CN111284714A - Commuting type electric airplane system - Google Patents
Commuting type electric airplane system Download PDFInfo
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- CN111284714A CN111284714A CN201911392493.7A CN201911392493A CN111284714A CN 111284714 A CN111284714 A CN 111284714A CN 201911392493 A CN201911392493 A CN 201911392493A CN 111284714 A CN111284714 A CN 111284714A
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- fan
- driving
- aircraft
- commuter
- motors
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- 230000003014 reinforcing effect Effects 0.000 claims description 6
- 229920000271 Kevlar® Polymers 0.000 claims description 3
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- 239000004761 kevlar Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims 1
- 229910052799 carbon Inorganic materials 0.000 claims 1
- 239000000835 fiber Substances 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
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- 239000000446 fuel Substances 0.000 description 1
- 239000011521 glass Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Images
Classifications
-
- 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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- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transmission Devices (AREA)
Abstract
The invention discloses a commuting type electric airplane system which comprises all components except a system for driving an airplane to move in a commuting type airplane and a driving system for driving the airplane to move. The commuting electric aircraft system provided by the invention is driven by the distributed motors, the redundancy of the system is increased, the safety and reliability of flight are improved, the system is green and environment-friendly, and the pollution to the atmospheric environment is reduced.
Description
Technical Field
The invention relates to the field of airplanes, in particular to a commuting electric airplane system.
Background
The current CCAR23 division of commuting class aircraft all adopts turboprop engine or turbojet to provide power, and these two types of engines are gas engine, produce heat energy through burning petrochemical fuel and promote the turbine and do work, and the turbine drives engine propeller or fan and provides the power of flight forward for the aircraft, and the tail gas that these two kinds of engines burning discharge causes the atmosphere pollution seriously, and the oil is non-renewable resources, adopts gas turbine engine to provide power and can not last for a long time.
Disclosure of Invention
The invention aims to provide a commuting electric aircraft system which can increase the system redundancy, improve the flight safety and reliability and has the green and environment-friendly performance.
The technical solution for realizing the purpose of the invention is as follows: the utility model provides a commuting class electric aircraft system, includes all parts except the system of drive aircraft motion in the commuting class aircraft, still includes the actuating system who is used for driving the aircraft motion, and this actuating system is including installing in fuselage rear portion and the axial and fuselage length direction unanimous fan to and many motors of drive fan pivoted, the thrust transmission of fan realizes driving the aircraft motion to organism structure.
Furthermore, the fan comprises a fan gear and a fan disc fixedly connected with the gear, and a plurality of blades are arranged on the fan disc; the motors drive the fan to move through a driving device, the driving device comprises a plurality of driving shafts fixedly connected with motor shafts of the motors and driving gears arranged at the tail ends of the driving shafts, and all the driving gears are meshed with the fan gears; the driving shafts correspond to the motors one by one, all the motors work synchronously, and the motors drive the driving shafts, the driving gears and the fan gears to move in sequence so as to drive the fan disc to rotate.
Furthermore, the motors are fixed through a reinforcing frame fixedly connected to the machine body.
Furthermore, the two axial sides of the fan disc are respectively clamped and fixed by a first inclined strut frame and a second inclined strut frame which are fixedly connected to the body, wherein the first inclined strut frame is connected with the spherical frame of the body, and the second inclined strut frame is connected with the reinforcing frame.
Furthermore, balls are assembled between the fan disc and the first inclined support frame and between the fan disc and the second inclined support frame.
Further, all the driving gears are distributed along the circumference and are positioned at the inner side of the fan gear.
Furthermore, all the driving gears are fixedly connected through connecting rods, and the connecting rods are respectively connected with the first inclined support frame and the second inclined support frame through longitudinal connecting rods.
Further, the fan is fixed to a nacelle cover outside the fuselage by a plurality of nacelle support ribs.
Furthermore, the nacelle comprises a double-layer paper honeycomb sandwich panel, and the panel is formed by adopting a carbon fiber composite material and a Kevlar mixed woven material.
Further, the system also comprises battery modules which are arranged on wings on two sides of the airplane and used for supplying power to the plurality of motors.
Compared with the prior art, the invention has the following remarkable advantages: 1) the environment is protected, and the pollution to the atmospheric environment is reduced; 2) and the distributed motor drive is adopted, so that the system redundancy is increased, and the safety and reliability of the flight are improved.
The present invention is described in further detail below with reference to the attached drawing figures.
