CN107284656A - Coaxial double-oar rotor mechanism in the same direction and its aircraft - Google Patents
Coaxial double-oar rotor mechanism in the same direction and its aircraft Download PDFInfo
- Publication number
- CN107284656A CN107284656A CN201710563613.XA CN201710563613A CN107284656A CN 107284656 A CN107284656 A CN 107284656A CN 201710563613 A CN201710563613 A CN 201710563613A CN 107284656 A CN107284656 A CN 107284656A
- Authority
- CN
- China
- Prior art keywords
- rotor
- propeller
- oar
- same direction
- coaxial double
- 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.)
- Pending
Links
Classifications
-
- 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
- B64C27/10—Helicopters with two or more rotors arranged coaxially
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
- B64C27/58—Transmitting means, e.g. interrelated with initiating means or means acting on blades
- B64C27/59—Transmitting means, e.g. interrelated with initiating means or means acting on blades mechanical
-
- 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
- B64D35/04—Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the transmission driving a plurality of propellers or rotors
Abstract
A kind of coaxial double-oar rotor mechanism in the same direction, it includes upper propeller, lower propeller, rotor shaft and tumbler, the upper propeller and the lower propeller are separately fixed at the upper and lower ends of the rotor shaft, the tumbler is solidly set in the rotor shaft, and the tumbler is located between the upper propeller and the lower propeller；The upper propeller is variable-pitch propeller, and the upper propeller controls displacement by displacement component.Additionally provide a kind of aircraft.Structure is simplified, and alleviates own wt, and lift and lifting capacity lifting, agility and stability are improved.
Description
Technical field
The present invention relates to aircraft field, and in particular to a kind of coaxial double-oar rotor mechanism in the same direction and its aircraft.
Background technology
The existing commonly used single-blade system of multi-rotor aerocraft, horn shake is big due to corner power, and it is not enough
Part is that high-power engine need to be used, has both increased the weight of aircraft, the production cost of aircraft is added again.
And existing multi-rotor aerocraft, each rotor be separately configured one driving motor, cause its rotating speed to have
Difference, influences the reliability of flight, and multi-motor driving fault rate is also higher, influences the safety of flight.
There is multi-rotor aerocraft quick maneuverability, reaction, unmanned flight, operation to require low advantage, not only in army
Exhibited one's skill to the full with field, it is also increasingly extensive in the application of civil area.But the displacement system of existing multi-rotor aerocraft is universal
Using single-blade displacement system, it, which is disadvantageous in that, need to use high-power engine, both increase the weight of aircraft, increase again
The production cost of aircraft, the rate of climb is slow.
The content of the invention
The present invention in view of the shortcomings of the prior art, proposes a kind of coaxial double-oar rotor mechanism in the same direction, and transmission is simple, weight
Gently, fault rate is low, and produces lift capability by force, additionally provides a kind of aircraft, can keep fly temperature stabilization and stronger liter
Power, the conversion of state of flight is more flexible, and concrete technical scheme is as follows：
A kind of coaxial double-oar rotor mechanism in the same direction, including upper propeller, lower propeller, rotor shaft and tumbler, it is described on
Propeller and the lower propeller are separately fixed at the upper and lower ends of the rotor shaft, and the tumbler is solidly set on the rotor shaft
On, and the tumbler is positioned between the upper propeller and the lower propeller；
The upper propeller is variable-pitch propeller, and the upper propeller controls displacement by displacement component.
The present invention is achieved in that tumbler drives rotor shaft to rotate, and rotor shaft drives upper propeller and lower propeller
Synchronous axial system, lower propeller provides a part of lift, and horn is held up from the bottom up, bigger lift, upper propeller can be produced
For variable-pitch propeller, upper propeller can change of flight at any time state so that aircraft reaction is more flexible.In a rotor
Axle rotates in same direction down, and the air-flow that twin screw rotation is produced can provide bigger lift for aircraft.Their rotating Vortexes, are reduced
The quantity of spin axis, reducing weight reduces fault rate, and the low engine of power may be selected, and alleviates the weight of aircraft
And production cost
A kind of further restriction of parallel technical solution, the lower propeller is variable-pitch propeller, and the lower propeller leads to
Cross displacement component control displacement displacement.
