CN102490904A - Small multipurpose unmanned plane - Google Patents
Small multipurpose unmanned plane Download PDFInfo
- Publication number
- CN102490904A CN102490904A CN2011104485667A CN201110448566A CN102490904A CN 102490904 A CN102490904 A CN 102490904A CN 2011104485667 A CN2011104485667 A CN 2011104485667A CN 201110448566 A CN201110448566 A CN 201110448566A CN 102490904 A CN102490904 A CN 102490904A
- Authority
- CN
- China
- Prior art keywords
- fuselage
- unmanned plane
- fuel tank
- airborne equipment
- fuel
- 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
Abstract
A small multipurpose unmanned plane can be used to execute flight tasks in scientific experiment, remote sensing and aerial photography and the like. The unmanned plane has the following characteristics that 1) endurance time is long and it is convenient to carry out flight tasks which have a high requirement on endurance time; 2) the unmanned plane is simple to use and convenient to control; 3) the unmanned plane has good stability and is applicable to be used to carry equipment such as an automatic pilot, an aerial photography camera, a camera and the like; and 4) the unmanned plane has low requirements on the rising and landing condition. In dependence on one aspect, the small unmanned plane contains a fuselage, wings connected on the fuselage, empennages, tail booms for connecting the empennages with the fuselage, an engine (10) installed at the front end of the fuselage (1), and propellers (11) which are driven by the engine (10) and used for providing the airplane with pulling force required by flight. In dependence on the other aspect, the unmanned plane further contains a modularization loading design. It contains a baseboard support plate (32) positioned at the central portion of the fuselage (1). The baseboard support plate is used to install airborne equipment.
Description
The application is dividing an application of No. the 201010127939.6th, one 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 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 transform housing construction sometimes even also.
Summary of the invention
To 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, a kind of SUAV is provided, has it is characterized in that comprising: fuselage; Be connected the wing on the said fuselage; Empennage; And shoe, be used to realize being connected of said empennage and fuselage.
According to a further aspect of the present invention, above-mentioned SUAV further comprises: the driving engine that is installed in the front end of said fuselage; Said engine-driven screw propeller, being used to aircraft provides flight required pulling force.
According to a further aspect of the present invention, above-mentioned SUAV further comprises: be arranged on a cabin lid on the top of said fuselage, itself and said 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 through 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 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 that fuel tank connects scheme drawing 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 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 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 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 through 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 through 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
This SUAV 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 through 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 through V tail mixing pattern.
Vee tail (7) was realized with being connected through 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), and left back fuel tank (15) links to each other with right front fuel tank (13) through oil pipe (21); Right front fuel tank (13) links to each other with right back fuel tank (14) through oil pipe (20); Right back fuel tank (14) links to each other with left front fuel tank (16) through oil pipe (19), and left front fuel tank (16) links to each other with anti-bubble fuel tank (18) through oil pipe (23), and anti-bubble fuel tank (18) links to each other with driving engine through oil pipe (24).
After fuel tank finishes by the preceding text connection; The order of driving engine consumption oil 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 the consumption of full machine in proper order is left back-right front-right back-left front; The fuel oil of a rear portion fuel tank of every like this consumption; With regard to the fuel oil of an anterior fuel tank of corresponding consumption, avoid two rear portion fuel tanks to consume simultaneously or two anterior fuel tanks consume simultaneously, thereby 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 the 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, is designed with 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 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) afterwards and goes up (as shown in Figure 6).
Through two instances embodiment of the present invention is explained more specifically below:
Instance one, band operation flight during long the boat
Whole machine using blended wing-body and design of " V " T tail and drawing-in type engine installation, 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 oily process of consumption, and because fuel tank has big volume, can realize the flight of long period.
Instance 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 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 like enclosed under the prerequisite of the present invention that claims limit not breaking away from, can carry out various changes, distortion and/or revise the foregoing description.
Claims (4)
1. SUAV is characterized in that comprising:
Fuselage (1);
Be connected the wing (3) on the said fuselage (1);
Empennage (7); And
Shoe (8) is used to realize being connected of said empennage (7) and fuselage (1);
Be positioned at the nose-gear (12) of the front lower place of fuselage (1);
Be positioned at the main landing gear system (2) of fuselage (1) middle and lower part.
2. SUAV according to claim 1 is characterized in that further comprising:
Be positioned at fuselage (1) bottom board supporting plate (32), be used to install airborne equipment.
3. SUAV according to claim 2 is characterized in that further comprising:
Be arranged on the screw hole (31) on the said backplanes support plate (32),
Be set in the anti-nut of grabbing at the back side of said screw hole (31), be used for installing the screw that is used for fixing base plate (42).
