CN102602535A - Double-engine rotor unmanned aerial vehicle system - Google Patents
Double-engine rotor unmanned aerial vehicle system Download PDFInfo
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- CN102602535A CN102602535A CN2012100966963A CN201210096696A CN102602535A CN 102602535 A CN102602535 A CN 102602535A CN 2012100966963 A CN2012100966963 A CN 2012100966963A CN 201210096696 A CN201210096696 A CN 201210096696A CN 102602535 A CN102602535 A CN 102602535A
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Abstract
The invention relates to the field of unmanned aircrafts, in particular to a double-engine rotor-wing unmanned aerial vehicle system. The double-engine rotor-wing unmanned aerial vehicle system consists of a power transmission system (1), a rotor-wing system (2), a machine body (3), a flight control system (4), a power supply and distribution system (5), a ground control center (6) and a communication link system (7), wherein the power transmission system (1) comprises two engines (101) and a main gearbox (102), the main gearbox (102) and the rotor-wing system (2) are synchronously driven by the two engines (101), when one engine (101) does not work, and the main gearbox (102) and the rotor-wing system (2) are still driven by the other engine (101) independently, so that the normal operation of the unmanned aerial vehicle system is ensured. The double-engine rotor-wing unmanned aerial vehicle system has the beneficial effects that the probability of the accident of the rotor-wing unmanned aerial vehicle caused by the fault of the engines is reduced greatly, and the safety and the reliability of the rotor-wing unmanned aerial vehicle system are improved.
Description
Technical field
The present invention relates to driverless operation aviation aircraft field, particularly a kind of rotor wing unmanned aerial vehicle with double engines system.
Background technology
Unmanned plane technical development in recent years is rapid, and its use field not only has been confined to military use, and beginning is used for many other fields such as emergency response, transport administration, water conservancy management, electric power line walking, environmental monitoring gradually.
Engine or driving engine are the major parts that thrust power or bearing capacity are provided for unmanned plane, are the hearts of unmanned plane, the especially support of rotor wing unmanned aerial vehicle work.And at present on the world market rotor wing unmanned aerial vehicle system all only adopt single driven by engine, the place one's entire reliance upon quality of engine of flight safety exists certain potential safety hazard for practical application.
Summary of the invention
The technical matters that the present invention will solve is based on the security hidden trouble of single engine rotor wing unmanned aerial vehicle, on principle, improves its safety and reliability greatly.
The technical solution adopted for the present invention to solve the technical problems is: a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system comprises the power drive system of being made up of two engines 101 and main-gear box 102 1; Two engine 101 driven in synchronism main-gear boxs 102 and rotor system 2; When an engine 101 is not worked, but another engine 101 still individual drive main-gear box 102 and rotor system 2 ensure the normal operation of UAS, will reduce to minimum because of the accident probability that engine failure causes thus.
A kind of rotor wing unmanned aerial vehicle with double engines system; Form by power drive system 1, rotor system 2, fuselage 3, flight control system 4, electric power supply and distribution system 5, ground control center 6 and communication link system 7; It is characterized in that: power drive system 1 is made up of two engines 101 and a main-gear box 102; Each engine 101 is individual drive main-gear box 102 and rotor system all, but when an engine 101 is not worked unmanned plane normal operation still.Power drive system 1 adopts turbo-shaft engine 101 and corresponding oil piping system and fuel tank to be equipped with.Main-gear box 102 has driving adaptation mechanism with double engines, and during driven in synchronism, engine speed needn't be consistent, and single engine can individual drive.Engine control unit 112 flows into engine 101 through fuel charger 108 control fuel oils, and two fuel chargers 108 are arranged below fuselage 3, and each turbine engine 101 is equipped with a fuel charger 108.
Be positioned at fuselage 3 anterior load cabins 301 and various useful load 8 equipment can be installed, comprise sensors such as digital camera, laser radar, pick up camera, positioning and directing equipment with the mount point 305 under the fuselage 3.Fuselage 3 is divided into 3a of fuselage portion and afterbody 3b, and two parts are detachable, is easy to carrying.
Electric power supply and distribution system 5 comprise the electrical generator 501 that a turbo-shaft engine 101 drives; To three unmanned plane storage batterys 502 power supply is provided; Wherein two storage batterys 502 are supplied power to UAS; Another piece is cargo-carring useful load 8 power supplies of unmanned plane, and the electric system of UAS and useful load 8 adopts relatively independent circuit, and storage battery 502 is in charge condition always.
A kind of rotor wing unmanned aerial vehicle with double engines of the present invention system, the flight time was not less than 2 hours, and the flight time is determined by factors such as amount of fuel, load weight.
The beneficial effect of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system is: greatly reduced rotor wing unmanned aerial vehicle because of engine failure causes the probability of accident, improved the safety and the reliability of rotor wing unmanned aerial vehicle system.The present invention provides a stable rotor wing unmanned aerial vehicle platform for realizing tasks such as emergency response, transport administration, water conservancy management, electric power line walking, environmental monitoring.