Be variable-pitch propeller up and down, displacement can be reduced to the monotropic load away from system simultaneously up and down, the load of system by
Upper propeller and lower propeller are shared, and reaction speed is faster quicker.
A kind of further restriction of parallel technical solution, the lower propeller is constant pitch airscrew.
Due to being provided with lower constant pitch airscrew in the bottom of rotor shaft, lower constant pitch airscrew is spun on the gas for absorbing upper propeller
While stream, the stabilization and lift of aircraft are Z can be continuously maintained, so improving 15% on the basis of equal engine power
Lift, had both alleviated the weight of aircraft, and the production cost of aircraft is reduced again.Other this aircraft rate of climb is fast, knot
Structure is simple, it is easy to manufacture.
Further limit, the variable-pitch propeller includes rotor head, rotor folder and adjustable blade；
The rotor head is fixed on one end of the rotor shaft；
The rotor presss from both sides one end and is stuck in the rotor head, and rotor folder and the rotor head rotate connection, described
Adjustable blade is fixed on the other end of the rotor folder, one fixation of a rotor folder and the adjustable blade formation
Blade, rotor folder two fixed blades of correspondence, and two fixed blades are on the same line, two institutes
Fixed blade is stated perpendicular to the rotor shaft.
In flight, rotor head and rotor shaft synchronous rotary, rotor folder and rotor head synchronously revolve round the sun together, displacement component control
Rotor processed presss from both sides rotation so that the angle of blade and airflow function changes, so that change of flight state.
Further limit, the rotor folder is provided with pole, the pole is suspended vacantly on rotor folder；
The displacement component includes steering wheel, transmission group and output group, transmission group described in the servo driving, the transmission group
Drive the output group；
The output group includes driven torus and pull bar, and the driven torus kink is in the rotor shaft, described pull bar one end
It is hinged with the driven torus, the pull bar other end and the pole are hinged；
The transmission group drives the driven torus vertically movable.
Operationally, driven torus is transmitted a group driving vertical motion so that pull bar is subjected to displacement vertically, and pull bar acts on branch
On bar, rotating torque is formed between the pivot center of pole and rotor folder, pole moves up and down, so that rotor folder is rotated,
Blade follows rotor folder rotation, so as to realize displacement.
Further limit, the transmission group includes active ring, pivot link, the first swing connecting bar, intermediate connecting rod, the second pendulum
Dynamic connecting rod and fixed seat, the active ring kink is in the rotor shaft, the pivot link, first swing connecting bar, institute
State intermediate connecting rod and the second swing connecting bar is hinged from beginning to end successively；
The output shaft of the pivot link and the steering wheel is vertical and is fixedly connected, second swing connecting bar and described solid
Reservation is hinged, and the intermediate connecting rod and the active ring are rotated by bearing pin and connected, and the bearing pin is perpendicular to the rotor shaft.
Operationally, steering wheel is rotated so that pivot link synchronous axial system, and pivot link drives the first swing connecting bar to swing,
First swing connecting bar drives intermediate connecting rod to swing, and the second swing connecting bar is hinged in fixed seat, and the motion to intermediate connecting rod is played
Restriction effect, intermediate connecting rod is when swinging, and intermediate connecting rod changes in the vertical position being connected with bearing pin, passes through bearing pin band
Dynamic active ring in the vertical direction displacement, active ring is contacted with driven torus, so as to drive driven torus vertical displacement, active ring and
Driven torus is enclosed in rotor shaft, and rotor shaft now also acts the effect of guiding.
Further limit, the intermediate connecting rod there are two, and two intermediate connecting rods are arc structure, described in two
Intermediate connecting rod is rotatably connected on the active ring by bearing pin, and the bearing pin passes through the midpoint of the intermediate connecting rod, two
The individual intermediate connecting rod is interfixed to form a collar, and the collar is enclosed on outside the active ring.
Two intermediate connecting rods can remain synchronous amplitude of fluctuation, so as to ensure that the reliability of control and accurate
Property.
