KR20170090037A - Power transmission apparatus for aircraft - Google Patents

Power transmission apparatus for aircraft Download PDF

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Publication number
KR20170090037A
KR20170090037A KR1020160010383A KR20160010383A KR20170090037A KR 20170090037 A KR20170090037 A KR 20170090037A KR 1020160010383 A KR1020160010383 A KR 1020160010383A KR 20160010383 A KR20160010383 A KR 20160010383A KR 20170090037 A KR20170090037 A KR 20170090037A
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KR
South Korea
Prior art keywords
case
electric motor
opening
cooling hole
magnet
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KR1020160010383A
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Korean (ko)
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KR101796564B1 (en
Inventor
김진원
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한국항공우주연구원
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Priority to KR1020160010383A priority Critical patent/KR101796564B1/en
Publication of KR20170090037A publication Critical patent/KR20170090037A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K5/00—Casings; Enclosures; Supports
    • H02K5/04—Casings or enclosures characterised by the shape, form or construction thereof
    • H02K5/20—Casings or enclosures characterised by the shape, form or construction thereof with channels or ducts for flow of cooling medium
    • B64C2700/6288—
    • Y02T50/54—
    • Y02T50/62—

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Power Engineering (AREA)
  • Motor Or Generator Cooling System (AREA)

Abstract

The present invention relates to a power transmission device for an aircraft having a moisture penetration prevention function and an overheat prevention function, and more particularly, to a power transmission device for an aircraft having a first magnet and having a power supply part connected to the stator, An electric motor including a second magnet corresponding to the first magnet of the stator and a case having a cooling hole formed therein; And opening and closing means mounted on the case of the electric motor to open and close the cooling hole or to adjust the opening amount of the cooling hole according to the rotational speed of the case.
Therefore, in the present invention, when the airplane is stopped, the opening and closing control means automatically closes the cooling hole of the case to introduce moisture or foreign matter into the electric motor And the opening / closing control means adjusts the amount of opening of the cooling holes of the case according to the rotational force of the case when the airplane is operated, thereby preventing the moisture penetration and the overheating prevention function that can effectively implement the cooling function of the electric motor And a power transmission device for an aircraft.

Description

TECHNICAL FIELD [0001] The present invention relates to a power transmission apparatus for an aircraft having a moisture penetration prevention function and an overheat prevention function.

In the present invention, when the airplane is stopped, the opening / closing control means automatically closes the cooling hole of the case to introduce moisture or foreign matter into the electric motor The opening / closing control means adjusts the amount of opening of the cooling hole of the case according to the rotational force of the case when the airplane is operated so that the cooling function of the electric motor can be effectively implemented. To a power transmission device for an aircraft.

Generally, a brushless electric motor used in an aircraft is composed of a stator to which a battery is connected, a case in which a stator is incorporated, and a propeller is mounted.

In this case, in the case of an electric motor for an aircraft, since the case serves as a rotor, the case itself rotates and rotates the propeller to generate propulsion force of the aircraft.

In addition, in the case of an electric motor for an aircraft, the case itself has a high torque because it rotates, and a large propeller can be directly turned without a reducer, and an electric motor such as a reducer is not necessary.

However, in the case of an electric motor, the case itself rotates to generate a lot of heat. In this case, when the speed of the airplane is high, the electric motor is cooled by the flow of air. However, Since the electric motor is overheated, it is necessary to cool the electric motor.

For this purpose, in the case of an electric motor used for an aircraft, an upper plate of the case is usually pierced, or a plurality of cooling holes formed by being cut into a certain area are provided.

Accordingly, when the electric motor is driven, air flows into the cooling holes of the case through the air flow caused by rotation of the propeller, thereby cooling the electric motor.

However, when the electric motor is driven and the case rotates at a constant speed, rain, moisture, and other foreign matter may not flow due to the rotational force of the case. However, when the airplane is stopped and positioned outside, Or foreign matter such as dust may be introduced.

Such foreign matter, such as rainwater, moisture, or dust, may act as a cause of an electric short or a fire due to a short circuit.

In order to solve such a problem, conventionally, measures such as covering an electric motor with a tarpaulin such as a vinyl or the like have been taken, but such a measure is temporary and cumbersome, and thus can not solve a fundamental problem.

Accordingly, the present invention proposes a power transmission device that retains the cooling function for preventing overheating while preventing foreign matter such as rainwater, moisture, dust and the like from being injected into the cooling hole for cooling the electric motor.

