CN105173075A - Tiltable hybrid rotor-wing aircraft - Google Patents
Tiltable hybrid rotor-wing aircraft Download PDFInfo
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- CN105173075A CN105173075A CN201510574196.XA CN201510574196A CN105173075A CN 105173075 A CN105173075 A CN 105173075A CN 201510574196 A CN201510574196 A CN 201510574196A CN 105173075 A CN105173075 A CN 105173075A
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- wing aircraft
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- tiltable
- rotor
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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
Abstract
The invention relates to the field of aircrafts, in particular to a tiltable hybrid rotor-wing aircraft. According to the tiltable hybrid rotor-wing aircraft disclosed by the invention, an electric multi-rotor-wing module and an aero-engine fixed-wing module are combined. At the take-off stage, two movable tilting wings are in a vertical state, and the maximum lift force can be provided for the tiltable hybrid rotor-wing aircraft when the tiltable hybrid rotor-wing aircraft takes off; four rotor wings keeps the aircraft body stable, so that the tiltable hybrid rotor-wing aircraft stably rises; when the tiltable hybrid rotor-wing aircraft rises to needed cruising height, two movable tilting wings which are in the vertical state are changed to be in a horizontal state, the four rotor wings are folded, and the air resistance is reduced, so that the tiltable hybrid rotor-wing aircraft flies safely and stably, the tiltable hybrid rotor-wing aircraft has the advantages of a fixed-wing aircraft and the advantages of a multi-rotor-wing aircraft, namely the requirements for take-off and landing sites are low, and the tiltable hybrid rotor-wing aircraft is stable and reliable during cruising; the tiltable hybrid rotor-wing aircraft is powered by both oil and electricity, and a needed power mode is selected according to actual situations when the tiltable hybrid rotor-wing aircraft is used, so that the effect of saving energy sources is reached.
Description
Technical field
The present invention relates to aircraft field, particularly relating to a kind of hybrid power can tilt wing aircraft.
Background technology
Existing aircraft mainly comprises two kinds of fixed-wings and many rotors, wherein fix autogiro and mainly comprise two large fixed-wings, can take off vertically, vertical landing and forward flight, flight safety is stablized, but fixed wing aircraft all needs longer runway to provide the power taken off usually, takes off limited.Many autogiros provide the power taken off without the need to runway, and can aloft stagnate, but the flight of many autogiros is unstable, and safety factor is low.
Summary of the invention
The object of the invention is the defect overcoming prior art existence, do not limit by place when providing one to take off and land, when cruising, the hybrid power of safety and steady can tilt wing aircraft.
The technical scheme realizing the object of the invention is: a kind of hybrid power can tilt wing aircraft, comprise main machine body, electronic many rotor module, aero-engine fixed-wing module, flight-control computer and empennage, flight-control computer is arranged in main machine body, empennage is arranged on the afterbody of main machine body, electronic many rotor module comprise four hydraulic actuators and four rotors, four hydraulic actuators two one group are arranged on the front-end and back-end of main machine body respectively, rotor comprises brushless motor, two leaves fold oar, carbon fiber support and rack joint bearing, two leaves fold oar and are arranged on brushless motor, brushless motor is arranged on the end of carbon fiber support, carbon fiber support is by the left and right sides being fixed on main machine body of rack joint bearing symmetry, four hydraulic actuators are connected in four carbon fiber support, four rotors launch respectively by four hydraulic actuators and pack up, aero-engine fixed-wing module comprises two movable tilting wings, wing root bearing, two aero-engine screw propellers and wing and to vert hydraulic actuator, two movable tilting wings are fixed on the middle part of main machine body by wing root bearing, two aero-engine screw propellers are arranged on two movable tilting wings respectively, the wing hydraulic actuator that verts is arranged on wing root bearing, and the wing hydraulic actuator that verts acts on wing root bearing and makes two movable tilting wings become level or plumbness.
As prioritization scheme of the present invention, electronic many rotor module provide power by lithium cell.
As prioritization scheme of the present invention, the end of two aero-engine screw propellers installs the fuel engines driving aero-engine screw propeller to rotate respectively.
As prioritization scheme of the present invention, hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane, Vertical Square guide vane is arranged on the top, rear of main machine body.
