To investigate the effect of rotor morphing technologies on helicopter performance improvement

a rotor model was derived. A fuselage model was coupled with this rotor model to establish the computational model of helicopter power. Several rotor morphing technologies

including varying rotor diameter

varying rotor speed

varying blade chord length and varying blade twist angle

were compared to investigate the influence on the helicopter power at different flight states. At the forward speed of 130km/h

10% reduction of the rotor speed

10% reduction of the rotor diameter

10% reduction of the blade chord length and the blade twist angle variation from -12 degree to -6 degree

the power can reduce by 15.7%

14.6%

5.8% and 3.1%

respectively. At the forward speed of 250km/h

10% reduction of the rotor speed and 10% reduction of the rotor diameter

can reduce the power by 14.5% and 23.9%

respectively. The results indicate varying rotor speed can achieve better performance improvement than varying blade chord length or varying blade twist angle. In high forward speed

varying rotor diameter can achieve better rotor power saving than varying rotor speed.