CN107298175A - A kind of multiple-motor aircraft based on control jet direction motion - Google Patents
A kind of multiple-motor aircraft based on control jet direction motion Download PDFInfo
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- CN107298175A CN107298175A CN201610232466.3A CN201610232466A CN107298175A CN 107298175 A CN107298175 A CN 107298175A CN 201610232466 A CN201610232466 A CN 201610232466A CN 107298175 A CN107298175 A CN 107298175A
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- guide system
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- 230000033001 locomotion Effects 0.000 title claims abstract description 20
- 238000005183 dynamical system Methods 0.000 claims abstract description 53
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000000034 method Methods 0.000 claims description 5
- 239000000203 mixture Substances 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 4
- 238000002485 combustion reaction Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 238000000354 decomposition reaction Methods 0.000 claims description 2
- 238000010276 construction Methods 0.000 abstract description 2
- 206010034719 Personality change Diseases 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 12
- 230000000694 effects Effects 0.000 description 3
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000001141 propulsive effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000011031 large-scale manufacturing process Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- 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
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
The invention discloses a kind of multiple-motor aircraft based on control jet direction motion, including fuselage and dynamical system mounted thereto, flow guide system, kinetic control system, attitude transducer, flight control system and computer；Dynamical system keeps constant relative to the direction of fuselage and produces jet vertically downward, controls the jet power output of dynamical system by flight control system by computer, keeps the balance of fuselage；Flow guide system is installed on the jet direction of dynamical system and adjustable relative to the direction of fuselage, is oriented to by computer or the artificial jet for controlling the direction of flow guide system to produce dynamical system by kinetic control system, the movement and steering of control aircraft.The present invention verting for flow guide system with the jet output of dynamical system realizes that the direction of dynamical system in the flight attitude change of aircraft, flight course keeps constant jointly, and fuselage can remain level, and simple in construction, control is flexible, is adapted to practical application.
Description
Technical field
The present invention relates to aircraft, and in particular to a kind of multiple-motor based on control jet direction motion flies
Row device.
Background technology
The steering mode of conventional aircraft, is the power output by changing dynamical system so that each power
Lift or moment of torsion is formed between system to realize.Period needs are accurately calculated by flight control system, efficiency
It is not high, it is difficult to deal with flight environment of vehicle complicated and changeable in real time.More serious the problem of is to make aircraft fuselage
Tilt, be unfavorable for carrying video recording equipment and manned manipulation on board the aircraft.
There are some more advanced Flight Vehicle Design schemes at present, made by changing the axial direction of each dynamical system
Aircraft hovering, translation, left-hand rotation, right-hand rotation, can make the fuselage of aircraft be protected all the time in flight course
Water holding is put down, and overcomes the inclined defect of fuselage when turning to of conventional aircraft.But to change dynamical system
Axial direction be actually highly difficult, the requirement for power is very high, will consume substantial amounts of energy, and
Need to re-start the structure of dynamical system design, so that the requirement that its satisfaction can be turned to, it is difficult to realize
Degree is larger, it is impossible to meet the demand of the large-scale production of consumer level aircraft and popularization and application.
The content of the invention
In order to solve the above problems, the invention discloses a kind of starting based on control jet direction motion more
Machine aircraft.
