CN101857086A - Dual-culvert vertical take-off and landing unmanned aerial vehicle - Google Patents
Dual-culvert vertical take-off and landing unmanned aerial vehicle Download PDFInfo
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- CN101857086A CN101857086A CN 201010190722 CN201010190722A CN101857086A CN 101857086 A CN101857086 A CN 101857086A CN 201010190722 CN201010190722 CN 201010190722 CN 201010190722 A CN201010190722 A CN 201010190722A CN 101857086 A CN101857086 A CN 101857086A
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- aerial vehicle
- culverts
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- vertical take
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- 239000000446 fuel Substances 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000009510 drug design Methods 0.000 abstract 1
- 108010066057 cabin-1 Proteins 0.000 description 6
- 206010000369 Accident Diseases 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000004891 communication Methods 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
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Abstract
The invention provides a dual-culvert vertical take-off and landing unmanned aerial vehicle, wherein, symmetrical culverts are arranged at the left-right sides of a cabin; an undercarriage is arranged under the culverts; a motor is arranged at the central axis of the culverts; the motor is arranged at the upper part inside the culverts through a propeller shaft and a connecting propeller; control vanes are symmetrically arranged at longitudinal front-rear ends of the bottom of the culverts respectively; control vanes are transversely arranged at a single end on the bottom of the culverts; and the cabin is internally equipped with an autopilot and power batteries. The unmanned aerial vehicle has the advantages of compact structure and rational design, low noise while flying, good concealment, low air speed, strong maneuverability, high flight efficiency, saved fuel, simple and convenient maintenance, being economical and practical, strong adaptability, being safe and reliable, and being capable of vertical take-off and landing, hovering, circling in any places and performing various aerobatic flight; the unmanned aerial vehicle is applicable to vertical take-off and landing flight in places such as cities, villages, factories, coasts, naval vessels, grasslands, high mountains, expressways and the like; and the design of the culvert propeller is very good for flight of the aerial vehicle and personnel safety.
Description
Technical field
The invention belongs to the unmanned airflight vehicle, especially a kind of vertical take-off and landing unmanned aerial vehicle.
Background technology
At present, common unmanned fixed-wing aircraft takeoff of known modern times and landing need higher speed just can make wing produce enough lift, causes about 50% left and right sides aircraft accident to take place when landing taking off, and park occupied ground on ground very big.Modern common rotor unmanned vehicle great majority adopt single rotor magnetic tape trailer oar and coaxial pair of paddle structure of helicopter.The blade of high speed revolution is fatal threat to operating personal.The blade of high speed revolution also is easy to run into object and produces aircraft accident.
Summary of the invention
The objective of the invention is to overcome the weak point that exists in the above-mentioned technology, a kind of compact conformation, reasonable in design is provided, the dual-culvert vertical take-off and landing unmanned aerial vehicle of low-altitude low-speed, vertical takeoff and landing, safe handling.
In order to achieve the above object, the technical solution used in the present invention is: the left and right sides, cabin is provided with the duct of symmetry, there is alighting gear the duct below, be positioned on the duct central axis electrical motor is housed, electrical motor places the duct internal upper part by oar axle, connection oar, duct bottom vertically rear and front end symmetry is equipped with control vane respectively, and the single-ended control vane that is equipped with of duct bottom transverse is equipped with autopilot and electrokinetic cell in the cabin.
Advantage of the present invention is:
1, compact conformation, reasonable in design, anywhere vertical takeoff and landing, hover, spiral, noise in flight is very low, disguised very good;
2, it has low-altitude low-speed, mobility strong, can do various aerobatics;
3, flight efficiency height, and fuel saving, easy maintenance, economical and practical;
4, comformability is strong, adapts to the city, country, factory, seashore, naval vessels, grassland, high mountain, the vertical takeoff and landing flight that express highway etc. are local;
5, safe and reliable, the design of duct oar benefits to aircraft flight and personnel's safety;
6, the present invention can take photo in the sky, advertising, communication repeating, the oil pipeline supervision, the monitoring of fire flood situation pursues and captures an escaped prisoner guiding of traffic etc., the advantage that has other vehicle to hardly match equally militarily, fight-terrorism warfare, military situation is scouted, antisubmarine clearance, the strike of all types of target, attack armed helicopter and low-to-medium altitude cruise missile etc.
