CN101177167A - Power-driven system of aircraft - Google Patents
Power-driven system of aircraft Download PDFInfo
- Publication number
- CN101177167A CN101177167A CNA2007101984277A CN200710198427A CN101177167A CN 101177167 A CN101177167 A CN 101177167A CN A2007101984277 A CNA2007101984277 A CN A2007101984277A CN 200710198427 A CN200710198427 A CN 200710198427A CN 101177167 A CN101177167 A CN 101177167A
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- transmission shaft
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- aircraft
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Abstract
The invention relates to a power drive system for an aircraft, comprising a motor and an engine room of an aircraft. The invention is characterized in that the motor is vertically or horizontally arranged in the engine room of the aircraft; wherein, a stator and a rotor of the motor are fixedly connected with a vertical or horizontal transmission shaft of the stator and a transmission shaft of the rotor respectively; the transmission shaft of the stator and the transmission shaft of the rotor are connected with the engine room through a taper roller bearing or are independently fixed in the engine room through a bearing support of the transmission shaft of the stator, and a propeller is assembled respectively at the end of the transmission shaft of the stator and the transmission shaft of the rotor which are protruding the engine room. The invention has the advantages of adopting both the stator and the rotor of the motor as the power output unit, effectively and compactly eliminating problems of torsion moment from the propeller in the prior aircraft design, reducing the torque resulting from the transmission shaft of the propeller to the frame to zero, meeting the design demands for miniature, simple and light aircraft, thus facilitating the popularization and manufacturing of aircraft.
Description
Technical field
The invention belongs to the power-driven system of aviation flight equipment, relate in particular to a kind of no torque power drive system that is applicable to the various aviation aircrafts that utilize the screw propeller driving.
Background technology
Existing autogyro, dirigible etc. all adopt screw propeller to drive, this class aviation aircraft all adopts indirect antagonistic force engine drive, its principle of work is to be rotated the air work done through the rotor that drives wind stick, helicopter after some row mechanical drive by driving engine, air is quickened backward or flow downward, at this moment air produces antagonistic force to screw propeller and just is used for advancing aircraft.This class driving engine has piston engine, propeller turbine, turboaxle motor, turbo-propeller Duct-Burning Turbofan etc.The then existing direct antagonistic force of turbofan engine also has indirect antagonistic force, but often it is incorporated into direct antagonistic force driving engine one class, so also be called turbofan.
No matter adopt which kind of driving engine, existing driving engine all adopts the transmission shaft of a connecting bolt oar as takeoff output, because the other end of transmission shaft is connected with the fuselage of aircraft or connects indirectly, when so screw propeller produces antagonistic force, can bring the opposing torque of respective action power to fuselage, influence the normal somatotype of aircraft, for eliminating this turn-back moment, existing aircraft all comes this moment of balance by long empennage is set.This not only makes the volume and weight of aircraft increase on the one hand, also can cause simultaneously the complexity of the design and the control of aircraft, make aircraft be difficult to realize miniaturization and simple for structureization, the cost of aircraft can't reduce, and this has hindered the development and the popularization of aircraft to a certain extent.Although the coaxial double-rotary wing autogyro has been arranged, balance turn-back moment, but this coaxial system still adopts the mechanical drive controlling unit to be able to the reactive torque of balance airframe, still makes aircaft configuration complexity, weight huge.
Summary of the invention
The purpose of this invention is to provide a kind of reasonable in design, make the twist moment of aircraft fuselage easily be reduced to zero, the power-driven system of the aircraft that drive efficiency improves, by adopting electrically operated electrical motor, by two-way takeoff output, satisfied that Flight Vehicle Structure is simple, the designing requirement of miniaturization, more helped the popularization and the manufacturing of aircraft.
For achieving the above object, the technical solution used in the present invention is as follows:
A kind of power-driven system of aircraft, comprise electrical motor and aircraft nacelle, it is characterized in that described electrical motor vertical or horizontal positioned in aircraft nacelle, the stator of described electrical motor and rotor are fixedly connected on respectively on stator transmission shaft and the rotor transmission shaft, and the end that stretches out outside the cabin of described stator transmission shaft and rotor transmission shaft all assembles screw propeller.
Specifically, the axle center of described stator transmission shaft and rotor transmission shaft is provided with one heart, and diaxon stretches out in the same direction outside the cabin or towards two opposite directions and stretches out respectively outside the cabin, and the end that stator transmission shaft and rotor transmission shaft stretch out outside the cabin all assembles screw propeller.
Described rotor transmission shaft and stator transmission shaft stretch out outside the cabin in the same direction, the stator transmission shaft is one to cooperate and concentric sleeve pipe with rotor transmission shaft, described stator drive shaft sleeve is contained in the outside of rotor transmission shaft, the stator transmission shaft by two bearing fixing in stator transmission shafts bearing, this bearing seat by bolt in the cabin inwall.
Described stator transmission shaft and rotor transmission shaft stretch out respectively outside the cabin towards two opposite directions, and the stator transmission shaft all is connected with the cabin by circular cone roller bearing with rotor transmission shaft.
