CN103303474A - Small-size multi-purpose unmanned aerial vehicle - Google Patents
Small-size multi-purpose unmanned aerial vehicle Download PDFInfo
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- CN103303474A CN103303474A CN2013101850329A CN201310185032A CN103303474A CN 103303474 A CN103303474 A CN 103303474A CN 2013101850329 A CN2013101850329 A CN 2013101850329A CN 201310185032 A CN201310185032 A CN 201310185032A CN 103303474 A CN103303474 A CN 103303474A
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Abstract
The invention discloses a small-size multi-purpose unmanned aerial vehicle which can be used for executing flight missions of scientific experiments, remote sensing detection, aerial photography in air and the like. The unmanned aerial vehicle has the characteristics that 1) the duration of flight is long, and flight missions with high requirements on the flight can be executed; 2) the use is easy, and the manipulation is convenient; 3) the stability is good, and equipment such as autopilots, aerial photography cameras, and cameras can be loaded; 4) the requirements on taking off and landing conditions are low. According to one aspect in the invention, the unmanned aerial vehicle comprises a vehicle body, wings, which are connected on the vehicle body, a tail wing, a tail support for connecting the tail wing with the vehicle body, an engine (10) which is arranged at the front end of the vehicle body (10), and a propeller (11) which is driven by the engine (10) and is used for supplying a tensile force necessary for the flight to the vehicle. According to another aspect in the invention, the unmanned aerial vehicle further is in a modular loading design and comprises a bottom plate support plate (32) which is positioned in the middle of the vehicle body (1) and is used for mounting vehicle-mounted equipment.
Description
The application is dividing an application of No. 201010127939.6, Chinese patent application.
Technical field
The present invention relates to a kind of design of small multi-purpose unmanned aerial vehicle, belong to the structure design field of aviation aircraft, the SUAV (small unmanned aerial vehicle) structure design that requires larger cruise duration is particularly arranged.
Background technology
The unmanned plane cost is comparatively cheap, can avoid the injures and deaths of navigating mate, can carry out many man-machine inexecutable tasks that have, and has a extensive future.
Existing unmanned plane mainly adopts simple box type fuselage, conventional hexahedral shape fuel tank, and flight resistance is large, and space availability ratio is low in the machine, and contained amount of fuel is less, and is all shorter during the voyage boat.And mostly make to measure according to concrete mission payload, the commonality of loading for mission payload is not strong; When the load that does not have formal typing is carried test, not to make things convenient for very much, sometimes even also need housing construction is transformed.
Summary of the invention
For the problems referred to above of prior art, the inventor has developed a kind of V tail layout unmanned plane of oil tank embedded into blended wing body.
Unmanned plane of the present invention is mainly used in carrying out scientific experiment, remote sensing and the aerial mission such as take photo by plane in the air.This unmanned plane has following features: 1) cruise duration longer, the aerial mission of having relatively high expectations when being convenient to carry out to boat; 2) use simply, be convenient to handle; 3) stability better is fit to carry the equipment such as autopilot, aerial camera, pick up camera; 4) lower to the landing conditional request.
According to an aspect of the present invention, provide a kind of SUAV (small unmanned aerial vehicle), it is characterized in that comprising: fuselage; Be connected to the wing on the described fuselage; Empennage; And shoe, be used for realizing being connected of described empennage and fuselage.
According to a further aspect of the present invention, above-mentioned SUAV (small unmanned aerial vehicle) further comprises: the driving engine that is installed in the front end of described fuselage; Described engine-driven screw propeller is used to aircraft to provide flight required pulling force.
According to a further aspect of the present invention, above-mentioned SUAV (small unmanned aerial vehicle) further comprises: be arranged on a cabin cover on the top of described fuselage, itself and described fuselage define a cabin; Wherein said fuselage is a flat lifting body with certain aerofoil profile.
According to a further aspect of the present invention, above-mentioned empennage is vee tail, and the empennage trailing edge is provided with control surface, thereby can realize by V tail mixing pattern the function of elevating rudder and yaw rudder.Unmanned plane according to another aspect of the present invention further comprises the modularized load design, comprises the backplanes support plate (32) that is positioned at fuselage (1) middle part, is used for installing airborne equipment.
Description of drawings
Fig. 1 has shown the monnolithic case figure of SUAV (small unmanned aerial vehicle) according to an embodiment of the invention.
Fig. 2 has shown fuel tank layout schematic diagram according to an embodiment of the invention.
