Rotorcraft having an electric drive for driving a main and/or tail rotor of the rotorcraft

A rotorcraft and drive technology, applied in the field of rotorcraft, can solve problems such as high maintenance requirements, large space requirements, and complex structures

Pending Publication Date: 2021-02-09
KOPTER GRP AG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0010] Disadvantages of this rotorcraft with a hybrid drive known from document US 2017 / 0225573 A1 are the disadvantages of large space requirements, complex construction and high maintenance requirements
[0011] Due to the presence of the second engine, such a hybrid drive such as that shown in the patent document US2017 / 0225573A1 has a fundamental problem, namely that the weight of the rotorcraft is disadvantageously increased compared to the single-engine variant, but a more high security level

Method used

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  • Rotorcraft having an electric drive for driving a main and/or tail rotor of the rotorcraft
  • Rotorcraft having an electric drive for driving a main and/or tail rotor of the rotorcraft
  • Rotorcraft having an electric drive for driving a main and/or tail rotor of the rotorcraft

Examples

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Embodiment Construction

[0045] figure 1 A perspective view of a preferred embodiment of the rotorcraft according to the invention is shown, which has a hybrid drive 1 . Such as figure 2 As shown in detail in , the electric drive E shown here is at least mechanically connected to the transmission housing 30 of the helicopter rotor drive or the main rotor drive 2 , wherein the part of the electric drive E that acts as a stator The outer ring 10 is fixedly connected via here four first fastening arms 12 of the outer ring 10 to here four corresponding second fastening arms 31 of the transmission housing 30 .

[0046] figure 2 A longitudinal section through a preferred embodiment of an inventive rotorcraft with a hybrid drive 1 is shown.

[0047] The hybrid drive 1 shown here comprises an electric drive E as well as a second drive TK, not shown here, which is designed as a thermodynamic engine, such as an internal combustion engine, a turbine, a spark ignition engine, a diesel engine, a fuel cell dri...

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PUM

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Abstract

The invention relates to a rotorcraft having an electric drive (E) for driving a main rotor of a rotorcraft, more particularly a helicopter, the electric drive (E) comprising: means for coupling the electric drive (E) to a rotor mast (4), which can be coupled for conjoint rotation with a drive unit of a helicopter rotor transmission (2), for coupling for conjoint rotation with the main rotor or tail rotor. According to the invention, a rotorcraft with an electric drive is provided with which the space requirement is reduced, the construction is simplified and the maintenance requirement is reduced. This problem is solved in that the electric drive (E) is designed as an electric ring motor, with the electric ring motor being arranged and attached coaxially with the rotor mast (4).

Description

technical field [0001] The invention describes a rotorcraft according to the preamble of the first claim, having an electric drive for driving the main rotor and / or the tail rotor of the rotorcraft. [0002] The invention also describes a rotorcraft with a hybrid drive for driving the main and / or tail rotor of the rotorcraft, comprising an electric drive according to the invention and a second drive designed as a thermodynamic machine. Background technique [0003] So-called multi-engine, in particular twin-engine helicopters are known from the prior art, ie helicopters with a drive system comprising several engines or drives. Usually fuel, mainly fossil fuels, is converted into mechanical work by means of one or more drives designed as thermodynamic engines, and the main rotor is driven by the main rotor drive or helicopter rotor drive, or the tail rotor by Tail rotor gear drive to drive. [0004] In an emergency in the form of a drive failure of such a multi-engine helic...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/12B64C27/14
CPCB64C27/12B64D27/24B64D27/26B64D2027/026Y02T50/60H02K1/2788B64C27/14Y02T10/70B64U50/14B64C2027/8209F16H3/44H02K1/2706B60L50/60B60L2200/10B64C27/82B64D31/06B64D35/02F16H3/64H02K7/116H02K11/0094
Inventor J·赫滕科费尔A·杜迈尔D·伊文A·洛温斯坦
Owner KOPTER GRP AG
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