Technical scheme is as follows：
A kind of multiple-motor aircraft based on control jet direction motion, including fuselage and installed in fuselage
On dynamical system, flow guide system, kinetic control system, attitude transducer, flight control system and calculating
Machine；The dynamical system keeps constant relative to the direction of fuselage and produces jet vertically downward, by
Computer controls the jet power output of the dynamical system by the flight control system, keeps the flat of fuselage
Weighing apparatus；The flow guide system be installed on it is on the jet direction of dynamical system and adjustable relative to the direction of fuselage,
By computer or the artificial direction by the kinetic control system control flow guide system to dynamical system
The jet of generation is oriented to, and controls the movement and steering of aircraft；
Moved for aircraft and the control mode of steering is：By the computer or artificial to motion control
System is controlled, and flow guide system is verted by the kinetic control system, passes through the flow guide system
It is oriented to towards to the jet that dynamical system is produced, the jet is broken down into the decomposition in vertical direction
Decomposing force in power and horizontal direction；Decomposing force in the horizontal direction realize advance to aircraft,
Laggard, hovering, left, right translation, anticlockwise, right rotation adjustment；
It is for the control mode that aircraft is balanced：Persistently visited in flight course by the attitude transducer
The flight attitude of aircraft is surveyed, flight attitude data are sent to computer；By the computer to flight
Attitude data outputs control signals to flight control system after calculating, by the flight control system according to control signal control
The jet power output of each dynamical system is made, the jet that each dynamical system is produced is oriented to by flow guide system
The decomposing force in vertical direction afterwards is equal or deviation range in permission in；And passed by the posture
Flight attitude after being adjusted is fed back to computer by sensor, constantly repeated by computer above-mentioned calculating and
Control process, it is always poised state to keep fuselage.
Further, the dynamical system and flow guide system are respectively provided with multiple, and both quantity are equal, one
The dynamical system and flow guide system that dynamical system and a flow guide system are corresponded in one group, every group can be connected
Install, be also removably installed.
Further, the dynamical system includes but is not limited to motor, internal combustion engine or jet plane.
Further, the flow guide system includes but is not limited to deflector or vector spout.
Further, the kind of drive of the kinetic control system include but is not limited to mechanical structure transmission or
Electric transmission.
Further, a kind of structure composition of the kinetic control system and flow guide system is：
The universal ball end that the kinetic control system includes being connected to outwardly directed horn end on fuselage is closed
Bearings, the universal ball end oscillating bearing is connected by rotating shaft with flow guide system；At least two fixed seats
Between the universal ball end oscillating bearing and horn, at least two push rods pass through hinges respectively
It is connected between the fixed seat and the side wall of rotating shaft；The every push rod includes multistage point push rod, each section
Mutually socket and can relative telescopic between point push rod；
The flow guide system be deflector, including four pieces in cross arrange split flow plates, described four pieces points
Deflector is arranged in the rotating shaft of the kinetic control system after being integrally formed, can also be respectively into 90
Degree is in the rotating shaft of the kinetic control system.
Further, another structure composition of the kinetic control system and flow guide system is：
The kinetic control system includes two rotating shafts arranged in cross, the end part of two rotating shafts
It is not arranged on by bearing in the cylinder of the flow guide system；
The flow guide system includes a cylinder for being connected to outwardly directed horn end on fuselage, described
Two supports above and below being provided with cylinder, dynamical system is arranged between described two supports；Four pieces of blades
On four branch roads for being separately mounted to the rotating shaft arranged in cross.
Further, the flow guide system in original state perpendicular to fuselage plane；When needing to make aircraft
During hovering, make each flow guide system all in plumbness；Put down when needing to make aircraft front, rear, left and right
During shifting, make each flow guide system and all tilted with angle of inclination identical towards translation direction；When needing to make flight
When device left steering, right turn, each flow guide system is set to be tilted towards different directions, each flow guide system is overall
Clockwise to fluidic vectoring thrust, rotate counterclockwise guiding.
The method have the benefit that：
The present invention needs to hover, advances, retreats, stopped by using above-mentioned technical scheme, when aircraft
When car, left, right translation, left-hand rotation, right-hand rotation action, aircraft pilot need to only control each fortune respectively
Autocontrol system, or each kinetic control system is automatically controlled by a computer, by each kinetic control system band
Move each flow guide system vert, the jet formed by the direction of each flow guide system to each dynamical system be distributed into
Row is oriented to realize.And in the process, each dynamical system only controls its power output by flight control system
Size, makes each dynamical system of substantially equal to the upward propulsive force of fuselage, to keep fuselage to be always water
Level state, and the direction of each dynamical system be to maintain all the time relative to fuselage it is constant.For to sum up, i.e.,
Exported by the jet of dynamical system, coordinate the deflecting of verting of deflector, to realize the flight of aircraft jointly
Attitudes vibration, and ensure the balance of aircraft fuselage simultaneously.The simple in construction of the present invention, control are flexible,
Easily fabricated and maintenance, is highly suitable in rotor craft, unmanned plane, manned vehicle extensive
Install and use.
