CN201395245Y - Helicopter powered with electricity - Google Patents
Helicopter powered with electricity Download PDFInfo
- Publication number
- CN201395245Y CN201395245Y CN2009203039436U CN200920303943U CN201395245Y CN 201395245 Y CN201395245 Y CN 201395245Y CN 2009203039436 U CN2009203039436 U CN 2009203039436U CN 200920303943 U CN200920303943 U CN 200920303943U CN 201395245 Y CN201395245 Y CN 201395245Y
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- CN
- China
- Prior art keywords
- rotor
- tail
- helicopter
- gas turbine
- electricity
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
The utility model relates to a helicopter powered with electricity, which consists of a rotor wing on a body, a tail, a gas turbine engine and a controller; the key points of the helicopter are as follows: the gas turbine engine is a gas turbine engine fully powered with electricity; a rotor wing is arranged on the rotor wing a rotary shaft of which is connected with a rotor wing actuator poweredwith electricity; a rotary shaft of a stroke oar motor of the tail is connected with the stroke oar and a stroke oar actuator powered with electricity. The helicopter adopts the gas turbine engine fully powered with electricity and drives the rotor wing and the stroke oar with electricity, requires no mechanical speed reduction drive system and hydraulic actuating device and has simple structure,small volume, little vibration and noise and high reliability and reduces weight by 10 percent compared with the existing helicopter.
Description
Technical field
The utility model relates to a kind of helicopter, is specifically related to a kind of electric power helicopter.
Background technology
Helicopter includes rotor, tail-rotor, fuselage, driving engine, driving system and control system usually.Helicopter provides power by the power take-off shaft of turboshaft engine, by the deceleration transmission system, power is passed to rotor, tail-rotor and hydraulic actuation device, and by hydraulic actuation device control rotor and tail-rotor, rotor and tail-rotor are respectively helicopter lift and balancing torque are provided.This helicopter need be joined a cover complicated mechanical formula deceleration transmission and a mechanical type hydraulic system.As main reduction gear, intermediate gearbox, tail reducer, tail-rotor axle and hydraulic actuation mechanism, bang path is long, and volume is big, Heavy Weight, and machine driven system also causes vibration easily, noise is big, poor reliability.
Summary of the invention
The purpose of this utility model is at the above-mentioned deficiency of existing helicopter, provides a kind of simple in structure, and volume is little, and is in light weight, the electric power helicopter that noise is little.
Electric power helicopter of the present utility model contains rotor, tail, gas turbine engine and the controller that is located on the fuselage, it is characterized in that described gas turbine engine is complete electric gas turbine generating engine; Also have additional the rotor motor on the described rotor, be connected with rotor electrical actuation device on the turning cylinder of rotor motor; Tail is provided with the tail-rotor motor, is connected with tail-rotor and tail-rotor electrical actuation device on the S. A. of tail-rotor motor.
In order to realize this purpose better, described controller and gas turbine engine, tail-rotor electrical actuation device, rotor electrical actuation device, rotor motor, the electrical connection of tail-rotor motor.
The principle of work of electric power helicopter of the present utility model is: gas turbine engine output electric energy, for other consumers in rotor motor, tail-rotor motor, electrical actuation device and the helicopter provide electric energy, controller provides the power and the balancing torque of flight by the rotating speed and the mode of operation of electrical actuation device control rotor, tail-rotor for helicopter.
Electric power helicopter of the present utility model has adopted complete electric gas turbine generating engine, rotor and tail-rotor are by driven by power, mechanical type deceleration transmission system and hydraulic actuation device have been cancelled, simple with existing helicopter structure compared, volume is little, weight can alleviate 10%, and vibration and noise are little, good reliability.
Description of drawings
Fig. 1 is a structural representation of the present utility model.
Fig. 2 is the electrical connection scheme drawing of the utility model controller.
Among the figure 1, the rotor motor, 2, rotor electrical actuation device, 3, rotor, 4, gas turbine engine, 5, lead, 6, the tail-rotor motor, 7, tail-rotor, 8, tail-rotor electrical actuation device, 9, controller, 10, fuselage, 11 tails.
The specific embodiment
Electric power helicopter of the present utility model comprises rotor motor 1, gas turbine engine 4 and controller 9 and the tail 11 that is fixed in the fuselage 10.Also have additional rotor motor 1 on the rotor 3, rotor 3 and rotor electrical actuation 2 devices are fixed on the S. A. of rotor motor 1; Tail 11 is provided with tail-rotor motor 6, and tail-rotor 7 and tail-rotor electrical actuation device 8 are fixed on the S. A. of tail-rotor motor 6.Gas turbine engine 4 is for only exporting the complete electric gas turbine generating engine of electric energy.Gas turbine engine 4, rotor motor 1, tail-rotor motor 6, rotor electrical actuation device 2, tail-rotor electrical actuation device 8 and controller 9 are electrically connected by lead 5.
During work, the electric energy that gas turbine engine 4 sends provides power for operation through lead 5 to rotor motor 1, tail-rotor motor 6, controller 9 is realized the flight of helicopter and the control of balance by the rotating speed and the mode of operation of rotor electrical actuation device 2, tail-rotor electrical actuation device 8 control rotor motors 1, tail-rotor motor 6.
Claims (2)
1. an electric power helicopter contains the rotor (3), tail (11), gas turbine engine (4) and the controller (9) that are located on the fuselage (10), and it is characterized in that: described gas turbine engine (4) is complete electric gas turbine generating engine; Also have additional rotor motor (1) on the described rotor (3), be connected with rotor electrical actuation device (2) on the turning cylinder of rotor motor (1); Described tail (11) is provided with tail-rotor motor (6), is connected with tail-rotor (7) and tail-rotor electrical actuation device (8) on the S. A. of tail-rotor motor (6).
2. helicopter according to claim 1 is characterized in that: described controller (9) and gas turbine engine (4), and rotor electrical actuation device (2), tail-rotor electrical actuation device (8), rotor motor (1), tail-rotor motor (6) is electrically connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203039436U CN201395245Y (en) | 2009-06-03 | 2009-06-03 | Helicopter powered with electricity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009203039436U CN201395245Y (en) | 2009-06-03 | 2009-06-03 | Helicopter powered with electricity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201395245Y true CN201395245Y (en) | 2010-02-03 |
Family
ID=41617746
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009203039436U Expired - Lifetime CN201395245Y (en) | 2009-06-03 | 2009-06-03 | Helicopter powered with electricity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201395245Y (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103879555A (en) * | 2012-12-21 | 2014-06-25 | 中国直升机设计研究所 | Electrically driven helicopter tail rotor transmission system |
| CN108791906A (en) * | 2018-06-04 | 2018-11-13 | 李江江 | A kind of dynamical system in the energy precisely large-scale multi-rotor aerocraft of speed governing |
-
2009
- 2009-06-03 CN CN2009203039436U patent/CN201395245Y/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103879555A (en) * | 2012-12-21 | 2014-06-25 | 中国直升机设计研究所 | Electrically driven helicopter tail rotor transmission system |
| CN103879555B (en) * | 2012-12-21 | 2016-10-26 | 中国直升机设计研究所 | A kind of driven type helicopter tail rotor drive system |
| CN108791906A (en) * | 2018-06-04 | 2018-11-13 | 李江江 | A kind of dynamical system in the energy precisely large-scale multi-rotor aerocraft of speed governing |
| CN108791906B (en) * | 2018-06-04 | 2020-12-18 | 李江江 | Power system used in large-scale multi-rotor aircraft capable of accurately adjusting speed |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20100203 |