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  1. C

    Residual Strength Composites- Last Ply Failure-Purpose Vs FARs.

    A composite structure in an aircraft is stressed to limit or ult as the case calls for. Defects are introduced during manufacture and may be inflicted on the aircraft in service. The materials test programme will establish acceptable levels of damage viz-a-viz the far field allowable strain...
  2. C

    Composite Anisotropy

    A question for those interested in composite panel buckling. It has been a curiosity as to why edge shear on a typical panel or structure is generally treated as a positive value or magnitude. It seems to be a practice and for metallics, it would be reasonable to assume that as metal is more a...
  3. C

    Design Phase Product Integration Management- A new GA Aircraft

    I need to answer a question about a practical thing in aircraft design management...maybe you could help? Here goes......during the design phase, for PDR, all the systems have to be integrated into the wing, engines, fuel lines, landing gear, wiring, flight controls, the whole lot that bolts...

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