Advantages of the present invention will be provided in the description of embodiment part below, partly will be from following
Description in become obvious, or by the present invention practice recognize.
Brief description of the drawings
Fig. 1 is state diagram of the embodiment of the present invention 1 when advancing, retreating.
Fig. 2 is state diagram of the embodiment of the present invention 1 in left, right translation.
Fig. 3 is state diagram of the embodiment of the present invention 1 in right rotation.
Fig. 4 is state diagram of the embodiment of the present invention 1 in anticlockwise.
Fig. 5 is the flow guide system of the embodiment of the present invention 1 and the component diagram of kinetic control system.
Fig. 6 is Fig. 5 partial enlarged drawing.
Fig. 7 is that the flow guide system and kinetic control system of the embodiment of the present invention 1 are integrated with dynamical system
Structure chart.
Fig. 8 is Fig. 7 partial enlarged drawing.
Fig. 9 is the structural representation of the embodiment of the present invention 2.
Figure 10 is the flow guide system of the embodiment of the present invention 2 and the component diagram of kinetic control system.
Figure 11 is that Figure 10 removes the view after part.
Figure 12 is movement and the course changing control schematic diagram of the present invention.
Figure 13 is the balance control principle drawing of the present invention.
Embodiment
The embodiment to the present invention is described further below in conjunction with the accompanying drawings.
【Embodiment 1】
As shown in Figures 1 to 4, the aircraft in the present embodiment is rotor craft.It is of course also possible to
For other kinds of aircraft, but it must be the aircraft of multi-power system.The rotor craft of the present invention
Including fuselage 1, the bottom of fuselage 1, which has, is provided with outwardly directed horn 2 on leg, fuselage 1.Horn 2
Quantity be at least three, they are relative to the vertical plane where the axis of fuselage 1, positional symmetry
Installation on the fuselage 1.Horn 2 has four in the present embodiment, and they are orthogonal, interval angles
For 90 degree of installations.
The end of horn 2 is provided with kinetic control system 3.Install dynamic in the top of kinetic control system 3
System 4.In the present embodiment, the top of dynamical system 4 is provided with propeller, and spiral shell is driven by dynamical system 4
Oar is revolved to rotate.Dynamical system can be motor, internal combustion engine or jet power system.
As shown in Figure 5 and Figure 6, in the present embodiment, the water conservancy diversion that the lower section of kinetic control system 3 is installed
System is deflector 5, and deflector 5 includes four blocks of split flow plates connected in cross, the lower end of split flow plate
With oblique angle.Four blocks of split flow plates are arranged in the rotating shaft of kinetic control system 3 again after being integrally formed,
It can also to be mounted directly to respectively in the rotating shaft of kinetic control system 3.
As shown in Figure 5 and Figure 6, in the present embodiment, the composition of kinetic control system 3 is as follows：Including
A universal ball end oscillating bearing 6 of the end of horn 2 is connected to, universal ball end oscillating bearing 6 passes through one
Rotating shaft 7 is connected with deflector 5.Two fixed seats 8 are arranged on universal ball end oscillating bearing 6 and horn 2
Between, two push rods 9 are connected between fixed seat 8 and the side wall of rotating shaft 7 by hinges respectively.
Every push rod 9 includes mutually being socketed between two sections of points of push rods, two sections of points of push rods, and can relative telescopic.
As shown in Figure 7 and Figure 8, dynamical system 4 and deflector 5 can be connected two-by-two is installed together；
It can be not connected to separately installed.But it must assure that deflector 5 is on the jet direction of dynamical system 4.
The operation principle of the present invention is as follows：
Dynamical system 4 only controls its output quantity by flight control system, but is kept not relative to the direction of fuselage 1
Become.Deflector 5 is by manually operating or computer by kinetic control system 3 controls it to turn to, i.e. its phase
Direction for fuselage 1 is adjustable.
