CN112357096A - Electromagnetic positive and negative propeller power device of electric fixed wing aircraft - Google Patents
Electromagnetic positive and negative propeller power device of electric fixed wing aircraft Download PDFInfo
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- CN112357096A CN112357096A CN202011327622.7A CN202011327622A CN112357096A CN 112357096 A CN112357096 A CN 112357096A CN 202011327622 A CN202011327622 A CN 202011327622A CN 112357096 A CN112357096 A CN 112357096A
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- 230000002457 bidirectional effect Effects 0.000 claims abstract description 22
- 238000006243 chemical reaction Methods 0.000 claims abstract description 5
- 230000005611 electricity Effects 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 3
- 238000010586 diagram Methods 0.000 description 4
- 239000000446 fuel Substances 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000010687 lubricating oil Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
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- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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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
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/40—Arrangements for mounting power plants in aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The invention discloses an electromagnetic forward and reverse propeller power device of an electric fixed wing aircraft, which comprises an electromagnetic forward and reverse propeller structure and a forward and reverse propeller control circuit, wherein the electromagnetic forward and reverse propeller structure comprises a variable pitch rod, a torque conversion mechanism, a hollow shaft brushless motor, a bidirectional self-holding electromagnet, a motor mounting seat and a bidirectional self-holding electromagnet mounting seat; by adopting the structure, the reverse thrust deceleration, ground backing and emergent stop takeoff of the electric fixed-wing aircraft can be realized under the condition that the electric fixed-wing aircraft comprises the electric unmanned aerial vehicle, and the electric motor of the electric aircraft and the electric aviation model aircraft are not changed. The device is convenient to maintain and replace parts, low in cost, compact in structure, small in size, light in weight, high in reliability, simple to operate, remarkable in function, novel and practical.
Description
Technical Field
The invention relates to the field of electric fixed-wing airplanes, in particular to an electromagnetic positive and negative propeller power device of an electric fixed-wing airplane.
Background
Along with popularization and development of new energy aircrafts such as electric aircrafts and the like and wide application of the electric unmanned aircrafts in the military science and technology field, the world has higher and higher requirements on functionality of electric fixed-wing aircrafts, a propeller pitch changing mode of a traditional fuel aircraft is no longer suitable for a purely electric driven aircraft, the propeller pitch changing mode of the traditional fuel aircraft is driven by hydraulic oil or lubricating oil, and the electric fixed-wing aircraft has the characteristics of large volume and whole weight and is not suitable for the purely electric driven aircraft.
In order to solve the problems, a pure electric drive electromagnetic positive and negative paddle power device is produced.
Disclosure of Invention
The invention aims to solve the technical problem of the reverse-propeller deceleration of a pure electric fixed-wing aircraft
In order to solve the technical problems, the technical scheme provided by the invention is as follows: an electromagnetic forward and reverse propeller power device of an electric fixed wing aircraft comprises an electromagnetic forward and reverse propeller structure and a forward and reverse propeller control circuit, wherein the electromagnetic forward and reverse propeller structure comprises a variable pitch rod, a torque conversion mechanism, a hollow shaft brushless motor, a bidirectional self-holding electromagnet, a motor mounting seat and a bidirectional self-holding electromagnet mounting seat;
positive and negative oar control circuit electric connection is on the electro-magnet, positive and negative oar control circuit includes electronic governor, power, receiver, electronic switch and delay relay, electronic switch includes first electronic switch and second electronic switch, delay relay includes first delay relay, second delay relay and third delay relay, the one end and the electricity of receiver are transferred electric connection, the other end and the electronic switch electric connection of receiver, second electronic switch respectively with first delay relay, second delay relay and third delay relay electric connection, first electronic switch, second electronic switch control corresponding contact through first delay relay, second delay relay and third delay relay, realize moving fixed wing aircraft electromagnetism positive and negative oar process.
Furthermore, one end of the bidirectional self-holding electromagnet is fixed on the variable pitch rod through a coupler.
Further, the one end of connecting double-end screw is connected with the motor mount pad, the other end electromagnet mount pad of connecting double-end screw is connected.
