CN204750567U - High -speed fan wing aircraft - Google Patents
High -speed fan wing aircraft Download PDFInfo
- Publication number
- CN204750567U CN204750567U CN201520290227.4U CN201520290227U CN204750567U CN 204750567 U CN204750567 U CN 204750567U CN 201520290227 U CN201520290227 U CN 201520290227U CN 204750567 U CN204750567 U CN 204750567U
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- wing
- aircraft
- fan
- speed
- thruster
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- 238000009434 installation Methods 0.000 claims description 7
- 230000005540 biological transmission Effects 0.000 abstract 2
- 230000002411 adverse Effects 0.000 abstract 1
- 238000002560 therapeutic procedure Methods 0.000 abstract 1
- 238000005516 engineering process Methods 0.000 description 4
- 238000012913 prioritisation Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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Abstract
The utility model discloses a high -speed fan wing aircraft contains wing, power device, transmission and thrust device, and wherein, the wing adopts the fan wing, and power device provides power for wing and thrust device through transmission, the thrust device is used for providing the partial thrust that flies before the big speed of aircraft, make the aircraft keep at high speed condition, has overcome the fan wing in the unstable shortcoming of little speed therapeutic method to keep the adverse qi flowing downward coefficient of dynamic force. The utility model discloses simple structure, convenient to use has great practical value.
Description
Technical field
The utility model relates to vehicle technology field, particularly relates to a kind of high speed fan rotor aircraft.
Background technology
The thrust flying air resistance before existing worldwide fan rotor aircraft overcomes when front flying all comes from the component of aerodynamic force in flying speed direction of fan wing generation, because the component size of this power is limited, and along with its size of change of flying speed is not along with flying speed presents the trend that parabola increases, so cannot provide enough overcome aircraft before the air resistance that is subject to when flying.
There is the problems such as flying speed not high, flight stability bad, handling quality bad at use fan wing aerodynamic force component as when front flying thrust at existing fan rotor aircraft simultaneously.
Typical fan rotor aircraft layout is shown in US Patent No. 6,527,229B1Fig.1., US20120111994A1.
Research finds, the fan wing is within the scope of nonchannel flow operation, and lift efficiency is not high, and aerodynamic coefficient is unstable, and when large speed, aerodynamic coefficient is stablized, and is convenient to manipulation.And in the fan rotor aircraft of existing design, lower using the flying speed scope that the thrust of the fan wing self generation reaches as kinetic force, the shortcoming of the fan wing little speed pneumatic force coefficient instability can not be solved.
Utility model content
Technical problem to be solved in the utility model is for defect involved in background technology, provides a kind of high speed fan rotor aircraft.Thruster provides thrust for aircraft, make up the fan wing and push away hypodynamic shortcoming, fly before making aircraft keep larger speed, also overcome the shortcoming of the fan wing little speed pneumatic force coefficient instability, the fan wing is made to remain on the stable state of large speed pneumatic force coefficient, road-holding property is good, good stability.
The utility model is for solving the problems of the technologies described above by the following technical solutions:
A kind of high speed fan rotor aircraft, comprises wing, engine installation and driving device, it is characterized in that, also comprise thruster;
Described wing is the fan wing;
Described engine installation provides power by driving device to wing and thruster;
Described thruster is used for providing extra-push model for aircraft.
As the further prioritization scheme of a kind of high speed fan rotor aircraft of the utility model, aircraft also comprises the afterbody fan wing.
As the further prioritization scheme of a kind of high speed fan rotor aircraft of the utility model, the described afterbody fan wing adopts the fan wing.
As the further prioritization scheme of a kind of high speed fan rotor aircraft of the utility model, described thruster adopts screw propeller, is arranged on the afterbody of aircraft.
As the further prioritization scheme of a kind of high speed fan rotor aircraft of the utility model, described wing is provided with control surface, for handling the flight attitude of aircraft.
The engine installation (as driving engine) of fuselage interior is respectively the full machine fan wing by driving system and thruster provides power, retarder successively in driving system of the power that driving engine spreads out of and rotating speed and link gear slow down and are delivered to the full machine fan wing and thruster, make it rotate and produce lift and thrust, wherein the effect of driving system the high rotating speed of driving engine is reduced to the rotating speed that the full machine fan wing and thruster can be suitable for.
Under low-speed situations, because when low speed, the startup of the fan wing can provide part thrust for aircraft in flying speed direction, with joint efforts so the thrust flown before the full machine of low-speed situations aircraft is made up of two parts; After vehicle flight speeds reaches design cruising speed, the aerodynamic resultant of the fan wing the component of heading become hinder aircraft before the resistance that flies, at this moment before aircraft, the power of flying comes from the power that thruster produces.
