CN216943525U - Distributed electric ducted flap lift-increasing system with deflection guide vanes - Google Patents
Distributed electric ducted flap lift-increasing system with deflection guide vanes Download PDFInfo
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- CN216943525U CN216943525U CN202220736138.8U CN202220736138U CN216943525U CN 216943525 U CN216943525 U CN 216943525U CN 202220736138 U CN202220736138 U CN 202220736138U CN 216943525 U CN216943525 U CN 216943525U
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- wing
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- electric ducted
- lift
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 238000000926 separation method Methods 0.000 description 5
- 238000007664 blowing Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 230000003416 augmentation Effects 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000000452 restraining effect Effects 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
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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 utility model discloses a distributed electric culvert flap lift-increasing system with deflection flow deflectors, which comprises a wing of an unmanned aerial vehicle, wherein the front and the back of the wing are respectively provided with a leading edge slat and a trailing edge flap, the upper wing surface of the wing is provided with a plurality of groups of culverts along the span direction of the wing, the culverts are n-shaped in appearance and are arranged on the upper wing surface of the wing at equal intervals, the horizontal direction of the trailing edge of each culvert is provided with three flow deflectors capable of deflecting at equal intervals, a support rod is arranged in each culvert, a motor is arranged on each support rod, and an electric culvert fan capable of generating slipstream is arranged on each motor. The lift-increasing efficiency of the wing is further improved.
Description
Technical Field
The utility model relates to an upper surface air blowing flap lift-increasing system, in particular to a distributed electric ducted flap lift-increasing system with deflection guide vanes.
Background
There are three types of externally blown flap lift systems for aircraft known at present: the jet engine comprises a jet engine upper wing surface blowing flap lift-rising system, a jet engine lower wing surface blowing flap lift-rising system and a propeller slipstream flap lift-rising system.
The propeller slipstream flap lift-rising system using the propeller can adopt electric drive, and is beneficial to linear arrangement at the front edge of the wing by using a distributed mode at intervals of a certain distance so as to fully utilize the wing span of a relatively large wing and efficiently carry out the lift-rising of the flap of the outer blowing. In 2015, 3 months, the American space navigation administration starts to perform experiments by using wings of a distributed electric propeller flap lift-increasing system, wherein the wings have 18 electric propellers in total, and the electric propellers are distributed at the leading edge of the wings to perform power lift-increasing on the wings when an aircraft takes off and lands; but the slipstream of the propeller is twisted by the slipstream, which is not beneficial to power lift increase; the fan slipstream of the upper wing surface of the wing in the propeller slipstream flap lift-rising system using the propeller cannot be well blown off to the upper surface of the flap backwards and downwards along the flap turning flow angle, but is blown more backwards, so that the lift-rising effect of the conventional distributed electric ducted flap lift-rising system is poor during rising/falling.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve the technical problems in the prior art and provides a distributed electric ducted flap lift-increasing system with deflection guide vanes.
In order to realize the purpose, the technical scheme provided by the utility model is as follows: the utility model provides a distributed electric duct flap lift augmentation system of water conservancy diversion piece deflects in area, includes unmanned aerial vehicle's wing, install leading-edge slat and trailing edge flap around the wing respectively, the last airfoil edge of wing is followed the exhibition of wing is to being provided with the multiunit duct, the appearance of duct is n shape, just is in the last airfoil equidistance of wing is arranged, the trailing edge horizontal direction department of duct is provided with three equidistant water conservancy diversion pieces that can deflect, be provided with the bracing piece in the duct, be provided with the motor on the bracing piece, be provided with the electronic duct fan that can produce the slipstream on the motor, electronic duct fan sets up at the distance the leading edge third department of duct.
Preferably, the guide vanes are arranged longitudinally along the duct outlet, and the guide vanes are installed along the air flow direction, and the cross section of the guide vanes is an airfoil shape.
