Multicyclic jet-flap control for alleviation of helicopter blade stresses and fuselage vibrationResults of wind tunnel tests of a 12-meter-diameter rotor utilizing multicyclic jet-flap control deflection are presented. Analyses of these results are shown, and experimental transfer functions are determined by which optimal control vectors are developed. These vectors are calculated to eliminate specific harmonic bending stresses, minimize rms levels (a measure of the peak-to-peak stresses), or minimize vertical vibratory loads that would be transmitted to the fuselage. Although the specific results and the ideal control vectors presented are for a specific jet-flap driven rotor, the method employed for the analyses is applicable to similar investigations. A discussion of possible alternative methods of multicyclic control by mechanical flaps or nonpropulsive jet-flaps is presented.
Document ID
19740054754
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Mccloud, J. L., III (NASA Ames Research Center Moffett Field, Calif., United States)
Kretz, M. (NASA Ames Research Center Moffett Field, Calif.; Giravions Dorand, Suresnes, Hauts-de-Seine, France)
Date Acquired
August 7, 2013
Publication Date
January 1, 1974
Subject Category
Aircraft
Meeting Information
Meeting: Specialists Meeting on Rotorcraft Dynamics