Korean Registration Practice No. 20-0365355 (October 11, 2004)

SUMMARY OF THE INVENTION The present invention has been made to solve the above problems,

Opening and closing means for opening and closing a cooling hole of a case formed for heat dissipation of the electric motor is introduced so that when the airplane is stopped, the opening / closing control means automatically closes the cooling hole of the case to allow moisture or foreign matter to flow into the electric motor And the opening / closing control means adjusts the amount of opening of the cooling hole of the case according to the rotational force of the case during the operation of the airplane, thereby effectively realizing the cooling function of the electric motor.

Another object of the present invention is to prevent the inflow of moisture or foreign matter into the electric motor as described above, thereby improving the driving efficiency of the device and extending the service life of the device.

In addition, the present invention is not only simple in the structure of the opening / closing control means, but also realized in a mechanical structure, minimizing operational errors, thereby ensuring operational reliability and facilitating the installation of the apparatus. The purpose of

Another object of the present invention is to improve the air resistance by adjusting the opening amount of the cooling hole according to the speed of the electric motor.

It is a further object of the present invention to provide a rotation preventing portion on a throttle plate of the opening / closing control means so that the throttle plate can maintain a predetermined position in a state where the cooling hole is closed.

A first embodiment of a power transmission apparatus for an aircraft having a moisture penetration prevention function and an overheat prevention function according to the present invention includes a stator having a first magnet and connected to a power supply unit and a propeller disposed outside the stator, An electric motor including a second magnet corresponding to a first magnet of the stator and a case having a cooling hole formed therein; And an opening / closing control unit mounted on a case of the electric motor to open and close the cooling hole.

In a second aspect of the present invention, there is provided a power transmission apparatus for an aircraft comprising a stator having a first magnet and connected to a power supply unit, a propeller disposed outside the stator and connected to the first magnet of the stator, An electric motor including a second magnet and a case having a cooling hole; And opening / closing means mounted on the case of the electric motor for adjusting the amount of opening of the cooling hole according to the rotational speed of the case.

The opening and closing control means according to the present invention comprises a throttle plate hinged to the case and opening and closing the cooling hole, and an elastic member mounted on the case and supporting the throttle plate.

The end of the throttle plate of the opening / closing control means according to the present invention is mounted around the rotation center of the case.

The throttle of the opening and closing control means according to the present invention is characterized in that it is formed in the form of external light.

The throttle plate according to the present invention is further provided with a rotation preventing portion in which the ends of the adjacent throttle plates abut against each other to prevent rotation of the throttle plate when the cooling hole is closed.

The rotation preventing portion of the throttle plate according to the present invention is formed in a curved shape which is recessed inward.

The power transmission device for an aircraft having a moisture penetration prevention function and an overheat prevention function according to the present invention includes opening and closing control means for opening and closing a cooling hole of a case formed for cooling an electric motor, The cooling hole of the case is automatically closed to prevent moisture or foreign matter from flowing into the electric motor, and when the airplane is operated, the open / close control means adjusts the opening amount of the cooling hole of the case according to the rotational force of the case, The cooling function can be effectively implemented.

Further, according to the present invention, as described above, it is possible to prevent moisture and foreign matter from flowing into the electric motor, thereby improving the driving efficiency of the device and extending the service life of the device.

Further, since the present invention is not only simple in the structure of the opening and closing control means but also realized in a mechanical structure, operation error can be minimized, operation reliability can be ensured, installation of the apparatus can be easily and easily performed, .

Further, the present invention can improve the air resistance by adjusting the opening amount of the cooling holes according to the speed of the electric motor.

Further, according to the present invention, the rotation preventing portion is formed on the throttle plate of the opening / closing control means, so that the throttle plate can maintain the correct position in a state where the cooling hole is closed, thereby preventing the cooling hole from being opened.

In addition, since the rotation preventing portion of the throttle plate is brought into contact with the adjacent throttle plate, it is not necessary to provide a separate device to prevent the throttle plate from rotating. Thus, the cost can be reduced and the economical effect can be obtained.

1 is a photograph showing a conventional power transmission device for an aircraft,
2 is a conceptual perspective view showing a power transmission apparatus for an aircraft according to the present invention,
3 is a conceptual diagram showing an operating state of the opening and closing control means in the power transmission apparatus for an aircraft according to the present invention,
4 is a conceptual diagram showing the components of the centrifugal force acting on the throttle in the opening and closing regulating device according to the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a power transmission apparatus for an aircraft having a moisture penetration prevention function and an overheat prevention function according to the present invention will be described in detail with reference to the accompanying drawings.