Preferably, the number of the support rods is consistent with the number of the blades of the electric ducted fan, the section of each support rod is a single-convex wing type, the front edge of each single-convex wing type is over against the slip flow direction generated by the electric ducted fan, and the rear edge of each single-convex wing type faces the rear direction.
Preferably, the airfoil of the wing is a high lift laminar flow airfoil.
Preferably, the exhaust ports of the ducts are located at the trailing edge of the wing, and the distance between the ducts is the same as the inlet diameter of the duct.
The utility model has the beneficial effects that:
according to the utility model, a plurality of groups of ducts are continuously arranged on the upper surface of the wing along the span direction, the electric ducted fan in the ducts is used for carrying out power lift-up on the wing, the slip flow generated by the electric ducted fan is deflected by the deflectable flow deflector arranged at the rear edge of the duct, the slip flow is guided to flow to the upper surface of the rear edge flap, and the airflow flow on the upper surface of the rear edge flap is accelerated, so that the airflow separation is inhibited, the pressure difference between the upper wing surface and the lower wing surface of the wing is increased, and the lift-up efficiency of the wing is further improved.
Drawings
The accompanying drawings, which are included to provide a further understanding of the utility model and are incorporated in and constitute a part of this specification, illustrate embodiments of the utility model and together with the description serve to explain the utility model and not to limit the utility model.
FIG. 1 is an isometric view of the present invention;
FIG. 2 is a rear view of the present invention;
FIG. 3 is a right side view of the present invention;
FIG. 4 is a partial front view of the electric ducted fan in the present invention;
fig. 5 is a partial rear view of the electric ducted fan in the present invention.
The attached drawings are marked as follows:
1. leading edge slat 2, wing 3, trailing edge flap 4, duct 5, electric ducted fan 6, motor 7, bracing piece 8, water conservancy diversion piece.
Detailed Description
Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If the first and second are described for the purpose of distinguishing technical features, they are not to be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.
In the description of the present invention, unless otherwise explicitly limited, terms such as arrangement, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention in combination with the specific contents of the technical solutions.
Referring to fig. 1 to 5, in a preferred embodiment of the present invention, a distributed electric ducted flap lift-increasing system with a deflecting guide vane includes a wing 2 of an unmanned aerial vehicle, a leading edge slat 1 and a trailing edge flap 3 are respectively installed at the front and the rear of the wing 2, a plurality of sets of ducts 4 are arranged on an upper wing surface of the wing 2 along a span direction of the wing 2, the ducts 4 are n-shaped and are arranged at equal intervals on the upper wing surface of the wing 2, three guide vanes 8 which are equally spaced and can deflect are arranged at a horizontal position of a trailing edge of the duct 4, a support rod 7 is arranged in the duct 4, a motor 6 is arranged on the support rod 7, an electric ducted fan 5 capable of generating a slipstream is arranged on the motor 6, and the electric ducted fan 5 is arranged at a position one third distance from the leading edge of the duct 4.
Specifically, the utility model can accelerate the airflow flow on the upper surface of the wing 2 through the suction effect of the electric ducted fan 5, and at the same time, the slipstream can smoothly flow through the upper surface of the trailing edge flap 3 after flowing through the outlet of the duct 4, so as to inject energy into the upper surface of the trailing edge flap 3, accelerate the airflow flow on the upper surface, and perform power boosting on the wing 2, and meanwhile, the electric ducted fan 5 has low speed when working, the slipstream generated by the electric ducted fan 5 erodes the skin of the wing 2 has low noise and vibration, the temperature of the slipstream in the duct 4 is low, and the structural influence on the skin of the wing 2 is relatively small.
According to the utility model, a plurality of groups of ducts 4 are continuously and equidistantly arranged on the upper surface of the wing 2 along the span direction, and the electric ducted fan 5 in the ducts 4 is used for carrying out power lift-up on the wing 2, and deflecting the slipstream generated by the electric ducted fan 5 through the deflectable guide vanes 8 arranged at the rear edge of the ducts 4, so that the slipstream is guided to flow to the upper surface of the rear edge flap 3, the airflow flow on the upper surface of the rear edge flap 3 is accelerated, the airflow separation is inhibited, the pressure difference between the upper wing surface and the lower wing surface of the wing 2 is increased, and the lift-up efficiency of the wing 2 is further improved.
