Vee-tail conceptual design criteria for commercial transport aeroplanes
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摘要
Vee-tail configuration is an unconventional tail configuration for commercial transport aviation, the use of which could suppose reductions on CO2 emissions. The conceptual design criteria have been selected inspired on the certification requirements established by the aviation regulation in force. They are static stability in cruise, control after Critical Engine Failure(CEF),control in crosswind landing, and trim in these three conditions. The study is carried out through a combination of semi-empirical techniques and Vortex-Lattice Methods(VLM) and thus this analyses the consequences of applying these criteria to a reference aeroplane substituting its conventional tail by a parametrised Vee-tail configuration. The Vee-tail is defined by four parameters:span, root chord, taper ratio and dihedral angle. The results of the study establish a relation between the parameters in order to accomplish the proposed conceptual design criteria. To sum up, minimum and maximum limits are obtained for dihedral angle depending on the combination of the rest of parameters. In addition, a design restriction to the yawing trailing-edge tail control is reached when the results are analysed, demonstrating that its minimum size must be between 60%and 80% of the half-span of the tail, depending on the Vee-tail geometry.
Vee-tail configuration is an unconventional tail configuration for commercial transport aviation, the use of which could suppose reductions on CO2 emissions. The conceptual design criteria have been selected inspired on the certification requirements established by the aviation regulation in force. They are static stability in cruise, control after Critical Engine Failure(CEF),control in crosswind landing, and trim in these three conditions. The study is carried out through a combination of semi-empirical techniques and Vortex-Lattice Methods(VLM) and thus this analyses the consequences of applying these criteria to a reference aeroplane substituting its conventional tail by a parametrised Vee-tail configuration. The Vee-tail is defined by four parameters:span, root chord, taper ratio and dihedral angle. The results of the study establish a relation between the parameters in order to accomplish the proposed conceptual design criteria. To sum up, minimum and maximum limits are obtained for dihedral angle depending on the combination of the rest of parameters. In addition, a design restriction to the yawing trailing-edge tail control is reached when the results are analysed, demonstrating that its minimum size must be between 60%and 80% of the half-span of the tail, depending on the Vee-tail geometry.
Vee-tail configuration is an unconventional tail configuration for commercial transport aviation, the use of which could suppose reductions on CO2 emissions. The conceptual design criteria have been selected inspired on the certification requirements established by the aviation regulation in force. They are static stability in cruise, control after Critical Engine Failure(CEF),control in crosswind landing, and trim in these three conditions. The study is carried out through a combination of semi-empirical techniques and Vortex-Lattice Methods(VLM) and thus this analyses the consequences of applying these criteria to a reference aeroplane substituting its conventional tail by a parametrised Vee-tail configuration. The Vee-tail is defined by four parameters:span, root chord, taper ratio and dihedral angle. The results of the study establish a relation between the parameters in order to accomplish the proposed conceptual design criteria. To sum up, minimum and maximum limits are obtained for dihedral angle depending on the combination of the rest of parameters. In addition, a design restriction to the yawing trailing-edge tail control is reached when the results are analysed, demonstrating that its minimum size must be between 60%and 80% of the half-span of the tail, depending on the Vee-tail geometry.
引文
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2.Aeronautics and air transport beyond Vision 2020(Towards2050).Brussels:Strategy Review Group,The Advisory Council for Aeronautics Research in Europe;2010.
3.Busquin P,Argu¨elles P,Bischoff M,Droste BAC,Evans RH,Kro¨ll W,et al.European aeronautics:A vision for 2020-Asynopsis.Air Sp Eur 2001;3(s 3-4):16-8.
4.Darecki M,Edelstenne C,Enders T,Fernandez E,Hartman P,Herteman JP,et al.Flightpath 2050 Europe’s vision for aviation:Report of the High Level Group on Aviation Research Policy;2011.
5.ICAO.Historic agreement reached to mitigate international aviation emissions.Montreal:ICAO News Release;2016.[cited2018 Jan 2].Available from:http://www.icao.int/Newsroom/Pages/Historic-agreement-reached-to-mitigate-international-aviation-emissions.aspx.
