CN106081100A - The double vector of single rotor advances autogyro and control method thereof - Google Patents
The double vector of single rotor advances autogyro and control method thereof Download PDFInfo
- Publication number
- CN106081100A CN106081100A CN201610629783.9A CN201610629783A CN106081100A CN 106081100 A CN106081100 A CN 106081100A CN 201610629783 A CN201610629783 A CN 201610629783A CN 106081100 A CN106081100 A CN 106081100A
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- power set
- rotating shaft
- wing
- autogyro
- tumbler
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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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)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
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Abstract
The invention discloses a kind of double vector of single rotor and advance autogyro and control method thereof, the double vector of single rotor advances autogyro to include fuselage, two wings, two rotating shafts, two power set, two tumblers and autorotation rotor driver, wherein, two wings are without rudder face wing, are fixedly installed on described fuselage both sides；Two wings are equipped with the rotating shaft hole through wing along wing expansion direction；Two rotating shafts are each passed through the rotating shaft hole of corresponding wing, and one end is fixedly linked with corresponding power set, and the other end is connected with the corresponding tumbler being fixedly installed in fuselage；Tumbler is used for exporting moment of torsion to rotating shaft, and then power set are rotated relative to fuselage；Autorotation rotor driver includes central siphon, rotary shaft, spinning propeller and steering wheel, utilizes raw lift of miscarrying.Present configuration is simple, and flight speed is fast, it is possible to very-short-reach landing, has bigger practical value.
Description
Technical field
The present invention relates to air line technology, particularly relate to a kind of double vector of single rotor and advance autogyro and control thereof
Method.
Background technology
Fixed wing airplane is the airborne vehicle being produced lift by the fixing wing of fuselage.Although fixed wing airplane is relative to going straight up to
Machine, gyroplane have the features such as fast, the safety and comfort of speed, but its low-speed performance is poor, and landing needs longer runway, to rising
The condition of fall requires harsher.
Harsher problem is required for solving landing condition, in traditional field, can the aircraft of short distance/VTOL
There are two kinds: helicopter, autogyro.
Helicopter is a kind of aircraft being produced lift by power drive top rotor wing rotation, and it has low altitude flight, low
Speed flight, can the feature such as VTOL.But the cruising speed of helicopter is relatively low, and voyage is shorter, structure is complicated, and due to directly
The rotor of the machine of liter is to be produced lift by power drive, and once engine cut-off will be unable to safe landing.
Autogyro is a kind of Corkscrews aircraft with unpowered spinning aerofoil as lifting surface, represents type and serves as reasons
U.S. NASA subsidizes the CarterCopter gyroplane developed and the Hawk-4 gyroplane of GBA company development.Due to autorotating rotor
Relying on front to carry out stream to blow and keep rotary state, therefore, once body runs out of steam, and it still can rely on autorotation to pacify
Full landing；Meanwhile, have very-short-reach take off, point type landing, simple in construction, the feature such as easy operation.But autogyro
Cruising speed is relatively low, it is difficult to obtain big speed as fixed wing airplane.
Summary of the invention
The technical problem to be solved is for defect involved in background technology, it is provided that a kind of single rotor
Double vectors advance autogyro and control method, very-short-reach landing, and flight speed fast, simple in construction, can safely
Land.
