CN101804865A - Small multi-purpose unmanned aerial vehicle - Google Patents
Small multi-purpose unmanned aerial vehicle Download PDFInfo
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- CN101804865A CN101804865A CN 201010127939 CN201010127939A CN101804865A CN 101804865 A CN101804865 A CN 101804865A CN 201010127939 CN201010127939 CN 201010127939 CN 201010127939 A CN201010127939 A CN 201010127939A CN 101804865 A CN101804865 A CN 101804865A
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Abstract
The invention relates to a small multi-purpose unmanned aerial vehicle, which can be used for performing scientific experiments, remote sensing, aerial photography and other flight tasks. The small multi-purpose unmanned aerial vehicle has the following advantages: 1) the cruising duration is long, thereby facilitating the performance of flight tasks with high requirement for the flight duration; 2) the utilization is simple, thereby facilitating the operation; 3) the stability is good and is suitable for carrying autopilots, aerial cameras, video cameras and the like; and 4) the requirements for takeoff and landing conditions are low. According to one aspect of the invention, the small unmanned aerial vehicle comprises a body, wings connected with the body, an empennage, a boom used for realizing connection of the empennage and the body, an engine (10) arranged on the front end of the body (1), and an engine driven propeller (11) used for providing thrust for the aerial vehicle to fly. According to the other aspect of the invention, the unmanned aerial vehicle further comprises a modular loading design with a bottom board supporting plate (32) arranged in the middle of the body (1) used for installation of airborne equipment.
Description
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 big 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 big, 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 make to measure according to concrete mission payload mostly, not strong for the cargo-carring commonality of mission payload; When the load that does not have formal typing is carried test, not very convenient, need housing construction is transformed sometimes even also.
Summary of the invention
At 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 carries out scientific experiment, remote sensing and aerial mission such as take photo by plane in the air.This unmanned plane has following characteristics: 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 equipment such as autopilot, the camera of taking photo by plane, 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 the wing on the described fuselage; Empennage; And shoe, be used to realize 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 lid 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 a vee tail, and the empennage trailing edge is provided with control surface, thereby can realize the function of elevating rudder and yaw rudder by V tail mixing pattern.Unmanned plane according to another aspect of the present invention further comprises the modularized load design, comprises being positioned at fuselage (1) bottom board supporting plate (32), is used to install 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 scheme drawing according to an embodiment of the invention.
Fig. 3 has shown fuel tank connection diagram according to one embodiment of present invention.
Fig. 4 has shown base plate scheme drawing 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 on airborne equipment " dismounting-installation " pattern, expend time in and problem such as grow, process is loaded down with trivial details; 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 big, 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 according to one embodiment of present invention by appropriate design and assembling and setting to the total arrangement of the V tail layout unmanned plane of blended wing-body.
A further embodiment according to the present invention mainly is by the appropriate design and the assembling and setting of the total arrangement of the V tail layout unmanned plane of oil tank embedded into blended wing body, the design of embedded fuel tank, alternative expression fuel system and modularization airborne equipment installation form are realized.
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 lid (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 aerodynamic characteristic preferably.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 about 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 the carbon fiber composite material pipe such as the band tapering; According to a specific embodiment, the less end of this pipe diameter is used to install vee tail (7), and the end that diameter is bigger 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 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 additive incrementation resistance like this, reserve big 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 with conventional hexahedral shape, but decide according to the blended wing-body fuselage appearance, promptly left and right preceding 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), and 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 is by after above connection finishes, the order of driving engine oil consumption is the fuel oil that uses earlier in the left back fuel tank (15) in-flight, then use the fuel oil in the right front fuel tank (13), then use the fuel oil in the right back fuel tank (14) again, use the fuel oil in the left front fuel tank (16) at last.Like this, that fuel oil is followed successively by in proper order 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 to the influence of machine gravity within permissible range.