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8.Kroo I.Nonplanar wing concepts for increased aircraft efficiency.VKI lecture series on innovative configurations and advanced concepts for future civil aircraft;2005 Jun 6-10;Sint-GenesiusRode,Belgium.Sint-Genesius-Rode:The Von Karman Institute for Fluid Dynamics;2005.p.1-29.
9.Torenbeek E.Blended wing body and all-wing airliners.European Workshop on Aircraft Design Education(EWADE);2007 May 29-Jun 02;Samara,Russia;2007.
10.Anderson JD.The airplane:A history of its technology.Reston:AIAA;2002.
11.Torenbeek E.Advanced aircraft design.Chichester,West Sussex,UK:John Wiley&Sons,Ltd.;2013.
12.Frota J,Nicholls K,Whurr J,Mu¨ller M,Gall P,Loerke J,et al.New Aircraft Concept Research(NACRE):Final activity report.Sixth framework programme:Priority 4 Aeronautics and space;2010.Report No.:FP6-2003-AERO-1.
13.Sharma R.Basic aerodynamic study of joined wing[dissertation].Gurgaon:Amity University Haryana;2015.p.68.
14.Sanchez-Carmona A,Cuerno-Rejado C,Garcia-Hernandez L.Unconventional tail configurations for transport aircraft.Progress Flight Phy 2017;9:127-48.
15.Musa NA,Mansor S,Ali A,Man MHC,Omar WZW.Effect of tail dihedral angle on lateral directional stability due to sideslipangles.53rd AIAA aerospace sciences meeting;2015 Jan 5-9;Kissimmee,Florida,USA.Reston:AIAA;2015.
16.Musa NA,Mansor S,Ali A,Omar WZW,Latif AA,Perumal K.Effects of aircraft tail configurations on sensitivity to yaw disturbances.Appl Mech Mater 2014;629:197-201.
17.Zhang G,Yang S,Xu Y.Song Q.Numerical simulation of the aerodynamic characteristics of Vee-tail based on cluster system.ITESS 2008;823-7.
18.Zhang GQ,Yu SCM,Chien A,Xu Y.Investigation of the tail dihedral effects on the aerodynamic characteristics for the low speed aircraft.Adv Mech Eng 2013;2013:1-12.
19.Garc?′a-Herna′ndez L,Cuerno-Rejado C,Pe′rez-Corte′s M.Dynamics and failure models for a V-tail remotely piloted aircraft system.J Guid Control Dyn 2017;41(2):506-14.
20.Song L,Yang H,Zhang Y,Zhang H,Huang J.Dihedral influence on lateral-directional dynamic stability on large aspect ratio tailless flying wing aircraft.Chinese J Aeronaut 2014;27(5):1149-55.
21.Roskam J.Airplane design,Part II:Preliminary configuration design and integration of the propulsion system.first ed.Ottawa:Roskam Aviation and Engineering Corporation;1989.p.310.
22.Cuerno-Rejado C,Sanchez-Carmona A.Preliminary sizing correlations for the rear-end of transport aircraft.Aircr Eng Aerosp Technol 2016;88(1):24-32.
23.Hettema T.Vertical tail design.Development of a rapid aerodynamic analysis method[dissertation].Delft:Delft University of1094 Technology;2015.p.50.
24.Wang Y,Yin H,Zhang S,Yu X.Multi-objective optimization of aircraft design for emission and cost reductions.Chinese JAeronaut 2014;27(1):52-8.
25.Lucas S,Velazquez A,Vega JM.An optimization method for an aircraft rear-end conceptual design based on surrogate models.In:Ao SI,Gelman L,Hukins DWL,Hunter A,Korsunsky AM,editors.Proceedings of the world congress on engineering Vol III;2011 Jul 6-8;London,UK.Hong Kong:Newswood Limited;2011.p.2610-5.
26.Certification specifications:CS-25 Large aeroplanes.Cologne:European Aviation Safety Agency;2017.
