To increase lift force acting to a convertiplane in both an aircraft and a helicopter modes, to increase the lift surface of the convertiplane in the aircraft mode, and to reduce the wing shielding effect between hoverings in the helicopter mode.
There is described a convertiplane 1 includes: a pair of semi-wings 3 and at least two rotors 4, wherein the rotors can rotate around the respective first axes B between a helicopter mode and an aircraft mode and at the same time can rotate around respective second axes C together with the first axis with respect to the semi-wings; the first axis, being in use in the helicopter mode, intersect to a longitudinal direction A of the convertiplane, and being, in use, substantially parallel to longitudinal direction in the aircraft mode; the convertiplane further includes at least two through openings 8 within which the rotor can tilt, when the convertiplane moves, in use, between the helicopter and the aircraft mode.
| JPH0664592A | 1994-03-08 | |||
| JP2006528583A | 2006-12-21 | |||
| JP2011126517A | 2011-06-30 | |||
| JP2001001995A | 2001-01-09 |
| US20090261209A1 | 2009-10-22 | |||
| US5320305A | 1994-06-14 | |||
| US3335977A | 1967-08-15 | |||
| WO2011066400A1 | 2011-06-03 | |||
| US6343768B1 | 2002-02-05 | |||
| US20090261209A1 | 2009-10-22 | |||
| US5320305A | 1994-06-14 |
Tetsuro Shimada
Shinji Mitsuhashi
Takuya Shinoda
Yoryo Mihashi
Yuichi Morimoto