CN104590568A - Long-endurance hybrid power UAV (Unmanned Aerial Vehicle) - Google Patents
Long-endurance hybrid power UAV (Unmanned Aerial Vehicle) Download PDFInfo
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- CN104590568A CN104590568A CN201510052424.7A CN201510052424A CN104590568A CN 104590568 A CN104590568 A CN 104590568A CN 201510052424 A CN201510052424 A CN 201510052424A CN 104590568 A CN104590568 A CN 104590568A
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Abstract
The invention discloses a long-endurance hybrid power UAV (Unmanned Aerial Vehicle). The UAV comprises two propeller engines, double tail booms and a pair of wings, wherein the propeller engines are respectively and relatively arranged in the front or at the back of a UAV body; the double tail booms are arranged at the rear part of the UAV body and the pair of wings is arranged on the UAV body; the two propeller engines are a methanol engine and a motor and both are arranged on the axis of the UAV body. According to the UAV provided by the invention, by adopting a high mounted wing with high aspect ratio, double tail booms layout, and the power configuration that the methanol engine is behind the motor, the oil and electric hybrid power has the characteristics of long-endurance of an oil driven airplane and the reliability of an electric driven airplane; furthermore, the motor can ensure that the oil-driven airplane is capable of making a return voyage when an extinguishment-trouble is caused, so that the safety of the air-plane, surrounding buildings and personnel can be ensured, and the survival rate of the airplane can be improved; more powerful power can be provided when the motor and the methanol engine are operating at the same time, so that the maximum load of the UAV can be improved, and the take-off distance can be shortened, besides the requirements on a take-off site by the UAV can be reduced, therefore, the UAV can take a plurality of task equipment to implement tasks.
Description
Technical field
What the present invention relates to is a kind of technology of oil electric mixed dynamic unmanned plane FIELD OF THE INVENTIONThe, specifically hybrid power unmanned plane during a kind of long boat.
Background technology
Most of SUAV (small unmanned aerial vehicle) adopts lithium cell to be power, there is the defect short when navigating, voyage is near; And adopt the engine reliability of the fuel such as gasoline, methyl alcohol lower than motor, exist easily stop working, have an accident after the deficiency such as inflammable and explosive.Existing SUAV (small unmanned aerial vehicle) is generally single power system, mostly is the combustion engine of lithium cell or fuel such as use gasoline, methyl alcohol etc., does not use the unmanned plane of lithium cell and methyl alcohol two kinds of power simultaneously.
Twin-engined plane two driving engines are generally arranged on wing, if an engine off, there will be the course line deflection because engine thrust overbalance occurs, jeopardize flight safety.
Most of SUAV (small unmanned aerial vehicle) adopts lithium cell to be power, there is the defect short when navigating, voyage is near; And adopt the engine reliability of the fuel such as gasoline, methyl alcohol lower than motor, exist easily stop working, have an accident after the deficiency such as inflammable and explosive.Driving engine be arranged in the twin-engined plane on wing continue after an engine off flight, there will be due to engine thrust overbalance occur course line deflection, aircraft safety is reduced.
Through finding the retrieval of prior art, open (bulletin) the day 2010.09.22 of Chinese patent literature CN101837835A, disclose a kind of Unmanned Aircraft Systems (UAS) being applicable to weather modification, comprise two driving engines, before one platform, pulling type engine is connected with unmanned plane head, provides forward direction pulling force, and a back-pushed driving engine is connected with tail, there is provided thrust, the line of pull of front pulling type engine overlaps with the line of thrust of back-pushed driving engine.During operation, two simultaneous firings, provide the power of unmanned plane during flying, and when wherein an engine breakdown goes out car, an other driving engine works on.But all there is et out of order and to go out the danger of car in this technology two driving engines in high altitude anoxia and high humidity environment, and two driving engines all go out after car aircraft to lose institute dynamic, easily crash.When two driving engines can not increase the boat of aircraft, just can provide larger thrust.And have more driving engine can increase the weight of unmanned plane, corresponding control system and oil circuit also can be more complicated, affect flight time and the load carrying ability of unmanned plane.
