CN102514712A - Vertical take-off and landing aircraft - Google Patents
Vertical take-off and landing aircraft Download PDFInfo
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- CN102514712A CN102514712A CN2011104012714A CN201110401271A CN102514712A CN 102514712 A CN102514712 A CN 102514712A CN 2011104012714 A CN2011104012714 A CN 2011104012714A CN 201110401271 A CN201110401271 A CN 201110401271A CN 102514712 A CN102514712 A CN 102514712A
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Abstract
The invention relates to a vertical take-off and landing aircraft comprising a wing, motors, screw propellers, a lithium battery, electronic speed regulators, a signal processing machine, elevation rudders, undercarriages, direction rudders, vertical empennages, and steering gears. According to the invention, with a fixed-wing vertical take-off and landing technology, the aircraft can take off vertically like a helicopter, can hover in the air, and can conduct high-speed cruising like a fixed-wing. The aircraft adopts a non-fuselage twin-finned empennage layout. The aircraft is advantaged in simple structure and simple layout, such that the aircraft can easily obtain a good aerodynamic performance.
Description
Technical field
The present invention relates to a kind of unmanned vehicle, especially a kind of can VTOL and the no fuselage tail sitting posture vertically taking off and landing flyer of flight fast.
Background technology
At present, the flying robot is bringing into play more and more important effect in multiple fields such as military and civilians, some or even irreplaceable.The development of flying robot's Along with computer technology, the communication technology and the Eltec etc. of all size and type and flourish.
Present existing aircraft is divided if press the type of wing, is broadly divided into two big types of fixed wing aircraft (for example common airline carriers of passengers, fighter plane etc.) and rotary wing aircrafts (helicopter).These two types of aircraft all have the similar wing of cross-sectional plane, and realize that just wing is different with the mode that air produces relative motion: fixed wing aircraft relies on engine to promote, and aircraft is moved in the air high speed, and wing and air produce relative fortune to obtain lift.Therefore, need long runway when the existing fixed wing aircraft takes off,, and also must keep enough flying speeds aloft so that aircraft can could obtain enough lift and take off from the static certain speed that accelerates to.And rotary wing aircraft (helicopter) relies on engine that rotor is rotated around S. A.; Make rotor and air produce relative motion and obtain to take off required lift; Need not on runway, to slide and can take off vertically, and aloft can hover, vertical lift, forwards, backwards about flight.Fixed wing aircraft has reliably, at a high speed, advantage such as high-altitude, load carrying ability be big; Be widely used in multiple field; But little in some landing places, not quite high to rate request or need aloft hover for a long time occasion, rotary wing aircraft has then obtained using widely.
Because fixed-wing flying robot and the traditional application of cyclogyro in some specific occasions have certain limitation, closely emerge some later-model flying robots, the application of particularly VTOL technology on the flying robot twenty or thirty year.
The accurate definition of vertically taking off and landing flyer (VTOL) is: can take off with zero velocity/land, possess hover capabilities, and can be with the mode horizontal flight of fixed-wing flight.Compare with conventional airplane, vertically taking off and landing flyer does not have dependence to runway, and has the advantage that can hover, compares with conventional helicopters, and vertically taking off and landing flyer has much higher forward flight speed, and has bigger voyage.Just be based on these advantages, vertically taking off and landing flyer is particularly useful for hovering or landing site is had the occasion of specific (special) requirements.The experimental prototype type of early development is varied, comprises the tail sitting posture, the duct formula of verting, gaseous blast steering-type and jet lift engine type etc.The VTOL technology makes aircraft have to integrate the performance of helicopter and fixed-wing, the possibility of advantage.
Summary of the invention
The objective of the invention is to overcome existing above-mentioned deficiency; A kind of vertically taking off and landing flyer is provided; Take into account the characteristics of helicopter VTOL and fixed wing aircraft high-performance cruise, and simple in structure, power is simplified, is controlled flexibly, flight path is more level and smooth, still less restricted.
Based on above-mentioned purpose, the present invention realizes through following technical scheme:
A kind of vertically taking off and landing flyer comprises wing, elevating rudder and vertical tail, it is characterized in that: the anterior two ends of said wing are symmetrically installed with two motors respectively, and said motor connects two independently positive counter propellers respectively; The rotating that two electronic governors are used to control motor is equipped with in the inside of said wing; Signal processor of the internal fixation of said wing; Two said vertical tails are installed respectively under the afterbody of said wing and the screw propeller; Said two vertical tail afterbodys are respectively installed a yaw rudder respectively, and an alighting gear is respectively installed on the both sides, front and back of said two vertical tails respectively; Between said wing and vertical tail respectively symmetry two elevating rudders have been installed, and said elevating rudder is hinged with said wing mutually; Built-in lithium battery in the said wing inner chamber, and four steering wheels; Said four steering wheels drive described yaw rudder and elevating rudder respectively.Said two motors and four steering wheels drive by said lithium battery power supply.