The principal feature of anti-bubble fuel tank (18) is that relative main oil tank volume is less, can guarantee like this in whole flight course, no matter how main oil tank (13), (14), (15), (16) interior oil level change, be full oil condition in the anti-bubble fuel tank (18), thereby stablize fuel feeding for driving engine.
4) modularized load
For ease of the installation and the replacement of airborne equipment, and reduce influence to 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 design has screw hole (31) above, 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 design of backplanes support plate (32) has 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 angle designs of base plate have 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) afterwards and goes up (as shown in Figure 6).
Below by two examples embodiments of the present invention are carried out more specific description:
Example one, band operation flight during long the boat
Complete machine adopts blended wing-body and design of " V " T tail and drawing-in type engine installation, and resistance is little, and lift is big.Because the embedded fuel tank that adopts alternative expression fuel feeding form has been 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, can realize the flight of long period because fuel tank has big volume.
Example two, the quick replacing 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 the unmanned aerial vehicle onboard equipment disposition fast.
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 embedded fuel tank design, under the prerequisite that does not increase additional friction, make full use 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 fuel feeding form, avoid in the flight course two preceding fuel tanks or two rear fuel tank fuel oils or two homonymy fuel tanks to exhaust simultaneously, thus guarantee fuel oil consumption to the influence of complete machine longitudinal center of gravity within permissible range;
4) modularized load design is convenient to the installation and the replacing of airborne equipment, and is reduced the influence to housing construction.
Should be understood that, in above narration and explanation to just explanation but not determinate of description that the present invention carried out, and do not breaking away under the prerequisite of the present invention that limits as appended claims, can carry out various changes, distortion and/or correction the foregoing description.
Claims (10)
1. SUAV (small unmanned aerial vehicle) is characterized in that comprising:
Fuselage (1);
Be connected the wing (3) on the described fuselage (1);
Empennage (7); And
Shoe (8) is used to realize being connected of described empennage (7) and fuselage (1).
2. SUAV (small unmanned aerial vehicle) according to claim 1 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 is used to aircraft to provide flight required pulling force.
3. SUAV (small unmanned aerial vehicle) according to claim 2 is characterized in that further comprising:
Be arranged on a cabin lid (9) on the top of described fuselage (1), itself and described fuselage (1) define a cabin;
Wherein said fuselage (1) is a flat lifting body with certain aerofoil profile.
4. SUAV (small unmanned aerial vehicle) according to claim 3 is characterized in that
Described wing (3) merges by rational curve and fuselage both sides, thereby guarantees aerodynamic characteristic preferably.
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).
5. SUAV (small unmanned aerial vehicle) according to claim 1 is characterized in that
Described empennage is vee tail (7), and the left and right sides empennage of vee tail (7) is mutually about 120 °, and trailing edge is provided with control surface (6), thereby can realize the function of elevating rudder and yaw rudder by V tail mixing pattern.
6. SUAV (small unmanned aerial vehicle) according to claim 1 is characterized in that
Described shoe (8) is a pipe, and pipe adopts carbon fiber composite material, and the less end of its diameter is used to install vee tail (7), and the end that diameter is bigger is connected with the afterbody of fuselage (1).
7. SUAV (small unmanned aerial vehicle) according to claim 1 is characterized in that further comprising:
Be positioned at the nose-gear (12) of the front lower place of fuselage (1), and
Be positioned at the main landing gear system (2) of fuselage (1) middle and lower part.
8. SUAV (small unmanned aerial vehicle) according to claim 7 is characterized in that further comprising:
Be positioned at fuselage (1) bottom board supporting plate (32), be used to install airborne equipment.
9. SUAV (small unmanned aerial vehicle) according to claim 8 is characterized in that further comprising:
Be arranged on the screw hole (31) on the described backplanes support plate (32),
Be set in the anti-nut of grabbing at the back side of described screw hole (31), be used for installing the screw that is used for fixing base plate (42).
