CN107380458A - A kind of manned investigation single-blade list rotor craft of long endurance of hovering - Google Patents
A kind of manned investigation single-blade list rotor craft of long endurance of hovering Download PDFInfo
- Publication number
- CN107380458A CN107380458A CN201710667846.4A CN201710667846A CN107380458A CN 107380458 A CN107380458 A CN 107380458A CN 201710667846 A CN201710667846 A CN 201710667846A CN 107380458 A CN107380458 A CN 107380458A
- Authority
- CN
- China
- Prior art keywords
- blade
- rotor
- propeller
- hovering
- manned
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D35/00—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions
-
- 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
- Y02T50/40—Weight reduction
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Abstract
The invention discloses a kind of manned investigation single-blade list rotor craft of long endurance of hovering, body part includes frame, bearing, hydrogen energy source system and electronic flight control system, Rotary-Wing Department is divided to including rotor shaft, propeller hub, single-blade leaf, arm bar, electric slip ring and two motors, rotor shaft is through electric slip ring and bearing, the end set of rotor shaft has propeller hub, single-blade leaf and arm bar are installed on the propeller hub, arm bar end horizontal both sides are respectively arranged with a motor, and propeller is provided with outside motor.Compared with prior art, the motor of the present invention drives propeller rotation to produce power, the rotation of single-blade leaf is driven to produce lift, the propeller of arm of force boom end promotes this system to eliminate the connection between rotor system and fuselage, and reverse torsion, therefore offset torsion without tail-rotor, transmission system simplifies, mitigate weight, also allow for hovering.
Description
Technical field
The present invention relates to a kind of single rotor craft, the manned investigation single-blade list rotor of particularly a kind of long endurance of hovering
Aircraft, belong to air line design field.
Background technology
Long endurance, heavy－duty are the permanent objectives that aviation people pursues.Long endurance typically requires that cruising time is tens hours
Or even several days, this target of long endurance is accomplished tentatively on Fixed Wing AirVehicle, but at present be still restriction helicopter/
One big bottleneck of gyroplane development.Helicopter/gyroplane has the incomparable advantage of many Fixed Wing AirVehicles, therefore develops
Long endurance helicopter/gyroplane is significant.
Someone/unmanned plane as a platform, combined with other industry more and more closer, including geographical mapping, big number
According to fields such as agricultural, police service security protection, intelligence reconnaissances, an instrument in solution, the potentiality and value of application are gradually become
It is huge, in conventional flight equipment, reach the technical level of single rotor, but the single rotor of tradition directly drives by engine
Dynamic rotor rotational, then in rotor rotational in the presence of the reverse torsion between fuselage, this torsion needs to support by tail-rotor
Disappear, and general double oar rotors need bigger initial drive force, and can be vibrated with obvious, therefore rotor system and fuselage
Between bonding strength also just have higher requirement, also cause single rotor craft to tend not to bear to fly for a long time,
And in hovering due to the effect of reverse torsion, fuselage nor highly stable, therefore, it is possible to bear flying for long time and
The vehicle airframe of steadily hovering will be got the favour of people.
, can be effectively such as a kind of structure design of new asymmetric lift of balance of Application No. 201510152040.2
Rotor lift uneven the drawbacks of restricting flying speed when avoiding flying before this helicopter, single-rotor helicopter can be allowed to keep special
The larger lifting of speed is realized in the case of point.The present invention by rotor head be designed to can to the inclined structure in side, in conjunction with
The measures such as the transverse shifting by weight on machine, body center of gravity is allowed to be held relative to rotor according to being continuously increased for flying speed
Continuously adjusted to advancing blade side, so as to realize that the dynamic with single Hingeless Rotor in Forward Flight asymmetry lift overlaps, and then realization can
High-speed flight, while and can avoids the drawbacks of co-axial rotor scenario-frame weight is big, complicated, its combination property will surpass easily
Cross co-axial rotor high-speed helicopter, single rotor craft in the program still be unable to do without the tail-rotor of twisting resistance, and hovering flight is not
It is enough stable.