Fig. 3 has shown according to one embodiment of present invention fuel tank connection diagram.
Fig. 4 has shown base plate schematic diagram according to an embodiment of the invention.
Fig. 5 has shown equipment according to an embodiment of the invention and base plate scheme of installation.
Fig. 6 has shown equipment installation according to an embodiment of the invention and design sketch.
The specific embodiment
Less when solving existing SUAV (small unmanned aerial vehicle) voyage, boat, and in airborne equipment " dismounting-install " pattern long, the problem such as process is loaded down with trivial details that expends time in; A basic sides of the present invention has provided that a resistance is little, the SUAV (small unmanned aerial vehicle) scheme of reasonable in design, can load and unload fast airborne equipment.
It is little that a further aspect of the present invention has provided a resistance, and fuel load is large, and is longer during boat, can carry out the SUAV (small unmanned aerial vehicle) scheme of distance flight task, and this division adopts airborne equipment modularization loading and unloading design, can load and unload fast airborne equipment.
Mainly be to realize by appropriate design and assembling and setting to the total arrangement of the V tail layout unmanned plane of blended wing-body according to one embodiment of present invention.
A further embodiment according to the present invention realizes by appropriate design and assembling and setting to total arrangement, embedded style fuel tank design, alternative expression fuel system and the modularization airborne equipment installation form of the V tail layout unmanned plane of oil tank embedded into blended wing body.
Below in conjunction with specific embodiment technical scheme of the present invention is described:
1) total arrangement of SUAV (small unmanned aerial vehicle)
This SUAV (small unmanned aerial vehicle) adopts conventional formula aerodynamic arrangement (as shown in Figure 1), blended wing-body design, drawing-in type engine installation, vee tail and tricycle landing gear.
Its middle machine body (1) is a flat lifting body with certain aerofoil profile, and top is provided with a cabin cover (9), and inside is a high-capacity cabin, is used for the installation of airborne equipment.Merge by rational curve and wing (3) the fuselage both sides, guarantees preferably aerodynamic characteristic.Front fuselage is equipped with driving engine (10), and driving engine (10) drives screw propeller (11), for aircraft provides flight required pulling force.
According to an embodiment, wing (3) aspect is trapezoidal, its leading-edge sweep, trailing edge sweepforward.Every side wing outside trailing edge is provided with aileron (4), and inboard trailing edge is provided with wing flap (5).
According to an embodiment, empennage adopts vee tail (7).According to a specific embodiment, the left and right sides empennage of empennage (7) is mutually approximately 120 °.The empennage trailing edge is provided with control surface (6), can realize the function of elevating rudder and yaw rudder by V tail mixing pattern.
Vee tail (7) was realized with being connected by shoe (8) of fuselage (1).Shoe (8) adopts such as the carbon fiber composite material pipe with tapering; According to a specific embodiment, the end that this pipe diameter is less is used for vee tail (7) is installed, and the end that diameter is larger is connected with the afterbody of fuselage (1).
Nose-gear (12) is positioned at the front lower place of fuselage (1), and main landing gear system (2) is positioned at fuselage (1) middle and lower part.
2) embedded style fuel tank design
According to one embodiment of present invention, as shown in Figure 2, fuselage interior left front, left back, right front and right abaft respectively are furnished with left front fuel tank (16), left back fuel tank (15), right front fuel tank (13) and right back fuel tank (14), design neither additionally increases resistance like this, reserve large as far as possible space for waist load cabin (17) again, improved the delelivered payload capability of aircraft.The profile of fuel tank is different from conventional hexahedral shape, but decide according to the blended wing-body fuselage appearance, namely left and right front fuel tank (13), (16) side are aerofoil profile leading edge shape, and left and right rear fuel tank (14), (15) rear portion are the airfoil trailing edge shape, inner hollow is loaded oil plant.
3) alternative expression fuel system
According to one embodiment of present invention, as shown in Figure 3, air inlet pipe (22) inserts left back fuel tank (15), left back fuel tank (15) links to each other with right front fuel tank (13) by oil pipe (21), right front fuel tank (13) links to each other with right back fuel tank (14) by oil pipe (20), right back fuel tank (14) links to each other with left front fuel tank (16) by oil pipe (19), left front fuel tank (16) links to each other with Anti-bubble fuel tank (18) by oil pipe (23), and Anti-bubble fuel tank (18) links to each other with driving engine by oil pipe (24).