Further limit, the tumbler is bevel gear, the bevel gear is solidly set in the rotor shaft.
The transmission of spur gear is more accurate, and error is small, while structure is also more consolidated.
A kind of aircraft, in addition to nacelle, engine, horn and driving member, the horn are fixed in the nacelle, institute
Driving member described in engine driving is stated, the driving member drives the tumbler to rotate；
The horn and the equal more than one of the driving member, and horn one driving member of correspondence, described in each
Driving member is by an engine driving；
The rotor shaft is fixed on the horn end by bearing, and the steering wheel and the fixed seat are fixedly mounted on
On the horn.
Pass through the setting of many rotors, it is ensured that the flexibility of flight, and each rotor shares gravity, effectively reduces its zero
The load-bearing pressure of part, and by an engine driving, structure has been simplified, while optimizing the transformation efficiency of lift.
Further limit, the engine output end is bevel gear structure, the driving member is power transmission shaft, and the transmission
Axle two ends are bevel gear structure, and the tumbler is bevel gear structure.
Using the engagement between bevel gear, it is ensured that transmission is accurately and reliably, and simple in construction, lightweight, effectively subtracts
The generation of few fault rate.
Beneficial effects of the present invention are：Designed by the displacement of upper propeller, and one lower propeller of configuration, effectively
The lift of flight is improved, the flight stress of each propeller is reduced so that aircraft is more clever when flying conversion
Live, and lift can also be effectively guaranteed；When lower propeller is constant pitch airscrew, lower propeller can provide stable
Lift, flight conversion is realized by upper Propeller variable pitch, and when lower propeller is variable-pitch propeller, displacement behaviour can be carried out up and down
Make so that the flight of aircraft is quicker；By an engine multiple rotors are entered with the driving of action edge, structure is simplified,
Mitigate weight, generally, the present invention is mitigating weight and while add agility, it is ensured that the liter of whole aircraft
Power, and its lifting capacity.
Brief description of the drawings
Fig. 1 is structural representation of the coaxial double-oar rotor mechanism in the same direction when lower propeller 12 is constant pitch airscrew.
Fig. 2 is structural representation of the coaxial double-oar rotor mechanism in the same direction when lower propeller 12 is variable-pitch propeller.
Fig. 3 is the structural representation of steering wheel 151 and transmission group 152.
Fig. 4 is the structural representation of output group 153.
Fig. 5 is structural representation when the lower propeller 12 of aircraft is constant pitch airscrew.
Fig. 6 is structural representation when the lower propeller 12 of aircraft is variable-pitch propeller.
Embodiment
Presently preferred embodiments of the present invention is described in detail below in conjunction with the accompanying drawings, so that advantages and features of the invention energy
It is easier to be readily appreciated by one skilled in the art, apparent is clearly defined so as to be made to protection scope of the present invention.
As shown in Figure 1, Figure 2, shown in Fig. 5, Fig. 6, a kind of aircraft, including coaxial double-oar rotor mechanism in the same direction, in addition to nacelle
2nd, engine 3, horn 4 and driving member 5.
As shown in Figure 1 and Figure 2, a kind of coaxial double-oar rotor mechanism in the same direction, including upper propeller 11, lower propeller 12, rotor
Axle 13 and tumbler 14, the upper propeller 11 and the lower propeller 12 are separately fixed at up and down the two of the rotor shaft 13
Under end, the tumbler 14 is solidly set in the rotor shaft 13, and the tumbler 14 is located at the upper propeller 11 and is described
Between propeller 12；The tumbler 14 is bevel gear, and the bevel gear is solidly set in the rotor shaft 13.
The upper propeller 11 is variable-pitch propeller, and the upper propeller 11 controls displacement displacement by displacement component 15.
