Development of a Graphite Horizontal Stabilizer.
Interim technical rept. 1 Nov 71-30 Jun 72,
DOUGLAS AIRCRAFT CO LONG BEACH CALIF
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Vibration and static test setups are described and results are presented for a graphite-epoxy stabilizer assembly for the A-4 Skyhawk aircraft. Natural vibration frequencies, mode shapes, and structural damping data are presented for both the graphite stabilizer and the analogous production metal stabilizer. Each configuration was tested both with and without the production elevator installed. Structural influence coefficients were derived from the vibration test results and used to analyze the flutter speed of the A-4 aircraft using the graphite stabilizer. The flutter characteristics of the graphite stabilizer are expected to be improved, with the flutter speed being increased by 22 percent. The reduced weight of the graphite stabilizer is not expected to have a significant effect on the fin flutter characteristics. The stabilizer was tested statically under two critical load conditions, a localized leading-edge condition and an unsymmetrical bending condition. Finite element analyses are expected to determine the magnitudes of secondary sheares and bending moments through the thickness of the laminate and their influences on ultimate strength of the stabilizer. Author
- Attack and Fighter Aircraft
- Laminates and Composite Materials