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Electric direct drive tail rotor assembly for hybrid helicopters, helicopters

A hybrid and helicopter technology, applied in the aviation field, can solve problems such as increasing the empty weight of helicopters, and achieve the effects of reducing weight, improving reliability and simplifying the transmission structure.

Active Publication Date: 2017-06-06
珠海隆华直升机科技有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the high-power generator generates a lot of heat when it is working, it is necessary to design a cooling device for it separately, which also increases the empty weight of the helicopter

Method used

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  • Electric direct drive tail rotor assembly for hybrid helicopters, helicopters
  • Electric direct drive tail rotor assembly for hybrid helicopters, helicopters

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Embodiment Construction

[0025] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.

[0026] The electric direct-drive tail rotor assembly 100 for a hybrid helicopter according to an embodiment of the present invention will be described in detail below with reference to the accompanying drawings.

[0027] refer to figure 1 and figure 2 As shown, an electric direct-drive tail rotor assembly 100 for a hybrid helicopter according to an embodiment of the present invention includes a tail rotor 10 , an electric motor 20 and an integrated hybrid power device 30 . The integrated hybrid device 30 can provide a power so...

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Abstract

The invention discloses an electronic direct-drive type stroke oar component for a hybrid-power helicopter and a helicopter with the electronic direct-drive type stroke oar component. The electronic direct-drive type stroke oar component comprises a stroke oar, a motor and an integrated type hybrid-power device, wherein the motor is connected with the stroke oar and is used for driving the stroke oar to rotate; the integrated type hybrid-power device comprises a power generator and an engine; the power generator comprises a rotor; the rotor is formed into a fly wheel of the engine; the power generator is connected with the motor so as to drive the motor to rotate. According to the electronic direct-drive type stroke oar component disclosed by the embodiment of the invention, the stroke oar is driven by the motor, and no extra speed reduction device is needed, so that a transmission structure of the stroke oar is effectively simplified, and the reliability is improved; meanwhile, the power generator is integrally arranged with the engine, and the rotor of the power generator is used as the fly wheel of the engine, the bottleneck that a conventional engine needs great power to generate power is solved, and the weight of the integrated hybrid-power device is effectively reduced.

Description

technical field [0001] The present invention relates to the field of aviation technology, and more particularly, relates to an electric direct-drive tail rotor assembly for a hybrid helicopter and a helicopter with the electric direct-drive tail rotor assembly. Background technique [0002] Main rotor with tail rotor is a common configuration for helicopters. Among them, on the one hand, the tail rotor is used to generate lateral force to balance the reaction torque of the main rotor, and on the other hand, it provides heading control. In related technologies, a common source of tail rotor power is that the engine outputs power to a reduction mechanism, and transmits power to the tail rotor through a mechanical transmission (such as a belt pulley, a drive shaft) to drive the tail rotor to rotate. [0003] Due to the large difference between the output shaft speed of the engine and the speed of the rotor and the tail rotor speed, a separate reducer must be designed for the r...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D27/02B64D35/00
CPCY02T50/40
Inventor 王浩文姜辰张玉文
Owner 珠海隆华直升机科技有限公司
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