CN101774429A - Small UAV aerodynamic layout for vertical rope-type recovery - Google Patents
Small UAV aerodynamic layout for vertical rope-type recovery Download PDFInfo
- Publication number
- CN101774429A CN101774429A CN 201010114220 CN201010114220A CN101774429A CN 101774429 A CN101774429 A CN 101774429A CN 201010114220 CN201010114220 CN 201010114220 CN 201010114220 A CN201010114220 A CN 201010114220A CN 101774429 A CN101774429 A CN 101774429A
- Authority
- CN
- China
- Prior art keywords
- wing
- tail
- vertical
- layout
- small
- 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.)
- Pending
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a small UAV aerodynamic layout for vertical rope-type recovery on a moving base within a small spatial scope, which comprises a UAV body, wings and an engine tail wing; the wings are upper single wings, and the installation angle is 3 degrees; an engine is arranged at the tail of the UAV body; the layout is characterized in that the aspect ratio of the wings is 9, a sweepback method is adopted, and a sweepback angle is 23 degrees; the lower surface of the middle part of the left wing or the right wing is provided with a horizontal strut for installing the tail wing; the rear end of the horizontal strut is provided with a horizontal tail wing and a vertical tail which is arranged in an inverted way, and the vertical tail is inclined inwards for 15 degrees. Compared with the prior art, the small UAV aerodynamic layout for vertical rope-type recovery has the advantages of reducing the number of operators, and improving the effective load capacity and the wind resistant capability of an airplane.
Description
Affiliated technical field
The present invention relates to be used for the small UAV aerodynamic layout that vertical rope-type reclaims, belong to aircraft aerodynamic arrangement design field.Be particularly suitable for promoting the use of on the moving pedestal in the small space scope.
The present invention is a kind of UAV aerodynamic layout that the medium aspect ratio, the swept back wing that reclaim add two shoe separation type empennages of falling V of can implementing efficiently in full landform small space scope, can't harm.
Background technology
As far back as the sixties in 20th century, people just thirst for using unmanned plane on the moving pedestal in the small space scope, yet this is not an easy thing.
At first, it is more difficult and much dangerous than people's aircraft is arranged that the unmanned plane that uses on the moving pedestal is carried out the landing task, needs the hand-in-glove between well-trained dispatcher and the engineering operator, increased the configuration of operating personal.
Secondly, because the limitation of the use in the landing, aircraft is had to install additional or is carried speed reduction gearing such as parachute, has taken the loading space of aircraft, has reduced the payload capability of aircraft.
Once more, the unmanned plane that uses on the moving pedestal needs to consider certain wind loading rating that under IFR conditions, flow-disturbing advances nearly recovery for aircraft will produce very big influence especially.Most of SUAV (small unmanned aerial vehicle) can not be taken off and land under the weather condition of fresh breeze speed.
Summary of the invention
The present invention designs at above-mentioned the deficiencies in the prior art just provides a kind of small UAV aerodynamic layout that vertical rope-type reclaims that is used for, and its objective is the quantity that reduces operating personal, payload capability and the wind loading rating that improves aircraft.
The objective of the invention is to be achieved through the following technical solutions:
This kind is used for the small UAV aerodynamic layout that vertical rope-type reclaims on the moving pedestal in the small space scope, comprise fuselage, wing, driving engine empennage, wing is a high mounted wing, and stagger angle is 3 °, and engine installation is at the afterbody of fuselage, it is characterized in that: the aspect ratio of wing is 9, adopt the swept-back, the sweepback angle is 23 °, and lower surface respectively is provided with the triatic stay that is used to install empennage at left and right sides wing middle part, tailplane is installed and is inverted vertical fin in the rear end of triatic stay, vertical fin slopes inwardly 15 °.
