CN112572785A - High-efficiency front edge distributed propeller aircraft power layout - Google Patents
High-efficiency front edge distributed propeller aircraft power layout Download PDFInfo
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- CN112572785A CN112572785A CN202011425347.2A CN202011425347A CN112572785A CN 112572785 A CN112572785 A CN 112572785A CN 202011425347 A CN202011425347 A CN 202011425347A CN 112572785 A CN112572785 A CN 112572785A
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- electric
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- leading edge
- propeller
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/02—Tailplanes
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
- B64C5/06—Fins
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- Other Liquid Machine Or Engine Such As Wave Power Use (AREA)
Abstract
The invention discloses a power layout of a high-efficiency leading edge distributed propeller aircraft, and particularly relates to the technical field of aircrafts. The utility model provides a high-efficient leading edge distributed propeller aircraft power overall arrangement, is including distributing a plurality of electric screw on the fixed wing of aircraft both sides, and is a plurality of the electric screw symmetry sets up in fixed wing the place ahead, every all be equipped with the nacelle of being connected with the fixed wing on the electric screw, the electric screw of the wing tip department of fixed wing is located fixed wing leading edge point dead ahead, all the other the screw center all is located fixed wing leading edge point top. The technical scheme of the invention solves the problem that all the distributed propellers of the existing aircraft are distributed right in front of the front edge point of the wing to influence the aerodynamic performance of the aircraft, and can be used for designing the aircraft.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a power layout of a high-efficiency front edge distributed propeller aircraft.
Background
At present, the application of distributed propulsion and electric propulsion technology in the aviation field is more and more extensive, the pure electric or oil-electric hybrid distributed propeller propulsion technology applied to small and medium-sized airplanes has become a new focus of aviation research, and the fundamental reason is that the distributed propulsion electric propeller has the advantages of high low-speed propulsion efficiency, capability of fully utilizing slipstream to increase lift, greatly improved aerodynamic performance of an aircraft, capability of meeting the flight requirements of short take-off and landing and long voyage, and good economical efficiency.
The aircraft using the distributed electric propellers as power, the slipstream generated by the propellers during operation thoroughly changes the flow field properties around the wings, the interference effect between the slipstream of the propellers and the pneumatic components such as the wings is very obvious, the difference of the aerodynamic characteristics of the aircraft is quite different from the surrounding flow of the wings without the slipstream. In the traditional propeller aircraft design, as the influence range of propeller slipstream on the wing flow field is limited, the influence of the power installation position on the aerodynamic characteristics of the aircraft is rarely considered, which has great defects on the power layout design of the distributed propeller aircraft. The research of the prior document on the distributed propellers focuses on the influence of slipstream on the aerodynamic performance of the wing or other parts, all the propellers are usually arranged right in front of the front edge point of the wing, and the research on the aspect of optimizing and designing the power layout of the distributed propellers is very little.
Disclosure of Invention
The invention aims to provide a power layout of a high-efficiency front edge distributed propeller aircraft, and solves the problem that all distributed propellers of the existing aircraft are distributed right in front of a wing front edge point to influence the aerodynamic performance of the aircraft.
In order to achieve the purpose, the technical scheme of the invention is as follows: the utility model provides a high-efficient leading edge distributed propeller aircraft power overall arrangement, is including distributing a plurality of electric screw on the fixed wing of aircraft both sides, and is a plurality of the electric screw symmetry sets up in fixed wing the place ahead, every all be equipped with the nacelle of being connected with the fixed wing on the electric screw, the electric screw of the wing tip department of fixed wing is located fixed wing leading edge point dead ahead, all the other the screw center all is located fixed wing leading edge point top.
The principle and the effect of the technical scheme are as follows: the center of the electric propeller at the wing tip in the power layout is positioned right in front of the front edge point of the wing, so that the rotation effect of the electric propeller, which causes slipstream, can inhibit the vortex of the wing tip, and the lift force of the fixed wing is improved.
Further, the center of the rest of the electric propellers is at a distance of 70% of the radius of the electric propellers from the electric propellers at the tips of the upper wings of the fixed wings.
Through the arrangement, the slipstream acceleration effect of the electric propeller can be fully utilized, and the slipstream effect of the electric propeller is better utilized to improve the lift force of the aircraft, so that the load capacity of the aircraft is improved, the take-off and landing distance is shortened, and the stall is delayed.
