Design, analysis, and fabrication of a pressure box test fixture for tension damage tolerance testing of curved fuselage panels

Smith, P. J.; Bodine, J. B.; Preuss, C. H.; Koch, W. J.

A pressure box test fixture was designed and fabricated to evaluate the effects of internal pressure, biaxial tension loads, curvature, and damage on the fracture response of composite fuselage structure. Previous work in composite fuselage tension damage tolerance, performed during NASA contract NAS1-17740, evaluated the above effects on unstiffened panels only. This work extends the tension damage tolerance testing to curved stiffened fuselage crown structure that contains longitudinal stringers and circumferential frame elements. The pressure box fixture was designed to apply internal pressure up to 20 psi, and axial tension loads up to 5000 lb/in, either separately or simultaneously. A NASTRAN finite element model of the pressure box fixture and composite stiffened panel was used to help design the test fixture, and was compared to a finite element model of a full composite stiffened fuselage shell. This was done to ensure that the test panel was loaded in a similar way to a panel in the full fuselage shell, and that the fixture and its attachment plates did not adversely affect the panel.

Document ID

19950022418

Acquisition Source

Legacy CDMS

Document Type

Conference Paper

Authors

Date Acquired

September 6, 2013

Publication Date

January 1, 1993

Publication Information

Publication: NASA. Langley Research Center, Third NASA Advanced Composites Technology Conference, Volume 1, Part 2

Subject Category

Accession Number

95N28839

Funding Number(s)

Distribution Limits

Public

Work of the US Gov. Public Use Permitted.

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