And for example a kind of single-oar disk type unmanned vehicle of Application No. 201010190699.4, undercarriage upper-end part of driving are fixed
There is triangular shape wing, triangular shape wing is connected with duct, and duct centre is on duct central axis equipped with motor, electricity
Motivation is placed in duct internal upper part by paddle shaft, connection oar, and duct bottom is provided with the spin-ended fixed rudder face of uniform circular arrangement, contains
Road bottom longitudinal direction rear and front end is symmetrically respectively provided with control vane, and both ends are symmetrically respectively provided with control vane to duct bottom transverse to the left and right,
Duct top is equipped with Aerial Electronic Equipment cabin, and Aerial Electronic Equipment cabin is built with automatic pilot and electrokinetic cell.The present invention is compact-sized, sets
Meter is reasonable, can VTOL anywhere, hover, spiral, noise in flight it is very low, disguised very good, it has low
Empty low speed, mobility strong, various aerobatics can be done, flight efficiency is high, and saves fuel, and easy maintenance is economical and practical, adapts to
Property it is strong, adapt to the VTOL flight in the place such as city, securely and reliably, the single-blade aircraft in the program has still continued to use tradition
Rotor shaft driving blade type of belt drive, bigger initial drive force, the company between rotor system and fuselage are needed during rotation
Connecing intensity also has higher requirement, therefore is not suitable for flying for long time and hovering.
The content of the invention
The technical problem to be solved in the invention is to be directed to above-mentioned the deficiencies in the prior art, and provides one kind and can hover and grow boat
When manned investigation single-blade list rotor craft.
In order to solve the above technical problems, the technical solution adopted by the present invention is：
A kind of manned investigation single-blade list rotor craft of long endurance of hovering, including body part and rotor part, the machine
Body portion includes frame, bearing, hydrogen energy source system and electronic flight control system, hydrogen energy source system and the electronic flight control
System is located at machine frame inside, and the bearing is located at upper rack；The Rotary-Wing Department point includes rotor shaft, propeller hub, single-blade leaf, the arm of force
Bar, electric slip ring and two motors, the electric slip ring are located at bearing top, and the rotor shaft is set through electric slip ring and bearing
Put, the end set of rotor shaft has propeller hub, and single-blade leaf is provided with the propeller hub, is set on propeller hub away from single-blade leaf direction strong
Armed lever, the arm bar end horizontal both sides are respectively arranged with a motor, spiral are provided with outside the motor
Oar.
As further preferred scheme, the blade of two propellers is in opposite direction, the rotation direction phase of two propellers
Instead.
As further preferred scheme, it is provided between propeller hub and the single-blade leaf for controlling the only of single-blade leaf displacement
Vertical blade controlling organization.
As further preferred scheme, air compression system, heat-exchange system, cold is additionally provided with the body part
But water management system and power control system.
Compared with prior art, the manned investigation single-blade list rotor craft of a kind of long endurance of hovering of the invention, lead to
Cross hydrogen energy source burning and produce electric energy to two motors power supplies, motor drives propeller rotation to produce power, drive list
Blade rotation produces lift, and the displacement of blade is carried out and then the flight attitude of change of flight device, arm bar by blade control
It is to change the driving shape for transmitting rotatory force from fuselage to rotor system in the past that the propeller of end, which promotes the benefit of this system,
Formula, it is thus basic to reduce the reverse torsion even eliminated between rotor system and fuselage, therefore no longer need tail-rotor to support
Disappear torsion, due to the power of active transmission being not present between fuselage and rotor system, therefore also reduces fuselage and rotor system
Between bonding strength, long-time navigate by water under also the connecting portion of fuselage and rotor will not be caused to damage, and departing from compared with
Big rotation driving force, also eliminates the vibration of connecting portion, makes more to stablize during hovering, is easy to hover for a long time, overall to pass
Dynamic system simplifies, and mitigates fuselage weight, reduces energy consumption.
