Civil aircraft composite material reinforced wallboard stringer rigidity determination method based on stability characteristics

Abstract

The invention belongs to the field of composite material body structure stability conformance verification, and provides a civil aircraft composite material stiffened wall plate stringer rigidity determination method based on stability characteristics, and a method for determining the minimum critical stiffness value of a stringer meeting the requirement that local buckling occurs before overall buckling in a failure mode of a composite material reinforced wallboard structure on the basis of known composite material stiffened wall plate skin laying layer information and stringer spacing. Basedon a composite material reinforced wall plate structure needing to be preliminarily designed, parameters of a skin laying layer are obtained through classical laminated plate theoretical calculation,a correction coefficient is obtained through combination of the stringer distance and an empirical curve fitted through tests, and the minimum rigidity value of a stringer is obtained through theoretical calculation. The method can be widely applied to the strength design work of the composite material structure airframe of the domestic civil aircraft, and plays a key role in shortening the design period, reducing the research and development cost, improving the structural economy and the like.

Description

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AI Technical Summary

Benefits of technology

This patented technology allows us to quickly identify if there are any issues with an airliner's frame made from composites or other materials during construction without having to take too much effort on them afterward. Additionally it provides technical means like compensating for weak spots caused by these materials while still maintaining their effectiveness over longer periods of use. Overall this makes the process more efficient and cost-effective compared to current methods such as trial manufacturing techniques.

Problems solved by technology

This patented technical problem addressed by this patents relates to improving the performance of composites made up from strong fibers like carbon fiber reinforce plastic materials due to their ability to resist compression without losing its shape during use. Existing solutions include adding extra layers at specific locations along the length of these weakly bonded plies, creating tough bridges within them through deformation mechanisms, or utilizing specialized techniques called Layer Shear Structure Thermodynamics ("LSTM"). These conventional approaches require extensive laborious calculations over many different scenarios and may result in poor reliance upon actual values provided by the manufacturer' s original model.

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