CN101204991A - Four channel row two-bladed helicopter - Google Patents
Four channel row two-bladed helicopter Download PDFInfo
- Publication number
- CN101204991A CN101204991A CNA2007101237207A CN200710123720A CN101204991A CN 101204991 A CN101204991 A CN 101204991A CN A2007101237207 A CNA2007101237207 A CN A2007101237207A CN 200710123720 A CN200710123720 A CN 200710123720A CN 101204991 A CN101204991 A CN 101204991A
- Authority
- CN
- China
- Prior art keywords
- rotor
- motor
- frame
- cantilever lever
- fixed
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 27
- 229910000831 Steel Inorganic materials 0.000 claims description 18
- 239000010959 steel Substances 0.000 claims description 18
- 230000009977 dual effect Effects 0.000 abstract 1
- 238000010276 construction Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000033001 locomotion Effects 0.000 description 1
Images
Classifications
-
- A—HUMAN NECESSITIES
- A63—SPORTS; GAMES; AMUSEMENTS
- A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
- A63H27/00—Toy aircraft; Other flying toys
- A63H27/12—Helicopters ; Flying tops
Abstract
The invention discloses a dual propellers helicopter with four channels arranged horizontally, which includes a frame which is internally encapsulated with a battery, an empennage arranged horizontally at the tail of the frame and aircraft wheel components arranged on the bottom of the frame; a left and a right cantilever bars which are connected with the frame and can rotate around self-axes are arranged on both sides of the frame horizontally. The left and the right cantilever bars are respectively connected with a left and right actuators which are arranged on the frame and can drive the left and the right cantilever bars to rotate around the self-axes through a group of connecting rod mechanisms; the ends of the left and the right cantilever bars are respectively provided with a group of vane actuated mechanisms and a motor and the left and the right actuators in two groups of vane actuated mechanisms are connected with a signal receiver in the frame, wherein, the motor is the speed changing motor. The invention has simple operation so that beginners without operation experience can also operate the helicopter to fly steadily. At the same time, the mechanical part of the helicopter is simple, thus reducing the production cost as well as greatly improving the performance stability of the helicopter.
Description
Technical field
The present invention relates to remote controlled model plane control technology field, relate in particular to a kind of four channel row two-bladed helicopter structure.
Background technology
At present, row two-bladed helicopter in the remote controlled model plane, be that different with the fixed-wing model of an airplane, the fixed-wing model of an airplane is because the structure of type usually with the vertical takeoff and landing (VTOL) device of rotor as its main lift source, make its operation comparatively simple, common people's response speed just can follow on, and the control surface of dual-rotor helicopter is more, makes the flight operation of row two-bladed helicopter complexity, if do not borrow electronic machine, be to be difficult to control without a large amount of training.
Control at the row two-bladed helicopter flight attitude, the normal change two sidespin wing angles that adopt are controlled, general rotor is the variation of being finished various angles by physical construction control, rotor forward, backward, left, be tilted to the right, can produce forward, backward, left, horizontal component of force to the right, thereby make helicopter left and right sides all directions flight forwards, backwards.Existing row two-bladed helicopter is finished various attitudes and is controlled, and all requires the rotor angle is handled, and makes its operation easier higher, and the physical construction of handling the variation of rotor angle simultaneously also can more complicated.When if helicopter runs into variations in flow in flight course, attitude will change, in order to control the dual-rotor helicopter flight course, generally to be furnished with three or above gyroscope and to control the helicopter flight course, gyroscope can utilize the orientation stability control aircraft of self to get back to original position.Yet the remote controlled model plane miniaturization becomes a kind of trend gradually, its consumer group mainly is the beginner, so this series products must be a low price, yet complex mechanical construction and adopt a plurality of gyroscopes must cause the increase of cost, be unfavorable for popularizing of this series products, the structure of existing equally row two-bladed helicopter complexity also is not easy to helicopter and controls.
Summary of the invention
The present invention is in order to solve the technical matters of existing row two-bladed helicopter complex structure, complicated operation, a kind of row two-bladed helicopter simple in structure, simple to operate to be provided.
For addressing the above problem, technical scheme of the present invention is a kind of four channel row two-bladed helicopter of structure, comprise that inside is packaged with the frame of battery, laterally be located at the empennage of frame afterbody, be located at the wheel assembly of frame bottom, the frame both sides laterally are provided with two, and be connected with frame can be around the left side of self rotational, right cantilever lever, a left side, right cantilever lever respectively by one group of connecting rod mechanism respectively with a driven left side of being located on the frame, right cantilever lever is around the left side of self rotational, the right standard rudder machine connects, a left side, right cantilever lever end respectively is provided with one group of rotor mechanism, a motor and a left side in two groups of rotor mechanisms, the right standard rudder machine signal receiver interior with being located at frame is connected, and motor is a variable speed motor.
