INVESTIGATION OF GENERALIZED METHODS FOR USE OF EXCITATION PANELS TO PRODUCE HELICOPTER ROTOR BLADE FLIGHT FATIGUE LOADS DURING WHIRL TEST.
Final rept., 14 Jan 65-14 Apr 66,
HUGHES TOOL CO CULVER CITY CALIF AIRCRAFT DIV
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To supplement previous data obtained with three blades, rotors with two and four blades were whirl tested using the excitation panel technique. Rotor blades were tested having two different chord widths. A survey was made of the transient pressures produced on the excitation panels by the rotor blades. The resonant frequency of the third bending mode of the rotor blade was shifted from below the normal operating range to the maximum continuous power-on rpm by adding external weights to the blade leading edge. The use of a counterweight to replace a fatigue-damaged rotor blade during whirl testing was studied and rejected as being overly complicated. Author