CN106672223A - Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers - Google Patents
Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers Download PDFInfo
- Publication number
- CN106672223A CN106672223A CN201610349733.5A CN201610349733A CN106672223A CN 106672223 A CN106672223 A CN 106672223A CN 201610349733 A CN201610349733 A CN 201610349733A CN 106672223 A CN106672223 A CN 106672223A
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- aircraft
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- fixed
- tilt rotor
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- 239000000446 fuel Substances 0.000 claims abstract description 7
- 230000009977 dual effect Effects 0.000 claims description 23
- 238000006243 chemical reaction Methods 0.000 claims 1
- 238000000034 method Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 abstract description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 238000013024 troubleshooting Methods 0.000 description 2
- 241000566150 Pandion haliaetus Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000015556 catabolic process Effects 0.000 description 1
- 238000005183 dynamical system Methods 0.000 description 1
- 238000004146 energy storage Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000007726 management method Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000005096 rolling process Methods 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
Abstract
The invention provides a tilt rotor aircraft with good safety, which can vertically take off and land and can execute fixed-wing flight. Four sets of coaxial contra-rotating propellers, which are driven by a motor and whose speeds can be independently adjusted, are placed at two ends of front and rear fixed wings of a tandem wing aircraft in rectangular positions together with the motor; and axial directions of the coaxial contra-rotating propellers can be deflected. When the axial directions of four rotors are in a vertical direction, the tilt rotor aircraft is in a vertical takeoff and landing mode and the aircraft can vertically take off and land and can hover; through converting the axial directions of the four propellers into forward horizontal directions, the tilt rotor aircraft is converted into a fixed wing flight mode from the vertical takeoff and landing mode so as to realize high speed cruising; in the flying process, the tilt rotor aircraft can be converted between two flight modes; by using petrol-electric hybrid power, a fuel engine drives a power generator to generate power so as to provide electric power to the aircraft and a power battery pack can also provide electric power to the aircraft; and meanwhile, the power generator can charge the power battery pack.
Description
Technical field
A kind of tiltrotor of hybrid power, energy VTOL and fixed-wing flight, possess higher safety, belong to technical field of aerospace.
Background technology
Presently, there are a large amount of four-axle aircrafts, although have preferable stability and operability, but be because the limitation of Flight Vehicle Structure, it is impossible to realize high speed cruise flight；If any one breaks down for its four sets of propellers and motor, four-axle aircraft all be able to can not be balanced because of propeller rotation counteracting force, cause aircraft out of control；And its battery energy storage is limited, it is impossible to long-distance flight.
The tiltrotor for uniquely producing on former world and coming into operation is V-22 " osprey " tiltrotor in the U.S..Although it realizes VTOL and remote high-performance cruise, according to the analyses that it runs for many years：, because bispin wing structure, rotor load is too high, easily produces ring of eddy for the tiltrotor；The rotating speed and power control response speed of fuel engines is slower, poor in the emergency capability of emergency；In order to balance the rotation counteracting force of rotor, DCB Specimen must be rotated with reverse and identical rotating speed, and if the lift on one side occurs exception, aircraft then can disequilibrium；Fuel engines is located at rear propeller, and high velocity air causes electromotor easily to inhale sand；The high-temperature gas that electromotor sprays downwards all has a great impact to ground and ground staff；These cause the stability of the type aircraft vertical landing and hovering, and reliability and safety are all undesirable.
The content of the invention
Present invention design one kind can carry out remote high-performance cruise with fixed-wing flying method again with VTOL, and possess higher-security and handling new tiltrotor.
The technical solution adopted in the present invention is：Using four sets by the motor-driven dual rotation propeller that can independently adjust rotating speed, rectangular location arrangements can be deflected in the two ends of the fixed-wing in front and back of tandem rotor aircraft, and the direction of principal axis of four sets of propellers together with motor.Afterbody is provided with empennage.Four sets of motors are equipped with special motor driver for controlling and adjusting the rotating speed and power of motor.When four sets of rotors direction of principal axis vertically when, it is possible to achieve VTOL and hovering, by the direction of principal axis and lift that adjust four groups of propellers, realize the control of various flight attitudes；By changing the direction of principal axis of four sets of propellers to forward horizontal direction, fixed-wing offline mode is converted to, realizes remote high-performance cruise, it can also be used to which short distance is slided takeoff and landing or provides bigger physical burden.Under fixed-wing offline mode, the achievable control to flight attitude in four groups of propeller shaft directions of movable aerofoil and deflection of fixed-wing and empennage is adjusted.Aircraft adopts oil electric mixed dynamic, drives electrical power generators and power battery pack can provide electric power for aircraft by turboaxle motor or piston engine, while electromotor can charge for power battery pack.