Be equipped with battery feed or generator power supply in the described cabin, described battery feed or generator power supply are connected by brush, current colector with described electrical motor.
Described stator transmission shaft and rotor transmission shaft all can vertically be placed or equal horizontal positioned, and the end that diaxon stretches out outside the cabin all assembles screw propeller.
Described electrical motor is internal rotor, outer stator structure electrical motor or internal stator, outer-rotor structure electrical motor.
Described aircraft is autogyro, toy helicopter, dirigible or aerocraft.
The power-driven system of this aircraft, the stator of electrical motor and rotor are on hand of rotation fixing, electrical motor only is erected in the cabin by stator transmission shaft and rotor transmission shaft, the bearing suit that is provided with on stator transmission shaft and rotor transmission shaft and the cabin or be fixed in the cabin by stator transmission shafts bearing separately, after the electrical motor energising, when the stator transmission shaft rotates counterclockwise, rotor transmission shaft will clockwise rotate, the torque of the two equates that direction is opposite, drives two screw propellers and rotates, two screw propellers are suppressed air, all obtain equidirectional lift or tractive force, drive aircraft and rise or advance, this moment, the cabin was not subjected to the effect of moment of torsion, can not rotate, thereby can omit the long empennage of pure helicopter, make the volume of aircraft littler, structure is simpler.
By different designs, can realize that the screw propeller of stator transmission shaft and rotor transmission shaft assembling lays respectively at the upper and lower in cabin or all is positioned at the top in cabin or the below in cabin to stator transmission shaft and rotor transmission shaft.In like manner, can realize that also the screw propeller of stator transmission shaft and rotor transmission shaft assembling lays respectively at the front and back in cabin or all is positioned at the place ahead in cabin or the rear in cabin by horizontal positioned to electrical motor.
Beneficial effect of the present invention is, the power-driven system of this aircraft adopts the stator of electrical motor and rotor all as power take-off unit, effectively also eliminated the problem that has screw propeller detorsion moment in the existing Flight Vehicle Design compactly, the moment of torsion that propeller drive shaft is produced fuselage is reduced to zero, miniaturization, simplification and the made of light design demand of aircraft be can satisfy, the popularization and the manufacturing of aircraft helped.
Description of drawings
Fig. 1 is the local section structural representation of the embodiment of the invention 1;
Fig. 2 is the local section structural representation of the embodiment of the invention 2.
The specific embodiment
Embodiment 1 as shown in Figure 1, the power-driven system of this aircraft comprises electrical motor and aircraft nacelle 8, is provided with the power of battery feed as electrical motor in the cabin, storage battery is connected by brush, current colector with electrical motor.Electrical motor is vertically placed in aircraft nacelle 8, the stator 6 of electrical motor and rotor 7 are captiveed joint respectively and are stretched out stator transmission shaft 3 and rotor transmission shaft 2 outside the cabin straight up, stator transmission shaft 3 is the sleeve pipe with rotor transmission shaft 2 concentric fit, stator transmission shaft 3 is sleeved on the outside of rotor transmission shaft 2, stator transmission shaft 3 is installed in the stator transmission shafts bearing 10 by two bearings 5 and 9, in cabin 8, screw propeller 1 is assembled in the upper end of rotor transmission shaft 2 to stator transmission shafts bearing 10 by bolt; The upper end assembling screw propeller 4 of stator transmission shaft 3.
Embodiment 2 as shown in Figure 2, the power-driven system of this aircraft comprises electrical motor and aircraft nacelle 8, is provided with the power of battery feed as electrical motor in the cabin, storage battery is connected by brush, current colector with electrical motor.Electrical motor is vertically placed in aircraft nacelle 8, and the inside of electrical motor is provided with rotor 7, and the upper end captive joint rotor transmission shaft 2 of rotor, rotor transmission shaft 2 stretch out upper end, cabin position assembling screw propeller 1; Rotor transmission shaft is connected by tapered roller bearing 5 assemblings with the top, cabin.The outer setting stator 6 of electrical motor, the stator transmission shaft 3 that described stator lower end captive joint stretches out downwards, the lower end of stator transmission shaft 3 is located in the tapered roller bearing 9 of bottom, cabin setting, external part assembling screw propeller 4.
Claims (8)
1. the power-driven system of an aircraft, comprise electrical motor and aircraft nacelle, it is characterized in that described electrical motor vertical or horizontal positioned in aircraft nacelle, the stator of described electrical motor and rotor are fixedly connected on respectively on stator transmission shaft and the rotor transmission shaft, and the end that stretches out outside the cabin of described stator transmission shaft and rotor transmission shaft all assembles screw propeller.
2. the power-driven system of aircraft according to claim 1, the axle center that it is characterized in that stator transmission shaft and rotor transmission shaft is provided with one heart, diaxon stretches out in the same direction outside the cabin or towards two opposite directions and stretches out respectively outside the cabin, and the end that stator transmission shaft and rotor transmission shaft stretch out outside the cabin all assembles screw propeller.
