册:结构设计[M].北京:航空工业出版社,2000.10.
[32]刘斌.无人机飞行载荷设计与计算研究[D].西安:西北工业大学,1999.
[34]金平主编.飞机结构强度[M].北京:海潮工业出版社,2003.
[35]王瑁成编著.有限单元法[M].北京:清华大学出版社,2003.7.
[36]Solar-powered helios completes record-breaking flight[J].Hight Performance Composite,2001(9,10):11.
[37]Kong,Cheol-Won.Testing and analysis of downscaled composite wing box[J].Journal of Aircraft,2002(6):480-485.
[38]Zhang Yuanming,Zhao Pengfei.Design and Manufacture of FRP Foam Sandwich Structure Wing for a UAV[J].18th Bristol Intentioned UAV Systems Conference.2003.
[39]PaRxida,Basant K.Structural integrity assessment of composite pressure test box through full scale test ASTM Special Technical Publication[J].Composite Materials,2002(4):69-84.
[40]Smith C S,Dow R S.Interactive buckling effects in stiffened FRP panels[J].Proceedings of the 4th International Conference on Composite Structures[C].Paisley,1987,122-137.
[41]Shu D,Mai Y W.Buckling of delaminated composites reexaminated[J].Composite Science and Technology,1993,47(1):35-41.
[42]Ziemkiewics O C.The Finite Element Method in Engineering Science[M].McGraw-Hill,London,1971.
[43]Clyne T,etal.An introduction to metal matrix composites[M].Cambridge:Cambridge University Press,1993.
[44]Leissa A W.An Overview of Composite Plate Buckling[J].Composite Structure,1987,1(4).
[45]Cerchie,D.Dockter,G.,Hardesty,M.,Kasprzyk,S.Rapid development of a rotorcraft UAV system[J].AHS International Specialists' Meeting-Unmanned Rotorcraft:Design,Control and Testing,Proceedings,2005:105-112.
[46]张广成,赵景利.蜂窝夹层结构复合材料的力学性能研究[J].机械科学与技术,2003,22(2):280-282.
[47]张胜,江大治,周升.高速列车复合材料司机室混杂结构有限元分析[J].玻璃钢/复合材料,2006,(2):10-13.
[48]张广平.复合材料夹心板及其应用[J].纤维复合材料,2000,(2):26-29.
[49]吴存利,师成梅,段世慧,陈焕星.飞机复合材料壁板稳定性分析[J].玻 结构强度研究,2003,(4):18-23.
[50]程改霞,郑晓亚,张铎,姜晋庆.蜂窝夹层结构等效板力学特性研究[J].弹箭与制导学报,2003,24(5):568-571.
[51]唐文勇,陈念众,张圣坤.复合材料加筋层合板的极限强度分析[J].工程力学,2007,24(8):43-48.
[52]顾慧芝,彭晓洪.复合材料夹芯结构翼面的有限元分析[J].南京航空学院学报,1989,21(1):1-11.
[2]朱宝鎏编著.无人飞机空气动力学[M].北京:航空工业出版社,2006.10
[3]强岁红.无人机发展的启示[J].飞机工程,2007,(3):5-8.
[4]王文雅摘编.各国无人机状况简介[J].信息广角,2006,(2):53-56.
[5]周军,徐文.无人机的发展趋势和前景[J].飞航导弹,2003,(7):32-40.
[6]丁红杰.复合材料在无人机上的应用[J].电光系统,2004,(1):62-64.
[7]陈绍介.无人机上复合材料的应用与研究[J].飞机设计,2003,(3):26-30.
[8]Barry Berenberg.Unmanned Composite Aircraft Patrol the Skies[J].High-performance Composite.2002,(5):18-22.
[9]王荣国等.复合材料概论[M].哈尔滨:哈尔滨工业大学出版社,1999.8.
[10]王震鸣编著.复合材料力学和复合材料结构力学[M].北京:机械工业出版社,1991.3.
[11]沈观林,胡更开编著.复合材料力学[M].北京:清华大学出版社,2006.9.
[12]陈建桥编著.复合材料力学概论[M].北京:科学出版社,2006.8.
[13]王兴业等编著.复合材料力学分析与设计[M].长沙:国防科技大学出版社,1 999.11.
[14]吕恩林编著.复合材料力学[M].重庆:重庆大学出版社,1992.1.
[15]李曙林编著.飞机与发动机强度[M].北京:国防工业出版社,2007.6.
[16]Kwon O J,Sankar L N.Viscous Flow Simulation of a Fighter Aircraft[J].J.Aircraft,1992,29(5):886-891.
[17]张元明,赵鹏飞.低速小型无人机中的复合材料结构及分析[J].玻璃钢/复合材料,2003,(6):36-40.