2 and 4 illustrate an electric motor and an opening / closing control means according to the present invention. For convenience, in FIGS. 2 and 3, an electric motor for an aircraft is shown in FIG. 1, 1 is the same as that of the conventional art shown in Fig. 1, and thus the illustration thereof is omitted.

1 to 4, a power transmission apparatus for an aircraft according to the present invention includes a stator 11, an electric motor 10 (including a case 13 having a cooling hole 13c) serving as a rotor, Closing means 20 for opening and closing the cooling hole 13c of the case 13. The cooling /

1, a power supply unit, that is, an electric motor 10 driven by a battery as a power source is used. The electric motor 10 used in the aircraft is exposed to the outside Therefore, when the brush is provided, the brush is exposed to the outside and is exposed to the spark and the friction. Therefore, the brushless electric motor 10 is used because the life is short and the dust is blown.

The electric motor 10 is connected to a power supply unit and includes a stator 11 having a first magnet 11a, that is, an electromagnet, and a cylindrical shape, such that the stator 11 can be housed therein. The case 13 is mounted.

In this case, the rotary shaft 17 connected to the lower plate 13b of the case projects upward through the stator 11 and the upper plate 13b of the case. The propeller 1 is coupled to the upper end of the rotary shaft 17, The propeller 1 is fixed to the upper plate 13b of the case by the screw 15.

 At this time, a bolt hole is formed to correspond to the upper plate 13b and the bracket 11 of the case. When the bolt is fastened to the bolt hole, the case 13 and the propeller 1 are integrally joined.

Since the permanent magnet corresponding to the first magnet 11a of the stator 11, that is, the second magnet 13a is provided on the inner peripheral surface of the case 13, the case 13 functions as a rotor, ) Itself rotates.

Further, in the case of the electric motor 10 for an aircraft, since the case 13 itself rotates, it has a high torque characteristic. Moreover, the large propeller 1 can be directly rotated without a reduction gear and an accessory such as a speed reducer is not required The electric motor 10 can be made lightweight.

However, in the case of the electric motor 10, much heat is generated because the case 13 itself rotates. In this case, if the speed of the aircraft is high, the electric motor 10 is cooled by the flow of air, It is necessary to cool the electric motor 10 because the electric motor 10 is overheated because there is almost no air flow.

In this case, a plurality of cooling holes 13c are formed in the upper plate 13b or the lower plate 13b of the case 13 or both of them to perform the cooling function of the electric motor.

Therefore, when the electric motor 10 is driven, the air flows into the cooling holes 13c of the case 13 through the air flow caused by the rotation of the propeller 1, thereby cooling the electric motor 10.

In this case, it is preferable that the cooling holes 13c are formed on both the upper plate 13b and the lower plate 13b of the case so that the air introduced through the cooling holes 13c can be smoothly discharged after cooling.

For this, the cooling holes 13c may be formed on the side surface of the case, as well as the upper and lower plates of the case.

However, since the cooling hole 13c is always kept open, when the electric motor 10 is driven and the case 13 rotates at a constant speed, rain, moisture and other foreign substances are generated by the rotational force of the case 13 Foreign matter such as rainwater, moisture, dust or the like may be introduced through the cooling hole 13c of the case 13 when the airplane is stopped and the electric motor 10 is not driven.

Such foreign matter, such as rainwater, moisture, or dust, may act as a cause of an electric short or a fire due to a short circuit.

In order to solve this problem, conventionally, measures such as covering the electric motor 10 with a tarpaulin such as vinyl have been taken. However, such a measure is temporary and cumbersome, and thus can not solve a fundamental problem.

In order to fundamentally solve the above-described problem, the present invention intends to introduce the opening / closing control means 20 capable of opening and closing the cooling hole 13c of the case 13, Will be described in detail.

As shown in FIGS. 2 to 4, the opening / closing control means 20 according to the present invention includes:

An elastic member 21 mounted on the upper plate 13b of the case 13 and disposed between the cooling holes 13c and an elastic member 21 supported by the elastic member 21 to open and close the cooling hole 13c, And a throttle plate 23 for adjusting the amount of opening of the throttle valve 13c.

The elastic member 21 of the opening and closing control means 20 according to the present invention is preferably constituted by a torsion spring and the rotation of the elastic member 21, A fixing protrusion 25 serving as a stopper is formed by supporting one end of the elastic member 21. [

In addition, the other end of the elastic member 21 supports the throttle plate 23 in contact with one side surface of the throttle plate 23.