27.Torenbeek E.Synthesis of subsonic airplane design.Dordrecht:Springer Netherlands;1982.p.598.
28.Roskam J.Methods for estimating stability and control derivatives of conventional subsonic airplanes.4th ed.Ottawa:Roskam Aviation and Engineering Corporation;1983.p.99.
29.Nicolosi F,Ciliberti D,Della Vecchia P,Corcione S,Cusati V.Acomprehensive review of vertical tail design.Aircr Eng Aerosp Technol 2017;89(4):547-57.
30.Khatri AK,Singh J,Sinha NK.Aircraft design using constrained bifurcation and continuation method.J Aircr 2014;51(5):1647-53.
31.Paranjape A,Sinha NK,Ananthkrishnan N.Use of bifurcation and continuation methods for aircraft trim and stability analysisA state-of the-art.J Aerosp Sci Technol 2008;60(2):85-100.
32.Central Reference Aircraft data System-CeRAS[Internet].Aechen:ILR,RWTH-Aechen-University[updated 2015 Aug 12;cited 2017 Dec 14].Available from:https://ceras.ilr.rwth-aachen.de/.
33.Code of Federal Regulations:Title 14-Chapter I-Subchapter C-Part 25.Washington,D.C.:Federal Aviation Administration;2017.
34.Lomax TL.Structural loads analysis for commercial transport aircraft:Theory and practice.Reston:AIAA Education Series;1996.p.275.
35.Melin T.A vortex lattice MATLAB implementation for linear aerodynamic wing applications[dissertation].Stockholm:Royal Institute of Technology(KTH);2000.p.45.
36.Polhamus EC.Charts for predicting the subsonic vortex-lift characteristics of arrow,delta,and diamond wings.Washington,D.C.:NASA;1971.Report No.:NASA TN D-6243.
37.Purser Paul E,Campbell John P.Experimental verification of a simplified Vee-tail theory and analysis of available data on complete models with Vee-tails.Washington,D.C.:NASA;1945.Report No.:NACA-TR 823.
38.Ciliberti D,Della Vecchia P,Nicolosi F,De Marco A.Aircraft directional stability and vertical tail design:A review of semi-empirical methods.Prog Aerosp Sci 2017;95:140-72.
39.Roskam J.Airplane design,Part VI:Preliminary calculation of aerodynamic,thrust and power characteristics.Ottawa:Roskam Aviation and Engineering Corporation;1987.p.550.
40.Jones PK,Weir J,Bonenfant D,Boyd EA,Burgin K,Carter EC,et al.Contribution of fin to sideforce,yawing moment and rolling moment derivatives due to sideslip,(Yv)F,(Nv)F,(Lv)F,in the presence of body,wing and tailplane.Denver:ESDU;1993.Report No.:82010.
41.Ciliberti D,Nicolosi F,Della Vecchia P.Aerodynamic interference issues in aircraft directional control.J Aerosp Eng 2015;28(1):04014048.
42.Risse K.Design of CeRAS CSR-01.Aachen:ILR RWTH Aachen University;2014.
43.Airbus.Flight crew operational manual A320.Toulouse:Airbus;2005.
44.XFOIL 6.99.Subsonic airfoil development system[Internet].Boston:MIT.[updated 2013 Dec 3;cited 2018 Jan 4].Available from:http://web.mit.edu/drela/Public/web/xfoil/.
2.Aeronautics and air transport beyond Vision 2020(Towards2050).Brussels:Strategy Review Group,The Advisory Council for Aeronautics Research in Europe;2010.
3.Busquin P,Argu¨elles P,Bischoff M,Droste BAC,Evans RH,Kro¨ll W,et al.European aeronautics:A vision for 2020-Asynopsis.Air Sp Eur 2001;3(s 3-4):16-8.
4.Darecki M,Edelstenne C,Enders T,Fernandez E,Hartman P,Herteman JP,et al.Flightpath 2050 Europe’s vision for aviation:Report of the High Level Group on Aviation Research Policy;2011.