The rope reclaiming type UAV aerodynamic layout that hangs down adopts anti-crosswind layout, by discoverys of taking a flight test of a large amount of CFD aerodynamic calculation and experimental engine, in topple over the design of V vertical fin and can better adapt to complex flowfield, take into account the accurately control requirement of recovery of moving pedestal in the small space scope; 9 medium aspect ratio makes aircraft have good lifting resistance characteristic; Wing tip is installed self-locking recovering hook device, can finish the harmless safety recovery of vertical rope-type by failure-free; Find by a large amount of test, swept-back, 23 ° of angles wing take into account aircraft have a broad flying speed scope in, can outstanding adaptation vertical rope-type hit rope and reclaim; The separation type tail structure is simple, and is in light weight, when good pitching and directional control characteristic is provided, and the structural failure that impact load may be brought in the time of can actv. avoiding hitting rope and reclaim.
The population parameter of aircraft is selected and optimized to the flight usage condition special according to this unmanned plane, finished the aerodynamic characteristic estimation, and by wind tunnel test with contract and verify than taking a flight test of proof machine, finally determined aerodynamic configuration.Small stationary wing unmanned plane can play a role better when the time comes, the ability that outstanding its handled easily uses.
Description of drawings
Fig. 1 is the scheme drawing that is used for the small UAV aerodynamic layout that vertical rope-type reclaims on the moving pedestal of the present invention
The specific embodiment
Below with reference to drawings and Examples technical solution of the present invention is further described:
Shown in accompanying drawing 1, this kind is used for the small UAV aerodynamic layout that vertical rope-type reclaims on the moving pedestal, comprise fuselage 1, wing 2, driving engine 3 and empennage, wing 2 is a high mounted wing, stagger angle is 3 °, driving engine 3 is installed in the afterbody of fuselage 1, it is characterized in that: the aspect ratio of wing 2 is 9, adopt the swept-back, the sweepback angle is 23 °, be provided with the triatic stay 4 that is used to install empennage at wing 2 middle part lower surfaces, tailplane 5 be installed and be inverted the vertical fin of installing 6 in the rear end of triatic stay 4, vertical fin 6 slopes inwardly 15 °.
According to the numerical Analysis result, the aerodynamic arrangement of the rope reclaiming type unmanned plane that hangs down on the moving pedestal in the small space scope has been carried out selecting design, and adopted scale model to finish a large amount of catapult-assisted take-offs, rolling start and hit the rope recovery test.Flight result and numerical result coincide preferably, show that the lifting resistance characteristic of this unmanned plane is good, have enough three axis stabilizations and anti-crosswind ability, can satisfy in the small space scope and use needs on the moving pedestal.
Adopt the population parameter of a kind of SUAV (small unmanned aerial vehicle) of technical solution of the present invention design-calculated as follows:
Full machine size
Length of aircraft 1792 mm
Aircraft width (containing the wing tip hook) 3092 mm
Aircraft altitude 382 mm
Wing gross area 1.0 m2
Wing
Gross area 1.0 m2
Long (not containing the wing tip hook) 3000 mm of exhibition
Theoretical root string (BL0.0) 333 mm
Theoretical sharp string (BL ± 2400) 333 mm
Mean aerodynamic chord (BL ± 1206) 333 mm
Aspect ratio 9
Taper ratio 1
23 ° of leading edge sweeps
0 ° at the dihedral angle
3 ° of stagger angles (BL0.0)
Aileron area (two) 0.05 * 2 m2
The aileron degree of bias (perpendicular to rotating shaft) ± 20 °
Aileron relative area 10.0%
Focus is apart from theoretical root string summit 401 mm
Quiet permanence 5～8% MAC
Horizontal tail
Horizontal tail area (two) 0.128 m2
Horizontal tail relative area 12.8%
Horizontal tail tail capacity 0.254
Vertical tail
Vertical tail area (two) 0.066 m2
Vertical tail relative area 6.6%
15 ° of leaning angles
Tail capacity 0.0134
Compared with prior art, the advantage of technical solution of the present invention is:
1. this layout SUAV can directly apply to TUAS, weaponry as UAS, its layout novelty, wind loading rating is strong, working service is convenient, efficient, safety, and with exclusive advanced technology developing fixed-wing unmanned plane market, its application value in army and economic results in society are huge, effect and prospect are very outstanding, and the development in science and technology of this area is had great impetus;
2. the rope reclaiming type unmanned plane that hangs down can apply transformations to the multi-user, adapts to the multiple landform such as level land, mountain region, automobile, steamer, is with a wide range of applications.
