CN105194883A - Motor for model airplane aircraft - Google Patents
Motor for model airplane aircraft Download PDFInfo
- Publication number
- CN105194883A CN105194883A CN201510592751.1A CN201510592751A CN105194883A CN 105194883 A CN105194883 A CN 105194883A CN 201510592751 A CN201510592751 A CN 201510592751A CN 105194883 A CN105194883 A CN 105194883A
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- China
- Prior art keywords
- armature winding
- winding stator
- rotor
- motor
- permanent magnet
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- 238000004804 winding Methods 0.000 claims abstract description 52
- 238000009434 installation Methods 0.000 claims description 12
- 238000010586 diagram Methods 0.000 description 3
- 230000001141 propulsive effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
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Abstract
The invention discloses a motor for a model airplane aircraft. The motor comprises an armature winding stator and a permanent magnet rotor, and is characterized in that the armature winding stator consists of a first armature winding stator and a second armature winding stator; the permanent magnet rotor consists of a first permanent magnet rotor and a second permanent magnet rotor; the first armature winding stator and the second armature winding stator are respectively arranged at two sides of a fixing element; the first permanent magnet rotor is connected to the outside of the first armature winding stator in a sleeving way; the second permanent magnet rotor is connected to the outside of the second armature winding stator in a sleeving way; the middle of the first permanent magnet rotor is provided with a rotating shaft; the rotating shaft sequentially passes through a first shaft hole of the first armature winding stator, a second shaft hole of the second armature winding stator and a third shaft hole of the second permanent magnet rotor. The invention provides a double-rotor motor for the model airplane aircraft; two propellers can be installed at the same time to be used. The flight power of the model airplane aircraft is increased.
Description
Technical field
The present invention relates to motor, specifically a kind of motor for aeromodelling aerocraft.
Background technology
The model of an airplane (aeromodelling aerocraft) is general the same with manned aircraft, primarily of wing, empennage, fuselage, undercarriage and engine five part form.Wing is the model of an airplane produces lift device when flying, and the horizontal side when model of an airplane can be kept to fly is stablized.Empennage comprises tailplane and vertical tail two parts.Pitching when tailplane can keep the model of an airplane to fly is stablized, and vertical tail keeps direction during model of an airplane flight to stablize.The lifting of the elevator energy Controlling model aircraft on tailplane, the rudder on vertical tail can the heading of Controlling model aircraft.Fuselage each several part of model is coupled to an overall trunk portion on fuselage.Necessary control parts can be loaded, equipment and fuel etc. in fuselage simultaneously.The device that undercarriage takes off for the model of an airplane, land and parks.An anterior undercarriage, after each undercarriage in two sides first three point type, each undercarriage in anterior two sides, after a undercarriage rear bikini.Engine is the device that the model of an airplane produces flying power.Modern Aviation model sport is divided into free flight, line manipulation, wireless remotecontrol, emulation and the five large classes such as electronic.Be divided into again by power mode: piston engine, jet engine, rubber-band model aircraft and motorless model glider etc.Screw is that to depend on that blade rotates in atmosphere by engine rotation power conversion be the device of propulsive force.When screw rotates, blade constantly pushes large quantity of air (propulsive medium) backward, and blade produces a propulsive force.
China Patent No. 201320038563.0, name is called " a kind of eight shaft model aircraft helical mounts ", disclose a kind of eight shaft model aircraft helical mounts, it comprises spiral support body, described spiral support body center is control device installation portion, an affixed annular shaft member installation portion in control device installation portion lower end, is connected with eight identical shaft member of structure, is provided with motor above each shaft member end in annular shaft member installation portion outside.Described eight shaft member have at least in three shaft member and are provided with foot rest.
Be provided with motor above shaft member end recited above, namely horn end mounted motor, screw is arranged on machine shaft.Control device installation portion is for installing control device and the battery of the model of an airplane.Control device comprises control circuit board and remote-controlled receiver, and motor is connected with control device, battery by wire.
In this technical scheme, in motor, only have a rotor, in same motor, two screws can not be installed simultaneously.Therefore, its power produced is limited, and flying speed is not good enough.
Summary of the invention
Technical problem to be solved: the present invention is not enough to prior art, provides a kind of double-rotor machine for aeromodelling aerocraft, can install two screws simultaneously and use.