5.ICAO.Historic agreement reached to mitigate international aviation emissions.Montreal:ICAO News Release;2016.[cited2018 Jan 2].Available from:http://www.icao.int/Newsroom/Pages/Historic-agreement-reached-to-mitigate-international-aviation-emissions.aspx.
6.European Commission Directorate-General for Climate Action.Proposal for a Regulation of the European Parliament and of the Council amending Directive 2003/87/EC to continue current limitations of scope for aviation activities and to prepare to implement a global market-based measure from 2021.COM/2017/054 final-2017/017(COD);2017.
7.European Commission Secretariat-General.Communication from the Commission to the European Parliament and the Council the Road from Paris:Assessing the implications of the Paris Agreement and accompanying the proposal for a council decision on the signing,on behalf of the European Union,of the Paris Agreement adopted under the United Nations Framework Convention on Climate Change.COM/2016/0110 final;2016.
8.Kroo I.Nonplanar wing concepts for increased aircraft efficiency.VKI lecture series on innovative configurations and advanced concepts for future civil aircraft;2005 Jun 6-10;Sint-GenesiusRode,Belgium.Sint-Genesius-Rode:The Von Karman Institute for Fluid Dynamics;2005.p.1-29.
9.Torenbeek E.Blended wing body and all-wing airliners.European Workshop on Aircraft Design Education(EWADE);2007 May 29-Jun 02;Samara,Russia;2007.
10.Anderson JD.The airplane:A history of its technology.Reston:AIAA;2002.
11.Torenbeek E.Advanced aircraft design.Chichester,West Sussex,UK:John Wiley&Sons,Ltd.;2013.
12.Frota J,Nicholls K,Whurr J,Mu¨ller M,Gall P,Loerke J,et al.New Aircraft Concept Research(NACRE):Final activity report.Sixth framework programme:Priority 4 Aeronautics and space;2010.Report No.:FP6-2003-AERO-1.
13.Sharma R.Basic aerodynamic study of joined wing[dissertation].Gurgaon:Amity University Haryana;2015.p.68.
14.Sanchez-Carmona A,Cuerno-Rejado C,Garcia-Hernandez L.Unconventional tail configurations for transport aircraft.Progress Flight Phy 2017;9:127-48.
15.Musa NA,Mansor S,Ali A,Man MHC,Omar WZW.Effect of tail dihedral angle on lateral directional stability due to sideslipangles.53rd AIAA aerospace sciences meeting;2015 Jan 5-9;Kissimmee,Florida,USA.Reston:AIAA;2015.
16.Musa NA,Mansor S,Ali A,Omar WZW,Latif AA,Perumal K.Effects of aircraft tail configurations on sensitivity to yaw disturbances.Appl Mech Mater 2014;629:197-201.
17.Zhang G,Yang S,Xu Y.Song Q.Numerical simulation of the aerodynamic characteristics of Vee-tail based on cluster system.ITESS 2008;823-7.
18.Zhang GQ,Yu SCM,Chien A,Xu Y.Investigation of the tail dihedral effects on the aerodynamic characteristics for the low speed aircraft.Adv Mech Eng 2013;2013:1-12.
19.Garc?′a-Herna′ndez L,Cuerno-Rejado C,Pe′rez-Corte′s M.Dynamics and failure models for a V-tail remotely piloted aircraft system.J Guid Control Dyn 2017;41(2):506-14.
20.Song L,Yang H,Zhang Y,Zhang H,Huang J.Dihedral influence on lateral-directional dynamic stability on large aspect ratio tailless flying wing aircraft.Chinese J Aeronaut 2014;27(5):1149-55.
21.Roskam J.Airplane design,Part II:Preliminary configuration design and integration of the propulsion system.first ed.Ottawa:Roskam Aviation and Engineering Corporation;1989.p.310.
22.Cuerno-Rejado C,Sanchez-Carmona A.Preliminary sizing correlations for the rear-end of transport aircraft.Aircr Eng Aerosp Technol 2016;88(1):24-32.
23.Hettema T.Vertical tail design.Development of a rapid aerodynamic analysis method[dissertation].Delft:Delft University of1094 Technology;2015.p.50.