Drawings
FIG. 1 is a side view of a commuter-like electric aircraft system in one embodiment.
FIG. 2 is a front view of a commuter-like electric aircraft system in one embodiment.
FIG. 3 is a top view of a commuter-like electric aircraft system in one embodiment.
Fig. 4 is a schematic block diagram of a drive system in the commuter-type electric aircraft system in one embodiment.
FIG. 5 is a detail view of the drive system assembly of the commuter electric aircraft system in one embodiment.
Fig. 6 is a schematic diagram of the thrust transfer of the drive system in the commuter electric aircraft system in one embodiment.
Fig. 7 is a schematic diagram of the reverse thrust transfer of the drive system in the commuter electric aircraft system in one embodiment.
FIG. 8 is a schematic electrical diagram of a commuter electric aircraft system according to one embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
In one embodiment, in combination with fig. 1, the invention provides a commuting electric aircraft system, which comprises all components except a system for driving the aircraft to move in the commuting aircraft, and further comprises a driving system for driving the aircraft to move, wherein the driving system comprises a fan 6 which is arranged at the rear part of a fuselage and has an axial direction consistent with the length direction of the fuselage, and a plurality of motors 7 for driving the fan 6 to rotate, and the thrust of the fan 6 is transmitted to a airframe structure to drive the aircraft to move.
Here, with reference to fig. 1 to 7, all the components of the commuter aircraft described above, except for the system for driving the aircraft in motion, include: the aircraft comprises wings 1, a T-shaped horizontal tail wing 2, a vertical tail wing 3, a nose landing gear 8, a main landing gear 9, a rudder 10, two boarding doors 11 positioned at the left side and the right side of an aircraft body 4, escape doors 12 positioned at the two wings, nine oval windows 13 at the left side and the right side of the aircraft body 4, and a driving window 14 formed by three pieces of high-strength double-layer glass at the left side and the right side of the front part of the aircraft body 4. The wing tip winglet comprises a wingtip winglet 18 arranged at the end part of the wing 1 and used for reducing the induced drag of the wing, a horizontal tail wing tip 19 arranged at the end part of the horizontal tail wing 2 and a wing body fairing 20 arranged at the joint part of the wing and the fuselage and used for reducing the induced drag of the horizontal tail wing. The aircraft wing structure further comprises an inner flap 21, an outer flap 22 and an aileron 23 which are designed on the rear edge of the wing 1, wherein three sections of leading edge slats which are designed on the leading edge of the wing are respectively a first slat 25, a second slat 26 and a third slat 27, a radome 24 which is arranged at the end part of the aircraft body 4 and an elevator 25 which is designed at the rear part of the horizontal tail wing 2; and a resistance plate 38 at the two sides of the tail of the fuselage 4, wherein the resistance plate 38 is driven by an actuating cylinder 39.
Above-mentioned commuting class electric aircraft system adopts distributed motor drive, has increased system redundancy, has improved flight fail safe nature, and green has reduced the pollution to atmospheric environment.
Further, in one embodiment, with reference to fig. 1 and 4, the fan 6 includes a fan gear 29 and a fan disc fixedly connected to the gear, the fan disc being provided with a plurality of blades; the motors 7 drive the fan 6 to move through a driving device, the driving device comprises a plurality of driving shafts 15 fixedly connected with motor shafts of the motors 7 and driving gears 16 arranged at the tail ends of the driving shafts 15, and all the driving gears 16 are meshed with fan gears 29; the driving shafts 15 correspond to the motors 7 one by one, all the motors 7 work synchronously, and the motors 7 drive the driving shafts 15, the driving gears 16 and the fan gears 29 to move in sequence, so that the fan disc is driven to rotate.
Further, in one embodiment, referring to fig. 5, the plurality of motors 7 are fixed by a reinforcing frame 31 attached to the body 4.
Further, in one embodiment, referring to fig. 5, two sides of the fan disc along the axial direction are respectively clamped and fixed by a first inclined strut frame 34 and a second inclined strut frame 32 fixedly connected to the body 4, wherein the first inclined strut frame 34 is connected to the spherical frame 35 of the body, and the second inclined strut frame 32 is connected to the reinforcing frame 31.
Further, in one embodiment, referring to fig. 4 and 5, the balls 30 are mounted between the fan disc and the first diagonal brace frame 34 and the second diagonal brace frame 32.
By adopting the scheme of the embodiment, the rotation of the fan disc can be kept smooth, and the thrust of the fan can be transmitted to the fixed frame.