Technical scheme: a kind of motor for aeromodelling aerocraft, comprise armature winding stator, PM rotor, it is characterized in that: described armature winding stator is made up of the first armature winding stator and the second armature winding stator, described PM rotor is made up of the first PM rotor and the second PM rotor, described first armature winding stator and the second armature winding stator are installed on fixture both sides respectively, described first PM rotor is socketed in outside the first armature winding stator, described second PM rotor is socketed in outside the second armature winding stator, a rotating shaft is had in the middle of described first PM rotor, described rotating shaft is successively through the first axis hole of the first armature winding stator, second axis hole of the second armature winding stator, the Triaxial hole of the second PM rotor.
There is installation portion described fixture periphery, and a support is connected in described installation portion.Described rotating shaft, through after the Triaxial hole of the second PM rotor, is arranged with positioning piece in rotating shaft.Described second PM rotor has screw installing hole.
Effect of the present invention is: the present invention, owing to have employed technique scheme, a motor has two rotors, and its scientific structure design is reasonable, can install two screws simultaneously and use, add the flying power of aeromodelling aerocraft.
Accompanying drawing explanation
Fig. 1 is one of structural representation of the present invention.
Fig. 2 is structural representation two of the present invention.
Fig. 3 is the present invention's one of schematic diagram when not installing the first armature winding stator and the second armature winding stator.
Fig. 4 is the present invention's schematic diagram two when not installing the first armature winding stator and the second armature winding stator.
Fig. 5 is the present invention's schematic diagram three when not installing the first armature winding stator and the second armature winding stator.
Fig. 6 is the present invention first PM rotor structural representation.
Fig. 7 is the present invention second PM rotor structural representation.
Number in the figure represents: 1 first armature winding stator, 2 second armature winding stators, 3 first PM rotors, 4 second PM rotors, 5 fixtures, 6 rotating shafts, 7 first axis holes, 8 second axis holes, 9 Triaxial holes, 10 installation portions, 11 supports, 12 keepers, 13 power lines, 14 permanent magnets, 15 screw installing holes.
Detailed description of the invention
See Fig. 1-7, a kind of motor for aeromodelling aerocraft, comprise armature winding stator, PM rotor, its special character is: described armature winding stator is made up of the first armature winding stator 1 and the second armature winding stator 2, described PM rotor is made up of the first PM rotor 3 and the second PM rotor 4, described first armature winding stator 1 and the second armature winding stator 2 are installed on fixture 5 both sides respectively, described first PM rotor 3 is socketed in outside the first armature winding stator 1, described second PM rotor 4 is socketed in outside the second armature winding stator 2, a rotating shaft 6 is had in the middle of described first PM rotor 3, described rotating shaft 6 is successively through the first axis hole 7 of the first armature winding stator, second axis hole 8 of the second armature winding stator, the Triaxial hole 9 of the second PM rotor.The visible second armature winding stator 2 of the visible first armature winding stator 1, Fig. 5 of Fig. 4.
There is installation portion 10 described fixture 5 periphery, and a support 11 is connected in described installation portion 10.Described second PM rotor 4 has screw installing hole 15.
See Fig. 2, described rotating shaft 6, through after the Triaxial hole 9 of the second PM rotor, is arranged with keeper 12 in rotating shaft 6.Its effect is that the first PM rotor 3 and the second PM rotor 4 can not be shifted.
Specifically details are as follows: have two groups of power lines 13, is connected respectively with an armature winding stator 1 with the second armature winding stator 2.First PM rotor 3 and the second PM rotor 4 have some permanent magnets 14.During use, support 11 rear end is mounted on the helical mount horn of aeromodelling aerocraft, each horn has two screws, and the second screw is arranged on the screw installing hole 15 of the second PM rotor, and the first screw is arranged on rotating shaft 6 end of the first PM rotor.First PM rotor 3 and the second PM rotor 4 can rotate in same direction, also can rotate in the opposite direction.When first PM rotor rotates, rotating shaft 6 is rotated thereupon, and the first screw be arranged in rotating shaft 6 rotates; Second PM rotor also drives the second screw to rotate thereupon when rotating.Two screws can be installed use simultaneously, add the flying power of aeromodelling aerocraft.
