Home Contact Sitemap

DTD Handbook

Handbook for Damage Tolerant Design

  • DTDHandbook
    • About
    • Contact
    • Contributors
    • PDF Versions
    • Related Links
    • Sections
      • 1. Introduction
      • 2. Fundamentals of Damage Tolerance
      • 3. Damage Size Characterizations
      • 4. Residual Strength
        • 0. Residual Strength
        • 1. Introduction
        • 2. Failure Criteria
        • 3. Residual Strength Capability
        • 4. Single Load Path Structure
        • 5. Built-Up Structures
          • 0. Built-Up Structures
          • 1. Edge Stiffened Panel with a Central Crack
          • 2. Centrally and Edge Stiffened Panel with a Central Crack
          • 3. Analytical Methods
          • 4. Stiffener Failure
          • 5. Fastener Failure
          • 6. Methodology Basis for Stiffened Panel Example Problem
          • 7. Tearing Failure Analysis
          • 8. Summary
        • 6. References
      • 5. Analysis Of Damage Growth
      • 6. Examples of Damage Tolerant Analyses
      • 7. Damage Tolerance Testing
      • 8. Force Management and Sustainment Engineering
      • 9. Structural Repairs
      • 10. Guidelines for Damage Tolerance Design and Fracture Control Planning
      • 11. Summary of Stress Intensity Factor Information
    • Examples

Section 4.5.6. Methodology Basis for Stiffened Panel Example Problem


Figure 4.5.16.  Riveted Panel with a Central Crack Between Two Stringers

In this subsection, the specific details are covered which are associated with conducting the stress-intensity factor analysis as well as the analysis to determine the stresses in the stringers and fastener loads.  To simplify the detailed calculations, it is assumed that only one fastener (rivet) on either side of the crack is active, as shown in Figure 4.5.17 and that this rivet is assumed to be rigid.  Thus, there is only one unknown fastener force F transferred between the stringers and the skin by this rivet.

Figure 4.5.17.  Stiffened Structure Broken into Components

Typically, the analysis proceeds by splitting up the structure shown in Figure 4.5.16 into its component parts as shown in Figure 4.5.17.  The unknown force F can be calculated from the displacement compatibility condition between the skin and the stringer.  The complicated expressions which correspond to the displacements Vs, VF, and VP due to the applied stress, s, the fastener force F and the distributed pressure P(x), respectively, can be obtained using a procedure suggested by Westergaard [1939] and by Love [1944].  The detailed discussions on the methods of obtaining the required relationships are presented by Broek [1974].  The necessary relationships for Vs, VF, Vp and Vst (displacement in the stringer) are given as:















The geometric variables r, r1, r2, q1, q2 and q are shown in Figure 4.5.18.  The displacement compatibility condition requires equal displacements in corresponding points of sheet and stringer; it yields the following equation to calculate the unknown fastener force F.

Figure 4.5.18.  Geometrical and Displacement Parameters Relative to the Crack Tip


Vs + VF + Vp = Vst


substituting the expressions 4.5.6 - 4.5.9 for Vs, VF, Vp, and Vst in the above relationship, and reassembling, we get


The next step is to obtain an expression for the stress-intensity factor for the entire stiffened panel configuration.  Using superposition, the stress-intensity factor is obtained as the sum of the stress-intensity factors for the three cases shown in Figure 4.5.17.  It can easily be seen that for Case I: K = sÖpa and for Case II: K = 0.  The stress-intensity factor (K) for Case III is a fairly complicated expression and it is given by,






where  are normalized with respect to the rivet pitch.  The estimation of KIII requires solution of the above integrals by numerical methods.  Replacing the fastener force F by the expression and rearranging the expression for KIII, the stress-intensity factor K for the stiffened panel then becomes






The stress-intensity factor K can be finally expressed in the following form,






To calculate K for a given stiffened panel the values of Fs, fF, fp, fst, and l1 have to be obtained.  These variables are numerically calculated and plotted as shown in Figures 4.5.19 to 4.5.23 for various values of .  For the given example data, we can now construct the residual strength diagram using the values obtained from these plots.