Fuel tank by above connect complete after, the order of engine oil consumption is the fuel oil that uses first in the left back fuel tank (15) in-flight, then use the fuel oil in the right front fuel tank (13), then use again the fuel oil in the right back fuel tank (14), use at last the fuel oil in the left front fuel tank (16).Like this, that fuel oil sequentially is followed successively by in the consumption of full machine is left back-right front-right back-left front, the fuel oil of a rear portion fuel tank of every like this consumption, fuel oil with regard to an anterior fuel tank of corresponding consumption, avoid two rear portion fuel tanks to consume simultaneously or two anterior fuel tanks consume simultaneously, thus guarantee fuel oil consumption on the impact of machine gravity within permissible range.
The principal feature of Anti-bubble fuel tank (18) is relative main oil tank small volume, can guarantee like this in whole flight course, no matter how main oil tank (13), (14), (15), (16) interior oil level change, Anti-bubble fuel tank is full oil condition in (18), thereby stablizes fuel feeding for driving engine.
4) modularized load
For ease of installation and the replacement of airborne equipment, and reduce impact on aircaft configuration, this machine waist has designed modularized load structure (as shown in Figure 4).
Backplanes support plate (32) designs in fuselage (1) middle part, and the above is designed with screw hole (31), and the screw hole back side studs with the anti-nut of grabbing, and is used for mounting screw with fixed base plate (42).The front portion of backplanes support plate (32) is designed with square hole (33), becomes " mouth " shape, for airborne equipment headspaces such as surveying The Cloud Terrace is installed.
Airborne equipment (41) is installed on base plate (42) upper surface (as shown in Figure 5), and four angles of base plate are designed with screw hole (43).
When airborne equipment is installed, at first airborne equipment (41) is fixed in base plate (42) upper surface, with screw base plate (42) is fixed in backplanes support plate (32) upper (as shown in Figure 6) afterwards.
Below by two examples embodiments of the present invention are carried out more specific description:
Example one, band operation flight during long boat
Complete machine adopts blended wing-body and the design of " V " T tail and drawing-in type engine installation, and resistance is little, and lift is large.Adopt alternative expression for the embedded style fuel tank of oil form owing to having installed, after unmanned plane takes off, adopt the order of left back fuel tank-right front fuel tank-right back fuel tank-left front fuel tank to be followed successively by engine oil, the vertical variable quantity of machine gravity is less in the oil consumption process, and because fuel tank has larger volume, can realize the flight of long period.
Example two, the quick-replaceable of airborne equipment in the normal work to do
Because modular design airborne equipment base plate is with low cost, can make a plurality of base plates, before the field trial various required airborne equipments are installed on the base plate.In the flight test process of outfield, detachable bottom plate screw is changed " airborne equipment-base plate " module, changes fast the configuration of unmanned aerial vehicle onboard equipment.
Beneficial effect
The invention has the advantages that:
1) this SUAV (small unmanned aerial vehicle) adopts the layout pattern of blended wing-body, single shoe, vee tail and drawing-in type power, and having excellent air dynamic behaviour, particularly blended wing-body design etc. increases full machine lift, reduces wing body interference drag;
2) adopt the embedded style fuel tank design, under the prerequisite that does not increase additional friction, take full advantage of the fuselage interior space and load fuel oil, not only save space, load cabin, also increased fuel load, improved complete machine cruise duration;
3) adopt alternative expression for oil form, avoid in the flight course two front fuel tanks or two rear fuel tank fuel oils or two homonymy fuel tanks to exhaust simultaneously, thus guarantee fuel oil consumption on the impact of complete machine longitudinal center of gravity within permissible range;
4) modularized load design is convenient to installation and the replacing of airborne equipment, and is reduced the impact on housing construction.
Should be understood that, the description of in above narration and explanation the present invention being carried out just illustrates but not is determinate, and do not breaking away under the prerequisite of the present invention that limits such as appended claims, can carry out various changes, distortion and/or correction to above-described embodiment.
Claims (3)
1. SUAV (small unmanned aerial vehicle) comprises:
Fuselage (1);
Be connected to the wing (3) on the described fuselage (1);
Vee tail (7);
Single shoe (8) is used for realizing being connected of described empennage (7) and fuselage (1),
It is characterized in that further comprising:
Be installed in the driving engine (10) of the front end of described fuselage (1),
The screw propeller (11) that driving engine (10) drives, described screw propeller (11) is installed in the front end of described fuselage (1), is used to aircraft to provide flight required pulling force,
Wherein said fuselage (1) is a flat lifting body with certain aerofoil profile.
