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Hybrid-Wing-Body Vehicle Composite Fuselage Analysis and Case StudyRecent progress in the structural analysis of a Hybrid Wing-Body (HWB) fuselage concept is presented with the objective of structural weight reduction under a set of critical design loads. This pressurized efficient HWB fuselage design is presently being investigated by the NASA Environmentally Responsible Aviation (ERA) project in collaboration with the Boeing Company, Huntington Beach. The Pultruded Rod-Stiffened Efficient Unitized Structure (PRSEUS) composite concept, developed at the Boeing Company, is approximately modeled for an analytical study and finite element analysis. Stiffened plate linear theories are employed for a parametric case study. Maximum deflection and stress levels are obtained with appropriate assumptions for a set of feasible stiffened panel configurations. An analytical parametric case study is presented to examine the effects of discrete stiffener spacing and skin thickness on structural weight, deflection and stress. A finite-element model (FEM) of an integrated fuselage section with bulkhead is developed for an independent assessment. Stress analysis and scenario based case studies are conducted for design improvement. The FEM model specific weight of the improved fuselage concept is computed and compared to previous studies, in order to assess the relative weight/strength advantages of this advanced composite airframe technology
Document ID
20140010063
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Mukhopadhyay, Vivek (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
July 24, 2014
Publication Date
June 16, 2014
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2014-2427
NF1676L-17674
Meeting Information
Meeting: AIAA Aviation Technology, Integration, and Operations (ATIO) Conference
Location: Atlanta, GA
Country: United States
Start Date: June 16, 2014
End Date: June 20, 2014
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
WBS: WBS 699959.02.22.07.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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