CN106828914A - A kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type force vector component - Google Patents
A kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type force vector component Download PDFInfo
- Publication number
- CN106828914A CN106828914A CN201710071906.6A CN201710071906A CN106828914A CN 106828914 A CN106828914 A CN 106828914A CN 201710071906 A CN201710071906 A CN 201710071906A CN 106828914 A CN106828914 A CN 106828914A
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- China
- Prior art keywords
- culvert type
- wing
- fixed
- power component
- mounting disc
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- 238000001816 cooling Methods 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 4
- 239000002828 fuel tank Substances 0.000 claims description 2
- 238000005303 weighing Methods 0.000 claims 1
- 230000009187 flying Effects 0.000 description 5
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- RLLPVAHGXHCWKJ-IEBWSBKVSA-N (3-phenoxyphenyl)methyl (1s,3s)-3-(2,2-dichloroethenyl)-2,2-dimethylcyclopropane-1-carboxylate Chemical compound CC1(C)[C@H](C=C(Cl)Cl)[C@@H]1C(=O)OCC1=CC=CC(OC=2C=CC=CC=2)=C1 RLLPVAHGXHCWKJ-IEBWSBKVSA-N 0.000 description 1
- 241001444201 Falco tinnunculus Species 0.000 description 1
- 108091092878 Microsatellite Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000010001 crabbing Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000009795 derivation Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
-
- 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
- B64D33/00—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
- B64C2027/8263—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft comprising in addition rudders, tails, fins, or the like
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention provides a kind of combination fixed-wing and the Modularized unmanned machine aircraft of culvert type unmanned plane two-fold advantage, enable that culvert type unmanned plane installs fixed-wing by setting detachable mounting disc at the top of culvert type unmanned plane.Quickly detachably it is related to so that unmanned plane possesses the VTOL and hovering of culvert type unmanned plane and possesses the advantage of fixed wing aircraft in long-distance flight by this.
Description
Technical field
The present invention relates to a kind of fixed-wing unmanned vehicle, and in particular to a kind of culvert type with VTOL function is moved
The fixed-wing unmanned vehicle of power.
Background technology
In recent years, the production of unmanned vehicle and research and development are progressively risen, the distinctness that unmanned vehicle possesses due to its own
Technical characterstic, military and civilian field be widely used with development at full speed, especially agricultural protection, communication in
After, prevent and reduce natural disasters, weather monitoring, power transmission, survey and draw, take photo by plane, the field tool such as entertain and have a wide range of applications.Unmanned plane includes
Polytype, and culvert type unmanned plane has the flight characteristic of VTOL and hovering, in volume, disguised and flying quality
All there is salient feature, it has also become more type is produced and applied in Small and micro-satellite field.
At present, the production company of culvert type unmanned vehicle is proposed the culvert type unmanned vehicle of Multiple Type successively.
For example, the Cypher unmanned plane during flyings device that Sikorsky companies release is flown using the culvert type of coaxial double-oar culvert type layout
Device；The Honeywell Inc. of U.S.'s name is proposed kestrel unmanned vehicles；Singapore is also proposed the culvert type fan of oneself
Unmanned plane fantai.
Culvert type unmanned vehicle generally mainly includes load cabin, ducted fan system, landing chassis and dynamical system institute group
Into.Above-mentioned these culvert type unmanned vehicles possess the function of VTOL and hovering, but in terms of high-speed flight, it is difficult to reach
To the flying speed of fixed-wing unmanned plane, and also usual fuel consumption is more in high-speed flight, it is difficult to remain prolonged
High-speed flight.
And fixed-wing unmanned plane can in flight by fixed-wing the characteristics of flight higher can be reached in flight
Speed, and also relatively low oil consumption can be simultaneously kept, the function of not possessing VTOL and hovering generally, thus, at some
In special purposes, it is difficult to reach use requirement.
The content of the invention
In order to overcome above-mentioned deficiency, have two the invention provides a kind of modularization VTOL fixed-wing unmanned vehicle
Configuration is planted, low speed flying quality high and hovering function is taken into account.The unmanned vehicle is based on the duct aircraft of conventional configuration
Configuration, using modular design concept, by basic duct body force vector control assembly fuselage and the wing group of high speed configuration
The combined transformation of part come realize can variant culvert type unmanned vehicle double configurations conversion.