Further, in one embodiment, with reference to fig. 4, all of the drive gears 16 are circumferentially distributed and located inside the fan gear 29.
As a specific example, a total of 6 drive gears 16 are included, forming a regular hexagon circumscribing the fan gear.
Further, in one embodiment, referring to fig. 4, all the driving gears 16 are connected and fixed by a connecting rod 28, and the connecting rod 28 is connected with the first inclined strut frame 34 and the second inclined strut frame 32 by a longitudinal connecting rod 37.
In summary, with reference to fig. 6, the working principle of the system of the present invention is as follows: the thrust of the fan is transmitted to the first inclined strut frame 34 and the side edge 36 of the fuselage by the ball bearings 30, then transmitted to the side edge 36 of the fuselage by the spherical frame 35 of the fuselage and longitudinally reinforced on the skin of the aircraft, and finally transmitted to the fuselage structure. Referring to fig. 7, when the aircraft is landed to provide reverse thrust to reduce the distance of the aircraft from sliding, the flaps 38 on both sides of the tail of the rear fuselage can be opened, the flaps 38 are driven by the actuating cylinders 39, and when the flaps 38 are raised, the fan jet generates a backward component force on the flaps 38 to reduce the sliding speed of the aircraft.
Further, in one embodiment, and with reference to fig. 1-5, the fan 6 is secured to the nacelle 5 external to the fuselage 4 by a plurality of nacelle support ribs 17.
As a specific example, the number of the nacelle support ribs 17 is 4, and they are symmetrically distributed on the body in the up-down and left-right directions.
Further, in one embodiment, the nacelle 5 includes a double-layered paper honeycomb sandwich panel formed by a carbon fiber composite material and a kevlar hybrid woven material.
By adopting the scheme of the embodiment, the nacelle can absorb possible fan blade breaking and flying energy while absorbing fan noise, and the rotor fragments are contained in the nacelle, so that personnel and airplane systems are prevented from being injured due to splashing.
Further, in one embodiment, in conjunction with fig. 8, the system further includes high power density battery modules 40 disposed on both wings 1 of the aircraft for powering the plurality of motors 7.
As a specific example, the battery module supplies power to the motor through a cable, as shown in fig. 8, which includes a wing side battery connection cable 41 and a motor and battery connection cable 42.
In conclusion, the commuting electric aircraft system provided by the invention adopts the distributed motor drive, increases the system redundancy, improves the safety and reliability of flight, is green and environment-friendly, and reduces the pollution to the atmospheric environment.
The technical features of the above embodiments can be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the above embodiments are not described, but should be considered as the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present application, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the concept of the present application, which falls within the scope of protection of the present application. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. The commuting type electric aircraft system comprises all components except a system for driving an aircraft to move in a commuting type aircraft, and is characterized by further comprising a driving system for driving the aircraft to move, wherein the driving system comprises a fan (6) which is installed at the rear part of the aircraft body (4) and is axially consistent with the length direction of the aircraft body (4), and a plurality of motors (7) for driving the fan (6) to rotate, and the thrust of the fan (6) is transmitted to the aircraft body structure to drive the aircraft to move.
2. The commuter-like electric aircraft system according to claim 1, wherein said fan (6) comprises a fan gear (29) and a fan disc secured to the gear, the fan disc being provided with a plurality of blades; the motors (7) drive the fan (6) to move through a driving device, the driving device comprises a plurality of driving shafts (15) fixedly connected with motor shafts of the motors (7) and driving gears (16) arranged at the tail ends of the driving shafts (15), and all the driving gears (16) are meshed with fan gears (29); the driving shafts (15) correspond to the motors (7) one by one, all the motors (7) work synchronously, and the motors (7) drive the driving shafts (15), the driving gears (16) and the fan gears (29) to move in sequence so as to drive the fan disc to rotate.
3. Commuter-type electric aircraft system according to claim 1 or 2, characterized in that the plurality of electric motors (7) are fixed by means of a reinforcing frame (31) attached to the fuselage (4).
4. The commuter electric aircraft system according to claim 3, wherein the fan tray is held on both sides in its axial direction by a first bracing frame (34) and a second bracing frame (32) respectively fastened to the fuselage (4), wherein the first bracing frame (34) is connected to the fuselage spherical frame (35) and the second bracing frame (32) is connected to the reinforcing frame (31).
5. Commuter-like electric aircraft system according to claim 4, characterized in that balls (30) are fitted between the fan disc and both the first and second diagonal bracing frames (34, 32).
