NASA NACA-TN-1222-1947 Buckling stresses of simply supported rectangular flat plates in shear《受剪的简支矩形平板和屈曲应力》.pdf

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1、A.%J.%,NATIONAL ADVISORY COMM,.BUCKLINGFOR AERONAUTICSTECHNICAL NOTENo. 1222STRESSES OF SIMPLY SUPPORTED RECTANGUIM.RFLAT PLATES IN SHEARBy Manuel Stein and John Neffangley Memorial Aeronautical LaboratoryLangley Field, Va.WashingtonMarch 1947 AFM9C TEGH:!2:iL L3RARYkL 2811:. =-a+,-i=.a=._-.-.=-E=-.

2、-. .,- Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-.,TECH LIBRARY KAFBsNM .I!lllllllll!lullllslllllllllllll.iJL445b2NATIOITALABVISORYCOMM33?12EEF .AEROHNJTICSEUCKLINGEYmE3sFJs OF SIMPLYSU2?POR13?DmFItATPLATEsINsfIEARBy ManuelSteinandJohnNeffThe p

3、resentpaperevaluatesthe shearbucklingrectanguif m+ n is odd, p + q mustalsobe odd. Each of thehomogeneouslinearequations(5) centhereforeinvolveonlycoefficientsO.l for whicli 1 + J iseitheroddor even. The Getof equatioL (5)canthereforebedividedIntotwoindependentgroups whichcanbo SOIVGdseparately,oneg

4、roupconsistingof equationsin which i + J is oddandtheothergroupconsistingof equationsin which i + j is event Thesetof equationsin which i + J is evencorrespondsto symetricbucHinthanthelmest alueof ksobtainedfromany tenth-orderdeterminantin which i + is eventIWEERENCES1.Timoshenko,S*: TheoryofElaticS

5、tabilitylJoGraw-HillBockCo. Zac.,1936,po525, 357-363* % “91 .1.0 9.35 I-I-63l.m -0.070 0.293 4 .V -00?3 o. one large buckle (symmetric buckling),NAI IONAL ADVISORYCOMMITTEE FM AERONAUTICS.(b) Length-width ratio, 2,5; two large buckles (antisymmetric buckling).Figure 2.- Buckling configurations of si

6、mply supported rectangularflat plates in shear.I J.,=Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I NACA TN No. 1222 Fig. 3NATlONAL ADVISORYCOMMITTEE FOR AERONAUTICS!Figure3.- Coordinate system for rectangular flat plate.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-