As shown in Figure 1 and Figure 2, the variable-pitch propeller includes rotor head a1, rotor folder a2 and adjustable blade a3；
The rotor head a1 is fixed on one end of the rotor shaft 13；
Described rotor folder a2 one end is stuck in the rotor head a1, and the rotor folder a2 and rotor head a1 is rotated
Connection, the adjustable blade a3 is fixed on the other end that the rotor presss from both sides a2, and a rotor presss from both sides a2 and displacement
Blade a3 one fixed blade of formation, rotor folder a2 two fixed blades of correspondence, and two fixed leaves
On the same line, two fixed blades are perpendicular to the rotor shaft 13 for piece.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the rotor folder a2 is suspended vacantly provided with pole a21, the pole a21
On rotor folder a2；
The displacement component 15 includes steering wheel 151, transmission group 152 and output group 153, and the steering wheel 151 drives the biography
Dynamic group 152, the transmission group 152 drives the output group 153；
The output group 153 includes driven torus 1531 and pull bar 1532, and the kink of driven torus 1531 is in the rotor shaft
On 13, described one end of pull bar 1532 and the driven torus 1531 are hinged, the other end of pull bar 1532 and pole a21 hinges
Connect；
The transmission group 152 drives the driven torus 1531 vertically movable.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the intermediate connecting rod 1524 has two, and two intermediate connecting rods 1524 are equal
For arc structure, two intermediate connecting rods 1524 are rotatably connected on the active ring 1521 by bearing pin 15241, and institute
The midpoint that bearing pin 15241 passes through the intermediate connecting rod 1524 is stated, two intermediate connecting rods 1524 interfix to form a set
Ring, the collar is enclosed on outside the active ring 1521.
As shown in Figure 1, Figure 2, Figure 3, Figure 4, the transmission group 152 includes active ring 1521, the pendulum of pivot link 1522, first
Dynamic connecting rod 1523, intermediate connecting rod 1524, the second swing connecting bar 1525 and fixed seat 1526, the kink of active ring 1521 is described
In rotor shaft 13, the pivot link 1522, first swing connecting bar 1523, the intermediate connecting rod 1524 and second, which are swung, to be connected
Bar 1525 is hinged from beginning to end successively；
The pivot link 1522 is vertical with the output shaft of the steering wheel 151 and is fixedly connected, second swing connecting bar
1525 and the fixed seat 1526 be hinged, the intermediate connecting rod 1524 and the active ring 1521, which pass through bearing pin 15241 and rotated, to be connected
Connect, the bearing pin 15241 is perpendicular to the rotor shaft 13.
As shown in Figure 1, Figure 2, shown in Fig. 5, Fig. 6, the horn 4 is fixed in the nacelle 2, and the engine 3 drives described
Driving member 5, the driving member 5 drives the tumbler 14 to rotate；
The equal more than one of the horn 4 and the driving member 5, and one driving member 5 of correspondence of horn 4, it is described
Horn 4 is hollow structure, and the driving member 5 is located in the horn 4, and each described driving member 5 is driven by an engine 3
It is dynamic；In fig. 5 and fig., it is only for expression is more clear, therefore only depicts two horns, when it is implemented, not merely
It is limited to two.
The rotor shaft 13 is fixed on the end of horn 4 by bearing, and the steering wheel 151 and the fixed seat 1526 are equal
It is fixedly mounted on the horn 4.
The output end of engine 3 is bevel gear structure, and the driving member 5 is power transmission shaft, and the power transmission shaft two ends are
Bevel gear structure, the tumbler 14 is bevel gear structure.
In the case of other structures identical, the embodiment one of lower propeller 12, as shown in Fig. 2, Fig. 5, the lower spiral shell
Rotation oar 12 is variable-pitch propeller, and the lower propeller 12 controls displacement by displacement component 15.
During work, lower spiral is while lift is lifted, and spiral can carry out displacement up and down so that the agility of aircraft
Property gets a promotion, while the lifting capacity of aircraft itself is also improved.
In the case of other structures identical, the embodiment two of lower propeller 12, as shown in Fig. 1, Fig. 6, the lower spiral shell
Rotation oar 12 is constant pitch airscrew.
During work, lower propeller 12 provides stable lift, and upper propeller 11 provides the displacement required for flight conversion, its
The lifting capacity of flight and the stability of flight are higher.