The present invention has positive effect: the present invention is combined by electronic many rotor module and aero-engine fixed-wing module, during takeoff phase, two movable tilting wings are in plumbness, becoming plumbness can provide hybrid power can the maximum lift of tilt wing aircraft when taking off, four rotors maintenance fuselages are stablized makes hybrid power steadily rise by tilt wing aircraft, when rising to required height and cruising, two movable tilting wings become horizontality, four rotors are packed up, reduce air resistance, thus make hybrid power can the flight of tilt wing aircraft safety and stability, the present invention has played fixed wing aircraft and many autogiros advantage separately, namely low to the site requirements taken off and land, reliable and stable when cruising, the dynamic mode of oil electricity mixing, the dynamic mode of needs can be selected according to actual conditions during use, reach the effect of saving the energy.
Accompanying drawing explanation
In order to make content of the present invention more easily be clearly understood, below according to specific embodiment also by reference to the accompanying drawings, the present invention is further detailed explanation, wherein:
Fig. 1 is that hybrid power can the constructional drawing of tilt wing aircraft;
Fig. 2 is that hybrid power can the schematic diagram of tilt wing aircraft takeoff phase;
Fig. 3 is that hybrid power can the schematic diagram of tilt wing aircraft acceleration phase;
Fig. 4 is that hybrid power can the schematic diagram of tilt wing aircraft cruising phase.
Wherein, 1, main machine body, 4, flight-control computer, 5, empennage, 21, hydraulic actuator, 22, brushless motor, 23, two leaves fold oar, and 24, carbon fiber support, 25, rack joint bearing, 31, movable tilting wing, 32, wing root bearing, 33, aero-engine screw propeller, 34, wing verts hydraulic actuator, 35, fuel engines, 6, Vertical Square guide vane.
Detailed description of the invention
As shown in Figure 1, the invention discloses a kind of hybrid power can tilt wing aircraft, comprise main machine body 1, electronic many rotor module, aero-engine fixed-wing module, flight-control computer 4 and empennage 5, wherein, flight-control computer 4 is arranged in main machine body 1, empennage 5 is arranged on the afterbody of main machine body 1, electronic many rotor module comprise four hydraulic actuators 21 and four rotors, four hydraulic actuators 21 two one group are arranged on the front-end and back-end of main machine body 1 respectively, rotor comprises brushless motor 22, two leaves fold oar 23, carbon fiber support 24 and rack joint bearing 25, two leaves fold oar 23 and are arranged on brushless motor 22, brushless motor 22 is arranged on the end of carbon fiber support 24, carbon fiber support 24 is by the left and right sides being fixed on main machine body 1 of rack joint bearing 25 symmetry, four hydraulic actuators 21 are connected in four carbon fiber support 24, four rotors launch respectively by four hydraulic actuators 21 and pack up, aero-engine fixed-wing module comprises two movable tilting wings 31, wing root bearing 32, two aero-engine screw propellers 33 and wing and to vert hydraulic actuator 34, two movable tilting wings 31 are fixed on the middle part of main machine body 1 by wing root bearing 32, two aero-engine screw propellers 33 are arranged on two movable tilting wings 31 respectively, the wing hydraulic actuator 34 that verts is arranged on wing root bearing 32, and the wing hydraulic actuator 34 that verts acts on wing root bearing 32 and makes two movable tilting wings 31 become level or plumbness.
Wherein, flight-control computer 4 control hybrid power can the state of flight of tilt wing aircraft.Rack joint bearing 25 is arranged on the below of main machine body 1, and be positioned at the below of main machine body 1 when four rotors are packed up by four hydraulic actuators 21, electronic many rotor module provide power by lithium cell, and wherein lithium cell is high-capacity lithium cell.
The end of two aero-engine screw propellers 33 installs the fuel engines 35 driving aero-engine screw propeller 33 to rotate respectively.Fuel engines 35 drives aero-engine screw propeller 33 to rotate, and offsets fuel engines 35 torsion and the thrust balancing two fuel enginess 35 makes hybrid power can tilt wing aircraft flight.
Hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane 6, Vertical Square guide vane 6 is arranged on the top, rear of main machine body 1.Vertical Square guide vane 6 major control hybrid power can tilt wing aircraft turn time direction.
Fig. 2 is that hybrid power can the schematic diagram of tilt wing aircraft takeoff phase, during takeoff phase, two movable tilting wings 31 are in plumbness, becoming plumbness can provide hybrid power can the maximum lift of tilt wing aircraft when taking off, four rotors are launched by four hydraulic actuators 21, controlled by flight-control computer 4, regulate flying speed, make hybrid power steadily increase to reach required height by tilt wing aircraft.
