1、d-. .%NATIONAL ADVISORY COMMITTEEFOR AERONAUTICSTECHNICAL iWTENo. 1310CHARTS FOR STRESS ANALYSIS OF REINFORCED CIRCULARCYLINDERS UNDER LATERAL LOADSBy Joseph Kempner and John E, DubergLangley Memorial Aeronautical LaboratoryLangley Field,. Va.WashingtonMay 1947Provided by IHSNot for ResaleNo reprodu
2、ction or networking permitted without license from IHS-,-,-.-.ERRATUM1NACA TN 1310CHARTSFOR STRESS ANALYSIS OF REINFOFED CIR-CYLmlmSmmBy Joseph Kempner and John E. DubergMay 1947Figure 40: When the curves for Csto in this figure were fainsd inbetween the computed points, the fairhgs for values of A/
3、B of 30and 100 were inadvertently reversed in the cross-over region nearh;82Lr Thh curves should be identical, except for sign, witho in figure 33, for which the fairings are correct.Values of the coefficient CHto can therefore be obtained from thelatter curvei with aigus reversed.H.4CA-LEJ - 104H4
4、- 776., - . . -,- .-. ,.- . ,1*IProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-%uNATRX?ALADVISORYC!OMMZITEEFOR KEWX?AUTICS.Z!Fmmcm ml!t? Iic a71 1310CH4RTSFOR SZRESS AT?ALYSIS OF FWORC!ED C12?CWCYLINDERS UMDER LAT!E3WL LOABy JosephKempnerandJohn3. D
5、uberis Ehowntolm inadcmuatefor thest,in.40 . . . . . .0 . . . . . . . . ,. . . , . . , . . . O.0*0I,in. . . . . . . . . . . . . . . . . . . . . . . . . . .o.04001.i?dncethecylinderhasno lontuMnal reinforcements,tf=Xt=o.0320 In. In reference4 Youngfsmodulusis takenas 10.6x 103 ksiend theshearmodulusa
6、s 4,00x 103ksi.Consequently,A= 156 x 0.03A3 s 27000.04001% 153al-laA-=BThe values of4.00x 103x 0.032x & -1020.l10.6x 10SX 0.0kO02X 15A end A/Bfromthechartthatarenearesttothe ccqyutedvaluesare “A=2x104,/”a71wandProvided by IHSNot for ResaleNo reproduction or networking permitted without license from
7、IHS-,-,-NACATN 0.1310 9The coefficientsfor loaW and stressesthatcorrespcmdtoa radialloadon thecylinder,therefore,are o%tainedfrcm thecurvesAcorrespondingto = 103 in figures18 to 22a71 The coefficientscanbe convertedto 10W ard stresses with the aid of the formulasgiven in the charts and izea in table
8、 1. The coefficientsfor%endtigmomentsin thekingsand shearflowsin thesheetforthisexampleareplottedinfiguresh8 and 49 wherecoefficientsdeterminedby othermethodsof analysisandby experhnentare alsoplottedfor comgmrison.SimPIY sup-portedcylindera71- f me e zed thepreviousyroblemisnow consideredSWPZY supp
9、ortedat theendringsandrd.iaUy loadedat themtda,lering (seesketchin figs X) theelementaryshearflowconsistent with this methodof supportmmt he computed,and the coigcti shearflowdue to thedistortionof thecylindercanlm determinedfromfigure21 (A= 2 x 104=a+= 03) a71 As time fi tie sectm of present paper.
10、entitled mpmcmm03msraf CHPECS,1the coefficients forr%stressesand loadscan be obtaineddirectlyfromthecharts(figs.18 to 20). The elementaryshearflowinbay O isA curvefor shear-flowcoefficientscorrespcmMmgto thisstandard.solutionis giveninfigure. The correctionshear-flowcoefficientsare determinedfrcnnfi
11、gure21 by su,tracthnof theAcoefficientsgivenby thecurvefor = O frcmWose givcm%Y theAcurvefor = 103. Thesecorrectionsareplottedin figure50a71Aaaitfm of theelementaryant correction-coefficientcurvesyieldsthecurvefor thetotalshear-flowcoefftcient$whichis alsoehomtn ftgum 50. Becauseof the setry of load
12、tig,tieshem-flcoefficientsforbay -1are thenegativeof thecorrespcdingcoefficientsforbay O.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-10 NACATN NO. 110. . REFERENCESJ1 Dulerg,John E., and Keqn.er, Joseph: Stress Analysis l.vRecurrence.Fornrul.aofR
13、einforcedCirculsrCyllndersunderLateralLcatls.NACA No. 1219,1.947. .2.Wignot,J. E., Cos, Henry,endEnsrud,A. F.: AnalysisofCircularShell-Supporte&Framesa71 NACA NO.,%9, 194k,3.”Eoff,N. J.: Stresses in a ReinforcedMonocoque Cylinder underConcentrated SymmetricTransverseZuatts.Jour.Appl.Mech.,vol.11,no.
