Electromagnetic power transmission for a rotary-wing aircraft or a fixed-wing aircraft
View Patent ↗Rotary-wing aircraft or fixed-wing aircraft consisting of one or a plurality of rotors and/or one or a plurality of airscrews being caused to rotate by means of at least one shaft, the said aircraft comprising a distributed electric motor unit configured to ensure the propulsion and/or the lifting of the said aircraft by causing the said shaft to rotate, the motor unit being a distributed electric motor unit connected directly to the rotating shaft, no mechanism for the transmission of movement being interposed between the said unit and the said shaft, the distributed electric motor unit being composed of a plurality of stacked electric motor elements, each said electric motor element being connected directly to the rotating shaft and consisting of at least one fixed stator and at least one moving rotor capable of connection to the said rotating shaft in order to transmit to it a mechanical power of the following kind where: ·Pr=the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft, ·Pim=the maximum mechanical power capable of being delivered by the electric motor element on level i, to the rotating shaft, for instance Pim<Pr, ·Ki=the power derating of the electric motor element on level i, for instance 0≦ki≦1, Ki being a variable that is adjustable as a function of the undamaged number of electric motor elements and/or as a function of the nominal mechanical power necessary for the propulsion and/or for the lifting of the said aircraft at a moment in time t, n=the number of electric motor elements comprising the distributed electric, motor unit, for instance n≧2,—the axes of rotation of the moving rotors and of the rotating shaft being coaxial.
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=Σ i−1 n K i ·P im
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.
2. A propulsion device for an aircraft according to claim 1 , wherein the electric motor elements are dimensioned such that the minimum number “Nmin” of undamaged electric motor elements that are together capable of delivering the nominal mechanical power necessary for propulsion or lifting of the aircraft is Nmin≧2.
3. A propulsion device for an aircraft according to claim 1 , wherein some of the electric motor elements are dimensioned to deliver a different maximum mechanical power Pim to the rotating shaft, the power derating factors Ki being different for each of the electric motor elements.
4. A propulsion device for an aircraft according to claim 1 , wherein all of the electric motor elements are dimensioned to deliver a different maximum mechanical power Pim to the rotating shaft, the power derating factors Ki being different for each of the electric motor elements.
5. A propulsion device for an aircraft according to claim 1 , wherein the stacked electric motor elements includes a number of fixed stators that is different from the number of moving rotors.
6. A propulsion device for an aircraft according to claim 1 , wherein the stacked electric motor elements includes a number of fixed stators that is equal to the number of moving rotors.
7. A propulsion device for an aircraft according to claim 1 , comprising:
an energy generation unit intended to produce electrical energy, the energy generation unit being associated with a means for distributing the energy,
a means for storing the electrical energy produced by the generation unit,
the distributed electric motor unit being supplied with electrical energy via a power controller integrated in or operated by an electronic control unit:
by the means for storing electrical energy,
or by the energy generation unit.
8. A propulsion device for an aircraft according to claim 7 , wherein the means for storing electrical energy is composed of a pack of batteries or super-capacitors.
9. A propulsion device for an aircraft according to claim 7 , wherein the electrical energy generation unit is composed of one of the following:
a thermo-chemical generator,
a thermoelectric generator,
a radio isotopic generator,
fuel cells,
a turbo shaft engine, or an internal combustion engine equipped with an internal generator or driving an external generator.
10. A propulsion device for an aircraft according to claim 7 , wherein the electronic control unit is configured to control the operating point of the distributed electric motor unit as a function of the power requirement of the aircraft.
11. A propulsion device for an aircraft according to claim 7 , wherein the electronic control unit is configured to control the supply to the distributed electric motor unit, the electronic control unit comprising a program containing:
instructions for supplying the distributed electric motor unit uniquely with the electrical energy produced by the energy generation unit,
instructions for supplying the distributed electric motor unit uniquely with the electrical energy stored in the storage means,
instructions for supplying the distributed electric motor unit by combining the electrical energy produced by the energy generation unit with the electrical energy stored in the storage means.
12. A propulsion device for an aircraft according to claim 7 , comprising:
a means for controlling the operational status of the energy generation unit,
the electronic control unit being configured to control the supply to the distributed electric motor unit, the electronic control unit comprising a program containing instructions for supplying the distributed electric motor unit uniquely with the electrical energy stored in the storage means, in the event of the failure of the energy generation unit.
13. A propulsion device for an aircraft according to claim 7 , wherein the electronic control unit is configured to control the supply to the distributed electric motor unit, the electronic control unit comprising a program containing instructions for supplying the electric motor unit uniquely with the electrical energy stored in the storage means, and instructions for simultaneously stopping the function of the energy generation unit.
14. A propulsion device for a helicopter comprising a rotor or an airscrew, the rotor or the airscrew being caused to rotate at a 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 helicopter in accordance with the following equation:
Pr=Σ t=1 n K i ·P im
where:
Pr represents the nominal mechanical power necessary for the propulsion or for the lifting of the helicopter,
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 helicopter 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 or the lifting of the helicopter.