Testing and Analysis of a Composite Non-Cylindrical Aircraft Fuselage Structure, Part I: Ultimate Design Loads

Przekop, Adam; Jegley, Dawn C.; Lovejoy, Andrew E.; Rouse, Marshall; Wu, Hsi-Yung T.

doi:10.2514/6.2016-2176

Cited by 9 publications

(7 citation statements)

References 15 publications

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“…Additional results are presented in Refs. [25,[28][29][30]33]. First, results are shown for DUL test 8 with internal pressure only, and DUL tests 3 and 9 with mechanical load of pitch up only.…”

Section: Resultsmentioning

confidence: 99%

“…Manufacturing imperfections of the crown panel OML surface resulted in a rework of some sections of the crown panel [28] before the final assembly of the test article. The presence of the repair patches was accounted for in the FEM.…”

Section: Resultsmentioning

confidence: 99%

“…Strain gauge results in the skin of the upper bulkhead indicate that buckling occurred and are shown in Ref. [28]. Nonlinear FEA of the test article with DSD to the crown panel indicated that there would be no catastrophic failure at load less than DUL in the pitch-up load condition.…”

Section: B Pitch Up (Tests 3 and 9)mentioning

confidence: 88%

“…and −0.0104 in:∕in:, respectively. Note that the magnitude of the failure tensile strain is greater than the failure compressive strain [28] and the forward notch tip buckled inward while the aft notch tip buckled outward. The crown continued to support load well past these initial failures because most of the load was carried by the frames rather than through the skin.…”

Section: B Pitch Up (Tests 3 and 9)mentioning

confidence: 99%

“…Additional results are presented in Refs. [28][29][30].…”

Section: Instrumentationmentioning

confidence: 99%

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Structural Response of a Stitched Composite Hybrid Wing Body Center Section

Jegley

Przekop

Lovejoy

et al. 2021

Journal of Aircraft

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Hybrid wing body is a fuel-efficient aircraft configuration where the pressurized center section is confined by almost-flat panels jointed at right angles. The combination of internal pressure and in-plane loads imparts cyclic large out-of-plane deformations to the noncircular fuselage. These repeated pressure loads would lead to separation between the skin and flanges and delaminations in traditional layered composite structure. To address this challenge, researchers at NASA and The Boeing Company selected the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS) concept, an integrally stiffened panel design that is stitched together and designed to maintain residual-load-carrying capabilities under a variety of damage scenarios. Analytical and experimental results of the structural response of an all-composite 80%-scale hybrid wing body center section are presented herein. Internal pressure and mechanical loads representative of flight loads and certification requirements were imparted to the pristine and damaged structure. The pristine structure, the structure with barely visible impact damage, and the structure with discrete source damage all supported design ultimate load and displayed significant nonlinear response. Based on comparison with the test data, the finite element analysis performed before testing accurately predicted deformations, strains, and onset of localized buckling for the load cases considered.

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Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

Section: B Pitch Up (Tests 3 and 9)mentioning

confidence: 88%

Section: B Pitch Up (Tests 3 and 9)mentioning

confidence: 99%

“…Additional results are presented in Refs. [28][29][30].…”

Section: Instrumentationmentioning

confidence: 99%

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Structural Response of a Stitched Composite Hybrid Wing Body Center Section

Jegley

Przekop

Lovejoy

et al. 2021

Journal of Aircraft

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Research on Setting Method of Neutral Plane Offset of Shell Element in PRSEUS Panel Structure Modeling

Zhang

2021

2021 12th International Conference on Mechanical and Aerospace Engineering (ICMAE)

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Lessons Learned from Large-Scale Aerospace Structural Testing

Lovejoy,

Jegley,

Hilburger

et al. 2023

AIAA Journal

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Large-scale testing of aerospace structures is frequently the final step in a development project to validate the structural performance, and that step typically involves a large cost and time investment. To ensure that the testing provides the required data, avoiding errors that can result in an unsuccessful test and failure to meet objectives is critical. Five lessons learned are presented herein to provide insight to those conducting large-scale tests to help them avoid known pitfalls that may result in an unsuccessful test. Five large-scale tests are described, and they include two composite wing tests, a full-scale 27.5-ft-diam metallic barrel test, an 8-ft-diam metallic barrel test, and a composite hybrid-wing–body center section test. Problems identified during the testing and mitigation approaches to solve the problems are presented, and then the lessons learned are identified and discussed.

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Testing and Analysis of a Composite Non-Cylindrical Aircraft Fuselage Structure, Part I: Ultimate Design Loads

Cited by 9 publications

References 15 publications

Structural Response of a Stitched Composite Hybrid Wing Body Center Section

Structural Response of a Stitched Composite Hybrid Wing Body Center Section

Research on Setting Method of Neutral Plane Offset of Shell Element in PRSEUS Panel Structure Modeling

Lessons Learned from Large-Scale Aerospace Structural Testing

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