APPLICATION OF GROUND VIBRATION TEST RESULTS TO CALCULATE AEROELASTIC STABILITY AND CONTROL PARAMETERS.

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Stockdale, C.R.
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| 1600年 / AIAA, New York, NY卷
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A method to integrate experimental ground vibration test results and theoretical aerodynamics to calculate symmetric aeroelastic stabilty and control parameters is presented. This method employs experimental asymmetric unconstrained vibration modes and aircraft geometrical and inertial properties to estimate a ″clamped″ asymmetric structural influence coefficient (SIC) matrix. This matrix is reduced to a proper format to be used in the FLEXSTAB computer program system. FLEXSTAB is used to estimate the desired parameters. SICs and resulting parameters calculated using this method compare favorably with similar data estimated using another method.
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