Summary of the invention
The present invention is directed to prior art above shortcomings, hybrid power unmanned plane when a kind of length is navigated is proposed, adopt the power configuration of high aspect ratio high mounted wing, Bi-Tail-Boom Layout and preposition motor postposition methanol-fueled engine, oil electric mixed dynamic has feature and electric airplane reliability when the dynamic aircraft length of oil is navigated concurrently.Still have the ability to make a return voyage when motor can guarantee that flame-out fault appears in oil machine, ensure the safety of aircraft and surrounding buildings and personnel, improve the survival rate of aircraft.
The present invention is achieved by the following technical solutions:
The present invention includes: be relatively arranged on two airscrew engines before and after fuselage, the two shoe being arranged at fuselage afterbody and the wing be arranged at for a pair on fuselage respectively.
Described airscrew engine is methanol-fueled engine and motor, the line of thrust of front pull-type motor and back-pushed methanol-fueled engine all with fuselage dead in line.
Described wing is syllogic, specifically comprises: be positioned at the wing centre section directly over fuselage and the right flank and the left wing that split both sides, and this wing is made up of the carbon pipe as beam, the wood of the paulownia as floor and the heat shrinkage film as covering.
Described fuselage is by wooden bulkhead, timber beam, wooden illiteracy plate and form as the heat shrinkage film of covering, and wherein: beam is fixed with the left and right sides of each bulkhead respectively, each side respectively has a beam up and down, and this fuselage bottom is provided with tricycle landing gear.
Tailplane in described two shoes and vertical tail form by the paulownia batten as framework and the heat shrinkage film as covering; Gluedd joint by empennage connecting strap between tailplane and vertical tail.
Technique effect
Compared with prior art, during the boat that the present invention adopts methanol-fueled engine can provide longer, motor can ensure that aircraft is safer, and two arbitrary of being arranged in the airscrew engine before and after fuselage work alone and all can ensure aircraft normal flight.Twin-enginedly can also provide stronger power, greatly improve the maximum load of aircraft, shorten take off distance, reduce aircraft to the requirement of take-off venue, be conducive to aircraft and carry multiple-task equipment and execute the task.
Accompanying drawing explanation
Fig. 1 is lateral plan of the present invention;
Fig. 2 is front view of the present invention;
Fig. 3 is birds-eye view of the present invention;
In figure: alighting gear, 10 fuel tanks, 11 lithium celies, 12 nose-gears, 13 ailerons, 14 elevating rudders, right section of 15 wings, left section of 16 wings, 17 carbon beams, 18 empennage connecting straps, 19 wing fixed links after 1 motor, 2 fuselages, 3 wing stage casings, 4 carbon beams, 5 vertical tails, 6 yaw rudders, 7 tailplanes, 8 methanol-fueled engines, 9.
Detailed description of the invention
Elaborate to embodiments of the invention below, the present embodiment is implemented under premised on technical solution of the present invention, give detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1
As depicted in figs. 1 and 2, the present embodiment comprises: be relatively arranged on respectively two airscrew engines before and after fuselage 21,8, two shoes 5,7 of being arranged at fuselage 2 rear portion and the wing be arranged at for a pair on fuselage.
Described airscrew engine is methanol-fueled engine 8 and motor 1, and these two airscrew engines are all arranged on fuselage axis
Described wing is syllogic, specifically comprise: be positioned at the wing centre section 3 directly over fuselage 2 and the right flank 15 and the left wing 16 that split both sides, wherein: the carbon beam of left wing 16 and right flank 15 is by assembling in the carbon beam of insertion wing centre section 3, then be screwed carbon beam to prevent from coming off, transport is convenient in the design of wing, and mounting or dismounting are convenient.