The invention has the beneficial effects as follows：Using the dual rotation propeller of four groups of rectangle position arrangements, the front face area of rotor under the rotor load under VTOL pattern, and reduction fixed-wing offline mode is not only reduced, reduce flight resistance；Its four sets of dual rotation propellers can freely adjust rotating speed and change lift and direction of principal axis without the rotating speed control constraints for symmetric screw propeller to the rotation counteracting force of aircraft, it is possible to achieve various flight attitude controls and emergency trouble shooting measures；Can realize freely mutually turning between fixed-wing offline mode and VTOL pattern and transition process more stablizes controllable；Fixed-wing offline mode can be used, is realized relative to the farther cruising range of pure helicopter, lower flight energy consumption and the cruising speed of Geng Gao.The tiltrotor possesses preferable safety：The repid discharge of peak power in short-term and quick response and power battery pack by motor, there is provided Ability of emergency management preferably in emergency circumstances；When a set of propeller electric machine assembly or motor driver failure, the other set propeller that can be allowed on rectangle position diagonal is served only for the control of aircraft balance and stability, and a pair of propellers on an other diagonal are operated with double power, enough lift is provided, before motor overtemperature emergency landing was implemented.Four sets of propellers, possess many power redundant safety mechanism under Fixed Wing AirVehicle pattern.Using oil electric mixed dynamic simultaneously, it is possible to use electrical power generators and power battery pack to be discharged and provide the emergent high-power electric of short time for aircraft or improve maximum take-off weight；When fuel power or power battery pack break down, electric power or the high power discharge of power battery pack, the time that troubleshooting can be provided for aircraft that fuel power is provided with electromotor, or provide short time electric power for emergency landing.
Description of the drawings
Fig. 1 is the dual rotation propeller tiltrotor embodiment VTOL view of hybrid power four.
Fig. 2 is the dual rotation propeller tiltrotor embodiment fixed-wing state of flight schematic diagram of hybrid power four.
1. aircraft fuselage in figure, 2. tandem fixed-wing front wing, 3. tandem fixed-wing rear wing, 4. empennage, 5. left front dual rotation propeller and electric machine assembly, 6. dual rotation propeller and electric machine assembly before right, 7. dual rotation propeller and electric machine assembly behind the right side, 8. left back dual rotation propeller and electric machine assembly.
Specific embodiment
In embodiment illustrated in fig. 1, the rotor assemblies 5 of four sets of dual rotation propellers and motor composition, 6,7,8 rectangular positions are arranged in the two ends of before and after fixed-wing 2,3；Every group of dual rotation propeller direction of principal axis can be deflected.Oil-fired power generating dynamical system and power battery pack and flight controller etc. can be arranged in fuselage 1, manned driving cabin can be also arranged.It is VTOL pattern shown in figure, by the lift for changing propeller, it is possible to achieve the various gesture stabilities in addition to rotation, such as translates, pitching etc.；By the dual rotation propeller 5,8 on the left of the differential deflection of low-angle and the dual rotation propeller 6,7 on right side, it is possible to achieve rotation gesture stability.Safety operation mode for assume dual rotation propeller 5 because it is various possible the reason for lose lift, at this moment the two groups of dual rotation propellers 6 and 8 in clinodiagonal are rapid in peak power improves lift, enough lift is provided for aircraft, and dual rotation propeller 7 is changed to stablize for the posture balancing of aircraft, then aircraft carries out emergency landing.
Fig. 2 is the fixed-wing offline mode schematic diagram of same embodiment.Four groups of direction of principal axis of dual rotation propeller 5,6,7,8 are deflected forward simultaneously, aircraft is lifted with flight speed, when fixed-wing 2,3 can provide enough lift, four groups of direction of principal axis of dual rotation propeller 5,6,7,8 deflect to completely level angle, provide only forward pulling force, lift is no longer provided, hence into low energy consumption and high speed fixed-wing offline mode.Can be with change of flight direction by manipulating empennage 4；Its gesture stability is referred to the control mode of traditional fixed wing airplane, it would however also be possible to employ the dual rotation propeller direction of principal axis of small angle deflection both sides is realizing：When the dual rotation propeller direction of principal axis at fixed-wing 2 before small angle deflection in the same direction or the rear two ends of fixed-wing 3, it is possible to achieve body pitching operates, climbs or reduce flying height；When the dual rotation propeller direction of principal axis at fixed-wing 2 before differential small angle deflection or the rear two ends of fixed-wing 3, rolling moment can be provided.Due to there is 4 groups of propellers to provide advance pulling force, itself has redundancy scheme, in the event of propeller failure, can still implement to slide forced landing and take off.