Concrete technical scheme of the invention is：A kind of modularization VTOL based on culvert type vector Power Component is fixed
Wing unmanned vehicle, including fixed-wing component and culvert type vector Power Component；The fixed-wing component is by fixed-wing component
Cylindrical body and the trapezoidal fixed-wing composition of two panels；The fixed-wing component and culvert type vector Power Component are removed stage makeup and costume by removable
Put and be attached, the detachable apparatus are to be arranged on the mounting disc at the top of culvert type vector Power Component；And the fixation
Wing component is vertically mounted in the mounting disc at the top of culvert type vector Power Component；The culvert type vector Power Component includes,
Annular fuel tank duct body, undercarriage, overhead engine, five vane propellers, balance piece, deflector, direction attitude controller,
Mounting disc；The top of the culvert type unmanned vehicle vector Power Component sets mounting disc, and the mounting disc can be detachable
Task device is installed；The mounting disc bottom of the culvert type unmanned vehicle vector Power Component sets overhead engine, described
Overhead engine bottom is installed by five vane propeller；The balance piece and deflector are co-located on the five leaves spiral
In the duct body of oar bottom, and balance piece and deflector are in vertical direction setting up and down, under balance piece
The top edge of edge and deflector is in same level；The direction attitude controller is arranged on the deflector；It is described
Balance piece is reverse tangent line balance piece, has 16 compositions；The direction attitude controller has 8 groups, controls respectively
Attitude processed and direction；Cooling device is additionally provided with the overhead engine.
The beneficial effect of the invention is：Modularization can variant culvert type unmanned vehicle be divided into low speed configuration and high speed configuration two
Type is planted, high speed configuration carries Wing-Body Configurations component, if removing Wing-Body Configurations component, can be used as low speed configuration（Conventional configuration is contained
Road formula aircraft）Use.Low speed configuration culvert type aircraft can carry out VTOL, hovering as traditional culvert type aircraft
Fly with low speed forward flight/side, can be flown under complicated narrow and small environment；High speed configuration fashionable dress top wing frame assembly, force vector
Control assembly flies as propulsion plant before realizing VTOL, hovering and high speed, can be flown under complicated long distance environment.Pass
System configuration culvert type aircraft have the shortcomings that pneumatic efficiency it is low, preceding/crabbing speed is small, voyage is limited with when navigating, and can
The combination configuration conversion of variant culvert type unmanned vehicle overcomes disadvantage mentioned above, and its collection fixed wing aircraft and helicopter performance are excellent
Point as helicopter all over the body, can both to have realized VTOL, hovering and high maneuverability, while can fly as fixed-wing again
The high speed that machine carries out relative low energy consumption using the lift of wing like that is flown for long-distance.Under different aerial missions, modularization is vertical
The fuselage module that landing fixed-wing unmanned vehicle can change the outfit different, flies in culvert type vertically taking off and landing flyer and fixed-wing
Switched between device, so as to meet the mission requirements of varying environment.Flying speed wide ranges, tool low to place use requirement
There are more preferable security and task, make it that there is broader use space in following dual-use field.In addition, this is dynamic
Force vector control assembly compact conformation, using safety, can VTOL, can steadily hovering, can installation of modular loading device,
Can be used as the propulsion plant of VTOL Fixed Wing AirVehicle.Pacified by being set at the top of culvert type unmanned vehicle
Sabot can the dismountable installed load device extension purposes of culvert type unmanned plane, and turned round using reverse tangent line is distributed
The swirling eddy that propeller is produced, can be gathered together smooth without hindrance derivation by square balancing patch, and not only rectification efficiency is high but also does not have
Have any loss of lift, the effect of counter balance torque is also very strong, and by optimize deflector and balance piece position and
Quantity and use control the attitude direction controller in attitude and direction to reach raising while rectification efficiency is improved respectively
To attitude and the stability contorting in direction, the uneoupled control to attitude and direction, and the damage for significantly reducing lift are realized
Consumption and the unstability of flight.In addition, overhead upper position of engine sets cooling device can improve the cooling effect of engine, drop
The oil consumption of low engine.
Brief description of the drawings
Fig. 1 is the modularization VTOL fixed-wing unmanned vehicle based on culvert type vector Power Component；Fig. 2 is duct
Formula vector Power Component.
