Abstract
A description is presented of the salient structural features and technical approach employed in the design of a high-performance light aircraft stressed to 8 g limit loads. This design exercise is analytical in scope only and is intended to show the feasibility of constructing primary airframe structures from fibrous composite materials. The results of minimum weight analyses of both fluted core and honeycomb core sandwich panels are presented, and their use in the selection of final sandwich geometry is detailed. Curves are presented showing the variation in elastic properties with changes in fiber orientation angle for typical basic laminate patterns employed in the air-frame components. The tradeoff in fiber orientation angle to obtain the best balance between transverse buckling stiffness and longitudinal stretching stiffness is discussed, together with expected strength performance of the oriented fiber laminates under static and dynamic loadings.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
