Publication Date:
2019-07-13
Description:
A comparison is made of results obtained from mathematical programming and optimality criteria procedures for the minimum-mass design of typical aircraft wing structures to satisfy prescribed flutter requirements. The mathematical programming method is based on an interior penalty function approach. A rigorous optimality criterion and an intuitive optimality criterion based on uniform strain energy density are considered. An intuitive resizing procedure is used for both optimality criterion solutions. All results are calculated using the same computer program, changing only the optimization procedure. Both high- and low-aspect-ratio wings are examined. Finite elements are used for structural modeling, and the generalized coordinates for the flutter solution are based on the natural vibration modes of the structure.
Keywords:
STRUCTURAL MECHANICS
Type:
AIAA PAPER 74-405
,
Structures, Structural Dynamics and Materials Conference; Apr 17, 1974 - Apr 19, 1974; Las Vegas, NV; US
Format:
text
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