The present invention solves above-mentioned technical problem by the following technical solutions:
The double vector of a kind of single rotor advances autogyro, including fuselage, the first to the second wing, the first to the second rotating shaft, the
One to the second power set, the first to the second tumbler and autorotation rotor driver；
Described the first to the second wing is without rudder face wing, is respectively fixedly disposed at described fuselage both sides；
Described the first to the second wing is equipped with the rotating shaft hole through wing along wing expansion direction；
Described first rotating shaft is through the rotating shaft hole of the first wing, and one end is fixedly linked with described first power set, the other end
It is connected with the first tumbler being fixedly installed in described fuselage；
Described first tumbler is used for exporting moment of torsion to described first rotating shaft, and then makes be connected in the first rotating shaft first
Power set rotate relative to fuselage；
Described second rotating shaft is through the rotating shaft hole of the second wing, and one end is fixedly linked with described second power set, the other end
It is connected with the second tumbler being fixedly installed in described fuselage；
Described second tumbler is used for exporting moment of torsion to described second rotating shaft, and then makes be connected in the second rotating shaft second
Power set rotate relative to fuselage；
Described first power set, the second power set are used to produce for the thrust advancing and changing attitude；
Described autorotation rotor driver includes central siphon, rotary shaft, spinning propeller and steering wheel；
Described central siphon is arranged on the axis of fuselage, and lower end is fixedly linked with fuselage top, upper end and the lower end of described rotary shaft
Hinged；
Described spinning propeller comprises rotating disk and some blades being uniformly arranged on rotating disk periphery, wherein, rotating disk
Center is provided with through hole, is provided with bearing in through hole；
Described spinning propeller is rotationally connected by the upper end of the bearing in rotating disk central through hole with described rotary shaft, it is possible to
Freely rotatable relative to rotary shaft；
Described steering wheel is fixed on described central siphon, and output shaft rotates with described rotary shaft, at described central siphon and fuselage axis
The angle between described rotary shaft and central siphon is regulated in the plane at place.
Advancing the further prioritization scheme of autogyro as the double vector of list rotor of the present invention, described first rotates dress
Put, the second tumbler all comprises motor, reduction gearing and drive link；
The outfan of described motor is engaged with one end of drive link by reduction gearing；
In described first tumbler, the other end of drive link engages with described first rotating shaft；
In described second tumbler, the other end of drive link engages with described second rotating shaft.
The further prioritization scheme of autogyro, described first power dress is advanced as the double vector of list rotor of the present invention
Put, the second power set all include propeller, electromotor, fuel tank, oil pipe, enging cabin, trim weight and throttle steering wheel；
Described fuel tank is arranged in enging cabin, by described oil pipe and the engine pipeline phase being arranged on enging cabin front end
Even；
Described throttle steering wheel is arranged on the engine, is used for controlling described oil in engine door folding degree；
Described propeller is fixedly linked with the output shaft of described electromotor, is used for producing thrust；
Described trim weight is arranged on the rear end of described enging cabin；
In described first power set, the side of enging cabin is fixedly linked with one end of described first rotating shaft, and trim weight is used
In the moment that balanced engine weight produces relative to the first rotating shaft；
In described second power set, the side of enging cabin is fixedly linked with one end of described second rotating shaft, and trim weight is used
In the moment that balanced engine weight produces relative to the second rotating shaft.
Advancing the further prioritization scheme of autogyro as the double vector of list rotor of the present invention, described central siphon points to Dan Xuan
The double vector of the wing advances the tail of autogyro, and the angle between central siphon and horizontal plane is 80 degree.
Advance the further prioritization scheme of autogyro as the double vector of list rotor of the present invention, described fuselage, first to
Second wing, autorotation rotor driver all use carbon fibre to make.
The invention also discloses the control method advancing autogyro based on the double vector of this list rotor, comprise following mistake
Journey:
When the double vector of single rotor advances autogyro to start, the first power set, the second power set produce thrust forward,
Autogyro is accelerated forwardly, and now, the first wing, the second wing produce lift, the spinning of autorotation rotor driver
Propeller produces lift owing to carrying out flow rotation；
When the double vector of single rotor advances the pace of autogyro to reach default threshold speed, revolved by regulation autorotation
Steering wheel in swing device changes the blade angle of attack of spinning propeller so that it is tending to zero degree, now, autorotation rotor driver does not produces
Raw lift, lift is produced by the first wing and the second wing；
When needing the double vector of single rotor to advance autogyro to make elevating movement, control the first tumbler and the second tumbler
In motor export simultaneously forward secondary to moment so that the first power set and the second power set produce simultaneously forward secondary to
Deflection, the thrust relative CG that the first power set and the second power set produce produce forward secondary to moment；
When needing the double vector of single rotor to advance autogyro to make rolling movement, control the first tumbler and the second tumbler
In motor export incorgruous moment so that the first power set and the second power set produce differential deflection, the first power set
The thrust relative CG produced with the second power set produces incorgruous moment.
