CN106184773B - A kind of tailstock formula duct unmanned aerial vehicle - Google Patents
A kind of tailstock formula duct unmanned aerial vehicle Download PDFInfo
- Publication number
- CN106184773B CN106184773B CN201610562641.5A CN201610562641A CN106184773B CN 106184773 B CN106184773 B CN 106184773B CN 201610562641 A CN201610562641 A CN 201610562641A CN 106184773 B CN106184773 B CN 106184773B
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- fuselage
- wing
- cabin
- duct
- engine bearer
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- 238000005096 rolling process Methods 0.000 claims abstract description 5
- 230000002093 peripheral effect Effects 0.000 claims description 2
- 230000002146 bilateral effect Effects 0.000 claims 1
- 238000013461 design Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
Classifications
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- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
-
- 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
- B64D29/00—Power-plant nacelles, fairings, or cowlings
- B64D29/02—Power-plant nacelles, fairings, or cowlings associated with wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Toys (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of tailstock formula duct unmanned aerial vehicle, including fuselage, two panels wing and two panels vertical fin totally four wings；The two panels wing is symmetrically, two panels vertical fin is symmetrical above and below is mounted on fuselage, and the fuselage is realized upright by four wing tips；The fuselage includes cabin, engine bearer, and the cabin lower part is connect with engine bearer, forms air inlet between cabin periphery and engine bearer；The engine bearer tail inner side is equipped with duct motor；The duct nozzle of the duct motor is provided with four rudder faces, is separately fixed on four wings, can realize pitching, rolling and yaw by the different deflection combination of four rudder faces.Unmanned plane structure of the invention is simple, high comprehensive performance, can be suitable for popularization and application with realizing VTOL, hovering, high-performance cruise and can load different loads.
Description
Technical field
The present invention relates to unmanned plane fields, more particularly to a kind of tailstock formula duct unmanned aerial vehicle.
Background technique
Unmanned plane application field is relatively broad, take photo by plane, agricultural, plant protection, self-timer, express transportation, disaster relief, observation
There is application in the fields such as wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, it is represented
An important development direction of the following aircraft.
The unmanned plane that hovering can be achieved at present has 2 kinds:(1) gyroplane.Such as helicopter, quadrotor etc..Using with fixed-wing
Entirely different working morphology, compared with fixed-wing, consumption power is big, and airborne period is short, cannot be a wide range of as fixed-wing
High-performance cruise.(2) 3D machine.Using fixed-wing normal arrangement, conventional take-off and landing, propeller arrangement, level speed is slower, generally can not
Install load additional.
There are also a type of duct unmanned aerial vehicles at present：It can put down at a high speed that winged, power is full mainly as prototype, but
Major part is unable to VTOL, extremely imitates the model of vertical take off and landing fighter individually, and installing extra power additional, (i.e. landing peace flies to have
Different power sources), principle is similar to gyroplane, and structure is complicated.
It can be seen that above-mentioned existing unmanned plane is in structure and use, it is clear that there are still there is inconvenient and defect, and urgently
It is further improved.How to found one kind can VTOL, can hover, can high-performance cruise, different loads and knot can be loaded
The simple unmanned plane of structure, which becomes current pole, needs improved target.
Summary of the invention
The technical problem to be solved in the present invention is to provide one kind can VTOL, can hover, can high-performance cruise, can load not
With load and the simple tailstock formula duct unmanned aerial vehicle of structure.
In order to solve the above technical problems, the present invention adopts the following technical scheme that：
A kind of tailstock formula duct unmanned aerial vehicle, including fuselage, two panels wing and two panels vertical fin totally four wings；The two panels wing
Symmetrically, two panels vertical fin is symmetrical above and below is mounted on fuselage, and the fuselage is realized upright by four wing tips；The fuselage packet
Cabin, engine bearer are included, the cabin lower part is connect with engine bearer, forms air inlet between cabin periphery and engine bearer；
The engine bearer tail inner side is equipped with duct motor；The duct nozzle of the duct motor is provided with four rudder faces, point
It is not fixed on four wings, can realize pitching, rolling and yaw by the different deflection combination of four rudder faces.
Further, the cabin lower part is fixedly connected by multiple cantilevers with engine bearer, is formed around the more of cabin
A air inlet.
Further, the wing, vertical fin and fuselage are detachably connected.