Fig. 3 is that hybrid power can the schematic diagram of tilt wing aircraft acceleration phase, when hybrid power can tilt wing aircraft reach predetermined height time, now hybrid power can be in acceleration phase by tilt wing aircraft, the wing hydraulic actuator 34 that verts acts on wing root bearing 32 and makes two movable tilting wings 31 become horizontality simultaneously, become horizontality and can reduce air resistance in accelerator, shorten pick-up time.
Fig. 4 is that hybrid power can the schematic diagram of tilt wing aircraft cruising phase, when hybrid power can after tilt wing aircraft acceleration phase completes, now two movable tilting wings 31 are horizontality, reduce air resistance, thrust during flight is provided, in order to make hybrid power better fly by tilt wing aircraft, four rotors are packed up by four hydraulic actuators 21, hybrid power can tilt wing aircraft can the flight of steady as common fixed wing aircraft, fast speed.
Above-described specific embodiment; object of the present invention, technical scheme and beneficial effect are further described; be understood that; the foregoing is only specific embodiments of the invention; be not limited to the present invention; within the spirit and principles in the present invention all, any amendment made, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (4)
1. a hybrid power can tilt wing aircraft, comprise main machine body (1), electronic many rotor module, aero-engine fixed-wing module, flight-control computer (4) and empennage (5), described flight-control computer (4) is arranged in main machine body (1), described empennage (5) is arranged on the afterbody of main machine body (1), it is characterized in that: electronic many rotor module comprise four hydraulic actuators (21) and four rotors, four described hydraulic actuators (21) two one group are arranged on the front-end and back-end of main machine body (1) respectively, described rotor comprises brushless motor (22), two leaves fold oar (23), carbon fiber support (24) and rack joint bearing (25), two described leaves fold oar (23) and are arranged on brushless motor (22), described brushless motor (22) is arranged on the end of carbon fiber support (24), described carbon fiber support (24) is by the left and right sides being fixed on main machine body (1) of rack joint bearing (25) symmetry, four hydraulic actuators (21) are connected on four carbon fiber support (24), four rotors launch respectively by four hydraulic actuators (21) and pack up, described aero-engine fixed-wing module comprises two movable tilting wings (31), wing root bearing (32), two aero-engine screw propellers (33) and wing vert hydraulic actuator (34), two movable tilting wings (31) are fixed on the middle part of main machine body (1) by wing root bearing (32), two aero-engine screw propellers (33) are arranged on two movable tilting wings (31) respectively, the described wing hydraulic actuator (34) that verts is arranged on wing root bearing (32), the described wing hydraulic actuator (34) that verts acts on wing root bearing (32) and makes two movable tilting wings (31) become level or plumbness.
2. a kind of hybrid power according to claim 1 can tilt wing aircraft, it is characterized in that: described electronic many rotor module provide power by lithium cell.
3. a kind of hybrid power according to claim 2 can tilt wing aircraft, it is characterized in that: the end of two aero-engine screw propellers (33) installs the fuel engines (35) driving aero-engine screw propeller (33) to rotate respectively.
