CN205186510U - No rudder face aircraft of independent air supply air feed - Google Patents
No rudder face aircraft of independent air supply air feed Download PDFInfo
- Publication number
- CN205186510U CN205186510U CN201520899558.8U CN201520899558U CN205186510U CN 205186510 U CN205186510 U CN 205186510U CN 201520899558 U CN201520899558 U CN 201520899558U CN 205186510 U CN205186510 U CN 205186510U
- Authority
- CN
- China
- Prior art keywords
- wing
- jet pipe
- aileron
- trailing edge
- rudder face
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn - After Issue
Links
Abstract
The utility model provides a no rudder face aircraft of independent air supply air feed, basic configuration are canard configuration fixed wing aircraft, including fuselage, the host computer wing, the duck wing, back pushing -type power device, screw, winglet, main landing gear and nose -gear, rely on one set of circular rector controlling means, replace traditional rudder face, simple structure is convenient for safeguard. And owing to cancelled conventional rudder face, the original sharp -pointed edge in wing surface, opening and boss etc. Can disappear, this radar scattering area that will reduce the aircraft can promote the stealth of aircraft.
Description
Technical field
The utility model relates to field of aviation machinery, specifically a kind of individual gas sources air feed without rudder face aircraft.
Background technology
Effective maneuvering and control of the primary control surface generation of aircraft, can carry out stable flight.But there is many defects in traditional rudder face, such as complex structure, overhaul loaded down with trivial details, increase flight resistance and reduce stealth etc.When excellent aeroperformance, long voyage, long boat and high stealth be important indicator in Flight Vehicle Design of future generation.Tradition circulation control technology often from engine bleed for device provides source of the gas, this will affect the Power output of driving engine.
Utility model content
The utility model in order to solve the problem of prior art, provide a kind of individual gas sources air feed without rudder face aircraft, instead of traditional rudder face with circulation control device, structure is simple, is convenient to safeguard.And owing to eliminating conventional rudder face, the original sharp edges of aerofoil surface, opening and boss etc. can disappear, this, by reducing the radar scattering area of aircraft, can promote the stealth of aircraft.
The utility model comprises the canard configuration's Fixed Wing AirVehicle be made up of fuselage, host wing, canard, back-pushed engine installation, screw propeller, winglet, main landing gear and nose-gear, and host wing inside is provided with some circulation control devices; Described circulation control device comprises the multi-wing centrifugal fan that connected by jet pipe and Koln reaches trailing edge, wherein jet pipe comprises the closed inner chamber be made up of upper sealing surface, lower sealing surface, both sides occluding surface, upper and lower two sealing surfaces are 15 ° and shrink junction from multi-wing centrifugal fan interface to coanda trailing edge, have out air cleft between upper and lower two sealing surfaces and coanda trailing edge; Be provided with dividing plate in jet pipe, two inner chambers up and down that jet pipe in the vertical direction is divided into volume equal by dividing plate, each inner chamber all with one independently multi-wing centrifugal fan be connected.
Loss of pressure is caused in order to prevent cross-sectional expansion, cause jet energy not enough, described jet pipe both sides occluding surface horizontal direction increases from multi-wing centrifugal fan interface gradually to coanda trailing edge, jet pipe inner chamber is divided into some areolas by shaped form deflecting plate, described areola is all equal to the sectional area of coanda trailing edge arbitrary section from multi-wing centrifugal fan interface, and the sectional area in any areola cross section, coanda trailing edge place amasss equal with the intracavity section of jet pipe multi-wing centrifugal fan interface.Circulation control aileron exiter, for replacing aileron, realizes the control of roll attitude.Usual conventional rudder face realizes this control by differential deflection, of the present utility modelly causes left and right lift overbalance to realize the manipulation of roll attitude without rudder face aircraft by opening the circulation control aileron exiter of side.The essential structure of circulation control aileron exiter is similar to circulation control raise/lower actuator, but only have a cavity and one to go out air cleft, by a centrifugal blower air feed, the air-flow of trailing edge can be made to deflect down, increase the circular rector of side wing, realize the object of lift-rising.
Described fuselage is provided with circulation control aileron exiter, described circulation control aileron exiter comprises the aileron centrifugal blower that connected by aileron jet pipe and aileron Koln reaches trailing edge, aileron jet pipe comprises upper and lower two sealing surfaces, has aileron and go out air cleft under aileron jet pipe between sealing surface and aileron coanda trailing edge.
The utility model beneficial effect is:
1, lift-rising drag reduction: circulation control technology can produce favourable interference to air-flow, can not only control flight attitude, can also promote the aeroperformance of aircraft, realizes lift-rising drag reduction.Experimental result shows, in normal flight angle-of-attack range, the lift coefficient maximal increment that circulation control device opens rear model can reach 23.1%, and drag coefficient decrease can reach 31.7%.