Kinetic control system 3 controls the direction of deflector 5, makes deflector 5 in the institute of kinetic control system 3
Horizontal plane under space in freely rotate.The steering of kinetic control system 3 can by it is mechanical, electronic,
A variety of kinds of drive such as Pneumatic hydraulic.Kinetic control system 3 can be directly by the operation of aircraft pilot
Handle is controlled.
Deflector 5 is perpendicular to the plane of fuselage 1 in original state.When needing to make aircraft hover,
Make each deflector 5 all in plumbness；When needing to translate aircraft front, rear, left and right, make
Each deflector 5 is all tilted with angle of inclination identical towards translation direction；When need to make aircraft left steering,
During right turn, each deflector 5 is tilted towards different direction, each deflector be integrally formed clockwise,
Rotate counterclockwise direction.
Fig. 1 is the flight attitude schematic diagram that moves forward and backward of aircraft.The arrow in deflector 5 is according to Fig. 1
When the direction of head changes incline direction, aircraft is in the posture advanced or retreated.
Fig. 2 is the left and right translation flight attitude schematic diagram of aircraft.When deflector 5 is according to Fig. 2
When the direction of middle arrow changes incline direction, aircraft is in the posture of left or right translation.
Fig. 3 is the right rotation flight attitude schematic diagram of aircraft.Deflector 5 inclines towards different directions respectively
Tiltedly, the incline direction of each deflector 5 can be seen in figure 3.Each collective effect of deflector 5, overall shape
The direction that turns clockwise into Fig. 3 shown in the direction of arrow.
Fig. 4 is the anticlockwise flight attitude schematic diagram of aircraft.Deflector 5 inclines towards different directions respectively
Tiltedly, the incline direction of each deflector 5 can be seen in Fig. 4.Each collective effect of deflector 5, overall shape
Rotate counterclockwise direction into Fig. 4 shown in the direction of arrow.
【Embodiment 2】
As shown in Fig. 9, Figure 10, Figure 11, in the present embodiment, flow guide system is deflector and cylinder
Two supports above and below being provided with combination, including a cylinder 10 for being connected to the end of horn 2, cylinder 10
11, dynamical system 4 is arranged between two supports 11 up and down.It is in cross that kinetic control system, which includes two,
The rotating shaft 12 of arrangement, the end of two rotating shafts 12 is arranged in cylinder 10 by bearing respectively, Ke Yishou
Control is rotated.Flow guide system also includes four pieces of blades 13, and four pieces of blades 13 are separately mounted to what is arranged in cross
On four branch roads of rotating shaft 12.So as to by controlling the rotation of rotating shaft 12 to change the direction of blade 13.
The effect of the present embodiment middle cylinder body 10 is to allow jet more to concentrate, and reduces turnover rate.
Above-described embodiment 1, embodiment 2 have been merely given as the possibility of two kinds of kinetic control systems and flow guide system
Structure, the structure of adoptable kinetic control system and flow guide system of the invention is not limited to this two,
For example flow guide system can also use the form of vector spout.
The control block diagram of the present invention is provided by Figure 12 and Figure 13.
As shown in figure 12, aircraft of the invention is when needing adjustment state of flight, by computer or artificial
Control deflector to tilt by kinetic control system, the jet of dynamical system is entered by the direction of deflector
Row is oriented to, and jet can be analyzed to the decomposing force on decomposing force and horizontal direction in vertical direction.Level side
Upward decomposing force realizes advance to aircraft, laggard, hovering, left, right translation, left-handed
Turn, right rotation is adjusted.And the decomposing force in vertical direction need to keep equal, or it is not completely equivalent but
In deviation range in permission, so all dynamical systems are basic to the upward propulsive force of fuselage
Equal, it is always poised state to keep fuselage.