The present invention uses above technical scheme compared with prior art, has following technical effect that
1., based on autogyro itself, cancel tail-rotor, rudder face so that whole body not only has traditional autobiography rotor
Machine short take-off and landing, engine cut-off can be while the features such as safe landing, and structure is simpler, and reliability significantly improves；
2. it is connected in the flight attitude to the present invention that verts of vector engine in rotating shaft by wing two ends to be controlled, permissible
Obtain bigger mobility, without the need for increasing extra attitude-control device, safety of having a smooth flight；
3. during low speed, spinning blade and wing provide lift jointly, and payload is higher；
4. changing body attitude by vector engine, the angle of attack that can make spinning blade is zero, is the most only provided by wing and rises
Power, can high-speed flight.
Accompanying drawing explanation
Fig. 1 is the side view that the double vector of list rotor of the present invention advances autogyro；
Fig. 2 is the top view that the double vector of list rotor of the present invention advances autogyro；
Fig. 3 is that the double vector of list rotor of the present invention advances the structural representation of tumbler in autogyro；
Fig. 4 is the structural representation that the double vector of list rotor of the present invention advances autogyro medium power device；
Fig. 5 is that the double vector of list rotor of the present invention advances the structural representation of autorotating rotor device in autogyro.
In figure: 1-fuselage, 2-wing, 3-power set, 4-tumbler, 5-autorotation rotor driver, 6-rotating shaft, 7-T
Type metallic plate, 8-motor, 9-reduction gearing, 10-potentiometer, 11-drive link, 12-output gear, 13-electromotor, 14-fuel tank,
15-oil pipe, 16-enging cabin, 17-trim weight, 18-throttle steering wheel, 19-engine blade, 20-central siphon, 21-rotary shaft,
22-spinning propeller, 23-steering wheel, 24-rotating disk, 25-blade.
Detailed description of the invention
Below in conjunction with the accompanying drawings technical scheme is described in further detail:
As shown in Figures 1 to 5, the invention discloses the double vector of a kind of single rotor and advance autogyro, including fuselage, first
Fill to the second wing, the first to the second rotating shaft, the first to the second power set, the first to the second tumbler and autorotation rotor
Put.
Described the first to the second wing is without rudder face wing, is respectively fixedly disposed at described fuselage both sides；First to
Two wings are equipped with the rotating shaft hole through wing along wing expansion direction；First rotating shaft passes the rotating shaft hole of the first wing,
One end is fixedly linked with described first power set, the other end and the first tumbler phase being fixedly installed in described fuselage
Even；First tumbler is used for exporting moment of torsion to described first rotating shaft, and then makes the first power being connected in the first rotating shaft
Device rotates relative to fuselage；Second rotating shaft is through the rotating shaft hole of the second wing, and one end is solid with described second power set
Fixed connected, the other end is connected with the second tumbler being fixedly installed in described fuselage；Second tumbler is used for exporting torsion
Square gives described second rotating shaft, and then the second power set being connected in the second rotating shaft are rotated relative to fuselage；First
Power set, the second power set are used to produce for the thrust advancing and changing attitude.