Further, the fuselage further includes the interconnecting piece for being provided with inserting groove, and the interconnecting piece is connected to cabin and hair
Engine-bed periphery, the wing, vertical fin are plugged on fuselage by the inserting groove being arranged on interconnecting piece.
Further, the interconnecting piece uses multiple sheet framework structures, and interconnecting piece periphery is provided with covering.
Further, the outer peripheral any side of the wing and/or empennage uses straight line, broken line or camber line.
Further, four rudder faces respectively connect a steering engine, independently drive each rudder face by four steering engines.
By using above-mentioned technical proposal, the present invention has at least the following advantages：
The present invention integrally uses symmetrical structure (wing, vertical fin are symmetrically arranged), adapts to the work of tailstock formula unmanned plane
Mode, using tailstock formula and air inlet, duct motor, the mutually matched mode of rudder face, high comprehensive performance can VTOL；
As 3D machine, freedom and flexibility can hover at any time；As duct unmanned aerial vehicle, high speed is flat to fly, and power is full.It is vdiverse in function, it can
To install different load additional, be both able to achieve the fixed point of gyroplane a small range, low speed is taken photo by plane, be also able to achieve fixed-wing on a large scale in
Quick aerial survey.
The configuration of the present invention is simple, using a set of dynamical system, a set of operating pattern is irredundant.Free design may be implemented,
As wing, vertical fin and fuselage use plug in construction, wing, vertical fin outer edge shape can random DIY, entire aerofoil profile can be in triangle
The wing, arc wing structure, can arbitrarily give the rein to imagination.
Detailed description of the invention
The above is merely an overview of the technical solutions of the present invention, in order to better understand the technical means of the present invention, below
In conjunction with attached drawing, the present invention is described in further detail with specific embodiment.
Fig. 1 is overall structure diagram of the invention (without covering, it is seen that inner skeleton)；
Fig. 2 is the airfoil cross-sectional view (exploded view) of tailstock formula duct unmanned aerial vehicle of the present invention；
Fig. 3 is the vertical fin face cross-sectional view (exploded view) of tailstock formula duct unmanned aerial vehicle of the present invention；
Fig. 4 is the sectional view along A-A of Fig. 2 middle fuselage.
Specific embodiment
As shown in Figs 1-4, a kind of tailstock formula duct unmanned aerial vehicle of the invention, including fuselage, two panels wing 2,3 and two panels are hung down
Totally four wings of tail 4,5；Two panels wing 2,3 is symmetrically, two panels vertical fin 4,5 is symmetrical above and below is mounted on fuselage, the wing of four wings
Reinforcement processing is done at sharp place, and fuselage realizes uprightly that stress forms four wing tail seat designs similar to arch bridge structure by four wing tips.
Fuselage includes cabin 11, engine bearer 12, and whole to use axially symmetric structure, 11 lower part of cabin and engine bearer 12 connect
It connects, it is preferred to use multiple cantilevers 13 are attached, and make to be formed between the periphery of cabin 11 and engine bearer 12 around the more of cabin 11
A air inlet 14；12 tail inner side of engine bearer is equipped with duct motor 6；The duct nozzle of duct motor 6 is provided with four
Rudder face 7,8,9,10, rudder face 7,8 are separately fixed on wing 2,3, and rudder face 9,10 is separately fixed on vertical fin 4,5, can pass through four
Pitching, rolling and yaw are realized in the different deflection combination of piece rudder face 7,8,9,10.Specifically, four rudder faces 7,8,9,10 pass through each
From one steering engine (not shown) of connection, the independent control of four rudder faces may be implemented.
The present invention passes through the tail seat design of above-mentioned symmetrically arranged four wings, cooperates air inlet, duct motor and rudder face,
VTOL, hovering and high-performance cruise may be implemented.
Plug in construction can be used in above-mentioned wing 2,3, vertical fin 4,5 and fuselage, and fuselage further includes being connected to cabin 11 and hair
The interconnecting piece 15 of the periphery of engine-bed 12 is provided with inserting groove 151, wing 2,3 on interconnecting piece 15, and vertical fin 4,5 passes through interconnecting piece 15
The inserting groove 151 of upper setting is plugged on fuselage, realizes the structure of blended wing-body.What interconnecting piece 15 as shown in Figure 1 used
It is multiple sheet framework structures, when finally forming, needs that covering is arranged in the sheet framework periphery, is formed complete pneumatic outer
Shape.Above-mentioned interconnecting piece 15 can also be integrally using the entity structure with inserting groove.