Operation principle：Engine 3 starts, and engine 3 drives all drive axis simultaneously, and power transmission shaft drives tumbler
14 are rotated, and the tumbler 14 of rotor shaft 13 is rotated together, and rotor shaft 13 drives upper propeller 11 and lower propeller 12 are synchronous together to turn
Dynamic, when needing displacement to adjust, control steering wheel 151 is rotated, and transmission group 152 transmits power to output group 153, and output group 153 is controlled
Rotor a2 rotations processed, so as to realize adjustable blade a3 upset, realize that displacement is adjusted.
Claims (10)
1. a kind of coaxial double-oar rotor mechanism in the same direction, it is characterised in that：Including upper propeller (11), lower propeller (12), rotor
Axle (13) and tumbler (14), the upper propeller (11) and the lower propeller (12) are separately fixed at the rotor shaft (13)
Upper and lower ends, the tumbler (14) is solidly set in the rotor shaft (13), and the tumbler (14) is located at the upper spiral shell
Revolve between oar (11) and the lower propeller (12)；
The upper propeller (11) is variable-pitch propeller, and the upper propeller (11) controls displacement by displacement component (15).
2. a kind of coaxial double-oar rotor mechanism in the same direction according to claim 1, it is characterised in that：The lower propeller (12)
For variable-pitch propeller, the lower propeller (12) controls displacement by displacement component (15).
3. a kind of coaxial double-oar rotor mechanism in the same direction according to claim 1, it is characterised in that：The lower propeller (12)
For constant pitch airscrew.
4. according to a kind of any described coaxial double-oar rotor mechanisms in the same direction of claim 1-3, it is characterised in that：The displacement spiral shell
Revolving oar includes rotor head (a1), rotor folder (a2) and adjustable blade (a3)；
The rotor head (a1) is fixed on one end of the rotor shaft (13)；
Described rotor folder (a2) one end is stuck in the rotor head (a1), and rotor folder (a2) and the rotor head (a1) turn
Dynamic connection, the adjustable blade (a3) is fixed on the other end of the rotor folder (a2), and a rotor presss from both sides (a2) and one
The adjustable blade (a3) forms a fixed blade, and a rotor presss from both sides two fixed blades of (a2) correspondence, and two
On the same line, two fixed blades are perpendicular to the rotor shaft (13) for the individual fixed blade.
5. a kind of coaxial double-oar rotor mechanism in the same direction according to claim 4, it is characterised in that：On the rotor folder (a2)
Provided with pole (a21), the pole (a21) is suspended vacantly on rotor folder (a2)；
The displacement component (15) includes steering wheel (151), transmission group (152) and output group (153), steering wheel (151) driving
The transmission group (152), the transmission group (152) drives the output group (153)；
The output group (153) includes driven torus (1531) and pull bar (1532), and driven torus (1531) kink is in the rotation
On wing axle (13), described pull bar (1532) one end and the driven torus (1531) are hinged, pull bar (1532) other end and institute
Pole (a21) is stated to be hinged；
The transmission group (152) drives the driven torus (1531) vertically movable.
6. a kind of coaxial double-oar rotor mechanism in the same direction according to claim 5, it is characterised in that：The transmission group (152)
Including active ring (1521), pivot link (1522), the first swing connecting bar (1523), intermediate connecting rod (1524), second company of swing
Bar (1525) and fixed seat (1526), active ring (1521) kink is in the rotor shaft (13), the pivot link
(1522), first swing connecting bar (1523), the intermediate connecting rod (1524) and the second swing connecting bar (1525) successively head and the tail
It is hinged；
The pivot link (1522) is vertical with the output shaft of the steering wheel (151) and is fixedly connected, second swing connecting bar
(1525) it is hinged with the fixed seat (1526), the intermediate connecting rod (1524) and the active ring (1521) pass through bearing pin
(15241) connection is rotated, the bearing pin (15241) is perpendicular to the rotor shaft (13).
7. a kind of coaxial double-oar rotor mechanism in the same direction according to claim 6, it is characterised in that：The intermediate connecting rod
(1524) there are two, and two intermediate connecting rods (1524) are arc structure, two intermediate connecting rods (1524) are led to
Bearing pin (15241) is crossed to be rotatably connected on the active ring (1521), and the bearing pin (15241) passes through the intermediate connecting rod
(1524) midpoint, two intermediate connecting rods (1524) interfix to form a collar, and the collar is enclosed on the active
Ring (1521) is outside.