Further, the receiver is used for receiving the signal and transmitting the signal to the first electronic switch and the second electronic switch simultaneously.
Furthermore, the first electronic switch and the second electronic switch respectively control the positive and negative propellers to control whether the main circuit, the first delay relay, the second delay relay and the third delay relay are powered on or not.
Compared with the prior art, the invention has the advantages that: by adopting the structure, the reverse thrust deceleration, ground backing and emergent stop takeoff of the electric fixed-wing aircraft can be realized under the condition that the electric fixed-wing aircraft comprises the electric unmanned aerial vehicle, and the electric motor of the electric aircraft and the electric aviation model aircraft are not changed. The device has the advantages of mutual independence of the mechanical structure and the electrical control, convenience in maintenance and replacement, low cost, compact structure, small size, light weight, high reliability, simplicity in operation, remarkable function, novelty and practicability. Meanwhile, the device meets various requirements of forward and reverse propellers of the propeller of the future electric aircraft, and has wide application prospect.
Drawings
FIG. 1 is a schematic structural diagram of an electromagnetic forward and reverse propeller power device of an electric fixed wing aircraft according to the present invention;
FIG. 2 is a schematic diagram of an electromagnetic positive and negative paddle power plant;
FIG. 3 is a schematic diagram of a first electronic switch and a main control circuit of forward and reverse propellers;
fig. 4 is a schematic diagram of the control of the second electronic switch and the contacts of the time delay relay.
As shown in the figure: 1. the device comprises a variable pitch rod, 2, a variable pitch mechanism, 3, a hollow shaft brushless motor, 4, a motor mounting seat, 5, an electromagnet mounting seat, 6, a coupler, 7, a connecting double-head screw rod and 8, and a bidirectional self-holding electromagnet.
Wherein 1#, 2#, 3# are respectively the first, second and third.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
The present invention will be described in detail with reference to the accompanying drawings.
The invention provides an electromagnetic forward and reverse propeller power device of an electric fixed wing aircraft, which comprises an electromagnetic forward and reverse propeller structure and a forward and reverse propeller control circuit, wherein the electromagnetic forward and reverse propeller structure comprises a variable pitch rod 1, a torque converter 2, a hollow shaft brushless motor 3, a bidirectional self-holding electromagnet 8, a motor mounting seat 4 and a bidirectional self-holding electromagnet mounting seat 5, a coupler 6 is arranged between the variable pitch rod 1 and the bidirectional self-holding electromagnet 8, a connecting double-head screw 7 is arranged between the electromagnet mounting seat 5 and the motor mounting seat 4, the torque converter 2, the hollow shaft motor 3 and the bidirectional self-holding electromagnet 8 are coaxially arranged, and the torque converter 2 is arranged at the front end of a main shaft;
positive and negative oar control circuit electric connection is on the electro-magnet, positive and negative oar control circuit includes electronic governor, power, receiver, electronic switch and delay relay, electronic switch includes first electronic switch and second electronic switch, delay relay includes first delay relay, second delay relay and third delay relay, the one end and the electricity of receiver are transferred electric connection, the other end and the electronic switch electric connection of receiver, electronic switch respectively with first delay relay, second delay relay and third delay relay electric connection, first electronic switch, second electronic switch control corresponding contact through first delay relay, second delay relay and third delay relay, realize moving fixed wing aircraft electromagnetism positive and negative oar process.
One end of the bidirectional self-holding electromagnet 8 is fixed on the variable-pitch rod 1 through a coupler 6. The one end of connecting double-end screw 7 is connected with motor mount pad 4, the other end electro-magnet mount pad 4 of connecting double-end screw 7 is connected. The receiver is used for receiving signals and transmitting the signals to the first electronic switch and the second electronic switch simultaneously. The first electronic switch and the second electronic switch respectively control the positive and negative propellers to control whether the main circuit, the first delay relay, the second delay relay and the third delay relay are powered.