Above-mentioned wing 2,3, vertical fin 4,5 may be implemented D IY and freely design, give the rein to imagination.Fig. 2, dotted line part shown in 3
It is divided into outer edge, straight line, broken line or camber line can be used in any side, makes entire aerofoil profile in dalta wing, the M type wing, arc shaped wing etc..
The working method of above-mentioned tailstock formula duct unmanned aerial vehicle of the invention is：Before taking off, four wing tips of unmanned plane land,
When taking off, hovering with landing, fuselage is vertical, and duct motor 6 provides upward thrust, and the screw current in duct motor 6 is made
For four rudder faces, torque is generated to adjust aspect, wherein with moving as pitching moment, rudder face 9,10 is rudder face 7,8 with moving
Yawing, 7,8 or 9,10 is differential for rolling moment.When vertically turning flat winged, rudder face 7,8 deflects simultaneously, generates pitching moment, machine
Body gradually tilts, and duct motor 6 provides horizontal and upward thrust simultaneously, promotes air speed gradually, and gradually switch to put down
Fly.When flat winged, origin stream and duct wake flow collective effect generate torque, realize high-performance cruise in rudder face.
The above described is only a preferred embodiment of the present invention, be not intended to limit the present invention in any form, this
Field technical staff makes a little simple modification, equivalent variations or modification using the technology contents of the disclosure above, all falls within this hair
In bright protection scope.
Claims (2)
1. a kind of tailstock formula duct unmanned aerial vehicle, which is characterized in that including fuselage, two panels wing and two panels vertical fin totally four wings；Institute
State that two panels wing bilateral symmetry, two panels vertical fin is symmetrical above and below is mounted on fuselage, the fuselage is realized upright by four wing tips；
The fuselage includes cabin, engine bearer, and the cabin lower part is connect with engine bearer, cabin periphery and engine bearer it
Between form air inlet；
The engine bearer tail inner side is equipped with duct motor；The duct nozzle of the duct motor is provided with four rudders
Face is separately fixed on four wings, can realize pitching, rolling and yaw by the different deflection combination of four rudder faces；
The wing, vertical fin and fuselage are detachably connected；
The fuselage further includes the interconnecting piece for being provided with inserting groove, and the interconnecting piece is connected to cabin and engine bearer periphery, institute
State wing, vertical fin is plugged on fuselage by the inserting groove being arranged on interconnecting piece；
The interconnecting piece uses multiple sheet framework structures, and interconnecting piece periphery is provided with covering；
The outer peripheral any side of the wing and/or empennage uses straight line, broken line or camber line；
Four rudder faces respectively connect a steering engine, independently drive each rudder face by four steering engines.
2. tailstock formula duct unmanned aerial vehicle according to claim 1, which is characterized in that the cabin lower part passes through multiple cantilevers
It is fixedly connected with engine bearer, forms multiple air inlets around cabin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610562641.5A CN106184773B (en) | 2016-07-15 | 2016-07-15 | A kind of tailstock formula duct unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610562641.5A CN106184773B (en) | 2016-07-15 | 2016-07-15 | A kind of tailstock formula duct unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106184773A CN106184773A (en) | 2016-12-07 |
| CN106184773B true CN106184773B (en) | 2018-11-23 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610562641.5A Active CN106184773B (en) | 2016-07-15 | 2016-07-15 | A kind of tailstock formula duct unmanned aerial vehicle |
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Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN114030603B (en) * | 2021-10-27 | 2022-11-04 | 南京航空航天大学 | Variable duct tail seat type high-speed unmanned aerial vehicle and working method thereof |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100228406A1 (en) * | 2009-03-03 | 2010-09-09 | Honeywell International Inc. | UAV Flight Control Method And System |
| CN201753104U (en) * | 2010-06-03 | 2011-03-02 | 哈尔滨盛世特种飞行器有限公司 | Single-oar disc-shaped unmanned aircraft |
| CN105151295A (en) * | 2015-09-29 | 2015-12-16 | 上海圣尧智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
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2016
- 2016-07-15 CN CN201610562641.5A patent/CN106184773B/en active Active
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| Publication number | Publication date |
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| CN106184773A (en) | 2016-12-07 |
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