Claims (1)
1. be used for the small UAV aerodynamic layout that vertical rope-type reclaims, comprise fuselage (1), wing (2), driving engine (3) and empennage, wing (2) is a high mounted wing, stagger angle is 3 °, driving engine (3) is installed in the afterbody of fuselage (1), it is characterized in that: the aspect ratio of wing (2) is 9, adopt the swept-back, the sweepback angle is 23 °, about the lower surface at the middle part of wing (2), respectively be provided with the triatic stay (4) that is used to install empennage, tailplane (5) is installed and is inverted the vertical fin of installing (6) in the rear end of triatic stay (4), vertical fin (6) slopes inwardly 15 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010114220 CN101774429A (en) | 2010-02-26 | 2010-02-26 | Small UAV aerodynamic layout for vertical rope-type recovery |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010114220 CN101774429A (en) | 2010-02-26 | 2010-02-26 | Small UAV aerodynamic layout for vertical rope-type recovery |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101774429A true CN101774429A (en) | 2010-07-14 |
Family
ID=42511060
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010114220 Pending CN101774429A (en) | 2010-02-26 | 2010-02-26 | Small UAV aerodynamic layout for vertical rope-type recovery |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101774429A (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN102336276A (en) * | 2011-06-24 | 2012-02-01 | 清华大学 | Crosswind overturning prevention device for parachuting of unmanned aerial vehicles |
| CN105892289A (en) * | 2014-12-15 | 2016-08-24 | 中国人民解放军军械工程学院 | Unmanned aerial vehicle parachute landing recovery method based on accurate measurement of wind field |
| CN106719230A (en) * | 2017-03-13 | 2017-05-31 | 广东工业大学 | Aquatic products cultivates unmanned plane automatically |
| CN108609201A (en) * | 2018-06-06 | 2018-10-02 | 中电科芜湖通用航空产业技术研究院有限公司 | Verification machine is compared in light-duty single-shot hybrid power aeroplane contracting |
| CN112407237A (en) * | 2020-09-30 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Medium-sized unmanned aerial vehicle with high lift-drag ratio |
| CN112896500A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Aircraft with four ducts in tilting layout |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040211862A1 (en) * | 2003-04-25 | 2004-10-28 | Elam Daryl B. | Unmanned aerial vehicle with integrated wing battery |
| CN1872623A (en) * | 2005-06-04 | 2006-12-06 | 张斌 | Hawk type airfoils five |
| CN200967562Y (en) * | 2006-11-20 | 2007-10-31 | 大连三科航空科技有限公司 | High subsonic speed unmanned plane |
| CN101264795A (en) * | 2007-03-16 | 2008-09-17 | 王存孝 | Superaltitude low speed positioning flight pilotless aircraft |
-
2010
- 2010-02-26 CN CN 201010114220 patent/CN101774429A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040211862A1 (en) * | 2003-04-25 | 2004-10-28 | Elam Daryl B. | Unmanned aerial vehicle with integrated wing battery |
| CN1872623A (en) * | 2005-06-04 | 2006-12-06 | 张斌 | Hawk type airfoils five |
| CN200967562Y (en) * | 2006-11-20 | 2007-10-31 | 大连三科航空科技有限公司 | High subsonic speed unmanned plane |
| CN101264795A (en) * | 2007-03-16 | 2008-09-17 | 王存孝 | Superaltitude low speed positioning flight pilotless aircraft |
Non-Patent Citations (1)
| Title |
|---|