14、 4, NC. 1944, 2P- A-235 - A-2394. Kuhn,Paul,Duberg,JohnE., andGriffith,GeorgeE.: The Wfec% of ConcentratedLoadsonFlexibleRingsin CircularShells. NACAARRNo. L5H23j1945.5.Wise,JosephA.: Analysisof CircularRimgsorMonocoqueFuelages.Jour.Aero.Sci.,vol. 6, no. U, Septa 1939,pp. 460-463,wrProvided by IHSNo
15、t for ResaleNo reproduction or networking permitted without license from IHS-,-,-TKECEI.-MXQKUASFWR-U)ADSANDSTKESSMsign Om.vention is shown h figure !2 - . . .IQuantity *A3m acdaba Radial led, P %m.genkkl lend, T hkmkalt load, MI shearingfovce g= cd = -v+ Vq = c, V$ Vp=%m:=v+IL *Sl”i?Provided by IHS
16、Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1310DF&Bay K-2 I-io iI Ring -2-1012Figure 1.- Part of infinitely long cylinder.rr-1L TJn- 0 )0NATIONAL ADVISORYCOMHITTSE Fm AERONAUTICS.Figure 2.- Sign convention,Provided by IHSNot for ResaleNo reproducti
17、on or networking permitted without license from IHS-,-,-Fig. 3 NACA TN No. 1310.Ia.P.Figure 3.- Ring bending-moment coefficients for radial load.(A = 2 x 102.)rProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN NO. 1310Figure 4.- Ring axid.-load
18、(A =2xFig. 4.coefficients for radial load.102.)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 5 NACA TN No. 1310IFigure 5.- Ring transverse-shear coefficients for radialload.(A = 2 x 102. )Provided by IHSNot for ResaleNo reproduction or network
19、ing permitted without license from IHS-,-,-NACA TN NO. 1310Fig. 6Figure 6.- Skin shearow coefficients for radid led.(A = 2 x 102.)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 7Figure 7.- Skin direct-stress coefficients.(A=2 X102. )NACA TN No.
20、 1310at rings for radial load.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-a71NACA TN NO. 1310Fig. 8Figure 8.- Ring bending-moment coefficients for tangenti load.(A = 2 x 10?)Provided by IHSNot for ResaleNo reproduction or networking permitted wit
21、hout license from IHS-,-,-Fig. 9 NACA TN NO. 1310a71.r. Figure 9.- Ring axial-load coefficients(A = 2 X 1020)for tangential load.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NACA TN No. 1310.Fig. 10,.Figure 10.- R transverse-shear coefficients for
22、 tangential load,(A = 2 x 102.)1Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 11 NACA TN No. 1310m.I* i1.)Figure 11. - Skin shear-flow coefficients for tangential load.(A = 2 X 102.)r.,Provided by IHSNot for ResaleNo reproduction or networking
23、 permitted without license from IHS-,-,-.a71NACA TN No. 1310 Fig. 12tFigure 12. - Skin direct-stress coefficients at rings for tangential load.(A = 2 X 102.)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 13 NACA TN No. 1310.IFigure 13. - Ring b
24、ending-moment coefficients for moment load.(A = 2 x 102.)rIProvided by IHS Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA TN No. 1310 Fig. 14.,3. Fie 14.- Ring axial-load coefficients for moment load.(A = 2 x 102.)IProvided by IHSNot for ResaleNo reproductio
25、n or networking permitted without license from IHS-,-,-Fig. 15NACA TN No. 1310.=Figure 15. - Ring transverse-shear coefficients for moment load.(A=2 x102.).a71Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA TN NO. 1310 Fig. 161I1Figure 16. - Sh
26、 shear-flow coefficients for moment load.(A = 2 x 102.).Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Fig. 17 NACA TN No. 1310.I,a71.a71Figure 17. - Skin direct-stress coefficients at rings for moment load.(A = 2 x 102.)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.NACA TN No. 1310 Fig. 18,Figure 18.- Ring bending-moment coefficients for radial load.(A = 2 x 104)Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
