Analysis of a D-box fixture for testing curved stiffened aircraft fuselage panels in axial compression and internal pressure-Reference-Cited by-同舟云学术

Analysis of a D-box fixture for testing curved stiffened aircraft fuselage panels in axial compression and internal pressure

Published:1994-04-18 Issue: Volume: Page:
ISSN:
Container-title:35th Structures, Structural Dynamics, and Materials Conference
language:
Short-container-title:

Author:

Ambur Damodar¹,Cerro Jeffrey²,Dickson John³

Affiliation:

1. NASA, Langley Research Center, Hampton, VA

2. Lockheed Engineering and Sciences Co., Hampton, VA

3. Analytical Services and Materials, Inc., Hampton, VA

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1994-1345

Reference6 articles.

1. Cylindrical shell: Linear analysis (1607 Iblin. axial load) Undamaged 15.38 5.95 15.66 6.15 15.38 5.95 46.41 18.04 72 28 Damaged 18.96 8.17 4.40 6.11 18.97 8.12 42.33 22.35 65 35

2. Cylindrical shell: Linear analysis (2350 Iblin. axial load) Undamaged 16.77 4.42 17.17 4.68 16.77 4.41 50.70 13.51 79 21 Damaged 20.54 6.65 5.20 4.88 20.54 6.65 46.28 18.18 72 28 Cylindrical shell: Nonlinear analysis (1607 Iblin. axial load) Undamaged 14.60 6.98 14.59 6.98 14.60 6.98 43.79 20.94 68 32 Damaged 15.53 10.90 0.70 11.15 15.53 10.90 31.76 32.95 49 51

3. Cylindrical shell: Nonlinear analysis Undamaged 12.88 8.73 12.88 8.73 12.88 8.73 38.64 26.19 60 40 Damaged 16.39 11.60 - 0.16 9.02 16.39 11.69 32.62 32.31 50 50 Table 2. Summaryof D-box testfixturecrossbar axialforcesforcombinationsof internalpressureandaxial

4. contoursforthecylindricalshellwith 20-in. longlongitudinalcrack forcombined 9psig intemalpressureand 16001blin.axial compressionloading. Figure 14. Comparisonof hoop stressdistributionsfor

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1. Utilization of the Building-Block Approach in Structural Mechanics Research;46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference;2005-04-18

2. D-box fixture for testing stiffened panels in compression and pressure;Journal of Aircraft;1995-11