[18]冯密荣.世界无人机大全[M].北京:航空工业出版社,2004.
[19]何景武,范曼华,张晓鸥.关于无人机结构设计技术的讨论[J].无人机, 2005,[5):23-27.
[20]中国航空研究所.GJB67.2-1985,军用飞机强度和刚度规范使用说明(S).北京:国防工业出版社,1986.2.
[21]中国人民解放军总装备部.GJB5435-2005,无人机强度和刚度规范(S).北京:总装备部军标出版发行部,2005.9
[22]杨乃宾等编著.复合材料飞机结构设计[M].北京:航空工业出版社,2002.
[23]石一平,周玉蓉.ABAQUS有限元分析实例详解[M].北京:机械工业出版社,2006.6.
[24]庄茁.ABAQUS非线性有限元分析与实例[M].北京:科学出版社,2005.
[25]Hu HT.Buckling analysis of fiber-composite laminate plates with material non-linearity[J].Finite Elements in Analysis and Design,1995(19):169-178.
[26]郭乙木,陶伟明,庄茁编著.线性与非线性有限元及其应用[M].北京:机械工业出版社,2003.10.
[27]Jinsoo Cho,Younhyuck Chang.Supersonic flutter analysis of wings using an unsteady 3D panel method[J].Computers & Fluids,2001,30:237-256.
[28]O'Connor C.Chan T H Dynamic wheel loads from bridge strains[J].Structural Engineering ASCE,1988(114):1703-1723.
[29]王志瑾,姚卫星编著.飞机结构设计[M].北京:国防工业出版社,2007.8.
[30]王肇荣,姚全珠编著.FORTRAN语言程序设计[M].西安:西安电子科技大学出版社,2005.1,第二版.
[31]《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,2001.12.
[32]《飞机设计手册》总编委会编.飞机设计手册,第10册:结构设计[M].北京:航空工业出版社,2000.10.
[32]刘斌.无人机飞行载荷设计与计算研究[D].西安:西北工业大学,1999.
[34]金平主编.飞机结构强度[M].北京:海潮工业出版社,2003.
[35]王瑁成编著.有限单元法[M].北京:清华大学出版社,2003.7.
[36]Solar-powered helios completes record-breaking flight[J].Hight Performance Composite,2001(9,10):11.
[37]Kong,Cheol-Won.Testing and analysis of downscaled composite wing box[J].Journal of Aircraft,2002(6):480-485.
[38]Zhang Yuanming,Zhao Pengfei.Design and Manufacture of FRP Foam Sandwich Structure Wing for a UAV[J].18th Bristol Intentioned UAV Systems Conference.2003.
[39]PaRxida,Basant K.Structural integrity assessment of composite pressure test box through full scale test ASTM Special Technical Publication[J].Composite Materials,2002(4):69-84.
[40]Smith C S,Dow R S.Interactive buckling effects in stiffened FRP panels[J].Proceedings of the 4th International Conference on Composite Structures[C].Paisley,1987,122-137.
[41]Shu D,Mai Y W.Buckling of delaminated composites reexaminated[J].Composite Science and Technology,1993,47(1):35-41.
[42]Ziemkiewics O C.The Finite Element Method in Engineering Science[M].McGraw-Hill,London,1971.
[43]Clyne T,etal.An introduction to metal matrix composites[M].Cambridge:Cambridge University Press,1993.
[44]Leissa A W.An Overview of Composite Plate Buckling[J].Composite Structure,1987,1(4).
[45]Cerchie,D.Dockter,G.,Hardesty,M.,Kasprzyk,S.Rapid development of a rotorcraft UAV system[J].AHS International Specialists' Meeting-Unmanned Rotorcraft:Design,Control and Testing,Proceedings,2005:105-112.
[46]张广成,赵景利.蜂窝夹层结构复合材料的力学性能研究[J].机械科学与技术,2003,22(2):280-282.
[47]张胜,江大治,周升.高速列车复合材料司机室混杂结构有限元分析[J].玻璃钢/复合材料,2006,(2):10-13.
[48]张广平.复合材料夹心板及其应用[J].纤维复合材料,2000,(2):26-29.
[49]吴存利,师成梅,段世慧,陈焕星.飞机复合材料壁板稳定性分析[J].玻 结构强度研究,2003,(4):18-23.
[50]程改霞,郑晓亚,张铎,姜晋庆.蜂窝夹层结构等效板力学特性研究[J].弹箭与制导学报,2003,24(5):568-571.
[51]唐文勇,陈念众,张圣坤.复合材料加筋层合板的极限强度分析[J].工程力学,2007,24(8):43-48.
[52]顾慧芝,彭晓洪.复合材料夹芯结构翼面的有限元分析[J].南京航空学院学报,1989,21(1):1-11.