Further, every electric screw all is connected with the motor and is transferred with the electricity.
Through the arrangement, the independent motor and the electric controller are adopted for driving control, the power of the aircraft can be subjected to vector adjustment in the flight process, the slip flow effect improves the steering effect of the ailerons and the empennage, and the pitching, rolling and yawing control of the aircraft can be efficiently realized.
Compared with the prior art, the beneficial effect of this scheme:
1. according to the power layout of the leading edge distributed propeller, the center of the electric propeller at the wing tip is positioned right in front of the front edge point at the outermost side of the wingspan, so that the vortex of the wing tip can be inhibited, and the lift force of the wing can be improved;
2. according to the power layout of the leading edge distributed propeller, the center of the electric propeller positioned on the inner side of the wing tip is positioned in front of and above the leading edge point of the wing, and the normal distance between the electric propeller and the leading edge point is 70% of the radius of the propeller, so that the lift force of an aircraft can be improved by fully utilizing the slipstream effect of the propeller, the load capacity of the aircraft can be improved, the take-off and landing distance can be shortened, and the stall can be;
3. the front edge distributed propeller power layout improves the rudder effect of the ailerons and the empennage, and is beneficial to improving the control efficiency of pitching, rolling and yawing of the aircraft.
Drawings
FIG. 1 is a schematic structural view of a power layout of a high efficiency leading edge distributed propeller aircraft of the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the aircraft comprises an aircraft body 1, a fixed wing 2, an electric propeller 3, a nacelle 4, ailerons 5, a flap 6, a horizontal tail 7 and a vertical tail 8.
Examples
As shown in figure 1: the utility model provides a high-efficient leading edge distributed propeller aircraft power layout, including aircraft body 1 and the fixed wing 2 of setting in aircraft body 1 both sides, a plurality of electric screw propeller 3 on the fixed wing 2 of aircraft body 1 left and right sides, it has six electric screw propeller 3 to adopt every fixed wing 2 equidistance distribution on the aircraft in this embodiment, six electric screw propeller 3 symmetries set up the place ahead of controlling two fixed wings 2, all be equipped with the nacelle 4 of being connected with fixed wing 2 on every electric screw propeller 3, the electric screw propeller 3 of two fixed wings 2 top wing tip departments is located fixed wing 2 front edge point dead ahead about, wherein the electric screw propeller 3 of wing tip department is the electric screw propeller 3 in every fixed wing 2 outside on aircraft body 1 promptly, all the other screw centers all are located fixed wing 2 front edge point top, and the normal direction distance of the electric screw propeller 3 of every electric screw propeller 3 of electric screw propeller 3's center and the wing department on the fixed wing 2 top wing is 70 of electric Percent; the acceleration effect of the slipstream of the electric propeller 3 can be fully utilized, and the slipstream effect of the electric propeller 3 is better utilized to improve the lift force of the aircraft, thereby improving the load capacity of the aircraft, shortening the take-off and landing distance and delaying stall. Each electric propeller 3 is electrically connected with a motor and an electric speed regulator. The aircraft body 1 is also rotatably connected with an aileron 5 and a flap 6 which are positioned behind each fixed wing 2, and a horizontal tail 7 and a vertical tail 8 which are rotatably connected with the tail part of the aircraft body 1.
The working process of the scheme is as follows: when the aircraft flies, the electric propeller 3 of the electric propeller 3 at the left wing tip is turned on and rotated counterclockwise, and the electric propeller 3 of the electric propeller 3 at the right wing tip is turned on and rotated clockwise, and this method can suppress the wing tip vortex, so that the lift force of the fixed wing 2 is increased. After the electric propeller 3 between the two wing tips is opened, the air flow speed on the surface of the aileron 55 can be improved by the slipstream of the electric propeller 3, so that the rudder effect of the aileron 5 is improved, and the rolling control efficiency of the aircraft is improved; the air flow speed on the surface of the horizontal tail 78 can be improved by the slip flow of the electric propeller 3, the steering effect of the horizontal tail 7 is improved, and the pitching control efficiency of the aircraft is improved; meanwhile, the air speed on the surface of the vertical fin 89 can be increased by the aid of the sliding flow of the electric propeller, the steering effect of the vertical fin 8 is improved, and accordingly yaw control efficiency of the aircraft is improved.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (3)
1. A high-efficient leading edge distributed screw propeller aircraft power overall arrangement which characterized in that: including distributing a plurality of electric screw on the fixed wing of aircraft both sides, it is a plurality of the electric screw symmetry sets up in fixed wing the place ahead, every all be equipped with the nacelle of being connected with the fixed wing on the electric screw, the electric screw of the wing tip department of fixed wing is located fixed wing leading edge point dead ahead, all the other the screw center all is located fixed wing leading edge point top.