Said wing, vertical tail and yaw rudder all adopt Transverse plane and longitudinal plane symmetric form to distribute and design.
The present invention has following conspicuous outstanding feature and significant advantage compared with prior art:
1) adopt no fuselage twin-finned layout, simple in structure, layout is succinct, helps aircraft acquisition better aerodynamic characteristics;
2) double-motor individual drive is simplified Poewr transmission mechanism, alleviates aircraft weight;
3) aircraft is symmetrical fully about Transverse plane and longitudinal plane; Help attitude of flight vehicle control;
4) twin vertical fin be distributed in screw propeller under because the effect of screw propeller purling, the attitude of flight vehicle adjustment is sensitiveer;
5) aircraft up-down rudder face and lift-over rudder face unite two into one, and reduce primary control surface, simplified topology;
6) can make the aircraft horizontal flight through regulating the up-down rudder face after aircraft takes off vertically.
Description of drawings
Fig. 1 is the structural representation of a kind of vertically taking off and landing flyer of the present invention;
Fig. 2 is the flight course scheme drawing of a kind of vertically taking off and landing flyer of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing and embodiment the present invention is further specified:
Embodiment: referring to Fig. 1, a kind of vertically taking off and landing flyer comprises wing 1, elevating rudder 7 and vertical tail 10.It is characterized in that: said wing 1 anterior two ends are symmetrically installed with two motors 2 respectively, and said motor 2 connects two independently positive counter propellers 3 respectively; The rotating that two electronic governors 5 are used to control motor 2 is equipped with in the inside of said wing 1; Signal processor 6 of the internal fixation of said wing 1; Be separately installed with two vertical tails 10 under the afterbody of said wing 1 and the screw propeller 3; Said vertical tail 10 afterbodys are installed both direction rudder 9 respectively, and four alighting gears 8 are installed on the both sides, front and back of said vertical tail 10 respectively; 10 of said wing 1 and vertical tails symmetry have respectively been installed two elevating rudders 7, and said elevating rudder 7 is hinged with said wing 1 mutually; Built-in lithium battery 4 in said wing 1 inner chamber, and four steering wheels 11; Said four steering wheels 11 drive described yaw rudder 9 and elevating rudder 7 respectively.Motor 2 that said screw propeller 3 links to each other and said steering wheel 11 all adopt lithium cell 4 to drive.Said wing 1, said vertical tail 10 all adopt symmetrical airfoil.
The working process of above-mentioned no fuselage tail sitting posture vertical take-off and landing unmanned aerial vehicle is: when taking off, four alighting gears 8 of vertically taking off and landing flyer land, and wing 1 is perpendicular to the ground; By lithium cell 4 CD-ROM drive motors 2, and drive screw propeller 3 rotations, produce pulling force upwards, overcome gravity and take off; After rising to certain altitude; Lithium cell 4 drives steering wheel 11, and drives up-down rudder face 7, regulates the up-down rudder face; Make aircraft before X, vert; Aircraft gets into vertically flight to the horizontal flight transition period, and the pulling force that produces along with screw propeller 3 changes horizontal flight power gradually into, and aircraft gets into the horizontal mission phase of high speed.When aircraft need land, be that lithium cell 4 drives elevating rudder 7 equally, regulate the up-down rudder face; Make aircraft behind X, vert; Aircraft gets into level to vertical flight transition period, and the horizontal flight power that provides along with screw propeller 3 changes pulling force upwards gradually into, and the lift that wing 1 produces reduces gradually; Lift that final screw propeller 3 produces and aircraft self gravitation are on a line, and aircraft is vertical landing slowly.Flight path in the longitudinal plane is as shown in Figure 2.When aircraft need be gone off course, can regulate the direction rudder face 9 of vertical tail 10 back through steering wheel 11.When aircraft needs rolling flight, can regulate the up-down rudder face 7 of wing 1 trailing edge through steering wheel 11.
