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.Fields, Roger A. and Richards, W. Lance and DeAngelis, Michael V.Armstrong Flight Research CenterFABRICATION; NATIONAL AEROSPACE PLANE PROGRAM; PANELS; STRUCTURAL ENGINEERING; COMPRESSION LOADS; REUSABLE LAUNCH VEHICLES; MECHANICAL PROPERTIES; TEMPERATURE DISTRIBUTION; THERMAL STRESSES; FINITE ELEMENT METHOD; FUSELAGES; METAL MATRIX COMPOSITES; STRAIN GAGES; NONUNIFORMITY; SHEAR STRESS...