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Hybrid/electric propulsion architecture and method for dissipating electrical energy in such an architecture

An electric propulsion and architecture technology, applied in hybrid vehicles, battery/battery traction, power management, etc., which can solve the problems of dissipation, dependence, and high system quality.

Pending Publication Date: 2021-10-29
SAFRAN HELICOPTER ENGINES
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0019] However, the mass of the system can be considerable and depends on the energy to be dissipated

Method used

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  • Hybrid/electric propulsion architecture and method for dissipating electrical energy in such an architecture
  • Hybrid/electric propulsion architecture and method for dissipating electrical energy in such an architecture
  • Hybrid/electric propulsion architecture and method for dissipating electrical energy in such an architecture

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Embodiment Construction

[0064] figure 2 A hybrid-electric propulsion architecture 100 is represented according to the invention for an aircraft, such as a helicopter or an aircraft of the aircraft type with multirotor rotors. For example, frame 100 may be integrated into an aircraft weighing less than 5000 kg and having an onboard mechanical power between 50 kW and 2000 kW.

[0065] Internal combustion engine 112 , such as a turbine, such as an auxiliary power unit (APU), is coupled to generator 114 . In operation, the generator 114 is driven by the internal combustion engine 112 .

[0066] The generator 114 is a motor-generator, ie the generator 114 is adapted to operate in a generator mode and a motor mode. In other words, the generator 114 may operate in a generator mode, particularly when driven by the internal combustion engine 112 , or the generator 114 may operate in a motor mode. The generator 114 may be a synchronous motor or an asynchronous motor. Thus, generator 114 is a reversible el...

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PUM

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Abstract

Disclosed is a hybrid / electric propulsion architecture (100) for a multi-rotor rotary wing aircraft, the hybrid / electric propulsion architecture comprising: an electricity generator (114) driven by an internal combustion engine (112), and configured to operate in motor mode; a rectifier (116) configured to convert an alternating current delivered by the electricity generator into direct current; an electrical network (120) comprising a high voltage direct current (HVDC) bus; electrical energy storage means (126) connected to the electrical network, wherein during electrical energy regeneration on the HVDC bus, depending on the state of charge of the storage means (126): the storage means are configured to recover electrical energy, the storage means and the rectifier are configured to recover electrical energy, and the electricity generator operating in motor mode is configured to recover electrical energy.

Description

technical field [0001] The invention relates to a hybrid-electric propulsion architecture for a multirotor rotorcraft, an aircraft comprising such a hybrid-electric propulsion architecture and a method for dissipating electrical energy in such a hybrid-electric propulsion architecture. Background technique [0002] In particular, the prior art includes patent applications FR-A1-3 056 555, US-A1-2018 / 162379, US-A1-2016 / 070266, DE-A1-10 2010 031540 and EP-A1-2 684 798. [0003] A hybrid propulsion architecture for aircraft is known from the prior art, generally referred to as series hybrid generating thermoelectric energy. [0004] Such as figure 1 As shown, a hybrid propulsion architecture 10 typically includes: [0005] - internal combustion engine 12, [0006] - a generator 14 coupled to the internal combustion engine such that in operation the internal combustion engine 12 drives the generator 14, [0007] - a rectifier 16 connected to the generator 14 and configured t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B60L15/20B60L50/61B60L58/12B60L7/14B60L7/20B60L7/02B64D27/24
CPCB60L15/20B60L2200/10B60L50/61B60L58/12B60L7/14B60L7/20B60L7/006B64C29/0016Y02T10/62Y02T10/64Y02T10/70Y02T10/72Y02T50/60Y02E10/72Y02T10/7072Y02T90/14B64D27/351B64D27/33B64D35/024F03D9/25B60L53/24B64D27/24F05B2220/706B60L58/10B64D27/026
Inventor 托马斯·克洛诺夫斯基托马斯·巴拉克卡梅尔·瑟雷吉娜
Owner SAFRAN HELICOPTER ENGINES