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DTD Handbook

Handbook for Damage Tolerant Design

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    • Sections
      • 1. Introduction
      • 2. Fundamentals of Damage Tolerance
      • 3. Damage Size Characterizations
      • 4. Residual Strength
      • 5. Analysis Of Damage Growth
        • 0. Analysis Of Damage Growth
        • 2. Variable-Amplitude Loading
        • 3. Small Crack Behavior
        • 4. Stress Sequence Development
          • 0. Stress Sequence Development
          • 1. Service Life Description and Mission Profiles
          • 2. Sequence Development Techniques
          • 3. Application of Simplified Stress Sequences for Design Studies
        • 5. Crack Growth Prediction
        • 6. References
      • 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 5.4.0. Stress Sequence Development

In order to predict the crack-growth behavior of an aircraft structure, the designer needs to know the sequence of stress cycles applied during the life of the structure.  This stress history for a new design is developed from the service life requirements and the mission profile information specified by the procurement activity.  Based on this information a repeated load history due to ground handling, flight maneuvers, gusts, pressurization, landing, store ejection, and any other load source is developed.  The stress history at any given point is then determined from the applicable load/stress relations.  Giessler, et al. [1981] describes this procedure in detail. 

This section will outline the necessary steps and illustrate the development of a simplified stress sequence for the purpose of showing the effect of various sequence characteristics on crack-growth behavior.  Understanding of these effects is of great importance in determining the damage tolerance of a structure.