As a preferred embodiment of the present invention, it may also have the following additional technical features:
in this embodiment, the flow deflectors 8 are longitudinally arranged along the outlet of the duct 4, the flow deflectors 8 are installed along the air flowing direction, the cross section of each flow deflector 8 is an airfoil shape, and three of the flow deflectors 8 can be controlled to deflect upwards and downwards so as to deflect the slipstream generated by the electric duct fan 5, so that the slipstream smoothly flows to the upper surface of the trailing edge flap 3, and thus the lift-increasing efficiency of the wing 2 is improved.
In this embodiment, the number of the support rods 7 is consistent with the number of the blades of the electric ducted fan 5, the cross section of each support rod 7 is a single-convex wing type, the front edge of each single-convex wing type is over against the slip flow direction generated by the electric ducted fan 5, and the rear edge of each single-convex wing type faces the rear direction, so that the torsion effect of the slip flow generated by the electric ducted fan 5 can be eliminated.
In the present embodiment, the airfoil profile of the wing 2 is a high lift laminar profile.
In this embodiment, the exhaust ports of the ducts 4 are located at the trailing edge of the wing 2, and the distance between the ducts 4 is the same as the inlet diameter of the ducts 4.
Detailed description of the utility model
The utility model can be applied to various aircrafts and can be arranged at two sides of the fuselage of the aircraft, when the aircraft needs to take off/land, the leading edge slat 1 and the trailing edge flap 3 of the wing 2 are put down and deflected by a certain angle, because a plurality of electric ducted fans 5 are arranged at the rear edge of the upper surface of the wing 2, the electric ducted fans 5 generate suction action on airflow in front of the duct 4 through high-speed rotation to accelerate the flow of the airflow on the upper surface of the wing 2, because the electric ducted fans 5 do work on the airflow on the upper surface of the wing 2 through the rotation, the airflow on the upper surface is accelerated through injecting energy into the upper surface of the wing 2, so that the airflow of the aircraft can still flow closely to a boundary layer under a large attack angle, the separation of the airflow is inhibited, the slip flow generated by the electric ducted fans 5 flows along the upper surface of the trailing edge flap 3 through the deflection of the guide vanes 8, and the airflow on the upper surface of the trailing edge flap 3 is accelerated and the flow separation is inhibited, part of component of the thrust generated by the utility model is directed above the wing 2, namely the lift force of the wing 2, and the slipstream of the electric ducted fan 5 generates a restraining effect on the separation of the airflow on the upper surface of the wing 2, so that the airflow of the aircraft is not separated under a large attack angle, and the maximum stall attack angle of the aircraft and the maneuverability of the aircraft are improved. When the aircraft provided with the utility model flies forwards, the leading edge slat 1 and the trailing edge flap 3 of the wing 2 are gradually retracted, meanwhile, the deflection angle of the flow deflector 8 is kept consistent with the trailing edge flap 3 through control, the slipstream generated by the electric ducted fan 5 on the upper wing surface of the wing 2 gradually turns to blow off backwards, the resultant force direction of the lift force of the wing 2 gradually turns upwards from the back, the forward thrust component force of the slipstream generated by the electric ducted fan 5 is greater than the backward lift component force of the wing 2, so that the aircraft flies forwards continuously, the leading edge slat 1 and the trailing edge flap 3 continue to retract, the slipstream generated by the electric ducted fan 5 on the upper wing surface of the wing 2 further turns backwards to blow off, the lift force of the wing 2 turns upwards more, the corresponding flight speed of the aircraft continuously rises, and when the leading edge slat 1 and the trailing edge flap 3 are completely retracted, the flow deflector 8 returns to the horizontal position, the slipstream generated by the electric ducted fan 5 completely pushes the aircraft to fly forwards, at the moment, the aircraft enters a cruising state, and the slipstream generated by the electric ducted fan 5 flows backwards along the wing 2, so that most of the thrust of the slipstream generated by the electric ducted fan 5 is used for propulsion, and high propulsion efficiency is generated.