Description of drawings
Fig. 1 is system's composition diagram of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system.
Fig. 2 is the front elevation of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system.
Fig. 3 is the lateral plan of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system.
Fig. 4 is fuselage 3 scheme drawings of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system.
Fig. 5 is the schematic diagram of the function of power drive system 1 of the present invention.
Fig. 6 is the scheme drawing of power drive system 1 of the present invention.
Fig. 7 is the schematic diagram of the function of electric power supply of the present invention and distribution system 5.
The specific embodiment
The specific embodiment below in conjunction with accompanying drawing contrast invention is done detailed explanation, set forth some details in the following description so that make much of the present invention, but the present invention can also implement through being different from other modes described here.
Fig. 1 is system's composition diagram of a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system, and a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system comprises power drive system 1, rotor system 2, fuselage 3, flight control system 4, electric power supply and distribution system 5, ground control center 6 and communication link system 7.As shown in Figures 2 and 3, a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system comprises the main rotor of being made by carbon-fiber composite material 201 and empennage 202.Load cabin 301 is positioned at the head section of unmanned plane, can be used for installing Miniature Sensors such as digital camera, pick up camera.Electronic compartment 302 is positioned at fuselage 3 front portions, 301 back, load cabin, and electronic machines such as flight control system 4, engine control unit 112, power control unit just are integrated in here.System also comprises an integral tank 303, circuit control panel 307, source switch 504, a fixing alighting gear 304 and the mount point 305 of external sense equipment is installed.Be positioned at the power control unit of electronic compartment 302 and the circuit control panel 307 in fuselage 3 left sides power distribution control is provided.The engine control unit 112 that is positioned at electronic compartment 302 provides the automatic management of two engines 101, comprises starting and closing, and fuel-flow control.The fuel liquid level meter 306 in fuselage 3 left sides is used to show current amount of fuel.
Because UAS often need be transported to different regions and execute the task, transportation means is generally ordinary traffic instruments such as automobile, ship, train, and its space is limited; Can't hold oversize unmanned aerial vehicle body, therefore, a kind of rotor wing unmanned aerial vehicle with double engines of the present invention system is designed to dismountable structure with fuselage 3; Be divided into 3a of fuselage portion and afterbody 3b; As shown in Figure 4, two parts are separable, are easier to carrying.
Flight control system 4 is supported following four kinds of offline mode: manually control offline mode; The assisting in flying pattern is promptly used handle, keyboard and mouse or radio telecommand (remote control equipment (RCE)) to assist and is positioned and speed control; The operation flight pattern is promptly according to predefined route planning autonomous flight; Backtrack mode, promptly unmanned plane comes back to the base automatically.In flight course; Can cancel ongoing aerial mission at any time, transfer handle control to, come back to the base or reformulate flight planning in control center; When the extraordinary circumstances of data communication interruption occurring, unmanned function is calculated Fuel Oil Remaining automatically and is independently come back to the base.
As shown in Figure 6; A kind of rotor wing unmanned aerial vehicle with double engines of the present invention system is furnished with two turbo-shaft engines 101; Be left engine 1011 and right engine 1012; These two turbo-shaft engines 101 are identical with the principle of work of comprehensive turbine system, are made up of main gas generator turbine 103, inferior turbo-machine 104, freeing pipe 105, motor drive 106, cooling vessel 107 and the change speed gear box that drives unmanned plane main-gear box 102.Main-gear box 102 has driving adaptation mechanism with double engines, and during driven in synchronism with double engines, the rotating speed of two engines needn't be consistent, and under special circumstances, single engine also can individual drive.
Fig. 5 is the schematic diagram of the function of power drive system 1.Engine 101 is made up of engine control unit 112, fuel charger 108 and fuel oil strainer 110 that both sides are provided with valve 111 respectively with related system.Consider that from safety factor cross when low or too high when the exhaust temperature of freeing pipe 105, valve 111 will be closed engine 101.Valve 111 not with fuel charger 108 common circuits, be provided with special independent circuits.
Power drive system 1 is made up of two engines 101 and a main-gear box 102.Each engine 101 is individual drive main-gear box 102 and rotor system 2 all, but unmanned plane normal operation still when an engine is not worked like this.Power drive system 1 Mechanical Driven main rotor 201 and empennage 202.Five servomotors 109 are further controlled rotor system: 201, one servomotors of four servomotors 109 control main rotors, 109 control empennages 202.
Fig. 7 is the schematic diagram of the function of electric power supply and distribution system 5.Electric power supply and distribution system 5 normally are electrical generator 501 power supplies that driven by a turbo-shaft engine 101, and to three unmanned plane storage batterys 502 power supply are provided.This system converts the power supply of electrical generator 501 into 12 volts of straight-flow system power supplys through direct current transducer 503.Wherein two storage batterys 502 are to the UAS power supply, through switch 504 control autopilots 401, servomotor 109, left engine 1011 and right engine 1012 power supply states.Another piece storage battery 502 is cargo-carring capacity weight 8 power supplies.UAS and 8 electric system of cargo-carring capacity weight adopt relatively independent circuit, and storage battery 502 is in charge condition always.