Described autorotation rotor driver includes central siphon, rotary shaft, spinning propeller and steering wheel；Central siphon is arranged on fuselage
On axis, lower end is fixedly linked with fuselage top, and upper end is hinged with the lower end of described rotary shaft；Spinning propeller comprises rotation
Dish and some blades being uniformly arranged on rotating disk periphery, wherein, the center of rotating disk is provided with through hole, is provided with bearing in through hole；
Spinning propeller is rotationally connected by the upper end of the bearing in rotating disk central through hole with described rotary shaft, it is possible to relative to turning
Moving axis is freely rotatable；Steering wheel is fixed on described central siphon, and output shaft rotates with described rotary shaft, at described central siphon and fuselage
The angle between described rotary shaft and central siphon is regulated in the plane at axis place.
Described first tumbler, the second tumbler all comprise motor, reduction gearing and drive link, the outfan of motor
Engaged with one end of drive link by reduction gearing；In first tumbler, the other end of drive link is nibbled with described first rotating shaft
Close；In second tumbler, the other end of drive link engages with described second rotating shaft.Can by the first tumbler, the
Two tumblers arrange potentiometer, to obtain the first rotating shaft and the turned position of the second rotating shaft.
Described first power set, the second power set all include propeller, electromotor, fuel tank, oil pipe, enging cabin,
Trim weight and throttle steering wheel；Fuel tank is arranged in enging cabin, by described oil pipe be arranged on enging cabin front end send out
Motivation pipeline is connected；Throttle steering wheel is arranged on the engine, is used for controlling described oil in engine door folding degree；Propeller with
The output shaft of described electromotor is fixedly linked, and is used for producing thrust；Trim weight is arranged on the rear end of described enging cabin；First
In power set, the side of enging cabin is fixedly linked with one end of described first rotating shaft, and trim weight is used for balanced engine
The moment that weight produces relative to the first rotating shaft；In second power set, the side of enging cabin and one end of described second rotating shaft
It is fixedly linked, the moment that trim weight produces relative to the second rotating shaft for balanced engine weight.
Described central siphon points to the double vector of single rotor and advances the tail of autogyro, and the angle between central siphon and horizontal plane
It it is 80 degree.
Described fuselage, the first to the second wing, autorotation rotor driver all use carbon fibre to make, and intensity is high, quality
Gently.
When the double vector of single rotor advances autogyro to start, the first power set, the second power set produce forward
Thrust so that autogyro is accelerated forwardly, now, the first wing, second wing produce lift, autorotation rotor driver from
Rotating screw produces lift owing to carrying out flow rotation；
When the double vector of single rotor advances the pace of autogyro to reach default threshold speed, revolved by regulation autorotation
Steering wheel in swing device changes the blade angle of attack of spinning propeller so that it is tending to zero degree, now, autorotation rotor driver does not produces
Raw lift, lift is produced by the first wing and the second wing；
When needing the double vector of single rotor to advance autogyro to make elevating movement, control the first tumbler and the second tumbler
In motor export simultaneously forward secondary to moment so that the first power set and the second power set produce simultaneously forward secondary to
Deflection, the thrust relative CG that the first power set and the second power set produce produce forward secondary to moment；
When needing the double vector of single rotor to advance autogyro to make rolling movement, control the first tumbler and the second tumbler
In motor export incorgruous moment so that the first power set and the second power set produce differential deflection, the first power set
The thrust relative CG produced with the second power set produces incorgruous moment.
It is understood that unless otherwise defined, all terms used herein (include skill to those skilled in the art of the present technique
Art term and scientific terminology) have with the those of ordinary skill in art of the present invention be commonly understood by identical meaning.Also
It should be understood that those terms defined in such as general dictionary should be understood that have with in the context of prior art
The consistent meaning of meaning, and unless defined as here, will not explain by idealization or the most formal implication.
Above-described detailed description of the invention, has been carried out the purpose of the present invention, technical scheme and beneficial effect further
Describe in detail, be it should be understood that the detailed description of the invention that the foregoing is only the present invention, be not limited to this
Bright, all within the spirit and principles in the present invention, any modification, equivalent substitution and improvement etc. done, should be included in the present invention
Protection domain within.
