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Electric propulsion architecture for multi-rotor vertical take-off and landing aircraft and method for controlling such architecture

An electric propulsion, vertical take-off and landing technology, applied in vertical take-off and landing aircraft, aircraft, unmanned aerial vehicles, etc., can solve the problems of increasing the complexity and quality of the electric propulsion system of helicopters or aircraft, and achieve easy detection and isolation. Effect

Pending Publication Date: 2022-02-18
SAFRAN
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This results in increased complexity and mass of the electric propulsion system of the helicopter or aircraft

Method used

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  • Electric propulsion architecture for multi-rotor vertical take-off and landing aircraft and method for controlling such architecture
  • Electric propulsion architecture for multi-rotor vertical take-off and landing aircraft and method for controlling such architecture
  • Electric propulsion architecture for multi-rotor vertical take-off and landing aircraft and method for controlling such architecture

Examples

Experimental program
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Effect test

Embodiment Construction

[0070] figure 1 An electric propulsion configuration is shown for a multi-rotor VTOL aircraft and, more precisely, for an octorotor, ie an aircraft with eight lifting rotors.

[0071] The structure includes an electrical energy storage device 102 that supplies power to generators G1-G4, four in this example.

[0072] The generators G1-G4 can be batteries, or fuel cells, or turbine generators.

[0073] Generators G1-G4 are connected to communication buses 104a-d.

[0074] The structure includes R1_2, R2_1, R3_4, R4_3, R5_6, R6_5, R7_8, and R8_7 in this example, for a total of 8 rotors. Each rotor includes two electric motors 106a-h and 108a-h, and propellers 110a-h. The propellers are coupled to the electric motors of the rotors such that during operation, the first electric motors 106a-h drive the propellers.

[0075] The electric motor is connected to a generator such that, during operation, the generator supplies power to the electric motor, in particular via a communica...

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Abstract

The invention relates to an electric propulsion architecture for a multi-rotor vertical take-off and landing aircraft, comprising four electric generators (G1-G4); four pairs of rotors (R1_2 -R2_1; R3_4-R4_3; R5_6-R6_5; R7_8-R8_7); for each rotor, a first electric motor (106a-h) configured to operate in an active mode, a second electric motor (108a-h) configured to be in a standby mode and being able to operate in an active mode in a breakdown situation; and a propeller (110a-h) coupled to said electric motors, wherein, for each pair of rotors, one of the electric generators powers the first electric motors, and another of the electric generators powers the second electric motors, and wherein the rotors form counter-rotors (R1_2-R6_5; R2_1-R5_6; R3_4-R8_7; R4_3-R7_8), and for each counter-rotor, said electric motors are each powered by one of the four electric generators so that the four electric generators power said electric motors of the rotors of each counter-rotor.

Description

technical field [0001] The present invention relates to an electric propulsion structure for a multi-rotor vertical take-off and landing (VTOL) aircraft, the electric propulsion structure comprising at least two electric motors for each rotor of the helicopter, one electric motor being activated mode, the other electric motor operates in standby mode, and relates to a method for controlling such a structure. Background technique [0002] The prior art includes, inter alia, the documents US-A1-2017 / 203839, EP-A1-3208909 and WO-A1-2017 / 114643. [0003] Aircraft are known for use in urban areas. However, such use of aircraft poses stringent objectives in terms of safety as well as pollutant and noise emissions. [0004] Single-rotor helicopters include a single electric motor for the rotor and are capable of vertical take-off and landing. However, the traditional architecture of these helicopters does not meet safety and emissions targets. The structure is the definition of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D27/24
CPCB64D27/24B64U50/19Y02T50/60B64D31/16B64C29/00B64D31/00B64D35/06B64D35/08
Inventor 克莱利亚·勒韦尔克里斯多夫·莫里R·默尼耶B·索拉瓦尔
Owner SAFRAN
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