Described wing is fixed by elastic and fuselage, and concrete mode is to tie tight the wing fixed link 19 and wing centre section 3 that are positioned at fuselage with elastic, simple and reliable, is convenient to dismounting.
Described right flank 15 and left wing 16 are all hinged with aileron 13, and this aileron 13 controls aileron by the steering wheel in left wing 16 and right flank 15 and rocking bar.
Described alighting gear is tricycle landing gear, comprising: nose-gear 12 and rear alighting gear 9.
Lithium cell 11, fuel tank 10 and controlled in wireless mechanism is provided with in described fuselage 2.
Described fuselage 2 bottom is provided with the screw hole for installing simple and easy The Cloud Terrace, is convenient to execution and takes photo by plane task.
Described fuselage 2 is made up of bulkhead, beam, illiteracy plate, covering.Beam is fixed with the left and right sides of each bulkhead respectively, and each side respectively has a beam up and down, is mainly used to bear the power of aspect before and after fuselage.Be made up of the stress frame of fuselage beam and bulkhead, while wood frame structure alleviates fuselage weight, ensure that the intensity of fuselage.Fuselage outer side veneer does illiteracy plate, and appearance covering wraps up, and makes smooth in appearance, reduces air resistance.Its middle frame and beam are made up of laminate, and paulownia timber does illiteracy plate, and heat shrinkage film is as covering.
Described wing is by carbon Guan Zuoliang, and paulownia is wooden makes floor, and most appearance covers heat shrinkage film.
Described tailplane 7 and vertical tail 5 paulownia batten make framework, and appearance covers heat shrinkage film.Be connected by empennage connecting strap 18 between tailplane 7 with vertical tail 5, be fixed on carbon pipe by glue, carbon pipe is connected on wing wing centre section 3 bottom.
Described empennage connecting strap 18 is laminate.Nose-gear 12 is that stainless steel and tire are formed, and rear alighting gear 9 is aluminum strip and tire.
When length in the present embodiment is navigated, hybrid power unmanned plane adopts rolling start and landing: control aileron by remote controller, Aircraft Lateral roller can be made to move, and then change aircraft flight direction; Control elevating rudder, aircraft pitch angle can be changed, control aircraft and rise or decline; Control yaw rudder, aircraft direction can be changed.Aircraft is divided into single control and double control, and during single control, remote controller throttle channel controls the throttle size of motor and methanol-fueled engine simultaneously; Double control is used for taking photo by plane, main manipulation hand shift motor throttle and aileron, yaw rudder, elevating rudder, the methanol-fueled engine throttle of secondary manipulation hand shift aircraft and The Cloud Terrace.
As shown in Figure 3, the present embodiment type is fixed-wing, and landing mode is rolling start landing.
Claims (9)
1. hybrid power unmanned plane during long boat, is characterized in that, comprising: be relatively arranged on two airscrew engines before and after fuselage, the two shoe being arranged at fuselage afterbody and the wing be arranged at for a pair on fuselage respectively;
Described airscrew engine is methanol-fueled engine and motor, the line of thrust of front pull-type motor and back-pushed methanol-fueled engine all with fuselage dead in line.
2. hybrid power unmanned plane during long boat according to claim 1, it is characterized in that, described wing is syllogic, specifically comprises: be positioned at the wing centre section directly over fuselage and the right flank and the left wing that split both sides.
3. hybrid power unmanned plane during long boat according to claim 2, is characterized in that, it is fixing that described wing centre section realizes with fuselage by elastic and the wing fixed link that is attached thereto.
4. hybrid power unmanned plane during long boat according to claim 1, it is characterized in that, described fuselage bottom is provided with tricycle landing gear.
5. hybrid power unmanned plane during long boat according to claim 4, it is characterized in that, in described tricycle landing gear: nose-gear is that stainless steel and tire form, rear alighting gear is that aluminum strip and tire form.