Claims (6)
1. the double vector of a single rotor advances autogyro, it is characterised in that include fuselage, the first to the second wing, first
To the second rotating shaft, the first to the second power set, the first to the second tumbler and autorotation rotor driver；
Described the first to the second wing is without rudder face wing, is respectively fixedly disposed at described fuselage both sides；
Described the first to the second wing is equipped with the rotating shaft hole through wing along wing expansion direction；
Described first rotating shaft is through the rotating shaft hole of the first wing, and one end is fixedly linked with described first power set, the other end
It is connected with the first tumbler being fixedly installed in described fuselage；
Described first tumbler is used for exporting moment of torsion to described first rotating shaft, and then makes be connected in the first rotating shaft first
Power set rotate relative to fuselage；
Described second rotating shaft is through the rotating shaft hole of the second wing, and one end is fixedly linked with described second power set, the other end
It is connected with the second tumbler being fixedly installed in described fuselage；
Described second tumbler is used for exporting moment of torsion to described second rotating shaft, and then makes be connected in the second rotating shaft second
Power set rotate relative to fuselage；
Described first power set, the second power set are used to produce for the thrust advancing and changing attitude；
Described autorotation rotor driver includes central siphon, rotary shaft, spinning propeller and steering wheel；
Described central siphon is arranged on the axis of fuselage, and lower end is fixedly linked with fuselage top, upper end and the lower end of described rotary shaft
Hinged；
Described spinning propeller comprises rotating disk and some blades being uniformly arranged on rotating disk periphery, wherein, rotating disk
Center is provided with through hole, is provided with bearing in through hole；
Described spinning propeller is rotationally connected by the upper end of the bearing in rotating disk central through hole with described rotary shaft, it is possible to
Freely rotatable relative to rotary shaft；
Described steering wheel is fixed on described central siphon, and output shaft rotates with described rotary shaft, at described central siphon and fuselage axis
The angle between described rotary shaft and central siphon is regulated in the plane at place.
The double vector of single rotor the most according to claim 1 advances autogyro, it is characterised in that described first rotates dress
Put, the second tumbler all comprises motor, reduction gearing and drive link；
The outfan of described motor is engaged with one end of drive link by reduction gearing；
In described first tumbler, the other end of drive link engages with described first rotating shaft；
In described second tumbler, the other end of drive link engages with described second rotating shaft.
The double vector of single rotor the most according to claim 1 advances autogyro, it is characterised in that described first power dress
Put, the second power set all include propeller, electromotor, fuel tank, oil pipe, enging cabin, trim weight and throttle steering wheel；
Described fuel tank is arranged in enging cabin, by described oil pipe and the engine pipeline phase being arranged on enging cabin front end
Even；
Described throttle steering wheel is arranged on the engine, is used for controlling described oil in engine door folding degree；
Described propeller is fixedly linked with the output shaft of described electromotor, is used for producing thrust；
Described trim weight is arranged on the rear end of described enging cabin；
In described first power set, the side of enging cabin is fixedly linked with one end of described first rotating shaft, and trim weight is used
In the moment that balanced engine weight produces relative to the first rotating shaft；
In described second power set, the side of enging cabin is fixedly linked with one end of described second rotating shaft, and trim weight is used
In the moment that balanced engine weight produces relative to the second rotating shaft.
The double vector of single rotor the most according to claim 1 advances autogyro, it is characterised in that described central siphon points to single
The double vector of rotor advances the tail of autogyro, and the angle between central siphon and horizontal plane is 80 degree.
The double vector of single rotor the most according to claim 1 advances autogyro, it is characterised in that described fuselage, first
Carbon fibre is all used to make to the second wing, autorotation rotor driver.