3. the power-driven system of aircraft according to claim 2, it is characterized in that described rotor transmission shaft and stator transmission shaft stretch out outside the cabin in the same direction, the stator transmission shaft is one to cooperate and concentric sleeve pipe with rotor transmission shaft, described stator drive shaft sleeve is contained in the outside of rotor transmission shaft, the stator transmission shaft by two bearing fixing in stator transmission shafts bearing, this bearing seat by bolt in the cabin inwall.
4. the power-driven system of aircraft according to claim 2 is characterized in that described stator transmission shaft and rotor transmission shaft stretch out respectively outside the cabin towards two opposite directions, and the stator transmission shaft all is connected with the cabin by circular cone roller bearing with rotor transmission shaft.
5. the power-driven system of aircraft according to claim 1 is characterized in that being equipped with in the described cabin battery feed or generator power supply, and described battery feed or generator power supply are connected by brush, current colector with described electrical motor.
6. the power-driven system of aircraft according to claim 1,, it is characterized in that described stator transmission shaft and rotor transmission shaft all can vertically be placed or equal horizontal positioned, the end that diaxon stretches out outside the cabin all assembles screw propeller.
7. the power-driven system of aircraft according to claim 1 is characterized in that described electrical motor is internal rotor, outer stator structure electrical motor or internal stator, outer-rotor structure electrical motor.
8. the power-driven system of aircraft according to claim 1 is characterized in that described aircraft is autogyro, toy helicopter, dirigible or aerocraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101984277A CN101177167A (en) | 2007-12-11 | 2007-12-11 | Power-driven system of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNA2007101984277A CN101177167A (en) | 2007-12-11 | 2007-12-11 | Power-driven system of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101177167A true CN101177167A (en) | 2008-05-14 |
Family
ID=39403629
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNA2007101984277A Withdrawn CN101177167A (en) | 2007-12-11 | 2007-12-11 | Power-driven system of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101177167A (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009143669A1 (en) * | 2008-05-27 | 2009-12-03 | Tian Yu | Aircraft and the power driving system thereof |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN103625632A (en) * | 2013-11-29 | 2014-03-12 | 陈科学 | Manned aircraft |
| CN105799926A (en) * | 2016-05-03 | 2016-07-27 | 任孝忠 | Autorotation device |
| CN105857577A (en) * | 2016-04-20 | 2016-08-17 | 曾治蛟 | Quick disassembling self-locking mechanism for propeller |
| WO2017114245A1 (en) * | 2015-12-31 | 2017-07-06 | 歌尔科技有限公司 | Coaxial twin-propeller twin-motor aerial vehicle |
| CN107054632A (en) * | 2015-12-23 | 2017-08-18 | 克里斯琴.施米德 | Rotary-wing aircraft and the take-off and landing equipment for this rotary-wing aircraft |
| CN109878711A (en) * | 2019-01-25 | 2019-06-14 | 珠海磐磊智能科技有限公司 | Double paddle power devices and its mobile devices |
| CN112429195A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Translation flying device |
-
2007
- 2007-12-11 CN CNA2007101984277A patent/CN101177167A/en not_active Withdrawn
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009143669A1 (en) * | 2008-05-27 | 2009-12-03 | Tian Yu | Aircraft and the power driving system thereof |
| CN102730192A (en) * | 2011-04-14 | 2012-10-17 | 戴瑾 | Vertical take-off and landing aircraft |
| CN103625632A (en) * | 2013-11-29 | 2014-03-12 | 陈科学 | Manned aircraft |
| CN107054632A (en) * | 2015-12-23 | 2017-08-18 | 克里斯琴.施米德 | Rotary-wing aircraft and the take-off and landing equipment for this rotary-wing aircraft |
| WO2017114245A1 (en) * | 2015-12-31 | 2017-07-06 | 歌尔科技有限公司 | Coaxial twin-propeller twin-motor aerial vehicle |
| JP6453527B1 (en) * | 2015-12-31 | 2019-01-16 | ゴーアテック テクノロジー カンパニー リミテッド | Coaxial twin propeller twin motor aircraft |
| US10259573B2 (en) | 2015-12-31 | 2019-04-16 | Goertek Technology Co., Ltd. | Coaxial twin-propeller twin-motor aerial vehicle |
| CN105857577A (en) * | 2016-04-20 | 2016-08-17 | 曾治蛟 | Quick disassembling self-locking mechanism for propeller |
| CN105799926A (en) * | 2016-05-03 | 2016-07-27 | 任孝忠 | Autorotation device |
| CN109878711A (en) * | 2019-01-25 | 2019-06-14 | 珠海磐磊智能科技有限公司 | Double paddle power devices and its mobile devices |
| CN112429195A (en) * | 2020-11-26 | 2021-03-02 | 广东国士健科技发展有限公司 | Translation flying device |
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Legal Events
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| C06 | Publication | ||
| PB01 | Publication | ||
| C04 | Withdrawal of patent application after publication (patent law 2001) | ||
| WW01 | Invention patent application withdrawn after publication |