6. Commuter-like electric aircraft system according to claim 5, characterized in that all the driving gears (16) are circumferentially distributed and located inside the fan gear (29).
7. The commuter electric aircraft system as claimed in claim 6, wherein all the driving gears (16) are connected and fixed by a connecting rod (28), and the connecting rod (28) is connected with the first inclined strut frame (34) and the second inclined strut frame (32) by a longitudinal connecting rod (37).
8. Commuter-like electric aircraft system according to claim 7, characterized in that the fan (6) is fixed to the nacelle (5) external to the fuselage (4) by means of a plurality of nacelle supporting ribs (17) surrounding it.
9. Commuter-like electric aircraft system according to claim 8, characterized in that the nacelle (5) comprises a double-layer paper honeycomb sandwich panel formed of carbon fibre composite material with kevlar hybrid woven material.
10. Commuter-type electric aircraft system according to claim 9, characterized in that it further comprises battery modules (40) arranged on the wings (1) of the aircraft for powering a plurality of electric motors (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911392493.7A CN111284714A (en) | 2019-12-30 | 2019-12-30 | Commuting type electric airplane system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911392493.7A CN111284714A (en) | 2019-12-30 | 2019-12-30 | Commuting type electric airplane system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111284714A true CN111284714A (en) | 2020-06-16 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911392493.7A Withdrawn CN111284714A (en) | 2019-12-30 | 2019-12-30 | Commuting type electric airplane system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111284714A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011023396A2 (en) * | 2009-08-28 | 2011-03-03 | Benjamin Parzy | Aircraft having at least two electrical propulsion groups mounted at a rear portion thereof. |
| WO2012081926A2 (en) * | 2010-12-17 | 2012-06-21 | 한국항공우주연구원 | Long-endurance airplane using wind power energy |
| US20140179535A1 (en) * | 2011-06-14 | 2014-06-26 | Eads Deutschland Gmbh | Electric drive device for an aircraft |
| WO2014178503A1 (en) * | 2013-05-03 | 2014-11-06 | 한국항공우주연구원 | Solar airplane structure and solar cell plate control method |
| CN104229144A (en) * | 2013-06-14 | 2014-12-24 | 空中客车公司 | Aircraft with electric propulsion means |
| CN107719671A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of ducted fan promotes all-electric unmanned plane |
| CN107848629A (en) * | 2015-07-22 | 2018-03-27 | 赛峰飞机发动机公司 | Include the aircraft of the propulsion assembly with fan on fuselage afterbody |
| CN109421920A (en) * | 2017-08-22 | 2019-03-05 | 通用电气公司 | Aircraft propulsion and method |
| CN211076356U (en) * | 2019-11-21 | 2020-07-24 | 中电科芜湖钻石飞机制造有限公司 | Commuting type electric airplane system |
-
2019
- 2019-12-30 CN CN201911392493.7A patent/CN111284714A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011023396A2 (en) * | 2009-08-28 | 2011-03-03 | Benjamin Parzy | Aircraft having at least two electrical propulsion groups mounted at a rear portion thereof. |
| WO2012081926A2 (en) * | 2010-12-17 | 2012-06-21 | 한국항공우주연구원 | Long-endurance airplane using wind power energy |
| US20140179535A1 (en) * | 2011-06-14 | 2014-06-26 | Eads Deutschland Gmbh | Electric drive device for an aircraft |
| WO2014178503A1 (en) * | 2013-05-03 | 2014-11-06 | 한국항공우주연구원 | Solar airplane structure and solar cell plate control method |
| CN104229144A (en) * | 2013-06-14 | 2014-12-24 | 空中客车公司 | Aircraft with electric propulsion means |
| CN107848629A (en) * | 2015-07-22 | 2018-03-27 | 赛峰飞机发动机公司 | Include the aircraft of the propulsion assembly with fan on fuselage afterbody |
| CN109421920A (en) * | 2017-08-22 | 2019-03-05 | 通用电气公司 | Aircraft propulsion and method |
| CN107719671A (en) * | 2017-10-09 | 2018-02-23 | 武汉卓尔无人机制造有限公司 | A kind of ducted fan promotes all-electric unmanned plane |
| CN211076356U (en) * | 2019-11-21 | 2020-07-24 | 中电科芜湖钻石飞机制造有限公司 | Commuting type electric airplane system |
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| PB01 | Publication | ||
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| WW01 | Invention patent application withdrawn after publication | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20200616 |