CN201712787U - Electric tilt rotor unmanned aircraft - Google Patents
Electric tilt rotor unmanned aircraft Download PDFInfo
- Publication number
- CN201712787U CN201712787U CN2010202475356U CN201020247535U CN201712787U CN 201712787 U CN201712787 U CN 201712787U CN 2010202475356 U CN2010202475356 U CN 2010202475356U CN 201020247535 U CN201020247535 U CN 201020247535U CN 201712787 U CN201712787 U CN 201712787U
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Abstract
The utility model relates to an electric tilt rotor unmanned aircraft. Rotor rotating shafts are connected on ducts of an aircraft body with rotor ducts in the center; positioning carbon plate shelves are arranged in the centers of the rotor rotating shafts; power motors are respectively installed at the upper end lower ends of the positioning carbon plate shelves; the two power motors are respectively and correspondingly connected with an upper rotor and a lower rotor through gears; and the rotating shafts of the upper rotor and the lower rotor are coaxially fixed in the centers of the positioning carbon plate shelves. The electric tilt rotor unmanned aircraft has the benefits that firstly, the problem of the side-turning over of an aircraft as a left tilt rotor and a right tilt rotor in the prior art are easy to cause uneven lift force is effectively overcome; secondly, the stability of flight mode conversion of the aircraft is ensured during rotor tilting; and thirdly, the attitude of the aircraft in hovering and flight modes can be conveniently controlled through the flexible combination of four attitude control flaps and the adjustment of rotor rotate speed.
Description
Technical field
The utility model relates to a kind of unmanned plane, relates in particular to a kind of electric tilting rotor wing unmanned aerial vehicle.
Background technology
Unmanned plane all obtains widespread use and develop rapidly in the army and the people field in recent years because of the application of its uniqueness, is also representing an important development direction of following aviation.In various unmanned plane schemes, tilting rotor wing unmanned aerial vehicle is being taken into account flying speed, landing and the operator's mask that hovers has good comprehensive advantage, but existing tilting rotor wing unmanned aerial vehicle also exists some to be not so good as the people's will part aspect control stiffness, the quiet feature of environmental protection and the economy.The electric tilting rotor wing unmanned aerial vehicle of the present invention research can effectively improve aircraft flight controlling stability, airworthiness and environmental protection and economy by the power scheme of employing later-model electronic " push away oar+co-axial rotor verts ".
Summary of the invention
The purpose of this utility model is to provide a kind of electric tilting rotor wing unmanned aerial vehicle, adopts electronic " pushing away oar+tilting rotor " power scheme, has the advantage of depopulated helicopter and unmanned fixed wing aircraft concurrently, can realize vertical takeoff and landing, hover operation and fast before fly.Compare with depopulated helicopter, owing to adopted uncoupled power-driven system, for Design of Flight Control has been brought facility; Compare with common tilting rotor wing unmanned aerial vehicle, stay the coaxial rotor of verting of fuselage central authorities, can effectively prevent the unstability of turning on one's side, rotor verts before and when verting, adopt the tail-rotor additional thrust, help rotor the steady of process that vert owing to adopt; Adopt multiple spot electric propulsion power system, power and control stabilization are reliable, and be simple in structure, quiet environmental protection.
The utility model is achieved like this, it comprises that central authorities have the fuselage of rotor duct, the rotor S. A., the location carbon plate shelf, power motor, last rotor, following rotor, the steering wheel servomechanism, the steering wheel rocking bar, aspect control rudder, rotor upset servomechanism, advance propeller, it is characterized in that central authorities have on the duct of fuselage of rotor duct is connected with the rotor S. A., the intracardiac location carbon plate shelf that is provided with in the rotor S. A., on the carbon plate shelf of location, the lower end is separately installed with power motor, two power motors are gone up rotor and following rotor by corresponding respectively connection of gear, the rotating shaft coaxle of last rotor and following rotor is fixed on the center of location carbon plate shelf, the left side of location carbon plate shelf, the right side connects two steering wheel servomechanisms respectively, the steering wheel servomechanism connects aspect control rudder by the steering wheel rocking bar, the side of one aspect control rudder is connected with rotor upset servomechanism, and the afterbody that central authorities have the rotor duct is provided with the propelling propeller.
