CN105173075B - A kind of hybrid power can tilt wing aircraft - Google Patents
A kind of hybrid power can tilt wing aircraft Download PDFInfo
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- CN105173075B CN105173075B CN201510574196.XA CN201510574196A CN105173075B CN 105173075 B CN105173075 B CN 105173075B CN 201510574196 A CN201510574196 A CN 201510574196A CN 105173075 B CN105173075 B CN 105173075B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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Abstract
The present invention relates to aircraft field, more particularly to a kind of hybrid power can tilt wing aircraft, the present invention is combined by electronic many rotor module and aero-engine fixed-wing modules, two movable tilting wings are in plumbness during takeoff phase, be changed into plumbness hybrid power can be provided can maximum lift of tilt wing aircraft when taking off, four rotors keep fuselages it is stable make hybrid power can tilt wing aircraft steadily rise, when the height cruise needed for rising to, two movable tilting wings are changed into horizontality, four rotors are packed up, reduce air drag, so that hybrid power can tilt wing aircraft safety and stability flight, fixed wing aircraft and the respective advantage of many gyroplanes are played, it is i.e. low to the site requirements taken off and landed, it is reliable and stable during cruise, the dynamic mode of oily electricity mixing, the dynamic mode needed can be selected when using according to actual conditions, the effect for saving the energy is reached.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of hybrid power can tilt wing aircraft.
Background technology
Existing aircraft mainly includes two kinds of fixed-wings and many rotors, wherein fixed gyroplane mainly includes two big
Fixed-wing, can take off vertically, vertical landing and forward flight, and flight safety is stable, but fixed wing aircraft is generally required for
There is longer runway to provide the power taken off, take off limited.Many gyroplanes provide the power taken off, Er Qieke without runway
To stagnate in the air, but the flight of many gyroplanes is unstable, and safety coefficient is low.
The content of the invention
The purpose of the present invention be overcome prior art exist defect there is provided do not limited during a kind of takeoff and landing by place
System, the hybrid power of safety and steady can tilt wing aircraft during cruise.
Realizing the technical scheme of the object of the invention is：A kind of hybrid power can tilt wing aircraft, it is including main machine body, electronic many
Rotor module, aero-engine fixed-wing module, flight-control computer and empennage, flight-control computer are arranged on main machine body
On, empennage is arranged on the afterbody of main machine body, and electronic many rotor modules include four hydraulic actuators and four rotors, four hydraulic pressure
One group of actuator two is separately mounted to the front-end and back-end of main machine body, and rotor includes brushless electric machine, two leaves and folds oar, carbon fiber
Support and rack joint bearing, two leaves fold oar and are arranged on brushless electric machine, and brushless electric machine is arranged on the end of carbon fiber support,
Carbon fiber support is symmetrically fixed on the left and right sides of main machine body by rack joint bearing, and four hydraulic actuators are connected respectively
In four carbon fiber supports, four rotors are respectively by four hydraulic actuator expansion with packing up；Aero-engine fixed-wing
Module includes two movable tilting wings, wing root bearing, two aero-engine propellers and wing and verted hydraulic actuator, two
Individual movable tilting wing is fixed on the middle part of main machine body by wing root bearing, and two aero-engine propellers are separately mounted to two
On individual movable tilting wing, wing verts hydraulic actuator on the wing root bearing, and the wing hydraulic actuator that verts is acted on
Wing root bearing makes two movable tilting wings be changed into horizontally or vertically state.
As the prioritization scheme of the present invention, electronic many rotor modules provide power by lithium battery.
As the prioritization scheme of the present invention, the end of two aero-engine propellers is respectively mounted driving aero-engine
The fuel engines of propeller rotation.
As the present invention prioritization scheme, hybrid power can tilt wing aircraft also include control hybrid power can vert the wing fly
The Vertical Square guide vane turned during machine flight, Vertical Square guide vane is arranged on the rear top of main machine body.
