The aeromechanics design of the Active Elevon Rotor (AER) has been completed. The AER elevon is a 15% chord, plain, trailing-edge flap actuated by a piezoceramic-based conformal actuator. A trade study is performed to determine the location of the elevon for reducing the (4/rev) vibratory hub loads at mu = 0.125. Both single- and dual-elevon configurations are considered, with the dual-elevon configuration being selected. In addition, a linear engineering analysis is used to approximate elevon finite-span effects, which are found to be of sufficient size to warrant further investigation. Additional results are given for the selected AER design, including rotor blade modal frequencies and damping, and vibratory hub loads and elevon motions at four advance ratios. The design choice is predicted to have the six vibratory hub loads reduced by 50-90% at mu = 0.125 and by 80-98% at mu = 0.225; the effectiveness is compromised, however, at mu = 0.400, with an 80% reduction of the vertical force being achieved at the expense of four other hub loads. Overall, the AER design should provide a reasonable basis for ongoing rotor blade development and future wind-tunnel testing.
Aeromechanics of the Active Elevon Rotor
2005
13 pages
Report
Keine Angabe
Englisch
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