As shown in figure 13, the balance control of fuselage, be by the attitude transducer installed on aircraft (such as
Gyroscope, acceleration transducer etc.), the flight of attitude transducer continuous explorer vehicle in flight course
Posture, then will detect data and be sent to computer.Calculating by computer to flight attitude data
Output control signal is to flight control system afterwards, and flight control system controls the defeated of each dynamical system according to control signal
Go out power, make longitudinal decomposing force of each dynamical system equal or be in the deviation range of permission.And
By backfeed loop, the flight attitude after being adjusted is sent to by computer by attitude transducer again,
Above-mentioned calculating is constantly repeated by computer and control process is modified to flight attitude, fuselage is realized
Balance.
Above-described is only the preferred embodiment of the present invention, and the invention is not restricted to above example.Can
With understand, those skilled in the art without departing from the spirit and concept in the present invention directly export or
The oher improvements and changes associated, are considered as being included within protection scope of the present invention.
Claims (8)
1. a kind of multiple-motor aircraft based on control jet direction motion, it is characterised in that：Including machine
Body and dynamical system on fuselage, flow guide system, kinetic control system, attitude transducer, fly
Control system and computer；The dynamical system keeps constant relative to the direction of fuselage and produced vertical
Downward jet, the jet power output of the dynamical system is controlled by computer by the flight control system,
Keep the balance of fuselage；The flow guide system is installed on the jet direction of dynamical system and relative to machine
The direction of body is adjustable, and the flow guide system is controlled by computer or manually by the kinetic control system
It is oriented to towards to the jet that dynamical system is produced, controls the movement and steering of aircraft；
Moved for aircraft and the control mode of steering is：By the computer or artificial to motion control
System is controlled, and flow guide system is verted by the kinetic control system, passes through the flow guide system
It is oriented to towards to the jet that dynamical system is produced, the jet is broken down into the decomposition in vertical direction
Decomposing force in power and horizontal direction；Decomposing force in the horizontal direction realize advance to aircraft,
Laggard, hovering, left, right translation, anticlockwise, right rotation adjustment；
It is for the control mode that aircraft is balanced：Persistently visited in flight course by the attitude transducer
The flight attitude of aircraft is surveyed, flight attitude data are sent to computer；By the computer to flight
Attitude data outputs control signals to flight control system after calculating, by the flight control system according to control signal control
The jet power output of each dynamical system is made, the jet that each dynamical system is produced is oriented to by flow guide system
The decomposing force in vertical direction afterwards is equal or deviation range in permission in；And passed by the posture
Flight attitude after being adjusted is fed back to computer by sensor, constantly repeated by computer above-mentioned calculating and
Control process, it is always poised state to keep fuselage.
2. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by：The dynamical system and flow guide system are respectively provided with multiple, and both quantity are equal, a power
The dynamical system and flow guide system that system and a flow guide system are corresponded in one group, every group can connect installation,
Also it is removably installed.
3. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by：The dynamical system includes but is not limited to motor, internal combustion engine or jet plane.
4. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by：The flow guide system includes but is not limited to deflector or vector spout.
5. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by：The kind of drive of the kinetic control system includes but is not limited to mechanical structure transmission or electronic
Transmission.
6. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by, a kind of structure composition of the kinetic control system and flow guide system is：
The universal ball end that the kinetic control system includes being connected to outwardly directed horn end on fuselage is closed
Bearings, the universal ball end oscillating bearing is connected by rotating shaft with flow guide system；At least two fixed seats
Between the universal ball end oscillating bearing and horn, at least two push rods pass through hinges respectively
It is connected between the fixed seat and the side wall of rotating shaft；The every push rod includes multistage point push rod, each section
Mutually socket and can relative telescopic between point push rod；
The flow guide system be deflector, including four pieces in cross arrange split flow plates, described four pieces points
Deflector is arranged in the rotating shaft of the kinetic control system after being integrally formed, can also be respectively into 90
Degree is in the rotating shaft of the kinetic control system.
7. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by, another structure composition of the kinetic control system and flow guide system is：
The kinetic control system includes two rotating shafts arranged in cross, the end part of two rotating shafts
It is not arranged on by bearing in the cylinder of the flow guide system；
The flow guide system includes a cylinder for being connected to outwardly directed horn end on fuselage, described
Two supports above and below being provided with cylinder, dynamical system is arranged between described two supports；Four pieces of blades
On four branch roads for being separately mounted to the rotating shaft arranged in cross.
