Optimal Design of Composite-Material Panels for Business Aircraft 770453
Simple design equations and optimal design procedures have been developed for determination of the optimal lamination arrangement for flat panels of filamentary composite materials under a variety of design criteria. The design criteria include buckling and material failure under uniaxial compression, fundamental frequency of free vibration and panel flutter. The equations are applied to the design of a panel typical of business aircraft and subjected to multiple design criteria.