The utility model adopts above technical scheme compared with prior art, has following technique effect:
1. overcome the unstable shortcoming of existing fan rotor aircraft low velocity pneumatic power, can fly in larger speed range;
2. thruster compensate for the fan wing and to advance hypodynamic shortcoming, takes full advantage of the advantage that fan wing lift coefficient is high;
3. the thrust of thruster can make fan rotor aircraft enter stabilized flight condition very soon;
4. full machine good stability, road-holding property is good, and flight quality is high, is convenient to pilot guidance.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model embodiment;
Fig. 2 is the structural representation of another embodiment of the utility model.
In figure, the oblique vertical fin of 1-, 2-thruster, 3-driving engine, 4-fan wing wing, 5-fuselage, the 6-afterbody fan wing.
Detailed description of the invention
Below in conjunction with accompanying drawing, the technical solution of the utility model is described in further detail:
The utility model discloses a kind of high speed fan rotor aircraft, comprise wing, engine installation and driving device, it is characterized in that, also comprise thruster;
Described wing is the fan wing;
Described engine installation provides power by driving device to wing and thruster;
Described thruster is used for providing extra-push model for aircraft.
Described wing is provided with control surface, for handling the flight attitude of aircraft.
Described thruster can adopt screw propeller, is arranged on the afterbody of aircraft.
As shown in Figure 1, driving engine provides power to the fan wing of fan wing wing and thruster, the screw propeller High Rotation Speed of the fan wing of fan wing wing and thruster produces aerodynamic force, lift required when the rotation of the fan wing of its fan wing wing mainly produces aircraft cruising flight.The screw propeller High Rotation Speed of thruster produces aerodynamic force then provides for during aircraft cruising flight the thrust overcoming extraneous air resistance.Fuselage links together each system.
As shown in Figure 2, the fan wing can also be used as the form of the afterbody fan wing to control the flight attitude of aircraft.
Those skilled in the art of the present technique are understandable that, unless otherwise defined, all terms used herein (comprising technical term and scientific terminology) have the meaning identical with the general understanding of the those of ordinary skill in field belonging to the utility model.Should also be understood that those terms defined in such as general dictionary should be understood to have the meaning consistent with the meaning in the context of prior art, unless and define as here, can not explain by idealized or too formal implication.
Above-described detailed description of the invention; the purpose of this utility model, technical scheme and beneficial effect are further described; be understood that; the foregoing is only detailed description of the invention of the present utility model; be not limited to the utility model; all within spirit of the present utility model and principle, any amendment made, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (5)
1. a high speed fan rotor aircraft, comprises wing, engine installation and driving device, it is characterized in that, also comprise thruster;
Described wing is the fan wing;
Described engine installation provides power by driving device to wing and thruster;
Described thruster is used for providing extra-push model for aircraft.
2. high speed fan rotor aircraft according to claim 1, is characterized in that, also comprises the afterbody fan wing.
3. high speed fan rotor aircraft according to claim 2, is characterized in that, the described afterbody fan wing adopts the fan wing.
4. high speed fan rotor aircraft according to claim 1, is characterized in that, described thruster adopts screw propeller, is arranged on the afterbody of aircraft.
5. high speed fan rotor aircraft according to claim 1, is characterized in that, described wing is provided with control surface, for handling the flight attitude of aircraft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520290227.4U CN204750567U (en) | 2015-05-07 | 2015-05-07 | High -speed fan wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520290227.4U CN204750567U (en) | 2015-05-07 | 2015-05-07 | High -speed fan wing aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204750567U true CN204750567U (en) | 2015-11-11 |
Family
ID=54465301
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520290227.4U Expired - Fee Related CN204750567U (en) | 2015-05-07 | 2015-05-07 | High -speed fan wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204750567U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107554784A (en) * | 2017-08-10 | 2018-01-09 | 中国科学院力学研究所 | A kind of cross flow fan and on cross flow fan random regulation fan wing angle of inclination method |
| CN107600409A (en) * | 2017-08-10 | 2018-01-19 | 中国科学院力学研究所 | Device and method caused by the lift of air circulation flow is accelerated based on cross flow fan |
-
2015
- 2015-05-07 CN CN201520290227.4U patent/CN204750567U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107554784A (en) * | 2017-08-10 | 2018-01-09 | 中国科学院力学研究所 | A kind of cross flow fan and on cross flow fan random regulation fan wing angle of inclination method |
| CN107600409A (en) * | 2017-08-10 | 2018-01-19 | 中国科学院力学研究所 | Device and method caused by the lift of air circulation flow is accelerated based on cross flow fan |
| CN107600409B (en) * | 2017-08-10 | 2019-10-29 | 中国科学院力学研究所 | The device and method for accelerating the lift of air circulation flow to generate based on cross flow fan |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151111 Termination date: 20170507 |