8. the multiple-motor aircraft according to claim 1 based on control jet direction motion, its
It is characterised by：The flow guide system is in original state perpendicular to fuselage plane；When needing aircraft is hovered
When, make each flow guide system all in plumbness；When needing to translate aircraft front, rear, left and right,
Make each flow guide system and all tilted with angle of inclination identical towards translation direction；When needing aircraft is turned left
During to, right turn, each flow guide system is set to be tilted towards different directions, each flow guide system is integrally to jet
Form the clockwise, guiding of rotate counterclockwise.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610232466.3A CN107298175A (en) | 2016-04-14 | 2016-04-14 | A kind of multiple-motor aircraft based on control jet direction motion |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610232466.3A CN107298175A (en) | 2016-04-14 | 2016-04-14 | A kind of multiple-motor aircraft based on control jet direction motion |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107298175A true CN107298175A (en) | 2017-10-27 |
Family
ID=60136660
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610232466.3A Pending CN107298175A (en) | 2016-04-14 | 2016-04-14 | A kind of multiple-motor aircraft based on control jet direction motion |
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| CN (1) | CN107298175A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590400A (en) * | 2022-03-09 | 2022-06-07 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
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| GB1059961A (en) * | 1962-07-10 | 1967-02-22 | Ripper Robots Ltd | Improvements in and relating to helicopters with rigid rotors |
| RU2083431C1 (en) * | 1993-04-23 | 1997-07-10 | Анатолий Васильевич Никульшин | Propeller for flying vehicles and water craft |
| EP1174338A1 (en) * | 2000-07-20 | 2002-01-23 | EADS Deutschland Gmbh | Rotor blade comprising ailerons |
| CN101934858A (en) * | 2010-07-08 | 2011-01-05 | 王泽峰 | Miniature electric ducted propeller type intelligent unmanned aerial vehicle |
| CN104843178A (en) * | 2015-04-30 | 2015-08-19 | 江苏数字鹰科技发展有限公司 | Flying motorcycle or automobile and flight attitude adjustment method thereof |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN104986329A (en) * | 2015-06-29 | 2015-10-21 | 廖其凌 | Portable and foldable double-rotor aircraft |
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2016
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1059961A (en) * | 1962-07-10 | 1967-02-22 | Ripper Robots Ltd | Improvements in and relating to helicopters with rigid rotors |
| RU2083431C1 (en) * | 1993-04-23 | 1997-07-10 | Анатолий Васильевич Никульшин | Propeller for flying vehicles and water craft |
| EP1174338A1 (en) * | 2000-07-20 | 2002-01-23 | EADS Deutschland Gmbh | Rotor blade comprising ailerons |
| CN101934858A (en) * | 2010-07-08 | 2011-01-05 | 王泽峰 | Miniature electric ducted propeller type intelligent unmanned aerial vehicle |
| CN104859851A (en) * | 2015-04-27 | 2015-08-26 | 刘朝阳 | Multi-rotor aircraft driven by duct lift fans with diversion helms |
| CN104843178A (en) * | 2015-04-30 | 2015-08-19 | 江苏数字鹰科技发展有限公司 | Flying motorcycle or automobile and flight attitude adjustment method thereof |
| CN104986329A (en) * | 2015-06-29 | 2015-10-21 | 廖其凌 | Portable and foldable double-rotor aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114590400A (en) * | 2022-03-09 | 2022-06-07 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
| CN114590400B (en) * | 2022-03-09 | 2022-12-20 | 南京航空航天大学 | Coaxial sail type rotor wing structure with wings and control method thereof |
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Address after: 214000 Room 411, building A1, 999 Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Applicant after: JIANGSU DIGITAL EAGLE TECHNOLOGY DEVELOPMENT Co.,Ltd. Address before: 214000 Room 411, building A1, 999 Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Applicant before: JIANGSU DIGITAL EAGLE TECHNOLOGY DEVELOPMENT Co.,Ltd. |
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Application publication date: 20171027 |