Claims (3)
1. vertically taking off and landing flyer; Comprise wing (1), elevating rudder (7) and vertical tail (10); It is characterized in that: the anterior two ends of said wing (1) are symmetrically installed with two motors (2) respectively, and said motor (2) connects two independently positive counter propellers (3) respectively; The rotating that two electronic governors (5) are used to control motor (2) is equipped with in the inside of said wing (1); A signal processor of the internal fixation of said wing (1) (6); Have two described vertical tails (10) be installed in respectively said wing (1) afterbody and screw propeller (3) under; Said two vertical tails (10) afterbody is respectively installed a yaw rudder (9) respectively, and an alighting gear (8) is respectively installed on the both sides, front and back of said two vertical tails (10) respectively; Between said wing (1) and vertical tail (10) respectively symmetry two elevating rudders (7) have been installed, and said elevating rudder (7) is hinged with said wing (1) mutually; Built-in lithium battery (4) in said wing (1) inner chamber, and four steering wheels (11); Said four steering wheels (11) drive described both direction rudder (9) and two elevating rudders (7) respectively.
2. according to claims 1 described a kind of vertically taking off and landing flyer, it is characterized in that: motor (2) that said screw propeller (3) links to each other and said steering wheel (11) are all by said lithium cell (4) powered.
3. a kind of vertically taking off and landing flyer according to claim 1 is characterized in that: adopt no fuselage double tail layout, and said wing (1), vertical tail (10) and yaw rudder (9) adopt all Transverse plane and longitudinal plane to be symmetrically distributed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104012714A CN102514712A (en) | 2011-12-07 | 2011-12-07 | Vertical take-off and landing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011104012714A CN102514712A (en) | 2011-12-07 | 2011-12-07 | Vertical take-off and landing aircraft |
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| Publication Number | Publication Date |
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| CN102514712A true CN102514712A (en) | 2012-06-27 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN2011104012714A Pending CN102514712A (en) | 2011-12-07 | 2011-12-07 | Vertical take-off and landing aircraft |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287569A (en) * | 2013-05-15 | 2013-09-11 | 西北工业大学 | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering |
| CN103318410A (en) * | 2013-07-05 | 2013-09-25 | 西北工业大学 | Vertical take-off and landing micro aerial vehicle without control surface |
| CN105000174A (en) * | 2014-12-05 | 2015-10-28 | 上海交通大学 | Tiltrotor mixed multi-state aircraft with operational control surfaces |
| CN105173076A (en) * | 2015-09-29 | 2015-12-23 | 上海圣尧智能科技有限公司 | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) |
| CN106114817A (en) * | 2016-08-17 | 2016-11-16 | 优利科技有限公司 | A kind of aircraft and flight system |
| CN106364662A (en) * | 2016-10-19 | 2017-02-01 | 吴瑞霞 | Aircraft pitching, rollover and yaw control system |
| CN106379524A (en) * | 2016-09-23 | 2017-02-08 | 齐继国 | Aircraft with multiple vertical take-off and landing aircraft module units |
| CN106516097A (en) * | 2016-10-19 | 2017-03-22 | 吴瑞霞 | Unpiloted aircraft |
| CN106628162A (en) * | 2016-12-21 | 2017-05-10 | 曹萍 | Composite unmanned aerial vehicle |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107499513A (en) * | 2017-09-01 | 2017-12-22 | 无锡翼鸥科技有限公司 | Microminiature can hover Fixed Wing AirVehicle |
| CN108528717A (en) * | 2018-03-09 | 2018-09-14 | 王金瀚 | A kind of miniature Fixed Wing AirVehicle |
| CN108557075A (en) * | 2017-12-04 | 2018-09-21 | 中国人民解放军陆军工程大学 | Novel multi-drive vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN109159890A (en) * | 2018-10-29 | 2019-01-08 | 拓攻（南京）机器人有限公司 | A kind of single rotor vertically taking off and landing flyer |
| CN111532429A (en) * | 2020-05-09 | 2020-08-14 | 北京航空航天大学 | Miniature fixed wing unmanned aerial vehicle capable of being adsorbed on plane |