Description of drawings
Fig. 1 is a structural representation of the present invention;
Fig. 2 is the cutaway view of the A-A of Fig. 1;
Fig. 3 is the upward view of Fig. 1;
Fig. 4 is a schematic perspective view of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing embodiments of the invention are described in further detail.
By Fig. 1-Fig. 4 as can be known, 1 left and right sides, cabin of the present invention is provided with the duct 2 of symmetry, there is alighting gear 10 duct 2 belows, be positioned on duct 2 central axis electrical motor 5 is housed, electrical motor 5 places duct 2 internal upper parts by oar axle 3, connection oar 4, vertical rear and front end, duct 2 bottoms symmetry is equipped with control vane 6 respectively, and the single-ended control vane 7 that is equipped with of duct 2 bottom transverse is equipped with autopilot 9 and electrokinetic cell 8 in the cabin 1.
Described control vane 6 and control vane 7 are made up of 1-20 rudder face.
The present invention is fixed with duct 2 on the alighting gear 10 in Fig. 1, cabin 1 left and right sides symmetry is connecting duct 2, and vertical rear and front end, duct 2 bottoms symmetry is equipped with control vane 6 respectively, the single-ended control vane 7 that is equipped with of duct 2 bottom transverse.
In Fig. 2, be fixed with duct 2 on the alighting gear 10, cabin 1 left and right sides symmetry is connecting duct 2, electrical motor 5 is positioned over duct 2 middle parts and is on duct 2 central axis, electrical motor 5 connects oar 4 by oar axle 3 and places duct 2 internal upper parts, electrokinetic cell 8 and autopilot 9 are equipped with in 1 inside, cabin, the single-ended control vane 7 that is equipped with of duct 2 bottom transverse.
In Fig. 3, be fixed with duct 2 on the alighting gear 10, cabin 1 left and right sides symmetry is connecting duct 2, and electrical motor 5 is positioned over duct 2 middle parts and is on duct 2 central axis, connects oar 4 and places duct 2 inside.
In Fig. 4 kind, be fixed with duct 2 on the alighting gear 10, cabin 1 left and right sides symmetry is connecting duct 2, electrical motor 5 is positioned over duct 2 middle parts and is on duct 2 central axis, electrical motor 5 connects oar 4 by oar axle 3 and places duct 2 internal upper parts, electrokinetic cell 8 and autopilot 9 are equipped with in 1 inside, cabin, and vertical rear and front end, duct 2 bottoms symmetry is equipped with control vane 6 respectively, the single-ended control vane 7 that is equipped with of duct 2 bottom transverse.
The dual-culvert vertical take-off and landing unmanned aerial vehicle principle of work is such, self-starting motor 5 after the floor mounted inspection of outfield, internal field finishes, electrical motor 5 outputting powers are given oar axle 3, oar axle 3 drives and connects oar 4 rotations, electrokinetic cell 8 provides propulsion source for electrical motor 5, between blade tip and duct 2, produce negative pressure when connecting the rotation of oar 4, connecting oar 4 and duct 2 produces jointly to raising force, control vane 6 and control vane 7 are by autopilot 9 automatic guidances and increase three flight attitudes of steady aircraft, be equipped with in the cabin 1: electrokinetic cell, remote-control romote-sensing equipment, satellite navigational equipment, mission payload equipment etc.Alighting gear 10 is supported the aircraft vertical and landing takeoff.