2, simple without rudder face structure: not adopt traditional primary control surface, the mode of the application circulation control pose adjustment that is aircraft and motor-drivenly provide force and moment, realizes flying without rudder.Design and optimize circulation control device, makes its miniaturization, lightness is convenient to airborne, and has good control steerage.Wing structure without rudder face unmanned plane is simple, without the need to the driving device of complexity, the substitute is easy fluidic device.
3, stealth is promoted: conventional airfoil is furnished with a large amount of movable rudder face, this is for stealthy very unfavorable.The utility model circulation control device replaces traditional rudder face, and on wing, original sharp edges, opening and projection are eliminated, and aerofoil surface is very level and smooth without any opening, and reduce radar scattering area, Stealth Fighter is improved.
Accompanying drawing explanation
Fig. 1 is the utility model structural representation.
Fig. 2 is A-A cutaway view in Fig. 1.
Fig. 3 is circulation control device place close-up schematic view in Fig. 2.
Fig. 4 is the tangential section-drawing of coanda trailing edge.
Fig. 5 is the bench section of the jet pipe of circulation control raise/lower actuator.
Fig. 6 is jet pipe both sides occluding surface schematic diagrams.
Fig. 7 is the flow deflector structure schematic diagram of jet pipe inside.
Fig. 8 is the schematic diagram of upper and lower two cavitys of jet pipe.
Fig. 9 is circulation control device integral structure schematic diagram.
Figure 10 is circulation control aileron exiter integral structure schematic diagram.
Detailed description of the invention
The utility model provide a kind of individual gas sources air feed without rudder face aircraft, its structure as shown in Figure 1, Figure 2 and Figure 3, comprise the canard configuration's Fixed Wing AirVehicle be made up of fuselage 5, host wing 3, canard 6, back-pushed engine installation 7, screw propeller 8, winglet 11, main landing gear 12 and nose-gear 13, host wing inside is provided with circulation control device, the control that can conventional aileron and elevating rudder not relied on to realize rolling and pitch attitude, realizes flying without rudder face.
Circulation control raise/lower actuator is made up of a multi-wing centrifugal fan 2 and a jet pipe 1, wherein multi-wing centrifugal fan 2 is as an independently source of the gas, by multi-wing centrifugal fan motor 9 from wing tip bleed, provide high-voltage high-speed airflow, jet pipe makes air-flow deflect for the formation of Coanda effect.The side of jet pipe 1 connects multi-wing centrifugal fan 2, and opposite side is elongated coanda trailing edge, and trailing edge radius is 4.5mm, and what trailing edge place had a 300mm to grow goes out air cleft, and the ratio that trailing edge radius is high with going out air cleft is 15, stitches high 0.3mm as shown in Figure 4.Because the inner space of aircraft wing is limited, for the ease of jet pipe is imbedded wing inside, the upper sealing surface 15 of jet pipe and lower sealing surface 16 shrink junction in 15 ° of angles from centrifugal blower interface to coanda trailing edge, its thickness be 1mm as shown in Figure 5.Loss of pressure is caused in order to prevent cross-sectional expansion, cause jet energy not enough, the configuration design of jet pipe is carried out one according to following steps and from centrifugal blower interface, is equidistantly chosen 5 cross sections until the area in these 5 cross sections is decided to be i.e. 15.5mm × 70mm consistent with admission port area by coanda trailing edge two, determine the cross section transverse width that the transverse width three needed for lower each cross section is fixed according to second step, smooth connection boundary point successively, obtain profile shown in Fig. 6, two N-Side surf thickness are 1mm.In order to make to give vent to anger evenly, jet pipe inside is provided with deflecting plate 18, and inner chamber is divided into 5 regions by the curved shape of flow deflector, and the thickness of flow deflector is 1mm, is being provided with rounding, as shown in Figure 7 close to admission port place.In order to complete the function the same with rudder face, air-flow is made to occur to deflect up and down, jet pipe is designed to up and down independently two parts by the utility model from admission port, separated by the one flat plate at middle part, upper and lower two parts cavity volume is equal, see Fig. 8, when providing the centrifugal blower rotor turns of source of the gas for the latter half pipeline, outer gas stream is inhaled into the latter half pipeline, this strand of air-flow can upward deflect along circular coanda trailing edge from when going out air cleft injection, same principle, when providing the centrifugal blower rotor turns of source of the gas for the first half pipeline, outer gas stream is inhaled into the first half pipeline, this strand of air-flow can deflect down along circular coanda trailing edge from when going out air cleft injection.Final centrifugal blower with jet pipe combination after as shown in Figure 9.
