AeroVantage ~ Trim, Stability & Control - Control

• Flight and Power ~ since both are to be electric.
• Consider the use of conventional fixed-wing mechanical flight controls for cruise. Consider electric/electronic flight controls (quad rotor) for hover. Consider an interfacing of the two methods during transition.

• A crude comparison of the V22 and Eagle Eye vs. the AeroVantage.
• The V-22 has a rotor diameter of 38'. Assuming that the center of lift on the blades is at 75% of span (.75R) then the control moment arm is .75 * 38 / 2 = 14.25'. The GW is 52,600 lbs.
• The Eagle Eye has a rotor diameter of 10'. Assuming that the center of lift on the blades is at 75% of span (.75R) then the control moment arm is .75 * 10 / 2 = 3.75'. The GW is 1,960 lbs.
• The AeroVantage 2x4 has; 160" between the fore and aft rotor centers in hover The rotor radiuses of 50" and 40" will not be considered since there is only collective and no cyclic.. The control moment arm is (160/12)/2 = 6.7'. The GW is 1,320 lbs.
• The implication is that the longitudinal gap between the fore and aft rotors can be significantly reduced.
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