Claims (2)
1. dual-culvert vertical take-off and landing unmanned aerial vehicle, comprise electrical motor (5), alighting gear (10), it is characterized in that: the left and right sides, cabin (1) is provided with the duct (2) of symmetry, there is alighting gear (10) duct (2) below, be positioned on duct (2) central axis electrical motor (5) is housed, electrical motor (5) is by oar axle (3), connect oar (4) and place duct (2) internal upper part, duct (2) bottom vertically rear and front end symmetry is equipped with control vane (6) respectively, the single-ended control vane (7) that is equipped with of duct (2) bottom transverse is equipped with autopilot (9) and electrokinetic cell (8) in cabin (1).
2. dual-culvert vertical take-off and landing unmanned aerial vehicle according to claim 1 is characterized in that: described control vane (6) and control vane (7) are made up of 1-20 rudder face.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010190722 CN101857086A (en) | 2010-06-03 | 2010-06-03 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010190722 CN101857086A (en) | 2010-06-03 | 2010-06-03 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101857086A true CN101857086A (en) | 2010-10-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010190722 Pending CN101857086A (en) | 2010-06-03 | 2010-06-03 | Dual-culvert vertical take-off and landing unmanned aerial vehicle |
Country Status (1)
| Country | Link |
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| CN (1) | CN101857086A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730189A (en) * | 2011-03-29 | 2012-10-17 | 郑鹏 | Marine flying lifesaving method and device |
| CN103332293A (en) * | 2013-06-13 | 2013-10-02 | 上海大学 | Tilting double-duct subminiature unmanned plane |
| CN105346716A (en) * | 2015-09-30 | 2016-02-24 | 上海圣尧智能科技有限公司 | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
| WO2018209911A1 (en) * | 2017-05-16 | 2018-11-22 | 华南理工大学 | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6604706B1 (en) * | 1998-08-27 | 2003-08-12 | Nicolae Bostan | Gyrostabilized self propelled aircraft |
| CN2772962Y (en) * | 2005-03-30 | 2006-04-19 | 王忠信 | Special aerobat with circular wing |
| CN1944091A (en) * | 2006-11-07 | 2007-04-11 | 北京航空航天大学 | Multifunction aircraft |
| US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
| CN201670358U (en) * | 2010-06-03 | 2010-12-15 | 哈尔滨盛世特种飞行器有限公司 | Double-duct vertical take-off and landing unmanned aerial vehicle |
-
2010
- 2010-06-03 CN CN 201010190722 patent/CN101857086A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6604706B1 (en) * | 1998-08-27 | 2003-08-12 | Nicolae Bostan | Gyrostabilized self propelled aircraft |
| US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
| CN2772962Y (en) * | 2005-03-30 | 2006-04-19 | 王忠信 | Special aerobat with circular wing |
| CN1944091A (en) * | 2006-11-07 | 2007-04-11 | 北京航空航天大学 | Multifunction aircraft |
| CN201670358U (en) * | 2010-06-03 | 2010-12-15 | 哈尔滨盛世特种飞行器有限公司 | Double-duct vertical take-off and landing unmanned aerial vehicle |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102730189A (en) * | 2011-03-29 | 2012-10-17 | 郑鹏 | Marine flying lifesaving method and device |
| CN103332293A (en) * | 2013-06-13 | 2013-10-02 | 上海大学 | Tilting double-duct subminiature unmanned plane |
| CN105346716A (en) * | 2015-09-30 | 2016-02-24 | 上海圣尧智能科技有限公司 | Unmanned aerial vehicle power system and vertical take-off and landing unmanned aerial vehicle |
| WO2018209911A1 (en) * | 2017-05-16 | 2018-11-22 | 华南理工大学 | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
| US11634222B2 (en) | 2017-05-16 | 2023-04-25 | South China University Of Technology | Vertical take-off and landing unmanned aerial vehicle having foldable fixed wing and based on twin-ducted fan power system |
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| C06 | Publication | ||
| PB01 | Publication | ||
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| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20101013 |