Fig.1

Coaxial rigid rotor lift offset［17］

Fig.2

SB>1 high speed helicopter［22］

Fig.3

Tilt-rotor aircraft development history［30］

Fig.4

V-280 tilt-rotor aircraft［33］

Fig.5

X3 technical verification aircraft［40］

Fig.6

RACER concept verification aircraft［36］

Fig.7

Airbus VAHANA technical verification aircraft［41］

Fig.8

NASA LA-8 technical verification aircraft［42］

Fig.9

S-72 verification aircraft［44］

Fig.10

X-50A canard rotor/wing vehicle［44］

Fig.11

Aerodynamic environment for high-speed forward flight of coaxial rigid rotor

Fig.12

CFD analysis of all-aircraft aerodynamic interference of high-speed helicopter based on Helios/RCAS［45］

Fig.13

Forward wake interference of coaxial rigid high-speed helicopter［47］

Fig.14

X2 flight test data of lift offsets and tip clearance［48］

Fig.15

Effect diagram of X2 load reduction control system when closed/opened［48］

Fig.16

X2 helicopter actuator installation location［61］

Fig.17

X2 effect prediction of helicopter vibration active control effect［61］

Fig.18

CFD simulation of tilting transition state［63］

Fig.19

Wind-tunnel test of rotor/wing aerodynamic interaction in tilting transition state［65］

Fig.20

ADYN tilting rotor advance aerodynamic layout design scheme［68-69］

Fig.21

Rolling， pitching and yawing moment control distribution with velocity［70-71］

Fig.22

Bell 4-blade semi articulated swing flexible configuration rotor［75］

Fig.23

Interference flow of dual thrust compound high-speed helicopter in different flight states［78］

Fig.24

Vortex ring state diagram of negative pitch propeller［80］

Fig.25

X3 measured flight load［83-84］

Fig.26

Complex flow field of electric-driven multi-rotor tilting high-speed helicopter［88］

Fig.27

American GL-10 electric-driven tilting wing aircraft［90］

Fig.28

Helios solar impulse verification aircraft［94］