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The Behavior of a Stitched Composite Large-Scale Multi-Bay Pressure BoxNASA has created the Environmentally Responsible Aviation (ERA) Project to develop technologies to reduce impact of aviation on the environment. A critical aspect of this pursuit is the development of a lighter, more robust airframe to enable the introduction of unconventional aircraft configurations. NASA and The Boeing Company have worked together to develop a structural concept that is lightweight and an advancement beyond state-of-the-art composite structures. The Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) is an integrally stiffened panel design where elements are stitched together and designed to maintain residual load-carrying capabilities under a variety of damage scenarios. With the PRSEUS concept, through-the-thickness stitches are applied through dry fabric prior to resin infusion, and replace fasteners throughout each integral panel. Through-the-thickness reinforcement at discontinuities, such as along flange edges, has been shown to suppress delamination and turn cracks, which expands the design space and leads to lighter designs. The pultruded rod provides stiffening away from the more vulnerable skin surface and improves bending stiffness. A series of building block tests were evaluated to explore the fundamental assumptions related to the capability and advantages of PRSEUS panels. The final step in the building block series of tests is an 80%-scale pressure box representing a portion of the center section of a Hybrid Wing Body (HWB) transport aircraft. The testing of this test article under maneuver and internal pressure loading conditions is the subject of this paper. The experimental evaluation of this article, along with the other building block tests and the accompanying analyses, has demonstrated the viability of a PRSEUS center body for the HWB vehicle. Additionally, much of the development effort is also applicable to traditional tube-and-wing aircraft, advanced aircraft configurations, and other structures where weight and through-the-thickness strength are design considerations.
Document ID
20160006307
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Jegley, Dawn C. (NASA Langley Research Center Hampton, VA, United States)
Rouse, Marshall (NASA Langley Research Center Hampton, VA, United States)
Przekop, Adam (NASA Langley Research Center Hampton, VA, United States)
Lovejoy, Andrew E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
May 17, 2016
Publication Date
April 1, 2016
Subject Category
Structural Mechanics
Composite Materials
Report/Patent Number
L-20630
NASA/TM-2016-218972
NF1676L-22992
Funding Number(s)
WBS: WBS 338881.02.22.07.01.01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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