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Combined Loads Test Fixture For Thermal Structural Testing Aerospace Vehicle Panel Concepts
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781720447108 Total Pages :64 pages Book Rating :4.4/5 (471 download)
Book Synopsis Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts by : National Aeronautics and Space Administration (NASA)
Download or read book Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-29 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Book Synopsis Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts by : Roger A. Fields
Download or read book Combined Loads Test Fixture for Thermal-Structural Testing Aerospace Vehicle Panel Concepts written by Roger A. Fields and published by BiblioGov. This book was released on 2013-06 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis NASA's Contributions to Aeronautics: Aerodynamics, structures, propulsion, controls by :
Download or read book NASA's Contributions to Aeronautics: Aerodynamics, structures, propulsion, controls written by and published by . This book was released on 2010 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two-volume collection of case studies on aspects of NACA-NASA research by noted engineers, airmen, historians, museum curators, journalists, and independent scholars. Explores various aspects of how NACA-NASA research took aeronautics from the subsonic to the hypersonic era.-publisher description.
Book Synopsis NASA's Contributions to Aeronautics by :
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Book Synopsis Configuration and Sizing of a Test Fixture for Panels Under Combined Loads by : Andrew E. Lovejoy
Download or read book Configuration and Sizing of a Test Fixture for Panels Under Combined Loads written by Andrew E. Lovejoy and published by BiblioGov. This book was released on 2013-06 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt: Future air and space structures are expected to utilize composite panels that are subjected to combined mechanical loads, such as bi-axial compression/tension, shear and pressure. Therefore, the ability to accurately predict the buckling and strength failures of such panels is important. While computational analysis can provide tremendous insight into panel response, experimental results are necessary to verify predicted performances of these panels to judge the accuracy of computational methods. However, application of combined loads is an extremely difficult task due to the complex test fixtures and set-up required. Presented herein is a comparison of several test set-ups capable of testing panels under combined loads. Configurations compared include a D-box, a segmented cylinder and a single panel set-up. The study primarily focuses on the preliminary sizing of a single panel test configuration capable of testing flat panels under combined in-plane mechanical loads. This single panel set-up appears to be best suited to the testing of both strength critical and buckling critical panels. Required actuator loads and strokes are provided for various square, flat panels.
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