The size, shape and number of the electric ducted fan 5 and the number of the blades of the electric ducted fan 5 can be designed according to specific requirements so as to meet the requirements of various aircrafts under different working conditions, and therefore the aircrafts can be in the best working state.
The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.
The above description is only a preferred embodiment of the present invention, and the technical solutions that achieve the objects of the present invention by basically the same means are all within the protection scope of the present invention.
Claims (5)
1. The utility model provides a distributed electric duct wing flap lift-rising system of area deflection water conservancy diversion piece, includes unmanned aerial vehicle's wing, its characterized in that: install leading-edge slat (1) and trailing edge flap (3) respectively around wing (2), the last aerofoil of wing (2) is followed the exhibition of wing (2) is to being provided with multiunit duct (4), the appearance of duct (4) is n shape, just the last aerofoil equidistance of wing (2) is arranged, the trailing edge horizontal direction department of duct (4) is provided with three equidistant water conservancy diversion pieces (8) that can deflect, be provided with bracing piece (7) in duct (4), be provided with motor (6) on bracing piece (7), be provided with on motor (6) and produce electronic ducted fan (5) of slipstream, electronic ducted fan (5) set up the distance the leading edge third department of duct (4).
2. The distributed electric ducted flap lift system with deflector vanes according to claim 1, wherein: the flow deflector (8) is longitudinally arranged along the outlet of the duct (4), the flow deflector (8) is installed along the air flowing direction, and the section of the flow deflector is an airfoil shape.
3. The distributed electric ducted flap lift system with deflector vanes according to claim 1, wherein: the number of the supporting rods (7) is consistent with the number of the blades of the electric ducted fan (5), the section of each supporting rod (7) is a single-convex wing type, the front edge of each single-convex wing type is over against the slip flow direction generated by the electric ducted fan (5), and the rear edge of each single-convex wing type faces the rear.
4. The distributed electric ducted flap lift system with deflector vanes according to claim 1, wherein: the airfoil profile of the wing (2) is a high-lift laminar flow airfoil profile.
5. The distributed electric ducted flap lift system with deflector vanes according to claim 1, wherein: the exhaust port of the duct (4) is located at the trailing edge of the wing (2), and the distance between the ducts (4) is the same as the inlet diameter of the duct (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220736138.8U CN216943525U (en) | 2022-03-31 | 2022-03-31 | Distributed electric ducted flap lift-increasing system with deflection guide vanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220736138.8U CN216943525U (en) | 2022-03-31 | 2022-03-31 | Distributed electric ducted flap lift-increasing system with deflection guide vanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216943525U true CN216943525U (en) | 2022-07-12 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220736138.8U Expired - Fee Related CN216943525U (en) | 2022-03-31 | 2022-03-31 | Distributed electric ducted flap lift-increasing system with deflection guide vanes |
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| CN (1) | CN216943525U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116119002A (en) * | 2023-04-14 | 2023-05-16 | 成都流体动力创新中心 | Wing flow control system based on duct fan driving cooperative blowing and sucking air |
-
2022
- 2022-03-31 CN CN202220736138.8U patent/CN216943525U/en not_active Expired - Fee Related
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116119002A (en) * | 2023-04-14 | 2023-05-16 | 成都流体动力创新中心 | Wing flow control system based on duct fan driving cooperative blowing and sucking air |
| CN116119002B (en) * | 2023-04-14 | 2023-06-20 | 成都流体动力创新中心 | Wing flow control system based on duct fan driving cooperative blowing and sucking air |
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| GR01 | Patent grant | ||
| 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: 20220712 |