Communication link system 7 is integrated three radio links comprise video links and the safe frequency hopping wireless radio link between remote control equipment (RCE) and the unmanned plane between data communication link, unmanned plane and the ground control center 6 between ground control system 6 and the flight control system 4.
Claims (10)
1. rotor wing unmanned aerial vehicle with double engines system; Form by power drive system (1), rotor system (2), fuselage (3), flight control system (4), electric power supply and distribution system (5), ground control center (6) and communication link system (7); It is characterized in that: power drive system (1) is made up of two engines (101) and a main-gear box (102); Each engine (101) is individual drive main-gear box (102) and rotor system (2) all, at an engine (101) but UAS normal operation still when not working.
2. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system is characterized in that: adopt turbo-shaft engine (101) and corresponding oil piping system and fuel tank outfit.
3. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system, it is characterized in that: main-gear box (102) has driving adaptation mechanism with double engines, and during driven in synchronism, engine speed needn't be consistent, and single engine can individual drive.
4. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system, it is characterized in that: rotor system (2) comprises main rotor (201) and empennage (202), and blade is by the carbon-fiber composite material manufacturing.
5. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system; It is characterized in that: engine control unit (112) flows into turbine engine (101) through fuel charger (108) control fuel oil; At fuselage (3) two fuel chargers (108) are arranged, each turbine engine (101) is equipped with a fuel charger (108).
6. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system; Electric power supply and distribution system (5) comprise the electrical generator (501) that a turbo-shaft engine (101) drives; It is characterized in that: electrical generator (501) provides power supply to three unmanned plane storage batterys (502); Wherein two storage batterys (502) are supplied power to UAS; Another piece is the cargo-carring capacity weight of unmanned plane (8) power supply, and the electric system of UAS and capacity weight (8) adopts relatively independent circuit, and storage battery (502) is in charge condition always.
7. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system; Ground control center (6) comprises antenna equipment and memory storage of a control computer, remote control equipment (RCE), modulatedemodulate depressor, data link system etc.; It is characterized in that: the said equipment is contained in the crash-resistant chest, makes ground control center (6) possess mobility.
8. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system is characterized in that: various useful loads (8) equipment can be installed being positioned at fuselage (3) anterior load cabin (301) and the mount point (305) under the fuselage (3).
9. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system, it is characterized in that: fuselage (3) is divided into fuselage portion (3a) and afterbody (3b), and two parts are detachable, is easy to carrying.
10. a kind of rotor wing unmanned aerial vehicle with double engines according to claim 1 system, it is characterized in that: the flight time of UAS was not less than 2 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN2012100966963A CN102602535A (en) | 2012-04-05 | 2012-04-05 | Double-engine rotor unmanned aerial vehicle system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN2012100966963A CN102602535A (en) | 2012-04-05 | 2012-04-05 | Double-engine rotor unmanned aerial vehicle system |
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| CN102602535A true CN102602535A (en) | 2012-07-25 |
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| CN2012100966963A Pending CN102602535A (en) | 2012-04-05 | 2012-04-05 | Double-engine rotor unmanned aerial vehicle system |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105270619A (en) * | 2015-10-27 | 2016-01-27 | 中航维拓（北京）科技有限责任公司 | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle |
| CN106892108A (en) * | 2015-12-21 | 2017-06-27 | 深圳市鼎创旭飞科技有限公司 | Police extinguishing device |
| CN108885463A (en) * | 2017-02-27 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Long-range control method, equipment and the system of unmanned plane |
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| CN101710732A (en) * | 2009-11-11 | 2010-05-19 | 北京航空航天大学 | Unmanned helicopter continuous voltage-stabilizing power supply system with engine air restarting function |
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2012
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Patent Citations (7)
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| KR20010112782A (en) * | 2000-06-15 | 2001-12-22 | 이균휴 | Pilotless helicopter for filming |
| WO2007086906A2 (en) * | 2005-05-31 | 2007-08-02 | Sikorsky Aircraft Corporation | Variable speed transmission for a rotary wing aircraft |
| CN200976108Y (en) * | 2006-11-24 | 2007-11-14 | 中国科学院沈阳自动化研究所 | Small-size unmanned helicopter is flight control system independently |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN105270619A (en) * | 2015-10-27 | 2016-01-27 | 中航维拓（北京）科技有限责任公司 | Oil-drive variable-pitch quad-rotor unmanned aerial vehicle |
| CN106892108A (en) * | 2015-12-21 | 2017-06-27 | 深圳市鼎创旭飞科技有限公司 | Police extinguishing device |
| CN108885463A (en) * | 2017-02-27 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Long-range control method, equipment and the system of unmanned plane |
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Address after: 100081 room 7016, building 683, science and technology building, No. 5 South Main Street, Beijing, Haidian District, Zhongguancun Applicant after: Tang Liang Address before: 100101 Beijing city Chaoyang District Datun Road Theo center B block 19 layer Applicant before: Tang Liang |
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Application publication date: 20120725 |