Claims (1)
1. a kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type vector Power Component, including fixed-wing group
Part and culvert type vector Power Component；The fixed-wing component by fixed-wing component the trapezoidal fixed-wing of cylindrical body and two panels
Composition；The fixed-wing component and culvert type vector Power Component are attached by detachable apparatus, the detachable apparatus
It is the mounting disc being arranged at the top of culvert type vector Power Component；And the fixed-wing component is vertically mounted on culvert type vector
In mounting disc at the top of Power Component；The culvert type vector Power Component includes, annular fuel tank duct body, undercarriage, overhead
Engine, five vane propellers, balance piece, deflector, direction attitude controller, mounting disc；The culvert type unmanned flight
The top of device vector Power Component sets mounting disc, and the mounting disc can detachably install task device；The culvert type without
The mounting disc bottom of people's aircraft vector Power Component sets overhead engine, and five leaf is installed in the overhead engine bottom
Propeller；The balance piece and deflector are co-located in the duct body of the five vane propellers bottom, and moment of torsion
Balancing patch and deflector are in vertical direction setting up and down, and the lower edge of balance piece and the top edge of deflector are same
In horizontal plane；The direction attitude controller is arranged on the deflector；The balance piece is flat for reverse tangent line moment of torsion
Weighing apparatus piece, has 16 compositions；The direction attitude controller has 8 groups, and attitude and direction are controlled respectively；The overhead engine
On be additionally provided with cooling device.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710071906.6A CN106828914A (en) | 2017-02-09 | 2017-02-09 | A kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type force vector component |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710071906.6A CN106828914A (en) | 2017-02-09 | 2017-02-09 | A kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type force vector component |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106828914A true CN106828914A (en) | 2017-06-13 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710071906.6A Pending CN106828914A (en) | 2017-02-09 | 2017-02-09 | A kind of modularization VTOL fixed-wing unmanned vehicle based on culvert type force vector component |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741916A (en) * | 2017-02-14 | 2017-05-31 | 深圳市航宇航空科技有限公司 | A kind of culvert type unmanned vehicle vector Power Component |
| CN109018330A (en) * | 2018-07-23 | 2018-12-18 | 西北工业大学 | Vertical landing unmanned plane |
| CN111976954A (en) * | 2020-09-15 | 2020-11-24 | 杨轲 | A fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and its realization method |
| CN114684360A (en) * | 2022-04-08 | 2022-07-01 | 西安泽盛航空科技有限公司 | Tandem type double-duct propulsion unmanned aerial vehicle |
| CN114802711A (en) * | 2022-04-08 | 2022-07-29 | 西安泽盛航空科技有限公司 | Unmanned aerial vehicle with single duct at tail part |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5295643A (en) * | 1992-12-28 | 1994-03-22 | Hughes Missile Systems Company | Unmanned vertical take-off and landing, horizontal cruise, air vehicle |
| EP2070815A2 (en) * | 2001-05-29 | 2009-06-17 | Romeo Yankee Ltd. | Ducted fan vehicles particularly useful as VTOL aircraft |
| CN102673780A (en) * | 2012-06-07 | 2012-09-19 | 李建波 | Double-configuration aircraft |
| CN104960666A (en) * | 2015-05-26 | 2015-10-07 | 北京理工大学 | Tilting vector control auxiliary system of flight vehicle provided with longitudinal double ducts |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
-
2017
- 2017-02-09 CN CN201710071906.6A patent/CN106828914A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5295643A (en) * | 1992-12-28 | 1994-03-22 | Hughes Missile Systems Company | Unmanned vertical take-off and landing, horizontal cruise, air vehicle |
| EP2070815A2 (en) * | 2001-05-29 | 2009-06-17 | Romeo Yankee Ltd. | Ducted fan vehicles particularly useful as VTOL aircraft |
| CN102673780A (en) * | 2012-06-07 | 2012-09-19 | 李建波 | Double-configuration aircraft |
| CN104960666A (en) * | 2015-05-26 | 2015-10-07 | 北京理工大学 | Tilting vector control auxiliary system of flight vehicle provided with longitudinal double ducts |
| CN105000180A (en) * | 2015-06-28 | 2015-10-28 | 杨盛 | Aircraft aerodynamic configuration device |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741916A (en) * | 2017-02-14 | 2017-05-31 | 深圳市航宇航空科技有限公司 | A kind of culvert type unmanned vehicle vector Power Component |
| CN109018330A (en) * | 2018-07-23 | 2018-12-18 | 西北工业大学 | Vertical landing unmanned plane |
| CN111976954A (en) * | 2020-09-15 | 2020-11-24 | 杨轲 | A fixed-wing unmanned aerial vehicle that can realize vertical take-off and landing and its realization method |
| CN114684360A (en) * | 2022-04-08 | 2022-07-01 | 西安泽盛航空科技有限公司 | Tandem type double-duct propulsion unmanned aerial vehicle |
| CN114802711A (en) * | 2022-04-08 | 2022-07-29 | 西安泽盛航空科技有限公司 | Unmanned aerial vehicle with single duct at tail part |
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| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170613 |
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| RJ01 | Rejection of invention patent application after publication |