Conference Presentation: A System for Simulation Governance of Engineered Repairs of Composite Aircraft Structures
Abstract: Modern military aircraft = composite skins + metallic sub-structure. Verification of structural integrity of standard repairs is costly, and requires structural and strength analysis. Traditional closed-form analysis techniques are unrepresentative and unsuitable, but construction of detailed finite element models requires Finite Element Analysis (FEA) expertise. Therefore, computational system with these requirements is needed to accelerate decision-making:
- Validated/certified methods
- Closed-form and FEA-based
- Readily employed
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“At DST Group, we have effectively used StressCheck® over the last 10 years to determine accurate stress intensity factors. The results have been used to improve our residual strength and structural life estimates for aircraft in service with the Royal Australian Airforce, including C-130, P-3C and F/A-18 A/B. We have found it to be extremely easy to use and a very versatile code with which to create parametric models.
We have recently used StressCheck® to obtain improved stress intensity factor solutions (Improved stress intensity factors for selected configurations in cracked plates and Improved stress intensity factors for a single corner crack at a loaded fastener hole) for five key generic configurations. These transferable parametric results have been published externally. One specific example is the non-linear contact analysis of a cracked, filled fastener hole, with both fastener and remote plate loading.”
Dr. Manfred Heller, HeadStructural & Damage Mechanics, DST Group