Phasing control for convertiplane

Details Phasing control for convertiplane Phasing control for convertiplane

1976-01-21

1978-05-09

Kelmachter, Barry L.

Aeronautics and astronautics

Aircraft, heavier-than-air

Airplane and helicopter sustained

244 124, 416 36, B64C 2728

Patent

active

040882845

ABSTRACT:
A convertiplane having control apparatus for modification of the control signals during the course of transition in either direction between a helicopter mode and the aircraft mode. The convertiplane has at least one pylon rotatable about a lateral axis, positioned parallel to the longitudinal axis of the convertiplane to a position normal to the axis for selective operation in the airplane mode and in the helicopter mode, respectively. Rotor blades are provided on each pylon with a control linkage responsive to pilot input in the helicopter mode to vary the collective and cyclic pitch of the rotor blades. Drive linkages are provided to change the pylons from one mode position to the other mode position. Control linkages are operatively associated in synchronism with the drive linkages to alter the authority of the pilot control to change the pitch of the blade during transition.

REFERENCES:
patent: 2702168 (1955-02-01), Platt
patent: 3112901 (1963-12-01), Kohman
patent: 3117745 (1964-01-01), Ellis et al.
patent: 3514052 (1970-05-01), McKeown

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