The present invention is only limitted to absolutely not these examples.The foregoing is only the good embodiment of the present invention, only for describing the present invention, the restriction to scope of the present invention can not be interpreted as.It should be pointed out that all any amendments done within the spirit and principles in the present invention, equivalent replacement and improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. the motor for aeromodelling aerocraft, comprise armature winding stator, PM rotor, it is characterized in that: described armature winding stator is made up of the first armature winding stator and the second armature winding stator, described PM rotor is made up of the first PM rotor and the second PM rotor, described first armature winding stator and the second armature winding stator are installed on fixture both sides respectively, described first PM rotor is socketed in outside the first armature winding stator, described second PM rotor is socketed in outside the second armature winding stator, a rotating shaft is had in the middle of described first PM rotor, described rotating shaft is successively through the first axis hole of the first armature winding stator, second axis hole of the second armature winding stator, second permanent magnet
The Triaxial hole of rotor.
2. the motor for aeromodelling aerocraft according to claim 1, is characterized in that: there is installation portion described fixture periphery, and a support is connected in described installation portion.
3. the motor for aeromodelling aerocraft according to claim 1, is characterized in that: described rotating shaft, through after the Triaxial hole of the second PM rotor, is arranged with positioning piece in rotating shaft.
4. the motor for aeromodelling aerocraft according to claim 1, is characterized in that: described second PM rotor has screw installing hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510592751.1A CN105194883A (en) | 2015-09-17 | 2015-09-17 | Motor for model airplane aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510592751.1A CN105194883A (en) | 2015-09-17 | 2015-09-17 | Motor for model airplane aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105194883A true CN105194883A (en) | 2015-12-30 |
Family
ID=54943044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510592751.1A Pending CN105194883A (en) | 2015-09-17 | 2015-09-17 | Motor for model airplane aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105194883A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0698957A1 (en) * | 1994-08-26 | 1996-02-28 | Eta SA Fabriques d'Ebauches | Electromechanical transducer having two rotors |
| US5838135A (en) * | 1995-12-22 | 1998-11-17 | Satake Corporation | Driving means formed by induction motor and method for starting the same |
| CN2632932Y (en) * | 2003-07-24 | 2004-08-11 | 常若福 | Coaxial double motor |
| CN1684342A (en) * | 2004-04-14 | 2005-10-19 | 沈超然 | Differential stepless speed changing motor |
| CN102801273A (en) * | 2011-05-26 | 2012-11-28 | 福斯特资产有限公司 | Brushless motor and system thereof |
| CN203318685U (en) * | 2013-04-16 | 2013-12-04 | 张锦海 | Motor for aerial photography of aeromodelling aircraft |
| CN103580407A (en) * | 2013-11-08 | 2014-02-12 | 北京明正维元电机技术有限公司 | Permanent magnetic synchronous combination motor |
| CN204996125U (en) * | 2015-09-17 | 2016-01-27 | 惠州市东阳智能技术股份有限公司 | A motor for model aeroplane and model ship aircraft |
-
2015
- 2015-09-17 CN CN201510592751.1A patent/CN105194883A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0698957A1 (en) * | 1994-08-26 | 1996-02-28 | Eta SA Fabriques d'Ebauches | Electromechanical transducer having two rotors |
| US5838135A (en) * | 1995-12-22 | 1998-11-17 | Satake Corporation | Driving means formed by induction motor and method for starting the same |
| CN2632932Y (en) * | 2003-07-24 | 2004-08-11 | 常若福 | Coaxial double motor |
| CN1684342A (en) * | 2004-04-14 | 2005-10-19 | 沈超然 | Differential stepless speed changing motor |
| CN102801273A (en) * | 2011-05-26 | 2012-11-28 | 福斯特资产有限公司 | Brushless motor and system thereof |
| CN203318685U (en) * | 2013-04-16 | 2013-12-04 | 张锦海 | Motor for aerial photography of aeromodelling aircraft |
| CN103580407A (en) * | 2013-11-08 | 2014-02-12 | 北京明正维元电机技术有限公司 | Permanent magnetic synchronous combination motor |
| CN204996125U (en) * | 2015-09-17 | 2016-01-27 | 惠州市东阳智能技术股份有限公司 | A motor for model aeroplane and model ship aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| CB02 | Change of applicant information |
Address after: Two road 516000 in Guangdong province Huizhou City Zhongkai high tech Zone No. 45 and (two) the first floor of building Applicant after: HUIZHOU DONGYANG INTELLIGENT TECHNOLOGY Co.,Ltd. Address before: 516000 Guangdong province Huizhou City Pingnan Zhongkai high tech area Huihuan Village No. 28 building four Applicant before: Dong Yang Model Technology Co.,Ltd. |
|
| COR | Change of bibliographic data | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20151230 |