Circulation control aileron exiter, for replacing aileron, realizes the control of roll attitude.Usual conventional rudder face realizes this control by differential deflection, of the present utility modelly causes left and right lift overbalance to realize the manipulation of roll attitude without rudder face aircraft by opening the circulation control aileron exiter of side.The essential structure of circulation control aileron exiter is similar to circulation control raise/lower actuator, but only have a cavity and one to go out air cleft, by a centrifugal blower air feed, the air-flow of trailing edge can be made to deflect down, increase the circular rector of side wing, realize the object of lift-rising.Circulation control aileron exiter 4 width of these works design is 240mm, and trailing edge radius 4.5mm, goes out air cleft height 0.3mm, as shown in Figure 10.
Flight attitude control principle without rudder face aircraft of the present utility model is: after input control signal, multi-wing centrifugal fan is started working, under the effect of centrifugal impeller, wing internal gas flow is accelerated, eject through jet pipe, utilize Coanda effect to be formed with profit interference to main flow air-flow, the aerodynamic force acting on wing can be changed.Based on above-mentioned principle, the circulation control aileron exiter opening side produces the not reciprocity control realizing roll attitude of left and right airfoil lift, deflect down air-flow by the circulation control raise/lower actuator controlling fuselage both sides and produce nose-down pitching moment, upward deflect air-flow by circulation control raise/lower actuator and produce nose-up pitching moment.When the circulation control raise/lower actuator of fuselage side is opened up and down while during blow mode, can yawing moment be formed, make aircraft toward the side driftage of not opening air blowing.
The utility model is configured as canard configuration, eliminates traditional rudder face, is embedded in the circulation control device of wing in the substitute is, all the other structures and conventional airplane similar, structure is simple, is convenient to safeguard.Owing to eliminating conventional rudder face, the original sharp edges of aerofoil surface, opening and boss etc. can disappear, and this, by reducing the radar scattering area of aircraft, can promote the stealth of aircraft.The utility model has completed a frame without rudder face aircraft material object, and it has been carried out to wind tunnel experiment and the Flight Test Research of system.Wind tunnel experimental results shows, this under 10m/s wind friction velocity, can produce commensurateiy wide aileron 50 ° of inclined effects of rudder and 20 ° of inclined effects of elevating rudder rudder without rudder face aircraft.According to result of taking a flight test, the circulation control device of the utility model design can proportional control attitude, and aircraft is very steady in flight course, takes a flight test very smooth without rudder face.
Below the basic specification in kind that the utility model has completed:
Title: a kind of individual gas sources air feed without rudder face aircraft
The span: 1.73m; Aspect ratio: 5; Captain: 1.25m; Maximum take-off weight: 6.00kg; Cruising speed: 15m/s; Circulation control source of the gas: multi-wing centrifugal fan; Main wing leading edge sweepback angle: 30 °; Canard sweepback angle: 15 °.
The utility model embody rule approach is a lot; the above is only preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model principle; can also make some improvement, these improvement also should be considered as protection domain of the present utility model.
Claims (3)
1. an individual gas sources air feed without rudder face aircraft, comprise the canard configuration's Fixed Wing AirVehicle be made up of fuselage (5), host wing (3), canard (6), back-pushed engine installation (7), screw propeller (8), winglet (11), main landing gear (12) and nose-gear (13), it is characterized in that: host wing (3) inside is provided with some circulation control devices; Described circulation control device comprises the multi-wing centrifugal fan (2) that connected by jet pipe (1) and Koln reaches trailing edge (10), wherein jet pipe (1) comprises the closed inner chamber be made up of upper sealing surface (15), lower sealing surface (16), both sides occluding surface, upper and lower two sealing surfaces are 15 ° and shrink junction from multi-wing centrifugal fan interface to coanda trailing edge, have out air cleft (14) between upper and lower two sealing surfaces and coanda trailing edge; Be provided with dividing plate (17) in jet pipe (1), jet pipe (1) in the vertical direction is divided into two inner chambers up and down that volume is equal by dividing plate (17), each inner chamber all with one independently multi-wing centrifugal fan (2) be connected.
2. individual gas sources air feed according to claim 1 without rudder face aircraft, it is characterized in that: described jet pipe (1) both sides occluding surface horizontal direction increases from multi-wing centrifugal fan (2) interface gradually to coanda trailing edge (10), jet pipe (1) inner chamber is divided into some areolas by shaped form deflecting plate (18), described areola is all equal to the sectional area of coanda trailing edge arbitrary section from multi-wing centrifugal fan interface, the sectional area in any areola cross section, coanda trailing edge (10) place amasss equal with the intracavity section of jet pipe (1) multi-wing centrifugal fan (2) interface.
