Analytical and experimental investigation of a low cost composite blade-skin stiffener
Book
·
OSTI ID:376016
- Univ. of Texas, Arlington, TX (United States)
Many studies have been conducted on composite stiffened panels used for primary aircraft structures. Here, an experimental and analytical stress and fracture analysis is conducted to optimize the design of a light weight and inexpensive composite blade stiffener. A low-cost manufacturing technique is used in which a composite blade and relatively thin skin are separately cured and bonded together using AF191 adhesive and composite tie-plies. Stiffener to skin pull-off tests are conducted to give a relative comparison of design parameters. Design parameters include radius size, filler material, tie-ply lay-up and blade elevation. Crack initiation and propagation take place along the blade and tie-ply interfaces in the radius region. Finite element stress and fracture analyses are conducted to analyze design parameters and study crack growth.
- OSTI ID:
- 376016
- Report Number(s):
- CONF-960154--; ISBN 0-9648731-8-4
- Country of Publication:
- United States
- Language:
- English
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