Brief description of the drawings
Fig. 1 is the structural representation of the present invention；
Fig. 2 is the structural representation of motor；
Wherein, 1- frames, 2- bearings, 3- hydrogen energy source systems, 4- electronic flight control systems, 5- rotor shafts, 6- propeller hubs, 7- single-blades
Leaf, 8- arm bars, 9- electric slip rings, 10- motors, 11- propellers, 12- individual pitch controls mechanism.
Embodiment
The optimal technical scheme that the invention will now be described in detail with reference to the accompanying drawings.
As shown in figure 1, a kind of manned investigation single-blade list rotor craft of long endurance of hovering of the present invention, including body
Part and rotor part；
The body part includes frame 1, bearing 2, hydrogen energy source system 3 and electronic flight control system 4, and wherein frame 1 is used for
Aircraft structure, installation seat, energy resource system and electronic equipment etc. are connected, bearing 2 is arranged on upper rack, reduces rotor system
Friction in system rotary course, hydrogen energy source system 3 are arranged on central rack, and the position of centre of gravity of aircraft is anti-by the burning of hydrogen
Energy should be produced, then by power conversion system, hydrogen is finally produced and supplies electricity to driving motor supplies power, electronic flight control is
System 4, installed in the position of centre of gravity of aircraft, control the posture and flight path of aircraft；
The hydrogen energy source system 3 and electronic flight control system 4 are located inside frame 1, and the bearing 2 is located at the top of frame 1, hydrogen
The storage mode of energy resource system 3 uses cryogenic high pressure storage of liquid hydrogen, and cryogenic high pressure hydrogen storage technology possesses current highest quality storage
Hydrogen density, and aneroid hydrogen loss in 24 hours can be realized；
The Rotary-Wing Department is divided to including rotor shaft 5, propeller hub 6, single-blade leaf 7, arm bar 8, electric slip ring 9 and two motors 10, its
Middle rotor shaft 5 is the central link part of fuselage and rotor system, and propeller hub 6 is used to install rotor blade, and makes rotor with going straight up to
The intermediate member that machine transmission system is connected with steerable system, single-blade leaf 7 is arranged on the upper of propeller hub, with individual pitch control mechanism
12 connections, for producing the flight lift of aircraft in rotary course, arm bar 8 is intended only as connection and arm of force part, no
The lifting force output of aircraft is participated in, when electric slip ring 9 is used for unrestricted continuous rotation, transimission power power supply, signal power source, mainly
For the power supply of two motors 10, motor 10 is positive to oppose dress for producing rotary power with propeller, eliminates rotation
Moment of torsion caused by turning；
The electric slip ring 9 is located at the top of bearing 2, is fixed between bearing 2 and the outer stator of electric slip ring 9 by support frame, the rotation
The internal stator and bearing 2 of wing axle 5 through electric slip ring 9 are set, and the end set of rotor shaft 5 has a propeller hub 6, on the propeller hub 6
Single-blade leaf 7 is installed, the direction of single-blade leaf 7 is provided with arm bar 8 on propeller hub 6, single-blade leaf 7 is located at same axle with arm bar 8
On line, the end horizontal both sides of arm bar 8 are respectively arranged with a motor 10, are provided with outside the motor 10
One propeller 11, there is a power output shaft on motor 10, propeller 11 is arranged on power output shaft, two drives
The power output shaft of dynamic motor 10 is in coaxial line position；
The combustion reaction of hydrogen produces electric energy and is transferred to the outer stator of electric slip ring 9, then is transferred to by the outer stator of electric slip ring 9
In it on internal rotor, electric energy is delivered to motor 10 by circuit by rotor, the inside of arm bar 8, which has, is connected to drive
The circuit of dynamic motor 10；
Rotor shaft 5, which is located in bearing 2, to be rotated, and can produce faint friction, and this friction can bring less torsion, is typically being flown
Row device afterbody installation direction rudder is offset.
