Stress Distribution in Stiffened Panels Under Compression

Sechler, E. E.

doi:10.2514/8.421

Cited by 10 publications

(4 citation statements)

References 1 publication

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“…1 in the manner developed by Sechler. 1 Three types of curves appear. Curves of the first type, including curves 4 to 7, are intended to follow the progress of a certain type of panel as the panel load is increased, defining the fashion in which the effective width decreases after initial buckling.…”

Section: A Number Of Investigators Have Developed Curvesmentioning

confidence: 99%

Measurement of Stiffener Stresses and Effective Widths in Stiffened Panels

Dickinson

1939

Journal of the Aeronautical Sciences

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In the design of a stressed skin metal airplane it is essential that correct stiffener stresses and effective widths of skin acting with the stiffener be known in order to insure that fictitious margins of safety in wing and fuselage analyses are not shown. In this paper the problem of determining these stresses and effective widths is discussed and some experimental results from Lockheed tests are presented. An experimental method is described which makes possible the accurate determination of these quantities, employing extensometer strain data interpreted by means of a compression stress-strain curve for the stiffener. NOMENCLATURE t s = Skin thickness (inches). PT = Total panel load in lbs. (TST = Stiffener stress in lbs. per sq.in. AST = Stiffener area in sq.in. b = Stiffener spacing (inches). n = Number of equal bays in test panel. W e -Total effective width of skin on test panel (inches). w e = Half the total effective width acting with each stiffener (inches). L = Panel length (inches). X = \/E/

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Section: A Number Of Investigators Have Developed Curvesmentioning

confidence: 99%

Measurement of Stiffener Stresses and Effective Widths in Stiffened Panels

Dickinson

1939

Journal of the Aeronautical Sciences

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“…Beginning in the 20th century, basic researches have been done to identify and formulate the critical elastic stress of local buckling 1,2 . The findings of these researches led to the introduction of an effective width method.…”

Section: Introductionmentioning

confidence: 99%

“…In general, these members usually fail either by local buckling or by lateral-torsional buckling (LTB).Beginning in the 20th century, basic researches have been done to identify and formulate the critical elastic stress of local buckling. 1,2 The findings of these researches led to the introduction of an effective width method. Subsequent experiments were performed to capture the postbuckling behavior of compression plates, which is the basis of existing design regulations using the ultimate strength capacity of structural elements for economic design.…”

mentioning

confidence: 99%

Flexural design curves of steel plate I‐girders at elevated temperatures: I‐girders with yield or local buckling failure mode

Rasoulnia,

Broujerdian,

Ghamari

et al. 2023

Structural Design Tall Build

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SummaryThe present study was undertaken to characterize the structural behavior and ultimate flexural strength of steel plate I‐girders under pure flexural moment at elevated temperatures. A novel design procedure along with flexural design curves was proposed to predict the flexural behavior of the I‐girders and estimate corresponding ultimate flexural strengths. The main strategy of the procedure is to find an ambient‐temperature equivalent of the I‐girder by quantifying and formulating the effects of elevated temperatures. The proposed procedure comprises overall and partial phases. The former phase deals with the determination of equivalent laterally unbraced length, and the latter phase addresses the equivalent web and compression flange slenderness parameters. The calibration factor was defined to adapt the design curves to the effects of high compression flange slenderness parameters and residual stress at elevated temperatures. To generate comparative results, a numerical study was conducted by analyzing 216 finite element (FE) models. Fifty‐four out of 216 FE models with different cross‐sectional elements were dedicated to the I‐girders fail by yield or local buckling failure mode, the results of which are reported in the present paper. Data fitting analysis was carried out to capture the variation of calibration factor with respect to compression flange slenderness parameters. By calibrating the proposed design procedure, the results were converged and, therefore, good conformity was reached between the numerical and parametric results.

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“…The total shear transferred from the side to the center stiffener is found as follows: The effective area of the stiffened sheet is calculated by means of Sechler's formula, 3 …”

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confidence: 99%

Stress Distribution in Reinforced Panels

Lin

1938

Journal of the Aeronautical Sciences

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T HE problem of "shear-lag" in the design of allmetal semi-monocoque wings has been investigated by R. J. White and H. M. Antz. 1 As presented there, the constants t\ and A T would have to be determined from test data and hence would involve considerable difficulty in applying the equation to practical cases. The empirical value of rj of 0.1175, as calculated from the White and Antz data, shows quite a deviation from the theoretical curve.The following analysis gives a rational method of calculation, which does not involve the use of constants obtained from test data on the particular panel to be designed. This gives a clearer comparison between the theoretical and test results.The lower value of T\ obtained by White and Antz is mainly due to the neglect of the effective width of sheet which is appreciable as compared to the small area of the stiffener.The change in modulus of rigidity after buckling is considerable. So instead of using an empirical factor calculated from the particular test, equations including the effect of the change during buckling are derived by the author in the following analysis.The following symbols are used: G = Shear rigidity G f = Modified shear rigidity for tension field = l /JL E = Modulus of elasticity r = Shearing stress 7 = Shearing strain t -Thickness of the sheet t x -Distance between two stiffeners A\ -Effective area of side stiffener A 2 = l / 2 Effective area of center stiffener Pi = Total load in side stiffener P2 = V2 Total load in center stiffener L = Total length of the panel 5 = Total shear transferred from the side stiffener to the center one u = Relative displacement of the two stiffeners.At x -0, u -UQ.Judging from the tests by different observers, after buckling, the sheet still carries the buckling shear stress in shear and only the surplus shear (r -r 0 ) in diagonal tension.Referring to Fig. 1 the loads in the side and center stiffeners are given by 4P,o P, -+-2o P 2 O Potr>4-o/~ buckling FIG. 1. -p M Pi = Pu + SGtydx; P 2 = P 2o -fGtydx the corresponding displacements of the stiffeners are Ml

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Stress Distribution in Stiffened Panels Under Compression

Cited by 10 publications

References 1 publication

Measurement of Stiffener Stresses and Effective Widths in Stiffened Panels

Measurement of Stiffener Stresses and Effective Widths in Stiffened Panels

Flexural design curves of steel plate I‐girders at elevated temperatures: I‐girders with yield or local buckling failure mode

Stress Distribution in Reinforced Panels

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