The present invention has positive effect：The present invention passes through electronic many rotor module and aero-engine fixed-wing module knots
Close, two movable tilting wings are in plumbness during takeoff phase, be changed into plumbness hybrid power can be provided can verting the wing
Maximum lift when taking off, four rotors keep fuselages it is stable make hybrid power can tilt wing aircraft steadily rise, when upper
When height needed for being raised to is cruised, two movable tilting wings are changed into horizontality, and four rotors are packed up, and reduce air drag,
So that hybrid power can tilt wing aircraft safety and stability flight, the present invention has played fixed wing aircraft and many gyroplanes are each
From advantage, i.e., it is low to the site requirements taken off and landed, cruise when it is reliable and stable, oil electricity mixing dynamic mode, make
Used time can select the dynamic mode needed according to actual conditions, reach the effect for saving the energy.
Brief description of the drawings
In order that present disclosure is easier to be clearly understood, it is right below according to specific embodiment and with reference to accompanying drawing
The present invention is described in further detail, wherein：
Fig. 1 be hybrid power can tilt wing aircraft structure chart；
Fig. 2 be hybrid power can tilt wing aircraft takeoff phase schematic diagram；
Fig. 3 be hybrid power can tilt wing aircraft boost phase schematic diagram；
Fig. 4 be hybrid power can tilt wing aircraft cruising phase schematic diagram.
Wherein, 1, main machine body, 4, flight-control computer, 5, empennage, 21, hydraulic actuator, 22, brushless electric machine, 23, two
Leaf folds oar, and 24, carbon fiber support, 25, rack joint bearing, 31, movable tilting wing, 32, wing root bearing, 33, aviation hair
Motivation propeller, 34, wing vert hydraulic actuator, 35, fuel engines, 6, Vertical Square guide vane.
Embodiment
As shown in figure 1, can tilt wing aircraft, including main machine body 1, electronic many rotors the invention discloses a kind of hybrid power
Module, aero-engine fixed-wing module, flight-control computer 4 and empennage 5, wherein, flight-control computer 4 is arranged on master
On fuselage 1, empennage 5 is arranged on the afterbody of main machine body 1, and electronic many rotor modules include four hydraulic actuators 21 and four rotations
The wing, four one group of hydraulic actuators 21 two are separately mounted to the front-end and back-end of main machine body 1, rotor include brushless electric machine 22,
Two leaves fold oar 23, carbon fiber support 24 and rack joint bearing 25, and two leaves fold oar 23 and are arranged on brushless electric machine 22, brushless
Motor 22 is arranged on the end of carbon fiber support 24, and carbon fiber support 24 is symmetrically fixed on main frame by rack joint bearing 25
The left and right sides of body 1, four hydraulic actuators 21 are connected in four carbon fiber supports 24, and four rotors pass through four respectively
The individual expansion of hydraulic actuator 21 is with packing up；Aero-engine fixed-wing module includes two movable tilting wings 31, wing root bearings
32nd, two aero-engine propellers 33 and wing vert hydraulic actuator 34, and two movable tilting wings 31 pass through wing root axle
32 middle parts for being fixed on main machine body 1 are held, two aero-engine propellers 33 are separately mounted on two movable tilting wings 31,
Wing verts hydraulic actuator 34 on the wing root bearing 32, and the wing hydraulic actuator 34 that verts acts on wing root bearing 32 and made
Two movable tilting wings 31 are changed into horizontally or vertically state.
Wherein, flight-control computer 4 control hybrid power can tilt wing aircraft state of flight.Rack joint bearing 25
It is electronic positioned at the lower section of main machine body 1 when four rotors are packed up by four hydraulic actuators 21 installed in the lower section of main machine body 1
Many rotor modules provide power by lithium battery, and wherein lithium battery is the lithium battery of Large Copacity.
The end of two aero-engine propellers 33 is respectively mounted the fuel oil of the rotation of driving aero-engine propeller 33
Engine 35.The driving aero-engine of fuel engines 35 propeller 33 rotates, and offsets the torsion of fuel engines 35 and balance two
The thrust of individual fuel engines 35 makes hybrid power can tilt wing aircraft flight.
Hybrid power can tilt wing aircraft also include control hybrid power can tilt wing aircraft flight when the Vertical Square turned
Guide vane 6, Vertical Square guide vane 6 is arranged on the rear top of main machine body 1.The major control hybrid power of Vertical Square guide vane 6 can vert the wing
Direction during aircraft turn.
Fig. 2 be hybrid power can tilt wing aircraft takeoff phase schematic diagram, two movable tilting wings during takeoff phase
31 are in plumbness, be changed into plumbness hybrid power can be provided can maximum lift of tilt wing aircraft when taking off, four rotations
The wing is deployed by four hydraulic actuators 21, is controlled by flight-control computer 4, is adjusted flying speed, is made hybrid power can
Tilt wing aircraft steadily rises to reach required height.