3. individual gas sources air feed according to claim 1 without rudder face aircraft, it is characterized in that: described host wing (3) is provided with circulation control aileron exiter (4), described circulation control aileron exiter (4) comprises the aileron centrifugal blower that connected by aileron jet pipe and aileron Koln reaches trailing edge, aileron jet pipe comprises upper and lower two sealing surfaces, has aileron and go out air cleft under aileron jet pipe between sealing surface and aileron coanda trailing edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520899558.8U CN205186510U (en) | 2015-11-12 | 2015-11-12 | No rudder face aircraft of independent air supply air feed |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520899558.8U CN205186510U (en) | 2015-11-12 | 2015-11-12 | No rudder face aircraft of independent air supply air feed |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205186510U true CN205186510U (en) | 2016-04-27 |
Family
ID=55779530
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520899558.8U Withdrawn - After Issue CN205186510U (en) | 2015-11-12 | 2015-11-12 | No rudder face aircraft of independent air supply air feed |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205186510U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314096A (en) * | 2015-11-12 | 2016-02-10 | 南京航空航天大学 | No-control-surface aircraft with air fed by independent air source |
| CN106364667A (en) * | 2016-09-28 | 2017-02-01 | 韩建刚 | Aircraft |
| CN113942651A (en) * | 2021-09-21 | 2022-01-18 | 西北工业大学 | Novel flight control device of SACCON type aircraft |
| CN114394224A (en) * | 2022-01-10 | 2022-04-26 | 太仓点石航空动力有限公司 | Bulge high-lift device based on three-dimensional coanda effect and design method thereof |
-
2015
- 2015-11-12 CN CN201520899558.8U patent/CN205186510U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105314096A (en) * | 2015-11-12 | 2016-02-10 | 南京航空航天大学 | No-control-surface aircraft with air fed by independent air source |
| CN106364667A (en) * | 2016-09-28 | 2017-02-01 | 韩建刚 | Aircraft |
| WO2018059244A1 (en) * | 2016-09-28 | 2018-04-05 | 韩建刚 | Aircraft |
| CN113942651A (en) * | 2021-09-21 | 2022-01-18 | 西北工业大学 | Novel flight control device of SACCON type aircraft |
| CN114394224A (en) * | 2022-01-10 | 2022-04-26 | 太仓点石航空动力有限公司 | Bulge high-lift device based on three-dimensional coanda effect and design method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105314096A (en) | No-control-surface aircraft with air fed by independent air source | |
| US10875658B2 (en) | Ejector and airfoil configurations | |
| US11485472B2 (en) | Fluid systems that include a co-flow jet | |
| US9180974B2 (en) | Aircraft with an integral aerodynamic configuration | |
| US10625847B2 (en) | Split winglet | |
| CN205186510U (en) | No rudder face aircraft of independent air supply air feed | |
| CN108394556A (en) | A kind of efficient tilting rotor wing unmanned aerial vehicle | |
| US20160152324A1 (en) | Fluidic fence for performance enhancement | |
| CN103419933A (en) | Vertical take-off and landing aircraft with front wings and rear wings on basis of novel high-lift devices | |
| CN103419935A (en) | Vertical take-off and landing aircraft in saucer-shaped arrangement and based on novel high-lift device | |
| CN113942651A (en) | Novel flight control device of SACCON type aircraft | |
| US20230075112A1 (en) | Deflected Slip Stream Wing System with Coflow Jet Flow Control | |
| RU192918U1 (en) | AIRCRAFT | |
| CN209241307U (en) | Without rudder face aircraft | |
| CN207902734U (en) | A kind of unmanned plane of aerodynamic arrangement | |
| CN110641679A (en) | Take V fin body to fuse overall arrangement aircraft | |
| CN216468522U (en) | But rhombus fixed wing VTOL unmanned aerial vehicle | |
| CN115195988A (en) | Novel aerodynamic layout of VTOL fixed wing unmanned aerial vehicle | |
| CN114212261A (en) | Rhombic fixed-wing vertical take-off and landing unmanned aerial vehicle | |
| Camci et al. | A Brief Description Of The Ducted Fan Inlet Flow Distortion Reduction Concept, Double-Ducted-Fan (Ddf) | |
| CN103754372A (en) | Airplane capable of vertically taking-off and landing as well as staying and inversely flying in air |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20160427 Effective date of abandoning: 20171031 |
|
| AV01 | Patent right actively abandoned |