Investigation of curved composite panels under high-g loading
Name
43583959-MIT.pdf
Description
Full printable version
Size
23.09 MB
Format
Adobe PDF
Checksum (MD5)
d0db4106e2b18bbe6ea0fcc2b57d7dc4
Author(s)
Jenkins, Staci Nicole, 1975-
Advisor(s)
Brent Appleby and S. Mark Spearing.
Date Issued
1999
Publisher
Massachusetts Institute of Technology
Abstract
Numerical and experimental work was conducted to investigate the use of composites within the Wide Area Surveillance Projectile (WASP) wing system by specifically studying the buckling behavior of curved composite panels under high-g loading. A finite element model was developed as a design tool to model the original WASP wing as a constant thickness curved panel and to predict the buckling response of the panels. The model predicted the critical buckling loads and mode shapes of the composite panels. Experimentally, controlled axial compression tests and high-g tests were performed to determine the buckling response of the panels. The buckling response, including critical loads and mode shapes, was obtained for the controlled axial compression tests. The high-g tests demonstrated that composite panels are a viable option for structures in a high-g environment. All of the samples tested showed no signs of damage and no loss in load carrying capability. The results were used to study the effect of lay-up, curvature, aspect ratio (width to height), and height on the buckling response. The results of the finite element model and the controlled axial compression tests showed good agreement. However, they do not accurately capture the buckling response of the composite panels in the high-g environment.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1999.
Includes bibliographical references (p. 129-133).
Subjects
Aeronautics and Astronautics
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
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