Fig. 3 be hybrid power can tilt wing aircraft boost phase schematic diagram, when hybrid power can tilt wing aircraft reach
During predetermined height, now hybrid power can tilt wing aircraft be in boost phase, the wing hydraulic actuator 34 that verts is acted on
Wing root bearing 32 makes two movable tilting wings 31 while being changed into horizontality, and becoming horizontality can be reduced in accelerator
Air drag, shorten the acceleration time.
Fig. 4 be hybrid power can tilt wing aircraft cruising phase schematic diagram, when hybrid power can tilt wing aircraft accelerate
After the completion of stage, now two movable tilting wings 31 are horizontality, reduce air drag there is provided thrust during flight, are
Make hybrid power can tilt wing aircraft preferably fly, four rotors are packed up by four hydraulic actuators 21, hybrid power
Can tilt wing aircraft can steady as common fixed wing aircraft, quick flight.
Particular embodiments described above, has been carried out further in detail to the purpose of the present invention, technical scheme and beneficial effect
Describe in detail it is bright, should be understood that the foregoing is only the present invention specific embodiment, be not intended to limit the invention, it is all
Within the spirit and principles in the present invention, any modification, equivalent substitution and improvements done etc., should be included in the guarantor of the present invention
Within the scope of shield.
Claims (4)
1. a kind of hybrid power can tilt wing aircraft, including main machine body (1), electronic many rotor modules, aero-engine fixed-wing
Module, flight-control computer (4) and empennage (5), described flight-control computer (4) are arranged in main machine body (1), described
Empennage (5) be arranged on main machine body (1) afterbody, it is characterised in that：Electronic many rotor modules include four hydraulic actuators
(21) and four rotors, (21) two one group described of four hydraulic actuators be separately mounted to the front end of main machine body (1) and after
End, described rotor includes brushless electric machine (22), two leaves and folds oar (23), carbon fiber support (24) and rack joint bearing
(25), two described leaves fold oar (23) and are arranged on brushless electric machine (22), and described brushless electric machine (22) is arranged on carbon fiber
The end of support (24), described carbon fiber support (24) is symmetrically fixed on main machine body (1) by rack joint bearing (25)
The left and right sides, four hydraulic actuators (21) are connected on four carbon fiber supports (24), and four rotors pass through respectively
Four hydraulic actuator (21) expansion are with packing up；Described aero-engine fixed-wing module includes two movable tilting wings
(31), wing root bearing (32), two aero-engine propellers (33) and wing are verted hydraulic actuator (34), and two activities are inclined
The favourable turn wing (31) is fixed on the middle part of main machine body (1) by wing root bearing (32), and two aero-engine propellers (33) are respectively
On two movable tilting wings (31), described wing verts hydraulic actuator (34) installed in wing root bearing (32)
On, the described wing hydraulic actuator (34) that verts acts on wing root bearing (32) and two movable tilting wings (31) is changed into water
Flat or plumbness, described flight-control computer (4) control hybrid power can tilt wing aircraft state of flight.
2. a kind of hybrid power according to claim 1 can tilt wing aircraft, it is characterised in that：Described electronic many rotors
Module provides power by lithium battery.
3. a kind of hybrid power according to claim 2 can tilt wing aircraft, it is characterised in that：Two aero-engine spiral shells
The end of rotation oar (33) is respectively mounted the fuel engines (35) of driving aero-engine propeller (33) rotation.