2. A high efficiency leading edge distributed propeller aircraft power layout as set forth in claim 1, wherein: the centers of the rest of the electric propellers are at a normal distance of 70% of the radius of the electric propellers at the tips of the upper wings of the fixed wings.
3. A high efficiency leading edge distributed propeller aircraft power layout as claimed in any one of claims 1 or 2, wherein: each electric propeller is electrically connected with a motor and an electric speed regulator.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011425347.2A CN112572785A (en) | 2020-12-09 | 2020-12-09 | High-efficiency front edge distributed propeller aircraft power layout |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011425347.2A CN112572785A (en) | 2020-12-09 | 2020-12-09 | High-efficiency front edge distributed propeller aircraft power layout |
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| Publication Number | Publication Date |
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| CN112572785A true CN112572785A (en) | 2021-03-30 |
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| CN202011425347.2A Pending CN112572785A (en) | 2020-12-09 | 2020-12-09 | High-efficiency front edge distributed propeller aircraft power layout |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110186679A1 (en) * | 2008-07-11 | 2011-08-04 | Daniel Reckzeh | Aircraft with at least two propeller drives arranged at a distance from one another in the span width direction of the wings |
| CN104670503A (en) * | 2013-11-28 | 2015-06-03 | 劳斯莱斯有限公司 | Aircraft |
| CN108583875A (en) * | 2018-05-21 | 2018-09-28 | 中国空气动力研究与发展中心计算空气动力研究所 | The latent empty general purpose vehicle layout of one kind |
| CN208360507U (en) * | 2018-06-22 | 2019-01-11 | 北京航空航天大学 | A kind of distributed electrical propulsion aircraft |
| CN110901890A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | High-speed rotor craft with rotor capable of being designed in classification mode |
| US20200148347A1 (en) * | 2018-05-10 | 2020-05-14 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| KR20200058204A (en) * | 2018-11-19 | 2020-05-27 | 한국항공우주연구원 | A Vertical take off and landing three surface aircraft with distributed propulsion system |
| CN211468780U (en) * | 2019-12-05 | 2020-09-11 | 中航(成都)无人机系统股份有限公司 | Short-distance take-off and landing unmanned conveyor |
-
2020
- 2020-12-09 CN CN202011425347.2A patent/CN112572785A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110186679A1 (en) * | 2008-07-11 | 2011-08-04 | Daniel Reckzeh | Aircraft with at least two propeller drives arranged at a distance from one another in the span width direction of the wings |
| CN104670503A (en) * | 2013-11-28 | 2015-06-03 | 劳斯莱斯有限公司 | Aircraft |
| US20200148347A1 (en) * | 2018-05-10 | 2020-05-14 | Joby Aero, Inc. | Electric tiltrotor aircraft |
| CN108583875A (en) * | 2018-05-21 | 2018-09-28 | 中国空气动力研究与发展中心计算空气动力研究所 | The latent empty general purpose vehicle layout of one kind |
| CN208360507U (en) * | 2018-06-22 | 2019-01-11 | 北京航空航天大学 | A kind of distributed electrical propulsion aircraft |
| KR20200058204A (en) * | 2018-11-19 | 2020-05-27 | 한국항공우주연구원 | A Vertical take off and landing three surface aircraft with distributed propulsion system |
| CN110901890A (en) * | 2019-12-04 | 2020-03-24 | 中国直升机设计研究所 | High-speed rotor craft with rotor capable of being designed in classification mode |
| CN211468780U (en) * | 2019-12-05 | 2020-09-11 | 中航(成都)无人机系统股份有限公司 | Short-distance take-off and landing unmanned conveyor |
Non-Patent Citations (1)
| Title |
|---|
| 廖忠权: "航空混合电推进系统发展研究", 《航空动力》 * |
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Application publication date: 20210330 |