| 《飞机设计》 20051231 邓扬晨，詹光，刘艳华，陈华，马明亮 无人机单、双尾撑布局的结构效率研究 第18-21页 , 第4期 * |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN102133926B (en) * | 2011-03-08 | 2013-05-08 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN102336276A (en) * | 2011-06-24 | 2012-02-01 | 清华大学 | Crosswind overturning prevention device for parachuting of unmanned aerial vehicles |
| CN102336276B (en) * | 2011-06-24 | 2013-08-21 | 清华大学 | Crosswind overturning prevention device for parachuting of unmanned aerial vehicles |
| CN105892289A (en) * | 2014-12-15 | 2016-08-24 | 中国人民解放军军械工程学院 | Unmanned aerial vehicle parachute landing recovery method based on accurate measurement of wind field |
| CN106719230A (en) * | 2017-03-13 | 2017-05-31 | 广东工业大学 | Aquatic products cultivates unmanned plane automatically |
| CN106719230B (en) * | 2017-03-13 | 2023-02-10 | 广东工业大学 | Automatic aquaculture unmanned aerial vehicle |
| CN108609201A (en) * | 2018-06-06 | 2018-10-02 | 中电科芜湖通用航空产业技术研究院有限公司 | Verification machine is compared in light-duty single-shot hybrid power aeroplane contracting |
| CN112407237A (en) * | 2020-09-30 | 2021-02-26 | 北京北航天宇长鹰无人机科技有限公司 | Medium-sized unmanned aerial vehicle with high lift-drag ratio |
| CN112896500A (en) * | 2021-03-08 | 2021-06-04 | 四川腾盾科技有限公司 | Aircraft with four ducts in tilting layout |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107176286B (en) | Double-duct fan power system-based foldable fixed wing vertical take-off and landing unmanned aerial vehicle | |
| CN101774429A (en) | Small UAV aerodynamic layout for vertical rope-type recovery | |
| US9669924B2 (en) | Unmanned aerial vehicle | |
| CN107933909A (en) | A kind of high-speed and high-efficiency tilting wing unmanned vehicle | |
| CN203681869U (en) | Power system structure suitable for vertical take-off and landing air vehicle | |
| CN205076045U (en) | Combined type aircraft of varistructure | |
| CN103738496A (en) | Dynamical system structure suitable for vertical take-off and landing aircraft and control method thereof | |
| CN209382267U (en) | A kind of combined type vertically taking off and landing flyer | |
| CN108791874A (en) | A kind of tilting duct power unmanned vehicle | |
| CN206857002U (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft | |
| CN102730183A (en) | Novel solar airplane | |
| CN206984354U (en) | A kind of aircraft | |
| CN105270625A (en) | Multi-purpose vertical take-off and landing unmanned aerial vehicle | |
| CN108501639A (en) | A kind of hovercar | |
| CN105217033A (en) | Amphibious rotor wing unmanned aerial vehicle | |
| CN110816806B (en) | Cluster type bionic solar unmanned aerial vehicle | |
| CN204489187U (en) | A kind of vertical takeoff and landing horizontal flight unmanned plane | |
| CN206734620U (en) | The round-the-clock long endurance fixed-wing unmanned plane of VTOL | |
| CN206068150U (en) | Combined type layout vertically taking off and landing flyer | |
| CN209535450U (en) | A kind of four ducted fan unmanned planes with duct inclination angle | |
| CN106184692A (en) | A kind of flying wing type hybrid lift dirigible of the dismantled and assembled power that verts | |
| CN107878746A (en) | A kind of VTOL fixed-wing long endurance unmanned aircraft of oil electric mixed dynamic | |
| CN204507270U (en) | Novel high lift joined wing configuration aircraft | |
| CN208683103U (en) | A kind of unmanned transporter | |
| CN103847964B (en) | A kind of can the arc shaped wing aircraft of vrille |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| 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: 20100714 |