4. SUAV according to claim 3 is characterized in that further comprising:
Be arranged on the hole (33) of the front portion of said 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 said base plate (42) can be used for installing airborne equipment (41).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104485667A CN102490904A (en) | 2010-03-16 | 2010-03-16 | Small multipurpose unmanned plane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104485667A CN102490904A (en) | 2010-03-16 | 2010-03-16 | Small multipurpose unmanned plane |
Related Parent Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201010127939 Division CN101804865A (en) | 2010-03-16 | 2010-03-16 | Small multi-purpose unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102490904A true CN102490904A (en) | 2012-06-13 |
Family
ID=46182776
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011104485667A Pending CN102490904A (en) | 2010-03-16 | 2010-03-16 | Small multipurpose unmanned plane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102490904A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523203A (en) * | 2013-10-15 | 2014-01-22 | 江苏艾锐泰克无人飞行器科技有限公司 | Front camera cabin of unmanned aerial vehicle |
| CN105573333A (en) * | 2016-01-22 | 2016-05-11 | 青岛大学 | Modular control method for four-rotor aircraft |
| CN105700535A (en) * | 2016-01-22 | 2016-06-22 | 青岛大学 | Modular type control panel for four-rotor aircraft |
| CN113978697A (en) * | 2021-11-18 | 2022-01-28 | 中国航空研究院 | Liquid hydrogen fuel ultra-remote wing body fusion layout transport airplane and operation method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4180221A (en) * | 1978-01-16 | 1979-12-25 | Harris Donald E | Self propelled kite |
| US4691879A (en) * | 1986-06-16 | 1987-09-08 | Greene Vibert F | Jet airplane |
| GB2359286A (en) * | 2000-02-10 | 2001-08-22 | Franklin Zee | A vehicle,e.g.a remote controlled toy or model aircraft, a piloted aircraft or glider, or a land- or water-borne vehicle,having a V-shaped tail |
| CN200939356Y (en) * | 2006-08-22 | 2007-08-29 | 青岛天骄无人机遥感技术有限公司 | Small remote monitoring pilotless plane |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
-
2010
- 2010-03-16 CN CN2011104485667A patent/CN102490904A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4180221A (en) * | 1978-01-16 | 1979-12-25 | Harris Donald E | Self propelled kite |
| US4691879A (en) * | 1986-06-16 | 1987-09-08 | Greene Vibert F | Jet airplane |
| GB2359286A (en) * | 2000-02-10 | 2001-08-22 | Franklin Zee | A vehicle,e.g.a remote controlled toy or model aircraft, a piloted aircraft or glider, or a land- or water-borne vehicle,having a V-shaped tail |
| CN200939356Y (en) * | 2006-08-22 | 2007-08-29 | 青岛天骄无人机遥感技术有限公司 | Small remote monitoring pilotless plane |
| CN101314409A (en) * | 2008-07-10 | 2008-12-03 | 周武双 | Swallow type inclined rotation rotorcraft |
Non-Patent Citations (1)
| Title |
|---|
| 陆方舟等: "可折叠V尾布局无人机飞行载荷分析", 《第十届全国空气弹性学术交流会会议论文集》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103523203A (en) * | 2013-10-15 | 2014-01-22 | 江苏艾锐泰克无人飞行器科技有限公司 | Front camera cabin of unmanned aerial vehicle |
| CN105573333A (en) * | 2016-01-22 | 2016-05-11 | 青岛大学 | Modular control method for four-rotor aircraft |
| CN105700535A (en) * | 2016-01-22 | 2016-06-22 | 青岛大学 | Modular type control panel for four-rotor aircraft |
| CN105573333B (en) * | 2016-01-22 | 2018-05-08 | 青岛大学 | A kind of modular control method for quadrotor |
| CN113978697A (en) * | 2021-11-18 | 2022-01-28 | 中国航空研究院 | Liquid hydrogen fuel ultra-remote wing body fusion layout transport airplane and operation method |
| CN113978697B (en) * | 2021-11-18 | 2024-04-09 | 中国航空研究院 | Liquid hydrogen fuel ultra-remote wing body fusion layout transportation aircraft and operation method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101792022B (en) | Small multipurpose unmanned aerial vehicle with oil tank embedded into blended wing body | |
| US9493226B2 (en) | Multi-role aircraft with interchangeable mission modules | |
| US9505484B1 (en) | Modular aircraft system | |
| US8967526B2 (en) | Multi-role aircraft with interchangeable mission modules | |
| CN100491200C (en) | Cargo aircraft | |
| US9884682B2 (en) | Aircraft configuration | |
| CN101804865A (en) | Small multi-purpose unmanned aerial vehicle | |
| US8366050B2 (en) | Blended wing body cargo airplane | |
| CN101314409A (en) | Swallow type inclined rotation rotorcraft | |
| CN107089328A (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft and its flight control method | |
| CN109398705A (en) | A kind of airfreighter | |
| CN103466074A (en) | Ship-based net collision recovery unmanned aerial vehicle | |
| US20060284010A1 (en) | Hydrofoil for an amphibious aircraft | |
| CN103213683A (en) | Small multipurpose unmanned plane with oil tank embedded into blended wing body | |
| CN110498041A (en) | A kind of small-sized Shipborne UAV suitable for the recycling of catapult-assisted take-off lanyard | |
| CN109795682A (en) | A kind of efficient tail sitting posture VTOL Fixed Wing AirVehicle and its control method | |
| CN103192981A (en) | Motor-driven low-noise short-distance taking-off and landing wing-connected aircraft | |
| CN102490904A (en) | Small multipurpose unmanned plane | |
| CN206857002U (en) | Hybrid power tail sitting posture VTOL long endurance unmanned aircraft | |
| CN103303474A (en) | Small-size multi-purpose unmanned aerial vehicle | |
| CN209241305U (en) | A kind of Bi-Tail-Boom Layout unmanned plane | |
| CN205022847U (en) | A high performance fixed wing uavs device for cruising monitoring | |
| CN102490903A (en) | Miniature multipurpose unmanned plane | |
| CN203958603U (en) | A kind of aerial survey unmanned plane | |
| CN101734376B (en) | Small multipurpose unmanned aerial vehicle capable of realizing modularized load and parachute recovery |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C12 | Rejection of a patent application after its publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20120613 |