Technique effect of the present utility model is: 1, adopt a coaxial reverse rotor that is opposite to fuselage central authorities, can effectively overcome traditional about two tilting rotors cause the uneven and problem of the aircraft rollover that produces of lift easily; 2, before rotor verts, adopt the thrust that advances propeller to carry out preacceleration and in the process of verting, keep necessity, guarantee the stability of aircraft flight MODAL TRANSFORMATION OF A when rotor verts; 3, the flexible combination that can be by four aspects control rudders and the adjusting of gyroplane rotate speed are controlled aircraft very easily and are being hovered and attitude during state of flight.
Description of drawings
Fig. 1 has the structural representation of the fuselage of rotor duct for the utility model central authorities.
Fig. 2 is a structural representation of the present utility model.
In the drawings, 1, central authorities have the rotor duct fuselage 2, rotor S. A. 3, location carbon plate shelf 4, power motor 5, go up rotor 6, down rotor 7, steering wheel servomechanism 8, steering wheel rocking bar 9, aspect control rudder 10, rotor upset servomechanism 11, advance propeller
The specific embodiment
As Fig. 1, shown in Figure 2, the utility model is achieved like this, central authorities have on the duct of fuselage 1 of rotor duct and are connected with rotor S. A. 2, the intracardiac location carbon plate shelf 3 that is provided with in the rotor S. A. 2, on the carbon plate shelf 3 of location, the lower end is separately installed with power motor 4, two power motors 4 are gone up rotor 5 and following rotor 6 by corresponding respectively connection of gear, the rotating shaft coaxle of last rotor 5 and following rotor 6 is fixed on the center of location carbon plate shelf 3, the left side of location carbon plate shelf 3, the right side connects two steering wheel servomechanisms 7 respectively, steering wheel servomechanism 7 connects aspect control rudder 9 by steering wheel rocking bar 8, the side of one aspect control rudder 9 is connected with rotor upset servomechanism 10, and fuselage 1 afterbody that central authorities have the rotor duct is provided with propelling propeller 11.
Now sketch the specific embodiment of the present invention in conjunction with the typical flight course of aircraft " take off vertically------flying the fast---vertical landing of hovering ".
(1) take off vertically: this moment, rotorshaft was in vertical state, two rotor constant speed counter-rotatings, and afterbody advances propeller not work, and rotor rotates the lift that produces vertically upward, aircraft vertical uplift.
(2) hover: when VUAV take off reach predetermined altitude after, thereby make lift equate to be in floating state with aircraft gravity by the control gyroplane rotate speed, for the stability that guarantees the hang state is being equipped with attitude coutrol mechanism in the middle of the rotor up and down---attitude control rudder, as shown in Figure 2.Above attitude control rudder, current plate is arranged, when about four control rudders rotate forward synchronously or the certain angle that rotates backward after, the effect that is subjected to the downward air-flow that rotor produces can realize pitch control subsystem.After turning an angle respectively before and after two control rudders of a side, can block a side direction downstream and change this side lift size, realize rolling control.When left and right sides control rudder rotates simultaneously in the opposite direction, can make the yaw angle about aircraft produces.Also can pass through above the change or the rotating speed of following rotor, make aircraft produce the driftage moment of torsion, the original place rotates, the control of realization course.
(3) fly before fast: the afterbody propeller is started working when VUAV will fly state before floating state forwards to, promoting aircraft flies forward, when reaching certain forward flight speed, wing produces certain lift, overturn forward when rotor and attitude coutrol mechanism can be opened under the drive of upset control motor this moment, the lift of loss when wing produces lift and compensates rotor and vert when being flown forward by aircraft.Rotor all is used for producing aircraft thrust forward when rotorshaft forwards level attitude to, and aircraft flies before beginning fast.Because VUAV adopted the tail-rotor propelling, so aircraft has possessed certain forward flight speed when rotor overturn, promptly wing has produced a part of lift, so the process that flies before the full speed of hovering is more stable, and manipulation easily.
Rotor inclines when turning 90 degrees, and the control rudder also rotates 90 degree with axle.When about after four control rudders upwards rotate synchronously or rotate certain angle, the effect of the air-flow that is subjected to flying can realize pitch control subsystem.After two control rudders of a side turn an angle respectively up and down, can realize course control.When left and right sides control rudder rotates simultaneously in the opposite direction, can realize the control of rolling.