The blade of propeller 11 described in two is in opposite direction, and the rotation direction of two propellers 11 is on the contrary, two spirals
The rotation of oar 11 produces the thrust of horizontal direction, and front propeller provides pulling force, and rear screw shaft provides thrust；Propeller 11 is to lean on spiral shell
Mother is fixed on motor 10, when motor 10 moves, drives propeller 11 to rotate to produce corresponding pulling force or thrust,
To drive whole rotor part to be rotated centered on rotor shaft 5.
The individual pitch control mechanism 12 for controlling the displacement of single-blade leaf 7 is provided between the propeller hub 6 and single-blade leaf 7,
Blade displacement is controlled by electromechanical actuator, and then to control the heading of aircraft and flight attitude.
Air compression system, heat-exchange system, cooling water management system and power supply control are additionally provided with the body part
System processed, it is accessory system above
Further, air compression system, system design are the two-stage centrifugal compressor of series connection, and it can be whole from engine by air
The suction of cover entrance is flowed, is supplied to fuel cell pack to do oxygen sources after compressed air；
Heat-exchange system heat exchanger assembly is located at the front portion of enging cabin, the lower section of motor.Air enters from cowling
Mouth is flowed into heat exchanger, cools down and air-water mixture is discarded caused by fuel cell.Air-water mixture after cooling comes cyclone
Device, part water come back to stand-by in cooling water tank, and part water and gas leave enging cabin by outlet discharge；
Cooling water management system, system are made up of water tank, water pump, filter and flowmeter, and fuel cell reaction will produce a large amount of
Heat, in order to ensure suitable stack temperature, coolant takes away caused used heat from cooling pipe into pile；
Power control system system exchanges plate, control plate and internal battery plate by center and formed（For starting fuel electricity
Pond）.
Further, the mode of low temperature and high pressure composite hydrogen occluding, container are integrally made up of three-decker, from outside to inside successively
Hydrogen cylinder is wound entirely for external jacket, insulation construction layer, aluminum liner carbon fiber.
Above-described embodiment, the purpose of the present invention, technical scheme and beneficial effect are carried out further
Describe in detail, should be understood that the embodiment that the foregoing is only the present invention, be not limited to this hair
It is bright, within the spirit and principles of the invention, any modification, equivalent substitution and improvements done etc., it should be included in the present invention
Protection domain within.
Claims (4)
- A kind of 1. manned investigation single-blade list rotor craft of long endurance of hovering, it is characterised in that：Including body part and rotation Alar part, the body part include frame（1）, bearing（2）, hydrogen energy source system（3）And electronic flight control system（4）, institute State hydrogen energy source system（3）And electronic flight control system（4）Positioned at frame（1）Inside, the bearing（2）Positioned at frame（1）On Portion；The Rotary-Wing Department point includes rotor shaft（5）, propeller hub（6）, single-blade leaf（7）, arm bar（8）, electric slip ring（9）With two drivings Motor（10）, the electric slip ring（9）Positioned at bearing（2）Top, the rotor shaft（5）Through electric slip ring（9）And bearing（2）If Put, rotor shaft（5）End set have propeller hub（6）, the propeller hub（6）On single-blade leaf is installed（7）, propeller hub（6）It is upper to deviate from list Blade（7）Direction is provided with arm bar（8）, the arm bar（8）End horizontal both sides are respectively arranged with a motor （10）, the motor（10）Outside is provided with propeller（11）.
- 2. a kind of manned investigation single-blade list rotor craft of long endurance of hovering according to claim 1, its feature exist In：Two propellers（11）Blade it is in opposite direction, two propellers（11）Rotation direction it is opposite.
- 3. a kind of manned investigation single-blade list rotor craft of long endurance of hovering according to claim 1, its feature exist In：The propeller hub（6）With single-blade leaf（7）Between be provided with for controlling single-blade leaf（7）The individual pitch control mechanism of displacement （12）.