4. a kind of hybrid power according to claim 3 can tilt wing aircraft, it is characterized in that: described hybrid power can tilt wing aircraft also comprise control hybrid power can tilt wing aircraft flight time turn Vertical Square guide vane (6), described Vertical Square guide vane (6) is arranged on the top, rear of main machine body (1).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510574196.XA CN105173075B (en) | 2015-09-10 | 2015-09-10 | A kind of hybrid power can tilt wing aircraft |
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| CN201510574196.XA CN105173075B (en) | 2015-09-10 | 2015-09-10 | A kind of hybrid power can tilt wing aircraft |
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| CN105173075A true CN105173075A (en) | 2015-12-23 |
| CN105173075B 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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Cited By (20)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005387A (en) * | 2016-07-20 | 2016-10-12 | 张学衡 | Vertical take-off and landing type dehazing aircraft |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106114847A (en) * | 2016-06-27 | 2016-11-16 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| CN107021206A (en) * | 2017-04-11 | 2017-08-08 | 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 |
| CN107215462A (en) * | 2017-07-01 | 2017-09-29 | 山东翔鸿电子科技有限公司 | A kind of VTOL fixed-wing unmanned plane landing method and landing-gear |
| 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 |
| 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 |
| CN110466752A (en) * | 2019-08-07 | 2019-11-19 | 深圳市道通智能航空技术有限公司 | A kind of control method and tilting rotor wing unmanned aerial vehicle of tilting rotor wing unmanned aerial vehicle |
| CN110844087A (en) * | 2018-07-25 | 2020-02-28 | 空客直升机 | Method and device for managing the energy of a hybrid power plant of a multi-rotor aircraft |
| CN111017231A (en) * | 2019-11-28 | 2020-04-17 | 嘉兴安行信息科技有限公司 | Mounting structure of engine among unmanned aerial vehicle |
| CN111801272A (en) * | 2018-03-05 | 2020-10-20 | 特克诺维特有限公司 | Thrust steering aircraft |
| CN112319790A (en) * | 2020-11-05 | 2021-02-05 | 国网福建省电力有限公司电力科学研究院 | Pneumatic layout structure of long-endurance aircraft integrating multiple rotor wings and fixed wings and control method of pneumatic layout structure |
| 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 |
| CN114212237A (en) * | 2021-12-23 | 2022-03-22 | 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 |
| WO2022099373A1 (en) * | 2020-11-13 | 2022-05-19 | Innovaero Technologies Pty Ltd | Aerial vehicles |
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| CN103192990A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Vertical/short take-off and landing flying wing layout aircraft |
| 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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| US3586262A (en) * | 1969-12-05 | 1971-06-22 | Irving Robert Sherman | Foreflapped airfoil |
| US6607161B1 (en) * | 1999-09-14 | 2003-08-19 | Eurocopter | Convertible aircraft with tilting rotors |
| CN103192990A (en) * | 2013-04-12 | 2013-07-10 | 北京航空航天大学 | Vertical/short take-off and landing flying wing layout aircraft |
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Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN106114847A (en) * | 2016-06-27 | 2016-11-16 | 湖北航天飞行器研究所 | A kind of vertically taking off and landing flyer |
| CN106081060A (en) * | 2016-07-05 | 2016-11-09 | 北京航空航天大学 | A kind of VTOL composite layouts unmanned plane rotor draw off gear |
| CN106005387A (en) * | 2016-07-20 | 2016-10-12 | 张学衡 | Vertical take-off and landing type dehazing aircraft |
| CN106428548A (en) * | 2016-10-12 | 2017-02-22 | 曹萍 | Vertical take-off and landing unmanned aerial vehicle |
| CN106428548B (en) * | 2016-10-12 | 2019-09-27 | 曹萍 | A kind of vertical take-off and landing unmanned aerial vehicle |
| CN107021206A (en) * | 2017-04-11 | 2017-08-08 | 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 |
| CN107215462A (en) * | 2017-07-01 | 2017-09-29 | 山东翔鸿电子科技有限公司 | A kind of VTOL fixed-wing unmanned plane landing method and landing-gear |
| 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 |
| CN111801272A (en) * | 2018-03-05 | 2020-10-20 | 特克诺维特有限公司 | Thrust steering aircraft |
| 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 |
| CN110844087A (en) * | 2018-07-25 | 2020-02-28 | 空客直升机 | Method and device for managing the energy of a hybrid power plant of a multi-rotor 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 |
| CN110466752A (en) * | 2019-08-07 | 2019-11-19 | 深圳市道通智能航空技术有限公司 | A kind of control method and tilting rotor wing unmanned aerial vehicle of tilting rotor wing unmanned aerial vehicle |
| CN111017231A (en) * | 2019-11-28 | 2020-04-17 | 嘉兴安行信息科技有限公司 | Mounting structure of engine among unmanned aerial vehicle |
| CN112319790A (en) * | 2020-11-05 | 2021-02-05 | 国网福建省电力有限公司电力科学研究院 | Pneumatic layout structure of long-endurance aircraft integrating multiple rotor wings and fixed wings and control method of pneumatic layout structure |
| 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 |
| WO2022099373A1 (en) * | 2020-11-13 | 2022-05-19 | Innovaero Technologies Pty Ltd | Aerial vehicles |
| EP4244133A4 (en) * | 2020-11-13 | 2024-04-10 | Innovaero Tech 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 |
| CN114212237A (en) * | 2021-12-23 | 2022-03-22 | 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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