| CN112046740A (en) * | 2020-08-12 | 2020-12-08 | 南方科技大学台州研究院 | Vertical take-off and landing aircraft and flight method |
| CN112896501A (en) * | 2014-03-18 | 2021-06-04 | 杰欧比飞行有限公司 | Aircraft suitable for vertical take-off and horizontal flight |
| CN113232826A (en) * | 2021-05-07 | 2021-08-10 | 南京航空航天大学 | Vertical take-off and landing aircraft with vertical tail seat and control method thereof |
| WO2024156193A1 (en) * | 2023-01-29 | 2024-08-02 | 西华大学 | Fuselage structure and unmanned aerial vehicle having same |
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| CN102133926A (en) * | 2011-03-08 | 2011-07-27 | 上海大学 | Tailstock type vertical take-off and landing unmanned aerial vehicle |
| CN201923320U (en) * | 2011-01-13 | 2011-08-10 | 杨苡 | Twin-engine vertical take-off and landing fixed-wing unmanned aerial vehicle |
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Cited By (26)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103287569A (en) * | 2013-05-15 | 2013-09-11 | 西北工业大学 | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering |
| CN103287569B (en) * | 2013-05-15 | 2015-04-22 | 西北工业大学 | Lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in non-runway field and hovering |
| CN103318410A (en) * | 2013-07-05 | 2013-09-25 | 西北工业大学 | Vertical take-off and landing micro aerial vehicle without control surface |
| CN112896501B (en) * | 2014-03-18 | 2024-04-09 | 杰欧比飞行有限公司 | Aircraft suitable for vertical take-off and horizontal flight |
| CN112896501A (en) * | 2014-03-18 | 2021-06-04 | 杰欧比飞行有限公司 | Aircraft suitable for vertical take-off and horizontal flight |
| CN105000174A (en) * | 2014-12-05 | 2015-10-28 | 上海交通大学 | Tiltrotor mixed multi-state aircraft with operational control surfaces |
| CN105173076A (en) * | 2015-09-29 | 2015-12-23 | 上海圣尧智能科技有限公司 | VTOL (vertical take-off and landing) UAV (unmanned aerial vehicle) |
| CN106114817A (en) * | 2016-08-17 | 2016-11-16 | 优利科技有限公司 | A kind of aircraft and flight system |
| CN106379524A (en) * | 2016-09-23 | 2017-02-08 | 齐继国 | Aircraft with multiple vertical take-off and landing aircraft module units |
| CN106828916A (en) * | 2016-10-19 | 2017-06-13 | 吴瑞霞 | Unmanned vehicle |
| CN106628177A (en) * | 2016-10-19 | 2017-05-10 | 吴瑞霞 | Unmanned aerial vehicle |
| CN106516098A (en) * | 2016-10-19 | 2017-03-22 | 吴瑞霞 | Unpiloted aircraft |
| CN106364662A (en) * | 2016-10-19 | 2017-02-01 | 吴瑞霞 | Aircraft pitching, rollover and yaw control system |
| CN106516097A (en) * | 2016-10-19 | 2017-03-22 | 吴瑞霞 | Unpiloted aircraft |
| CN106628162A (en) * | 2016-12-21 | 2017-05-10 | 曹萍 | Composite unmanned aerial vehicle |
| CN107097949A (en) * | 2017-04-25 | 2017-08-29 | 河南三和航空工业有限公司 | A kind of VTOL fixed-wing unmanned plane |
| CN107499513A (en) * | 2017-09-01 | 2017-12-22 | 无锡翼鸥科技有限公司 | Microminiature can hover Fixed Wing AirVehicle |
| CN108557075B (en) * | 2017-12-04 | 2020-07-31 | 中国人民解放军陆军工程大学 | Multi-drive vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN108557075A (en) * | 2017-12-04 | 2018-09-21 | 中国人民解放军陆军工程大学 | Novel multi-drive vertical take-off and landing fixed wing unmanned aerial vehicle |
| CN108528717A (en) * | 2018-03-09 | 2018-09-14 | 王金瀚 | A kind of miniature Fixed Wing AirVehicle |
| CN109159890A (en) * | 2018-10-29 | 2019-01-08 | 拓攻（南京）机器人有限公司 | A kind of single rotor vertically taking off and landing flyer |
| CN109159890B (en) * | 2018-10-29 | 2023-06-09 | 南京拓兴智控科技有限公司 | Single rotor vertical take-off and landing aircraft |
| CN111532429A (en) * | 2020-05-09 | 2020-08-14 | 北京航空航天大学 | Miniature fixed wing unmanned aerial vehicle capable of being adsorbed on plane |
| CN112046740A (en) * | 2020-08-12 | 2020-12-08 | 南方科技大学台州研究院 | Vertical take-off and landing aircraft and flight method |
| CN113232826A (en) * | 2021-05-07 | 2021-08-10 | 南京航空航天大学 | Vertical take-off and landing aircraft with vertical tail seat and control method thereof |
| WO2024156193A1 (en) * | 2023-01-29 | 2024-08-02 | 西华大学 | Fuselage structure and unmanned aerial vehicle having same |
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Application publication date: 20120627 |