Figure 4.5.19.  Normalized Panel Displacement Function (fs /p) Due to Applied Stress vs. Normalized Crack Length (a/p) for Various Stringer Spacing (s=S/p)

Figure 4.5.20.  Panel Displacement Function Due to Fastener Force vs. Normalized RivetDiameter (d/p) for All Stiffener Spacings

Figure 4.5.21.  Normalized Panel Displacement Function (Fp /p) Due to Crack Distributed Pressure Along Crack vs. Normalized Crack Length (a/p) for Various Stringer Spacings (s=s/p)

Figure 4.5.22.  Stringer Displacement Function vs. Normalized Rivet Diameter (d/p) for Various Halfinger Widths


Figure 4.5.23.  Parameter l1 Vs. Normalized Crack Length (a/p) for Various Normalized Stringer Spacings (s/p)

For a critical crack size (2a) of 4.0 inch, what is the fracture strength and for an operating stress of 20 ksi, what is the critical crack size?


Structural Geometry and Material Properties for Example 4.5.1


The first step is to obtain the stress-intensity factor by means of Equation 4.5.21 that involves the parameters l1 and l2.  For various crack lengths, these two variables can be calculated using Equation 4.5.20.  The calculations involve the values of fs, fF, fp, fst and l which are obtained from the plots for various values of  for the given  = 20 and d/p = 3/16.  Knowing the values of l1 and l2, the geometric parameter b can be estimated from Equation 4.5.22.  It is then straightforward to obtain the K vs. a plot by substituting the sets of values of a and b in the stress-intensity factor equation (K = sbÖpa) for a particular value of the applied stress s.  The

corresponding K vs. a plot is shown for s = 5, 10, and 15 ksi.  This figure shows that the stress-intensity factor decreases rapidly when the crack approaches the stringer.  The figure also shows the effect of stringer to panel thickness ratio on the stress-intensity factor.

Stress Intensity Factor Diagram for Panel and Riveted Stringers

The next step is to apply a failure criterion to evaluate the fracture stresses, scr, for various crack sizes.  Assuming that the material exhibits negligible subcritical crack growth, the fracture toughness failure criterion (K = Kcr) based on the plane stress condition can then be applied.  For K = Kc in Equation 4.5.12, sf can be evaluated for a particular crack size and the corresponding b which was obtained through Equation 4.5.22.  The residual strength diagram, i.e., the plot of sf vs. ac for the given data (Kc = 65 ksiÖin), is shown in the following figure.

Residual Strength Diagram for Panel and Riveted Stringers (Light Stringers)

The residual strength curves of the fastener and stiffeners are obtained by combining the equations for fastener failure and the equations stringer failure.  The corresponding equations are given by:




where l is a function of a, and the values of l for various crack lengths can be obtained using the Equation 4.5.16.  To obtain this Equation 4.5.24, note that the maximum stringer load (Pmax) is the source of the fastener force (F = sl) and the remote stringer force (sAs).  The composite residual strength diagram as shown in the figure above contains the three failure curves corresponding to panel, stringer, and fastener.  The stringer failure curve corresponds to a = 1 (light stringer).

For the crack length given (2a = 4 inches), the corresponding residual strength is found from the figure for a half crack length (a) of 2 inches.  Point A in this figure identifies the skin failure condition which occurs at a stress level of 25.9 ksi.  For the operating stress level of 20 ksi, the panel can be effective without catastrophic failure for cracks with length less than the critical crack (acr) of 3.4 inch (note 2acr = 6.8 inch).  If the panel develops a crack less than acr, it will not fail by unstable crack growth.  However, for any other crack size which is equal or

Assume that the panel develops a crack of size acr.  At point B in the figure, the crack extends rapidly.  When the rapidly extending crack becomes 15 inches, the stress level in the stiffener (point C) reaches its critical value and the stiffener fails.  Due to the stiffener failure, the stiffener becomes ineffective, leading to the total failure of the panel without any crack arrest possibilities.

In the next figure, the stiffener failure curve is plotted for a strong stiffener with a = 4 (the stiffener thickness if “assumed” four times the panel thickness).  If the panel develops a crack size acr, the crack will extend rapidly from point D to point E as shown in the next figure.  At point E, the fastener fails, leading to an ineffective stringer (loads are no longer transferred to the stringer).  Thus, the failure of the panel is unavoidable and the unstable crack growth without effective crack arrest leads to the total failure of the structure.

Residual Strength Diagram for Panel and Riveted Stringers

(Heavy Stringers)