- 4. a kind of manned investigation single-blade list rotor craft of long endurance of hovering according to claim 1, its feature exist In：Air compression system, heat-exchange system, cooling water management system and power supply system are additionally provided with the body part System.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710667846.4A CN107380458A (en) | 2017-08-07 | 2017-08-07 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710667846.4A CN107380458A (en) | 2017-08-07 | 2017-08-07 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107380458A true CN107380458A (en) | 2017-11-24 |
Family
ID=60354376
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710667846.4A Withdrawn CN107380458A (en) | 2017-08-07 | 2017-08-07 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
Country Status (1)
| Country | Link |
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| CN (1) | CN107380458A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111552307A (en) * | 2020-05-15 | 2020-08-18 | 航迅信息技术有限公司 | Rapid hovering method for unmanned aerial vehicle |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB504942A (en) * | 1937-11-02 | 1939-05-02 | John Josselyn | Improvements in and relating to aircraft sustaining and or lifting rotors |
| GB537478A (en) * | 1938-12-22 | 1941-06-24 | Cierva Autogiro Co Ltd | Improvements relating to aircraft sustaining rotors |
| US2281203A (en) * | 1939-11-14 | 1942-04-28 | Autogiro Co Of America | Driving mechanism for air rotors, especially aircraft sustaining rotors |
| GB659163A (en) * | 1948-06-17 | 1951-10-17 | Autogiro Co Of America | Mechanism for balancing single blade aircraft rotor |
| CN102700707A (en) * | 2012-05-28 | 2012-10-03 | 张明明 | Novel aircraft |
| CN204489177U (en) * | 2014-12-19 | 2015-07-22 | 国家电网公司 | Four rotor unmanned aircrafts |
| CN106143893A (en) * | 2015-04-13 | 2016-11-23 | 北京强度环境研究所 | A kind of NEW ADAPTIVE aircraft |
| CN106697274A (en) * | 2017-01-20 | 2017-05-24 | 蜂巢航宇科技（北京）有限公司 | Six-rotor wing unmanned aerial vehicle |
| CN207078328U (en) * | 2017-08-07 | 2018-03-09 | 雅各·维拉萨 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
-
2017
- 2017-08-07 CN CN201710667846.4A patent/CN107380458A/en not_active Withdrawn
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB504942A (en) * | 1937-11-02 | 1939-05-02 | John Josselyn | Improvements in and relating to aircraft sustaining and or lifting rotors |
| GB537478A (en) * | 1938-12-22 | 1941-06-24 | Cierva Autogiro Co Ltd | Improvements relating to aircraft sustaining rotors |
| US2281203A (en) * | 1939-11-14 | 1942-04-28 | Autogiro Co Of America | Driving mechanism for air rotors, especially aircraft sustaining rotors |
| GB659163A (en) * | 1948-06-17 | 1951-10-17 | Autogiro Co Of America | Mechanism for balancing single blade aircraft rotor |
| CN102700707A (en) * | 2012-05-28 | 2012-10-03 | 张明明 | Novel aircraft |
| CN204489177U (en) * | 2014-12-19 | 2015-07-22 | 国家电网公司 | Four rotor unmanned aircrafts |
| CN106143893A (en) * | 2015-04-13 | 2016-11-23 | 北京强度环境研究所 | A kind of NEW ADAPTIVE aircraft |
| CN106697274A (en) * | 2017-01-20 | 2017-05-24 | 蜂巢航宇科技（北京）有限公司 | Six-rotor wing unmanned aerial vehicle |
| CN207078328U (en) * | 2017-08-07 | 2018-03-09 | 雅各·维拉萨 | A kind of manned investigation single-blade list rotor craft of long endurance of hovering |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111552307A (en) * | 2020-05-15 | 2020-08-18 | 航迅信息技术有限公司 | Rapid hovering method for unmanned aerial vehicle |
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| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20171124 |
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