This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Wing/Fuselage Structural Concept Study for a Subsonic Transport Aircraft
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1973 by SAE International in United States
Annotation ability available
Results of a brief study program to devise and evaluate new structural materials and concepts for a subsonic, transport-type aircraft are presented. Comparisons of several wing concepts to the state-of-the-art baseline concept indicate a weight saving of 10%, but with corresponding total cost increases of 50-75%. One fuselage concept indicates a 7% weight saving with a 5% total cost saving. Corresponding aircraft performance payoffs with and without resizing are also established. The overall payoffs are somewhat nominal, based on the new concept impact on participating structure only. Both baseline and new concept analyses are based on a common set of requirements for ultimate strength, fatigue life, damage tolerance, and flutter rigidity. The study is directed to metallic concepts.
CitationDeneff, G., "Wing/Fuselage Structural Concept Study for a Subsonic Transport Aircraft," SAE Technical Paper 730886, 1973, https://doi.org/10.4271/730886.
- “Preliminary Concept Evaluation for the Wing Carry-through Structure of an Advanced Metallic Air-Vehicle.” The Boeing Co. June 1972
- Rosenkrantz C. et al. “Advanced Lightweight Fighter Structural Concept Study.” Northrop Corp. July 1972
- Danielson G. R. Deneff G. V. et al. “Advanced Military Tanker Wing/Fuselage Structural Concept Study.” Douglas Aircraft Co. July 1972
- Pickard J. et al. “Format-Fortran Matrix Abstraction Technique.” V-VII December 1968
- Crawford R. F. Burns A. B. “Strength, Efficiency and Design Data for Beryllium Structures.” February 1962