6. hybrid power unmanned plane during long boat according to claim 1, it is characterized in that, described fuselage is by wooden bulkhead, timber beam, wooden illiteracy plate and form as the heat shrinkage film of covering, and wherein: beam is fixed with the left and right sides of each bulkhead respectively, each side respectively has a beam up and down.
7. hybrid power unmanned plane during long boat according to claim 1 and 2, is characterized in that, described wing is made up of the carbon pipe as beam, the wood of the paulownia as floor and the heat shrinkage film as covering.
8. hybrid power unmanned plane during long boat according to claim 1, it is characterized in that, the tailplane in described two shoes and vertical tail form by the paulownia batten as framework and the heat shrinkage film as covering; Gluedd joint by empennage connecting strap between tailplane and vertical tail.
9. hybrid power unmanned plane during long boat according to claim 8, it is characterized in that, described empennage connecting strap is veneer structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN201510052424.7A CN104590568A (en) | 2015-02-02 | 2015-02-02 | Long-endurance hybrid power UAV (Unmanned Aerial Vehicle) |
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| CN201510052424.7A CN104590568A (en) | 2015-02-02 | 2015-02-02 | Long-endurance hybrid power UAV (Unmanned Aerial Vehicle) |
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| CN201510052424.7A Pending CN104590568A (en) | 2015-02-02 | 2015-02-02 | Long-endurance hybrid power UAV (Unmanned Aerial Vehicle) |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| CN109383784A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aerial platform with force aid system |
| CN112249303A (en) * | 2020-10-26 | 2021-01-22 | 东莞理工学院 | Tail fin balancer of flapping-wing micro flying robot |
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| CN201085931Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Insertion airfoil of miniature pilotless plane |
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| CN202879789U (en) * | 2012-09-26 | 2013-04-17 | 武汉智能鸟无人机有限公司 | Petrol-electric hybrid type unmanned aerial vehicle |
| CN103538714A (en) * | 2013-11-06 | 2014-01-29 | 张明 | Vertical take-off and landing model aircraft unmanned aerial vehicle |
| US20140250861A1 (en) * | 2013-03-09 | 2014-09-11 | Rolls-Royce Corporation | Aircraft power plant |
| CN204568065U (en) * | 2015-02-02 | 2015-08-19 | 上海交通大学 | Hybrid power unmanned plane during long boat |
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Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN201085931Y (en) * | 2007-08-03 | 2008-07-16 | 西安大地测绘工程有限责任公司 | Insertion airfoil of miniature pilotless plane |
| CN201175580Y (en) * | 2007-12-28 | 2009-01-07 | 卢铭津 | Aircraft shell |
| CN201143384Y (en) * | 2008-01-08 | 2008-11-05 | 周伟烘 | Glide model airplane with adjustable dihedral angle of main wing |
| CN101837835A (en) * | 2010-05-26 | 2010-09-22 | 中兵光电科技股份有限公司 | Unmanned aerial vehicle system applied to weather modification |
| CN202879789U (en) * | 2012-09-26 | 2013-04-17 | 武汉智能鸟无人机有限公司 | Petrol-electric hybrid type unmanned aerial vehicle |
| US20140250861A1 (en) * | 2013-03-09 | 2014-09-11 | Rolls-Royce Corporation | Aircraft power plant |
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| CN204568065U (en) * | 2015-02-02 | 2015-08-19 | 上海交通大学 | Hybrid power unmanned plane during long boat |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106155085A (en) * | 2016-08-05 | 2016-11-23 | 武汉捷特航空科技有限公司 | A kind of unmanned plane assisting in flying control method, system and unmanned plane |
| CN109383784A (en) * | 2018-08-31 | 2019-02-26 | 辽宁同心圆科技有限公司 | Aerial platform with force aid system |
| CN112249303A (en) * | 2020-10-26 | 2021-01-22 | 东莞理工学院 | Tail fin balancer of flapping-wing micro flying robot |
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