The specific embodiment of the invention is as follows: the device adopts the bidirectional self-holding electromagnet as a power source of the forward propeller and the reverse propeller, the bidirectional self-holding electromagnet is electrified with positive electricity, the bidirectional self-holding electromagnet 8 generates repulsive force, the variable pitch rod 1 is pushed forward, and the variable pitch rod 1 drives the variable pitch mechanism 2 to enable the propeller blade to be in a reverse propeller state, so that reverse propeller is realized. When the model airplane needs to be decelerated by reverse propeller or is backed on the ground, a fan switches on a five-channel switch, a reverse propeller signal is received by the model airplane receiver, the receiver simultaneously sends the signal to the first electronic switch and the second electronic switch, the two electronic switches work cooperatively to respectively control the main circuit of the electrical control of the forward propeller and the reverse propeller and 3 time delay relays to enable the electromagnet to be positively charged, the positive electricity of the bidirectional self-holding electromagnet 8 is enabled to generate repulsive force, the variable pitch rod is pushed forward, and the variable pitch rod drives the variable pitch mechanism to enable the blades to be in a reverse propeller state, so that the functions of reverse propeller reverse propulsion deceleration and backing are realized. On the contrary, when the reverse propeller or the forward propeller needs to be stopped, the aeromodelling fan closes the electric gates of the five channels, a signal for stopping the reverse propeller is received by the receiver, the receiver sends the signal to the two electronic switches, the two electronic switches respectively control the main circuit for electrically controlling the forward propeller and the reverse propeller and 3 time delay relays to supply negative electricity to the electromagnet, the bidirectional self-holding electromagnet 8 generates attraction force, the variable-pitch rod is pulled backwards, and the variable-pitch rod drives the variable-pitch mechanism 2 to enable the paddle to be in the forward propeller state, and positive pulling force is generated again. The principle of reverse propeller is explained by taking the variable-pitch rod to push out the reverse propeller as an example, the two poles of the power supply of the bidirectional self-holding electromagnet 8 are reversely connected, the state of the forward propeller of the electromagnet is changed at the same time, namely the push-out state is the state of the forward propeller, then the reverse propeller switch is switched on, and the variable-pitch rod is sucked back to be in the reverse propeller state
The principle of the invention adopting the time delay relay to control the contact is as follows: the contacts comprise a contact 1, a contact 2, a contact 3, a contact 4 and a contact 5, the contact 1, the contact 2 and the contact 5 are normally open contacts, the contact 3 and the contact 4 are normally closed contacts, and the contact 1 and the contact 3 are controlled by the first time delay relay to be opened and closed by the second electronic switch no-com; the contact 2 and the contact 4 are controlled by a second time delay relay to be opened and closed by a second electronic switch no-com; the contact 5 is controlled by the third delay relay to be opened or closed by the second electronic switch com-nc.
The present invention and its embodiments have been described above, and the description is not intended to be limiting, and the drawings are only one embodiment of the present invention, and the actual structure is not limited thereto. In summary, those skilled in the art should appreciate that they can readily use the disclosed conception and specific embodiments as a basis for designing or modifying other structures for carrying out the same purposes of the present invention without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (5)
1. The utility model provides an electronic fixed wing aircraft electromagnetism positive and negative oar power device which characterized in that: the electromagnetic forward and reverse propeller control device comprises an electromagnetic forward and reverse propeller structure and a forward and reverse propeller control circuit, wherein the electromagnetic forward and reverse propeller structure comprises a variable pitch rod (1), a torque conversion mechanism (2), a hollow shaft brushless motor (3), a bidirectional self-holding electromagnet (8), a motor mounting seat (4) and a bidirectional self-holding electromagnet mounting seat (5), a coupler (6) is arranged between the variable pitch rod (1) and the bidirectional self-holding electromagnet (8), a connecting double-end screw (7) is arranged between the electromagnet mounting seat (5) and the motor mounting seat (4), the torque conversion mechanism (2), the hollow shaft brushless motor (3) and the bidirectional self-holding electromagnet (8) are coaxially arranged, and the torque conversion mechanism (2) is arranged at the front end of a main shaft;
positive and negative oar control circuit electric connection is on the electro-magnet, positive and negative oar control circuit includes electronic governor, power, receiver, electronic switch and delay relay, electronic switch includes first electronic switch and second electronic switch, delay relay includes first delay relay, second delay relay and third delay relay, the one end and the electricity of receiver are transferred electric connection, the other end and the electronic switch electric connection of receiver, electronic switch respectively with first delay relay, second delay relay and third delay relay electric connection, first electronic switch, second electronic switch control corresponding contact through first delay relay, second delay relay and third delay relay, realize moving fixed wing aircraft electromagnetism positive and negative oar process.