The control plate 23 of the opening and closing control means 20 is hinged to the upper plate 13b of the case so that one end thereof is disposed around the rotation center of the case 13 so that when the electric motor 10 is not driven, The cooling hole 13c of the case 13 is closed by the elastic member 21. [

Therefore, the cooling holes 13c of the case 13 are closed by the throttle plate 23 when the electric motor 10 is not driven, so that even if the electric motor 10 is placed outdoors, foreign matter such as rainwater, moisture, It is not allowed to enter the inside thereof.

Conversely, when the electric motor 10 is driven, if the case 13 is rotated in the counterclockwise direction as shown in FIG. 3 (b), the centrifugal force acts in the clockwise direction on the throttle plate 23 of the opening / closing control means 20 .

In this case, since the centrifugal force acting on the throttle plate 23 varies depending on the rotational speed of the case 13, the throttle plate 23 compresses the elastic member 21 by the centrifugal force so that the cooling holes 13c of the cooling hole 13c are opened completely or only a part of the cooling hole 13c is opened to adjust the opening amount of the cooling hole 13c.

4 shows the vector of the force acting on the throttle plate 23 in accordance with the rotation of the case 13 when the electric motor 10 is driven.

4, 'O' is the rotation center of the electric motor 10, '' is the rotation center of the throttle plate 23, and 'is the center of gravity of the throttle plate 23.

together

Figure pat00001
Is the centrifugal force at the motor rotation center (O) acting on the center of gravity (G) of the throttle plate (23)
Figure pat00002
Is a rotational force component at the rotation center O 'of the throttle plate 23. [

Therefore, when the electric motor 10 is driven, the case 13 rotates. When the throttle plate 23 rotates in the direction opposite to the rotating direction of the case 13 to open the cooling hole 13c, 13c, air is introduced from the propeller 1, and the electric motor 10 is cooled.

When the electric motor 10 is driven as described above, the throttle plate 23 compresses the elastic member 21 to open the cooling hole 13c. However, when the electric motor 10 is stopped, Since the centrifugal force does not act, the compressed elastic member 21 is restored and the throttle plate 23 is rotated in the opposite direction to close the cooling hole 13c.

The control plate 23 of the opening and closing control means 20 according to the present invention is provided with a hinge shaft 27 for hinging the inner end portion and the upper plate 13b, And serves as a rotation center.

In this case, it is preferable that the hinge shaft 27 can be disposed around the rotation center of the electric motor 10 so that the centrifugal force acting on the throttle plate 23 can smoothly act.

Also, the shape of the throttle plate 23 is formed in an outer shape so as to increase in area as it goes outward as a whole, so that the center of gravity G of the throttle plate 23 can be formed on the outer side of the throttle plate 23 desirable.

This allows the magnitude of the centrifugal force acting on the throttle plate 23 to increase, thereby facilitating the operation of the throttle plate 23.

The throttle plate 23 of the opening and closing means can be rotated by the hinge shaft 27. In this case, when the throttle plate 23 closes the cooling hole 13c, the throttle plate 23 can rotate without being fixed.

In order to prevent this, the rotation preventing portion 23a is formed in the adjusting plate 23, and the rotation preventing portion 23a is provided at the end of the adjacent adjusting plate 23 in the state where the cooling hole 13c of the adjusting plate 23 is closed The rotation preventing portion 23a of the adjusting plate 23 adjacent to the inner end of the adjusting plate 23 hinged to the upper plate 13b of the case abuts against the rotation of the adjusting plate 23, .

It is preferable that the rotation preventing portion 23a is formed in a curved shape depressed inwardly because the movement of the throttle plate 23 is due to rotation. Therefore, when the throttle plate 23 is rotated, So that the inner end portion is naturally accommodated in the rotation preventing portion 23a and can be discharged.

While the present invention has been described with reference to specific embodiments thereof, it will be understood by those skilled in the art that various changes and modifications may be made by those skilled in the art without departing from the spirit and scope of the present invention as defined by the appended claims. And such variations and modifications are to be construed as being included within the scope of the present invention.

