US 9,810,224 B2
Electromagnetic power transmission for a rotary-wing aircraft or a fixed-wing aircraft
Eric Chantriaux, Venelles (FR); and Pascal Chretien, Karana Downs (AU)
Appl. No. 14/342,406
Filed by Eric Chantriaux, Venelles (FR); and Pascal Chretien, Karana Downs (AU)
PCT Filed Aug. 17, 2012, PCT No. PCT/AU2012/000968
§ 371(c)(1), (2), (4) Date Mar. 3, 2014,
PCT Pub. No. WO2013/029085, PCT Pub. Date Mar. 7, 2013.
Claims priority of application No. 11 57828 (FR), filed on Apr. 9, 2011.
Prior Publication US 2014/0248168 A1, Sep. 4, 2014
Int. Cl. B64C 27/14 (2006.01); B64C 27/24 (2006.01); F04D 13/06 (2006.01); B64D 27/24 (2006.01); B64D 35/08 (2006.01); B64D 35/02 (2006.01)
CPC F04D 13/06 (2013.01) [B64C 27/14 (2013.01); B64D 27/24 (2013.01); B64D 35/08 (2013.01); B64C 2201/042 (2013.01); B64D 35/02 (2013.01); B64D 2221/00 (2013.01); Y02T 50/44 (2013.01); Y02T 50/64 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A propulsion device for rotary-wing aircraft or fixed-wing aircraft comprising a rotor or an airscrew, the rotor or the airscrew being caused to rotate at a variable or constant speed by a rotating shaft, the propulsion device including a distributed electric motor unit, configured to ensure propulsion or lifting of the aircraft by causing the rotating shaft to rotate, wherein:
the electric motor unit includes a plurality of distributed electric motor elements connected directly to the rotating shaft, with no mechanism for the transmission of movement interposed between the motor elements and the shaft,
the electric motor elements are physically separated from each other and each of the electric motor elements is inserted into a dedicated housing,
the electric motor elements are stacked, each electric motor element comprising at least one fixed stator and at least one moving rotor, said moving rotor being connected to the rotating shaft in order to transmit to said rotating shaft a mechanical power,
each undamaged electric motor element producing a fraction of the nominal mechanical power necessary for the propulsion or for the lifting of the aircraft in accordance with the following equation:
Pr=Σi−1nKi·Pim
where:
Pr represents the nominal mechanical power necessary for the propulsion or for the lifting of the aircraft,
Pim represents the maximum mechanical power capable of being delivered by the undamaged electric motor element on level i, to the rotating shaft, where Pim<Pr,
Ki represents the power derating of the undamaged electric motor element on level i, where 0≤ki≤I, Ki being a variable that is adjustable as a function of the undamaged valid number of electric motor elements and as a function of the nominal mechanical power necessary for the propulsion or for the lifting of the aircraft at a moment in time t, and
n represents the number of undamaged electric motor elements comprising the distributed electric motor unit, where n≧2,
the axes of rotation of the moving rotors and the rotating shaft being coaxial, and
an electronic control unit is configured to continuously control the integrity of each electric motor element, such that, in the event of failure of an electric motor element, the control unit emits a set point, intended for the undamaged electric motor element, enabling the power delivered by each of the undamaged electric motor elements to be reconfigured in a linear fashion in real time by modifying the variable “Ki” such that the distributed electric motor unit continues to transmit to the rotating shaft a level of power that is sufficient for the propulsion of the aircraft.