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US 2026/0274462 A1Published application
Hybrid propulsion helicopter including main coaxial counter-rotating rotors and auxiliary tail rotors
OwnerItalo VANNELLIinventor
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OwnerItalo VANNELLIinventor
Estimating the term…
Helicopter comprising a body having a first yaw axis, a first propulsion unit on board the body, a transmission unit connected in torque transmission to the first propulsion unit, a first and second counter-rotating main rotor, rigidly connected to rotation to the transmission unit, the first axis passing through the transmission unit, and having said first and second main rotor respectively first and second main blades, wherein the first main blades are configured to have a variable first common angle of incidence and the second main blades a fixed second common angle of incidence when the first and second main rotors are rotating; the helicopter further comprising a first and a second auxiliary rotor configured to rotate respectively around second and third axes, a second electric propulsion unit connected in torque transmission to the first and to the second auxiliary rotor, wherein said first and second auxiliary rotors are arranged opposite to the roll axis of the helicopter and in a transversely spaced position with respect to the pitch axis; such first and second auxiliary rotors being configured to respectively generate a first and a second aerodynamic force to cause a rotation of the helicopter with respect to the pitch axis or the roll axis; all rotors of the helicopter having corresponding axes which, intercepting a barycentric plane of the helicopter including roll and pitch axes, define vertices of a non-axialsymmetric figure.
Helicopter (E) comprising a body (C) having a first yaw axis (A), a first propulsion unit (1) on board the body, a transmission unit (2) connected in torque transmission to the first propulsion unit, a first and second counter-rotating main rotor (3, 4), rigidly connected to rotation to the transmission unit (2), the first axis (A) passing through the transmission unit (2), and having said first and second main rotor (3, 4) respectively first and second main blades (3a, 4a), wherein the first main blades are configured to have a variable first common angle of incidence (C1) and the second main blades a fixed second common angle of incidence (C2) when the first and second main rotors are rotating;
Helicopter (E) according to one of the preceding claims, comprising an oscillating plate rigidly connected to rotation to the transmission unit (2) and to the first main blades (3a), comprising such an oscillating plate adjustment means configured to actuate the adjustment of the angle of incidence of the first main blades (3a) through the collective pitch control.
Helicopter (E) according to any of the preceding claims, comprising on board a control module (13) comprising an antenna (14) and an electronic control unit (15) connected in data exchange with a transceiver device (16) usable by a user on ground, such an electronic control unit being programmed to:
Helicopter according to any one of the preceding claims, wherein the second electric propulsion unit has a maximum power lower than or equal to the maximum power of the first propulsion unit (1), preferably a first internal combustion propulsion unit.
Helicopter according to any one of the preceding claims, defining an unmanned drone.
Helicopter according to any one of the preceding claims, wherein the second and third axes (B1, B2) are the only axes on board the helicopter (E) in addition to the counter-rotating axes of the first and second main rotor.
Helicopter according to any one of the preceding claims, wherein the axes of rotation of the first and second counter-rotating main rotors coincide on the first axis (A) and wherein the first, second and third axes (A, B1, B2) are parallel to each other.
Dependencies are inferred from the claim text.