6. advance the control method of autogyro based on the double vector of the single rotor described in claim 1, it is characterised in that comprise
Procedure below:
When the double vector of single rotor advances autogyro to start, the first power set, the second power set produce thrust forward,
Autogyro is accelerated forwardly, and now, the first wing, the second wing produce lift, the spinning of autorotation rotor driver
Propeller produces lift owing to carrying out flow rotation；
When the double vector of single rotor advances the pace of autogyro to reach default threshold speed, revolved by regulation autorotation
Steering wheel in swing device changes the blade angle of attack of spinning propeller so that it is tending to zero degree, now, autorotation rotor driver does not produces
Raw lift, lift is produced by the first wing and the second wing；
When needing the double vector of single rotor to advance autogyro to make elevating movement, control the first tumbler and the second tumbler
In motor export simultaneously forward secondary to moment so that the first power set and the second power set produce simultaneously forward secondary to
Deflection, the thrust relative CG that the first power set and the second power set produce produce forward secondary to moment；
When needing the double vector of single rotor to advance autogyro to make rolling movement, control the first tumbler and the second tumbler
In motor export incorgruous moment so that the first power set and the second power set produce differential deflection, the first power set
The thrust relative CG produced with the second power set produces incorgruous moment.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610629783.9A CN106081100B (en) | 2016-08-03 | 2016-08-03 | The double vectors of single rotor promote autogyro and its control method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610629783.9A CN106081100B (en) | 2016-08-03 | 2016-08-03 | The double vectors of single rotor promote autogyro and its control method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106081100A true CN106081100A (en) | 2016-11-09 |
| CN106081100B CN106081100B (en) | 2018-01-23 |
Family
ID=57453938
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610629783.9A Expired - Fee Related CN106081100B (en) | 2016-08-03 | 2016-08-03 | The double vectors of single rotor promote autogyro and its control method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106081100B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927035A (en) * | 2017-02-22 | 2017-07-07 | 南京航空航天大学 | High maneuver autogyro and its control method |
| CN111498101A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
| CN102267561A (en) * | 2010-04-27 | 2011-12-07 | 尤洛考普特公司 | Method of operating and controlling the deflection angle of a control surface of a hybrid helicopter |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| EP2690012A1 (en) * | 2012-07-27 | 2014-01-29 | Eurocopter Deutschland GmbH | Semi-convertible rotorcraft |
| CN104477377A (en) * | 2014-12-31 | 2015-04-01 | 北京航空航天大学 | Composite type multi-mode multi-purpose aircraft |
| CN205952310U (en) * | 2016-08-03 | 2017-02-15 | 南京航空航天大学 | Single rotor bivectorial volume impels autogyro |
-
2016
- 2016-08-03 CN CN201610629783.9A patent/CN106081100B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1907806A (en) * | 2005-08-02 | 2007-02-07 | 韩培洲 | helicopter with tilted front rotary wing |
| CN102267561A (en) * | 2010-04-27 | 2011-12-07 | 尤洛考普特公司 | Method of operating and controlling the deflection angle of a control surface of a hybrid helicopter |
| CN103241376A (en) * | 2012-02-01 | 2013-08-14 | 北京安翔动力科技有限公司 | Vector power vertical takeoff and landing aircraft and vector power system thereof |
| EP2690012A1 (en) * | 2012-07-27 | 2014-01-29 | Eurocopter Deutschland GmbH | Semi-convertible rotorcraft |
| CN104477377A (en) * | 2014-12-31 | 2015-04-01 | 北京航空航天大学 | Composite type multi-mode multi-purpose aircraft |
| CN205952310U (en) * | 2016-08-03 | 2017-02-15 | 南京航空航天大学 | Single rotor bivectorial volume impels autogyro |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106927035A (en) * | 2017-02-22 | 2017-07-07 | 南京航空航天大学 | High maneuver autogyro and its control method |
| CN111498101A (en) * | 2020-04-20 | 2020-08-07 | 飞的科技有限公司 | Aircraft with a flight control device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106081100B (en) | 2018-01-23 |
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