24.Wang Y,Yin H,Zhang S,Yu X.Multi-objective optimization of aircraft design for emission and cost reductions.Chinese JAeronaut 2014;27(1):52-8.
25.Lucas S,Velazquez A,Vega JM.An optimization method for an aircraft rear-end conceptual design based on surrogate models.In:Ao SI,Gelman L,Hukins DWL,Hunter A,Korsunsky AM,editors.Proceedings of the world congress on engineering Vol III;2011 Jul 6-8;London,UK.Hong Kong:Newswood Limited;2011.p.2610-5.
26.Certification specifications:CS-25 Large aeroplanes.Cologne:European Aviation Safety Agency;2017.
27.Torenbeek E.Synthesis of subsonic airplane design.Dordrecht:Springer Netherlands;1982.p.598.
28.Roskam J.Methods for estimating stability and control derivatives of conventional subsonic airplanes.4th ed.Ottawa:Roskam Aviation and Engineering Corporation;1983.p.99.
29.Nicolosi F,Ciliberti D,Della Vecchia P,Corcione S,Cusati V.Acomprehensive review of vertical tail design.Aircr Eng Aerosp Technol 2017;89(4):547-57.
30.Khatri AK,Singh J,Sinha NK.Aircraft design using constrained bifurcation and continuation method.J Aircr 2014;51(5):1647-53.
31.Paranjape A,Sinha NK,Ananthkrishnan N.Use of bifurcation and continuation methods for aircraft trim and stability analysisA state-of the-art.J Aerosp Sci Technol 2008;60(2):85-100.
32.Central Reference Aircraft data System-CeRAS[Internet].Aechen:ILR,RWTH-Aechen-University[updated 2015 Aug 12;cited 2017 Dec 14].Available from:https://ceras.ilr.rwth-aachen.de/.
33.Code of Federal Regulations:Title 14-Chapter I-Subchapter C-Part 25.Washington,D.C.:Federal Aviation Administration;2017.
34.Lomax TL.Structural loads analysis for commercial transport aircraft:Theory and practice.Reston:AIAA Education Series;1996.p.275.
35.Melin T.A vortex lattice MATLAB implementation for linear aerodynamic wing applications[dissertation].Stockholm:Royal Institute of Technology(KTH);2000.p.45.
36.Polhamus EC.Charts for predicting the subsonic vortex-lift characteristics of arrow,delta,and diamond wings.Washington,D.C.:NASA;1971.Report No.:NASA TN D-6243.
37.Purser Paul E,Campbell John P.Experimental verification of a simplified Vee-tail theory and analysis of available data on complete models with Vee-tails.Washington,D.C.:NASA;1945.Report No.:NACA-TR 823.
38.Ciliberti D,Della Vecchia P,Nicolosi F,De Marco A.Aircraft directional stability and vertical tail design:A review of semi-empirical methods.Prog Aerosp Sci 2017;95:140-72.
39.Roskam J.Airplane design,Part VI:Preliminary calculation of aerodynamic,thrust and power characteristics.Ottawa:Roskam Aviation and Engineering Corporation;1987.p.550.
40.Jones PK,Weir J,Bonenfant D,Boyd EA,Burgin K,Carter EC,et al.Contribution of fin to sideforce,yawing moment and rolling moment derivatives due to sideslip,(Yv)F,(Nv)F,(Lv)F,in the presence of body,wing and tailplane.Denver:ESDU;1993.Report No.:82010.
41.Ciliberti D,Nicolosi F,Della Vecchia P.Aerodynamic interference issues in aircraft directional control.J Aerosp Eng 2015;28(1):04014048.
42.Risse K.Design of CeRAS CSR-01.Aachen:ILR RWTH Aachen University;2014.
43.Airbus.Flight crew operational manual A320.Toulouse:Airbus;2005.
44.XFOIL 6.99.Subsonic airfoil development system[Internet].Boston:MIT.[updated 2013 Dec 3;cited 2018 Jan 4].Available from:http://web.mit.edu/drela/Public/web/xfoil/.