2. SUAV (small unmanned aerial vehicle) according to claim 1 is characterized in that further comprising:
Be arranged on a cabin cover (9) on the top of described fuselage (1), itself and described fuselage (1) define a cabin.
3. SUAV (small unmanned aerial vehicle) according to claim 2 is characterized in that
Described wing (3) merges by rational curve and fuselage both sides, thereby guarantees preferably aerodynamic characteristic.
Wing (3) aspect is trapezoidal, its leading-edge sweep, trailing edge sweepforward.Every side wing outside trailing edge is provided with aileron (4), and inboard trailing edge is provided with wing flap (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2013101850329A CN103303474A (en) | 2010-03-16 | 2010-03-16 | Small-size multi-purpose unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2013101850329A CN103303474A (en) | 2010-03-16 | 2010-03-16 | Small-size multi-purpose unmanned aerial vehicle |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201010127939 Division CN101804865A (en) | 2010-03-16 | 2010-03-16 | Small multi-purpose unmanned aerial vehicle |
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| CN103303474A true CN103303474A (en) | 2013-09-18 |
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| CN2013101850329A Pending CN103303474A (en) | 2010-03-16 | 2010-03-16 | Small-size multi-purpose unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| CN104608917A (en) * | 2015-01-28 | 2015-05-13 | 梧州晟裕科技有限公司 | Tail wing structure of fixed wing unmanned aerial vehicle |
| CN107406148A (en) * | 2015-02-19 | 2017-11-28 | 奥比托澳大利亚有限公司 | UAV fuel oils and lubricating system |
| CN108725743A (en) * | 2018-06-14 | 2018-11-02 | 中国水利水电科学研究院 | One kind formula hand of raising one's head throws small-sized fixed-wing unmanned aerial vehicle body |
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| US5941478A (en) * | 1998-04-28 | 1999-08-24 | Freewing Aerial Robotics Corporation | STOL/VTOL free wing aircraft with modular wing and tail |
| CN1351944A (en) * | 2001-11-30 | 2002-06-05 | 武汉大学 | Jet airplane |
| CN2681998Y (en) * | 2004-03-16 | 2005-03-02 | 清华大学 | Wing and airframe combination minisize aircraft |
| CN101332873A (en) * | 2008-06-13 | 2008-12-31 | 北京航空航天大学 | Small-sized bi-tail-boom propulsion layout parachute landing recovery device for unmanned aerial vehicle |
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| US5941478A (en) * | 1998-04-28 | 1999-08-24 | Freewing Aerial Robotics Corporation | STOL/VTOL free wing aircraft with modular wing and tail |
| CN1351944A (en) * | 2001-11-30 | 2002-06-05 | 武汉大学 | Jet airplane |
| CN2681998Y (en) * | 2004-03-16 | 2005-03-02 | 清华大学 | Wing and airframe combination minisize aircraft |
| CN101332873A (en) * | 2008-06-13 | 2008-12-31 | 北京航空航天大学 | Small-sized bi-tail-boom propulsion layout parachute landing recovery device for unmanned aerial vehicle |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818544A (en) * | 2014-01-24 | 2014-05-28 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body and manufacturing method thereof |
| CN103818544B (en) * | 2014-01-24 | 2016-05-18 | 深圳一电航空技术有限公司 | Unmanned plane, unmanned aerial vehicle body and manufacture method thereof |
| CN104608917A (en) * | 2015-01-28 | 2015-05-13 | 梧州晟裕科技有限公司 | Tail wing structure of fixed wing unmanned aerial vehicle |
| CN107406148A (en) * | 2015-02-19 | 2017-11-28 | 奥比托澳大利亚有限公司 | UAV fuel oils and lubricating system |
| US10717541B2 (en) | 2015-02-19 | 2020-07-21 | Orbital Australia Pty Ltd | UAV fuel and lubrication system |
| CN108725743A (en) * | 2018-06-14 | 2018-11-02 | 中国水利水电科学研究院 | One kind formula hand of raising one's head throws small-sized fixed-wing unmanned aerial vehicle body |
| CN108725743B (en) * | 2018-06-14 | 2023-07-14 | 中国水利水电科学研究院 | Unmanned aerial vehicle fuselage with head-leaning type hand-thrown small fixed wings |
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Application publication date: 20130918 |