8. according to a kind of any described coaxial double-oar rotor mechanisms in the same direction of claim 1-3, it is characterised in that：The tumbler
(14) it is bevel gear, the bevel gear is solidly set in the rotor shaft (13).
9. a kind of aircraft of any coaxial double-oar rotor mechanisms in the same direction of utilization claim 5-7, it is characterised in that：Also wrap
Nacelle (2), engine (3), horn (4) and driving member (5) are included, the horn (4) is fixed in the nacelle (2), the hair
Motivation (3) drives the driving member (5), and the driving member (5) drives the tumbler (14) to rotate；
The horn (4) and the driving member (5) more than one, and horn (4) one driving member (5) of correspondence,
Each described driving member (5) is driven by an engine (3)；
The rotor shaft (13) is fixed on the horn (4) end, the steering wheel (151) and the fixed seat by bearing
(1526) it is fixedly mounted on the horn (4).
10. a kind of aircraft according to claim 9, it is characterised in that：Engine (3) output end is bevel gear knot
Structure, the driving member (5) is power transmission shaft, and the power transmission shaft two ends are bevel gear structure, and the tumbler (14) is cone tooth
Wheel construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710563613.XA CN107284656A (en) | 2017-07-12 | 2017-07-12 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710563613.XA CN107284656A (en) | 2017-07-12 | 2017-07-12 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107284656A true CN107284656A (en) | 2017-10-24 |
Family
ID=60101097
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710563613.XA Pending CN107284656A (en) | 2017-07-12 | 2017-07-12 | Coaxial double-oar rotor mechanism in the same direction and its aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107284656A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108033013A (en) * | 2017-12-14 | 2018-05-15 | 邵文远 | A kind of VTOL fixed-wing unmanned plane |
| WO2022111537A1 (en) * | 2020-11-26 | 2022-06-02 | 广东国士健科技发展有限公司 | Flapping rotor device which vertically operates for ascending and horizontally operates for descending |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB151181A (en) * | 1919-11-19 | 1920-09-23 | Raul Pateras Pescara | Means for the transmission of power stress or torque to the propellers of flying machines of helicopteral type |
| CN105270617A (en) * | 2014-06-19 | 2016-01-27 | 庆安集团有限公司 | Coaxial double propeller helicopter middle propeller pitch control device |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN205633034U (en) * | 2016-03-28 | 2016-10-12 | 冯江 | Aircraft is sprayed to vertical engine central transmission's fast many rotors of formula agricultural of oily moment |
| CN106672228A (en) * | 2015-11-07 | 2017-05-17 | 马铿杰 | Multi-blade rotor tandem type aircraft |
-
2017
- 2017-07-12 CN CN201710563613.XA patent/CN107284656A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB151181A (en) * | 1919-11-19 | 1920-09-23 | Raul Pateras Pescara | Means for the transmission of power stress or torque to the propellers of flying machines of helicopteral type |
| CN105270617A (en) * | 2014-06-19 | 2016-01-27 | 庆安集团有限公司 | Coaxial double propeller helicopter middle propeller pitch control device |
| CN205060011U (en) * | 2015-10-27 | 2016-03-02 | 中航维拓（北京）科技有限责任公司 | Oil moves four rotor unmanned aerial vehicle rotor - control system of displacement |
| CN106672228A (en) * | 2015-11-07 | 2017-05-17 | 马铿杰 | Multi-blade rotor tandem type aircraft |
| CN205633034U (en) * | 2016-03-28 | 2016-10-12 | 冯江 | Aircraft is sprayed to vertical engine central transmission's fast many rotors of formula agricultural of oily moment |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108033013A (en) * | 2017-12-14 | 2018-05-15 | 邵文远 | A kind of VTOL fixed-wing unmanned plane |
| WO2022111537A1 (en) * | 2020-11-26 | 2022-06-02 | 广东国士健科技发展有限公司 | Flapping rotor device which vertically operates for ascending and horizontally operates for descending |
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