The power safety mechanism of aircraft is that fuel engines drives electromotor and power battery pack to backup each other, and can provide short time emergency electric power for aircraft, allows aircraft to have certain hour to fix a breakdown or implements forced landing.
Claims (2)
1. a kind of tiltrotor, using four groups of two ends by the rectangular location arrangements of motor-driven dual rotation propeller fixed-wing before and after tandem rotor aircraft；The direction of principal axis of propeller can be deflected：It is VTOL pattern when vertically upward, is fixed-wing offline mode when horizontal forward；And in flight course, aircraft can realize the mutual conversion between VTOL pattern and fixed-wing offline mode.
2. aircraft according to claim 1, is characterized in that adopting oil electric mixed dynamic, drive electromotor and power battery pack to provide electric power for aircraft by fuel engines, and electromotor can charge for power battery pack.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610349733.5A CN106672223A (en) | 2016-05-24 | 2016-05-24 | Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610349733.5A CN106672223A (en) | 2016-05-24 | 2016-05-24 | Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106672223A true CN106672223A (en) | 2017-05-17 |
Family
ID=58840231
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610349733.5A Pending CN106672223A (en) | 2016-05-24 | 2016-05-24 | Hybrid tilt rotor aircraft with four coaxial contra-rotating propellers |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106672223A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110155329A (en) * | 2019-05-30 | 2019-08-23 | 吉林大学 | A kind of novel wing hybrid power search and rescue unmanned plane that verts |
| WO2020035715A1 (en) * | 2018-08-15 | 2020-02-20 | Gary Anthony Daprato | Aircrafts with controllers and tiltable rotors for attitude-controlled flight |
| CN111348197A (en) * | 2020-03-16 | 2020-06-30 | 华中科技大学 | Combined power system of vertical take-off and landing fixed wing aircraft |
| CN112009677A (en) * | 2020-08-27 | 2020-12-01 | 彩虹无人机科技有限公司 | Variable-diameter unmanned tilt rotorcraft |
| CN112368208A (en) * | 2018-05-31 | 2021-02-12 | 杰欧比飞行有限公司 | Electric power system architecture and fault-tolerant VTOL (virtual volume on-board) aircraft using same |
| WO2021134542A1 (en) * | 2019-12-31 | 2021-07-08 | 李庆远 | Multi-rotor display and flight control method |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120234968A1 (en) * | 2005-10-18 | 2012-09-20 | Smith Frick A | Aircraft with freewheeling engine |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| CN204895858U (en) * | 2015-05-07 | 2015-12-23 | 张庆伟 | Aerial variant stationary vane four -axis unmanned aerial vehicle of VTOL |
| CN205675239U (en) * | 2016-05-24 | 2016-11-09 | 周光翔 | Hybrid power four dual rotation propeller tiltrotor |
-
2016
- 2016-05-24 CN CN201610349733.5A patent/CN106672223A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120234968A1 (en) * | 2005-10-18 | 2012-09-20 | Smith Frick A | Aircraft with freewheeling engine |
| CN104401480A (en) * | 2014-11-06 | 2015-03-11 | 南京航空航天大学 | Ducted tilt aircraft |
| CN104843181A (en) * | 2015-04-10 | 2015-08-19 | 桂林航龙科讯电子技术有限公司 | Petrol-electric hybrid power fixed wing vertical take-off and landing unmanned plane system |
| CN204895858U (en) * | 2015-05-07 | 2015-12-23 | 张庆伟 | Aerial variant stationary vane four -axis unmanned aerial vehicle of VTOL |
| CN205675239U (en) * | 2016-05-24 | 2016-11-09 | 周光翔 | Hybrid power four dual rotation propeller tiltrotor |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112368208A (en) * | 2018-05-31 | 2021-02-12 | 杰欧比飞行有限公司 | Electric power system architecture and fault-tolerant VTOL (virtual volume on-board) aircraft using same |
| WO2020035715A1 (en) * | 2018-08-15 | 2020-02-20 | Gary Anthony Daprato | Aircrafts with controllers and tiltable rotors for attitude-controlled flight |
| CN110155329A (en) * | 2019-05-30 | 2019-08-23 | 吉林大学 | A kind of novel wing hybrid power search and rescue unmanned plane that verts |
| WO2021134542A1 (en) * | 2019-12-31 | 2021-07-08 | 李庆远 | Multi-rotor display and flight control method |
| CN111348197A (en) * | 2020-03-16 | 2020-06-30 | 华中科技大学 | Combined power system of vertical take-off and landing fixed wing aircraft |
| CN112009677A (en) * | 2020-08-27 | 2020-12-01 | 彩虹无人机科技有限公司 | Variable-diameter unmanned tilt rotorcraft |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20170517 |
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