4. a kind of hybrid power according to claim 3 can tilt wing aircraft, it is characterised in that：The hybrid power can incline
Rotary wing plane also include control hybrid power can tilt wing aircraft flight when the Vertical Square guide vane (6) turned, described Vertical Square
Guide vane (6) is arranged on the rear top of main machine body (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510574196.XA CN105173075B (en) | 2015-09-10 | 2015-09-10 | A kind of hybrid power can tilt wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510574196.XA CN105173075B (en) | 2015-09-10 | 2015-09-10 | A kind of hybrid power can tilt wing aircraft |
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| Publication Number | Publication Date |
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| CN105173075A CN105173075A (en) | 2015-12-23 |
| CN105173075B true CN105173075B (en) | 2017-09-15 |
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| CN201510574196.XA Active CN105173075B (en) | 2015-09-10 | 2015-09-10 | A kind of hybrid power can tilt wing aircraft |
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| CN106114847B (en) * | 2016-06-27 | 2018-10-09 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106081060B (en) * | 2016-07-05 | 2018-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN107972867A (en) * | 2016-07-20 | 2018-05-01 | 陈勇波 | One kind can VTOL formula remove haze aircraft |
| CN106428548B (en) * | 2016-10-12 | 2019-09-27 | 曹萍 | A kind of vertical take-off and landing unmanned aerial vehicle |
| CN107021206B (en) * | 2017-04-11 | 2020-06-19 | 深圳智航无人机有限公司 | Unmanned plane |
| CN107150803A (en) * | 2017-06-07 | 2017-09-12 | 天津科技大学 | Mixed layout unmanned plane and its control method |
| CN107215462B (en) * | 2017-07-01 | 2021-08-31 | 山东翔鸿电子科技有限公司 | Landing method and landing device for vertical take-off and landing fixed wing unmanned aerial vehicle |
| RU2682756C1 (en) * | 2018-03-05 | 2019-03-21 | Общество с ограниченной ответственностью "Техноветер" | Convertible plane |
| CN108284958A (en) * | 2018-03-12 | 2018-07-17 | 张鹤 | The aircraft and fixed-wing unmanned plane of power plant module |
| CN108394560A (en) * | 2018-03-15 | 2018-08-14 | 成鑫 | A kind of fixed-wing unmanned plane and its landing method |
| CN108945394A (en) * | 2018-06-19 | 2018-12-07 | 浙江大学 | A kind of long continuation of the journey multi-rotor aerocraft and its control method having fixed aerofoil and horizontal propeller |
| FR3084318B1 (en) * | 2018-07-25 | 2020-06-26 | Airbus Helicopters | METHOD AND DEVICE FOR MANAGING THE ENERGY OF A HYBRID POWER PLANT OF A MULTIROTOR AIRCRAFT |
| CN109018331A (en) * | 2018-09-10 | 2018-12-18 | 观典防务技术股份有限公司 | It is capable of the VTOL fixed-wing unmanned plane of folding and unfolding rotor when a kind of cruise |
| CN109665097A (en) * | 2018-12-25 | 2019-04-23 | 浙江工业大学 | Compound offline mode unmanned plane |
| CN110466752B (en) * | 2019-08-07 | 2021-11-26 | 深圳市道通智能航空技术股份有限公司 | Control method of tilt rotor unmanned aerial vehicle and tilt rotor unmanned aerial vehicle |
| CN111017231B (en) * | 2019-11-28 | 2021-06-29 | 嘉兴安行信息科技有限公司 | Mounting structure of engine among unmanned aerial vehicle |
| CN112319790B (en) * | 2020-11-05 | 2024-01-23 | 国网福建省电力有限公司电力科学研究院 | Aerodynamic layout structure of long-endurance aircraft integrating multiple rotors and fixed wings and control method thereof |
| EP4244133A4 (en) * | 2020-11-13 | 2024-04-10 | Innovaero Technologies Pty Ltd | Aerial vehicles |
| CN112793773A (en) * | 2021-04-02 | 2021-05-14 | 成都云鼎智控科技有限公司 | Vertical take-off and landing unmanned aerial vehicle and driving method thereof |
| CN114212237B (en) * | 2021-12-23 | 2024-05-24 | 中国航空工业集团公司西安飞机设计研究所 | Accurate air drop/airborne power device |
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| US3586262A (en) * | 1969-12-05 | 1971-06-22 | Irving Robert Sherman | Foreflapped airfoil |
| FR2798359B1 (en) * | 1999-09-14 | 2001-11-09 | Eurocopter France | IMPROVEMENTS ON TILTING ROTOR CONVERTIBLE AIRCRAFT |
| CN103192990B (en) * | 2013-04-12 | 2015-09-09 | 北京航空航天大学 | Can Flying-wing's aircraft of short distance/vertical takeoff and landing |
| CN205044942U (en) * | 2015-09-10 | 2016-02-24 | 南京多零无人机技术有限公司 | But hybrid tilt wing aircraft |
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