10. SUAV (small unmanned aerial vehicle) according to claim 9 is characterized in that further comprising:
Be arranged on the hole (33) of the front portion of described backplanes support plate (32), be used to install airborne equipment,
Four angles of wherein said base plate (42) are provided with screw hole (43), and the upper surface of described base plate (42) can be used for installing airborne equipment (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010127939 CN101804865A (en) | 2010-03-16 | 2010-03-16 | Small multi-purpose unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201010127939 CN101804865A (en) | 2010-03-16 | 2010-03-16 | Small multi-purpose unmanned aerial vehicle |
Related Child Applications (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2013101850329A Division CN103303474A (en) | 2010-03-16 | 2010-03-16 | Small-size multi-purpose unmanned aerial vehicle |
| CN2011104485667A Division CN102490904A (en) | 2010-03-16 | 2010-03-16 | Small multipurpose unmanned plane |
| CN2011104399943A Division CN102490903A (en) | 2010-03-16 | 2010-03-16 | Miniature multipurpose unmanned plane |
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| Publication Number | Publication Date |
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| CN101804865A true CN101804865A (en) | 2010-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201010127939 Pending CN101804865A (en) | 2010-03-16 | 2010-03-16 | Small multi-purpose unmanned aerial vehicle |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102806990A (en) * | 2012-07-27 | 2012-12-05 | 沈阳航天新光集团有限公司 | Portable mapping unmanned aerial plane |
| CN103010458A (en) * | 2012-12-19 | 2013-04-03 | 天津全华时代航天科技发展有限公司 | Vectored thrust type unmanned aerial vehicle |
| CN103287578A (en) * | 2012-03-01 | 2013-09-11 | 贵州帝三数字技术有限公司 | General miniature unmanned aerial vehicle |
| CN103950534A (en) * | 2014-05-14 | 2014-07-30 | 北京航空航天大学 | Aerodynamic layout form of unmanned aerial vehicle with high-efficiency large-volume non-tail lifting force aircraft body |
| CN106585982A (en) * | 2016-12-20 | 2017-04-26 | 西北工业大学 | Combined type micro air vehicle driven by flapping wings |
| CN109665101A (en) * | 2019-01-07 | 2019-04-23 | 浙江自贸区协同科技有限公司 | A kind of modularization head |
| CN113226919A (en) * | 2018-12-19 | 2021-08-06 | 列奥纳多股份公司 | Aircraft and associated manufacturing method |
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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 |
| 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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2010
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287578A (en) * | 2012-03-01 | 2013-09-11 | 贵州帝三数字技术有限公司 | General miniature unmanned aerial vehicle |
| CN103287578B (en) * | 2012-03-01 | 2015-07-01 | 贵州帝三数字技术有限公司 | General miniature unmanned aerial vehicle |
| CN102806990A (en) * | 2012-07-27 | 2012-12-05 | 沈阳航天新光集团有限公司 | Portable mapping unmanned aerial plane |
| CN102806990B (en) * | 2012-07-27 | 2016-01-20 | 海鹰航空通用装备有限责任公司 | Portable type mapping unmanned plane |
| CN103010458A (en) * | 2012-12-19 | 2013-04-03 | 天津全华时代航天科技发展有限公司 | Vectored thrust type unmanned aerial vehicle |
| CN103950534A (en) * | 2014-05-14 | 2014-07-30 | 北京航空航天大学 | Aerodynamic layout form of unmanned aerial vehicle with high-efficiency large-volume non-tail lifting force aircraft body |
| CN106585982A (en) * | 2016-12-20 | 2017-04-26 | 西北工业大学 | Combined type micro air vehicle driven by flapping wings |
| CN113226919A (en) * | 2018-12-19 | 2021-08-06 | 列奥纳多股份公司 | Aircraft and associated manufacturing method |
| CN109665101A (en) * | 2019-01-07 | 2019-04-23 | 浙江自贸区协同科技有限公司 | A kind of modularization head |
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Application publication date: 20100818 |