(4) vertical landing: this moment rotor in the control turning down of upset motor, produce lift upwards, the loss that the airfoil lift that the speed that remedied reduces to bring reduces.The afterbody propeller stops the rotation after rotorshaft goes back to vertical state, and the aircraft forward flight speed reduces gradually, and the lift of aircraft changed by rotor and produced this moment.The revolution that reduces rotor can reduce the lift aircraft and begin vertical decline, realizes vertical landing.
Claims (1)
1. electric tilting rotor wing unmanned aerial vehicle, it comprises that central authorities have the fuselage of rotor duct, the rotor S. A., the location carbon plate shelf, power motor, last rotor, following rotor, the steering wheel servomechanism, the steering wheel rocking bar, aspect control rudder, rotor upset servomechanism, advance propeller, it is characterized in that central authorities have on the duct of fuselage of rotor duct is connected with the rotor S. A., the intracardiac location carbon plate shelf that is provided with in the rotor S. A., on the carbon plate shelf of location, the lower end is separately installed with power motor, two power motors are gone up rotor and following rotor by corresponding respectively connection of gear, the rotating shaft coaxle of last rotor and following rotor is fixed on the center of location carbon plate shelf, the left side of location carbon plate shelf, the right side connects two steering wheel servomechanisms respectively, the steering wheel servomechanism connects aspect control rudder by the steering wheel rocking bar, the side of one aspect control rudder is connected with rotor upset servomechanism, and the afterbody that central authorities have the rotor duct is provided with the propelling propeller.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202475356U CN201712787U (en) | 2010-07-05 | 2010-07-05 | Electric tilt rotor unmanned aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010202475356U CN201712787U (en) | 2010-07-05 | 2010-07-05 | Electric tilt rotor unmanned aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201712787U true CN201712787U (en) | 2011-01-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010202475356U Expired - Fee Related CN201712787U (en) | 2010-07-05 | 2010-07-05 | Electric tilt rotor unmanned aircraft |
Country Status (1)
| Country | Link |
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| CN (1) | CN201712787U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101879945A (en) * | 2010-07-05 | 2010-11-10 | 南昌航空大学 | Electric tilting rotor wing unmanned aerial vehicle |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
| CN103231803A (en) * | 2013-04-27 | 2013-08-07 | 哈尔滨飞机工业集团有限责任公司 | Small unmanned aircraft configuration |
| CN105539839A (en) * | 2015-12-30 | 2016-05-04 | 北京航空航天大学 | Miniature mechanical sliding rail type controllable flapping rotor craft |
| CN106502262A (en) * | 2015-09-08 | 2017-03-15 | 中国农业机械化科学研究院 | A kind of agricultural unmanned plane during flying platform and its control system and control method |
| CN107651188A (en) * | 2017-09-26 | 2018-02-02 | 孟凡星 | A kind of military anti-transport ship unmanned plane |
| US10839336B2 (en) | 2013-12-26 | 2020-11-17 | Flir Detection, Inc. | Unmanned delivery |
-
2010
- 2010-07-05 CN CN2010202475356U patent/CN201712787U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101879945A (en) * | 2010-07-05 | 2010-11-10 | 南昌航空大学 | Electric tilting rotor wing unmanned aerial vehicle |
| CN103129737A (en) * | 2013-03-27 | 2013-06-05 | 南京傲翼伟滕自动化科技有限公司 | Inclined fixed wing unmanned plane |
| CN103231803A (en) * | 2013-04-27 | 2013-08-07 | 哈尔滨飞机工业集团有限责任公司 | Small unmanned aircraft configuration |
| US10839336B2 (en) | 2013-12-26 | 2020-11-17 | Flir Detection, Inc. | Unmanned delivery |
| CN106502262A (en) * | 2015-09-08 | 2017-03-15 | 中国农业机械化科学研究院 | A kind of agricultural unmanned plane during flying platform and its control system and control method |
| CN105539839A (en) * | 2015-12-30 | 2016-05-04 | 北京航空航天大学 | Miniature mechanical sliding rail type controllable flapping rotor craft |
| CN107651188A (en) * | 2017-09-26 | 2018-02-02 | 孟凡星 | A kind of military anti-transport ship unmanned plane |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110119 Termination date: 20120705 |