Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts

Fields, Roger A. and Richards, W. Lance and DeAngelis, V. Michael (2004) Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts. Technical Report NASA/TM-2004-212039, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

A structural test requirement of the National Aero-Space Plane (NASP) program has resulted in the design, fabrication, and implementation of a combined loads test fixture. Principal requirements for the fixture are testing a 4- by 4-ft hat-stiffened panel with combined axial (either tension or compression) and shear load at temperatures ranging from room temperature to 915 °F, keeping the test panel stresses caused by the mechanical loads uniform, and thermal stresses caused by non-uniform panel temperatures minimized. The panel represents the side fuselage skin of an experimental aerospace vehicle, and was produced for the NASP program.
A comprehensive mechanical loads test program using the new test fixture has been conducted on this panel from room temperature to 500 °F. Measured data have been compared with finite-element analyses predictions, verifying that uniform load distributions were achieved by the fixture. The overall correlation of test data with analysis is excellent. The panel stress distributions and temperature distributions are very uniform and fulfill program requirements. This report provides details of an analytical and experimental validation of the combined loads test fixture. Because of its simple design, this unique test fixture can accommodate panels from a variety of aerospace vehicle designs.

EPrint Type:	NASA Technical Memorandum
Keywords:	Metal matrix composites, Reusable launch vehicles, Strain gages, Structural analysis, Structural testing
Subjects:	Aircraft/Project: Nonaircraft-specific (31 - 39) Engineering: (39) Structural Mechanics
ID Code:	15
Deposited On:	14 Febuary 2006
Additional Information:	64 pages.