1: Propeller
10: Electric motor
11: stator 11a: first magnet
13: Case 13a: Second magnet
13b: upper plate (lower plate) 13c: cooling hole
15: Bracket 17:
20: opening / closing control means
21: elastic member 23: throttle plate
23a: Anti-rotation part 25: Fixing projection
27: Hinge shaft

Claims (7)

A stator 11 having a first magnet 11a and connected to a power supply unit,
A second magnet 13a disposed on the outer side of the stator 11 and connected to the propeller 1 and corresponding to the first magnet 11a of the stator and a case 13 having a cooling hole 13c formed therein An electric motor (10) comprising; And
Closing means 20 mounted on the case 13 of the electric motor to open and close the cooling hole 13c;
And a power transmission device for an aircraft having a moisture penetration prevention function and an overheat prevention function.
A stator 11 having a first magnet 11a and connected to a power supply unit,
A second magnet 13a disposed on the outer side of the stator 11 and connected to the propeller 1 and corresponding to the first magnet 11a of the stator and a case 13 having a cooling hole 13c formed therein An electric motor (10) comprising; And
Closing means 20 mounted on the case 13 of the electric motor for adjusting the amount of opening of the cooling hole 13c in accordance with the rotational speed of the case 13;
And a power transmission device for an aircraft having a moisture penetration prevention function and an overheat prevention function.
The apparatus according to claim 1 or 2, wherein the opening / closing control means (20)
A throttle plate 23 hinged to the case 13 to open and close the cooling hole 13c,
And an elastic member (21) mounted on the case (13) and supporting the throttle plate (23).
The method of claim 3,
Wherein the rotation center of the throttle plate (23) of the opening / closing control means (20) is disposed around the rotation center of the case (13).
The method of claim 3,
Wherein the regulating plate (23) of the opening and closing regulating means (20) is formed in the shape of an external light (external) shape.
The method of claim 3,
Wherein the control plate 23 further includes a rotation preventing portion 23a contacting an end of the adjacent control plate 23 to prevent rotation of the control plate 23 when the cooling hole 13c is closed. Power transmission system for aircraft with penetration prevention and overheat prevention function.
The method according to claim 6,
Wherein the rotation preventing portion (23a) of the throttle plate (23) is formed in a curved shape which is recessed inward.
KR1020160010383A 2016-01-28 2016-01-28 Power transmission apparatus for aircraft KR101796564B1 (en)

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KR101796564B1 KR101796564B1 (en) 2017-11-10

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Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022225324A1 (en) 2021-04-23 2022-10-27 주식회사 아모텍 Rotor, and propeller driving device and aircraft using same
KR20220146066A (en) 2021-04-23 2022-11-01 주식회사 아모텍 Apparatus for Driving Propeller and Vehicle Using the Same
KR20220146067A (en) 2021-04-23 2022-11-01 주식회사 아모텍 Rotor Assembly and Apparatus for Driving Propeller Using the Same
KR20220146888A (en) 2021-04-26 2022-11-02 주식회사 아모텍 Apparatus for Driving Propeller and Vehicle Using the Same
WO2022231211A1 (en) 2021-04-26 2022-11-03 주식회사 아모텍 Stator, and propeller driving apparatus and aircraft using same
KR20220148360A (en) 2021-04-28 2022-11-07 주식회사 아모텍 Stator and BLDC Motor for Propeller Driving Apparatus Using the Same
WO2023018053A1 (en) 2021-08-09 2023-02-16 주식회사 아모텍 Stator having bus bar structure, propeller driving motor using same, and method for manufacturing stator

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JP2006075321A (en) 2004-09-09 2006-03-23 Namiki Precision Jewel Co Ltd Spinner unit for electric radio control model plane
JP2012196114A (en) * 2011-03-14 2012-10-11 Ogawa Seiki Kk Motor cooling mechanism

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2022225324A1 (en) 2021-04-23 2022-10-27 주식회사 아모텍 Rotor, and propeller driving device and aircraft using same
KR20220146066A (en) 2021-04-23 2022-11-01 주식회사 아모텍 Apparatus for Driving Propeller and Vehicle Using the Same
KR20220146067A (en) 2021-04-23 2022-11-01 주식회사 아모텍 Rotor Assembly and Apparatus for Driving Propeller Using the Same
KR20220146888A (en) 2021-04-26 2022-11-02 주식회사 아모텍 Apparatus for Driving Propeller and Vehicle Using the Same
WO2022231211A1 (en) 2021-04-26 2022-11-03 주식회사 아모텍 Stator, and propeller driving apparatus and aircraft using same
KR20220148360A (en) 2021-04-28 2022-11-07 주식회사 아모텍 Stator and BLDC Motor for Propeller Driving Apparatus Using the Same
WO2023018053A1 (en) 2021-08-09 2023-02-16 주식회사 아모텍 Stator having bus bar structure, propeller driving motor using same, and method for manufacturing stator
KR20230023836A (en) 2021-08-09 2023-02-20 주식회사 아모텍 Stator Having Busbar Structure, Motor for Driving Propeller Using the Same and Method for Manufacturing the Stator

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