2. The power device of the electric fixed wing aircraft with the electromagnetic positive and negative propellers of claim 1, characterized in that: one end of the bidirectional self-holding electromagnet (8) is fixed on the variable-pitch rod (1) through a coupler (6).
3. The power device of the electric fixed wing aircraft with the electromagnetic positive and negative propellers of claim 1, characterized in that: the motor is characterized in that one end of the connecting double-end screw (7) is connected with the motor mounting seat (4), and the other end of the connecting double-end screw (7) is connected with the electromagnet mounting seat (4).
4. The power device of the electric fixed wing aircraft with the electromagnetic positive and negative propellers of claim 1, characterized in that: the receiver is used for receiving signals and transmitting the signals to the first electronic switch and the second electronic switch simultaneously.
5. The power device of the electric fixed wing aircraft with the electromagnetic positive and negative propellers of claim 1, characterized in that: the first electronic switch and the second electronic switch respectively control the positive and negative propellers to control whether the main circuit, the first delay relay, the second delay relay and the third delay relay are powered.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011327622.7A CN112357096A (en) | 2020-11-24 | 2020-11-24 | Electromagnetic positive and negative propeller power device of electric fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011327622.7A CN112357096A (en) | 2020-11-24 | 2020-11-24 | Electromagnetic positive and negative propeller power device of electric fixed wing aircraft |
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| Publication Number | Publication Date |
|---|---|
| CN112357096A true CN112357096A (en) | 2021-02-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011327622.7A Pending CN112357096A (en) | 2020-11-24 | 2020-11-24 | Electromagnetic positive and negative propeller power device of electric fixed wing aircraft |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB577870A (en) * | 1943-03-11 | 1946-06-04 | Herbert Newport | Improvements in and relating to variable-pitch propellers |
| CN101026052A (en) * | 2006-02-20 | 2007-08-29 | 林贵生 | Permanent-magnetic self-retaining relay |
| CN103996486A (en) * | 2014-06-18 | 2014-08-20 | 重庆华渝电气集团有限公司 | Inner armature type high precision positioning electromagnet |
| CN104494810A (en) * | 2014-12-14 | 2015-04-08 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotating type propeller pitch-varying device |
| CN208996866U (en) * | 2018-08-02 | 2019-06-18 | 固安华电天仁控制设备有限公司 | A kind of pitch control device of power generation with marine energy unit |
| CN215399352U (en) * | 2020-11-24 | 2022-01-04 | 黄威 | Electromagnetic positive and negative propeller power device of electric fixed wing aircraft |
-
2020
- 2020-11-24 CN CN202011327622.7A patent/CN112357096A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB577870A (en) * | 1943-03-11 | 1946-06-04 | Herbert Newport | Improvements in and relating to variable-pitch propellers |
| CN101026052A (en) * | 2006-02-20 | 2007-08-29 | 林贵生 | Permanent-magnetic self-retaining relay |
| CN103996486A (en) * | 2014-06-18 | 2014-08-20 | 重庆华渝电气集团有限公司 | Inner armature type high precision positioning electromagnet |
| CN104494810A (en) * | 2014-12-14 | 2015-04-08 | 惠阳航空螺旋桨有限责任公司 | Coaxial contra-rotating type propeller pitch-varying device |
| CN208996866U (en) * | 2018-08-02 | 2019-06-18 | 固安华电天仁控制设备有限公司 | A kind of pitch control device of power generation with marine energy unit |
| CN215399352U (en) * | 2020-11-24 | 2022-01-04 | 黄威 | Electromagnetic positive and negative propeller power device of electric fixed wing aircraft |
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