Wherein, the middle part of described frame is provided with a permanent seat, the permanent seat top cross is provided with a bar cover, kink has the left and right cantilever lever of laterally being located at the frame both sides that inserts from its both sides in this bar cover, the equal in length of left and right cantilever lever, its pivot center is on the same straight line, and the rotor mechanism that is fixed on the left and right cantilever lever becomes to be symmetrical arranged.
Described connecting rod mechanism comprises the lifting rocking arm that is fixed on the cantilever lever, be located at the actuating arm on the steering wheel output shaft, be connected through second sling between lifting rocking arm and actuating arm, second sling is by one section steel wire and be fixed in buckleing with lifting rocking arm and two bulbs of actuating arm pivotally attached respectively of steel wire two ends and form.
Two lifting rocking arms that are fixed on the left and right cantilever lever respectively are provided with a ball pin, left and right cantilever lever interconnects by first sling, first sling is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, two bulb deduction of points not and the ball pin on two lifting rocking arms be connected.
Described rotor mechanism comprises a motor fixed cover, be located at the motor in the motor fixed cover, be located at the motor gear on the motor drive shaft, big gear wheel with the parallel motor drive shaft axis of motor gear ingear rotation axis, comprise that also top is equipped with the rotor shaft of rotor and balanced component, the motor fixed cover is provided with the connecting bore and the main shaft fixed cover of grafting cantilever lever, rotor shaft is set in the axis hole and main shaft fixed cover of big gear wheel, its end is resisted against on the main shaft block that is positioned at main shaft fixed cover bottom, rotor shaft and big gear wheel are flush fit, the motor drive shaft of motor is exposed to outside the motor fixed cover, on the rotor shaft between big gear wheel and main shaft fixed cover, be equipped with the plain bearing of radial force between main shaft fixed cover and main shaft block.
Described rotor is fixed in a rotor and puts, and the rotor cover is fixed on the rotor shaft top, is provided with Connection Block on rotor cover top; Balanced component comprises trammel beam, and is fixed in two bob-weights at these trammel beam two ends, and the place is provided with set collar in the middle of the trammel beam, and the set collar both sides are provided with ball pin in trammel beam, and set collar is connected with Connection Block; Interconnect through the 3rd sling between trammel beam and rotor simultaneously, the 3rd sling is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, and one on two bulb buttons are connected another rotor connection with ball pin on the trammel beam.
Described left and right cantilever lever is provided with and is equipped with clamping frame.
Described wheel assembly comprises the preceding wheel of being located at frame front and is located at an offside wheel of central rack both sides.
The present invention, lifting airscrew have only forward, recede two kinds of angles change, by to rotor forward, forward and backward flight or the direction of finishing helicopter that recede rotate.The lifting of model copter increases simultaneously or reduces by the both sides motor rotary speed to be controlled; And control the inclination of helicopter by controlling variation that two motor rotary speeds control anti-torsion, reach the purpose that helicopter flight turns to.Compared with prior art, the present invention has simplified the rotor operation, and the physical construction that drives the variation of rotor angle is simplified relatively, has reduced productive costs, has also reduced the helicopter operation difficulty, makes the beginner who does not have the manipulation basis also can handle the helicopter smooth flight.The mechanics of helicopter simply also makes the helicopter stability improve greatly simultaneously.
Description of drawings
The present invention is described further below in conjunction with drawings and Examples, wherein:
Fig. 1 is the birds-eye view of preferred embodiment of the present invention;
Fig. 2 is the schematic perspective view of preferred embodiment of the present invention;
Fig. 3 is the decomposing schematic representation of preferred embodiment of the present invention.
The specific embodiment
Show the basic structure of preferred embodiment of the present invention as Fig. 1,2,3, a kind of four channel row two-bladed helicopter, comprise that inside is packaged with the frame 2 of battery 1, laterally is located at the empennage 3 of frame 2 afterbodys, be located at the wheel assembly of frame 2 bottoms, frame 2 both sides laterally are provided with two, and be connected with frame 2 can be around the left and right cantilever lever 4,5 of self rotational.Left and right cantilever lever 4,5 respectively by one group of connecting rod mechanism respectively be located at frame 2 on the left and right cantilever lever 4,5 that drives be connected around the left and right steering wheel 6,7 of self rotational, left and right cantilever lever 4,5 ends respectively are provided with one group of rotor mechanism, and motor 8 in two groups of rotor mechanisms and left and right steering wheel 6,7 are connected with signal receiver 9 in being located at frame 2.In the present embodiment, because of the flicon of helicopter has the rotation speed change that depends in part on motor 8, so motor 8 adopts variable speed motor.The wheel assembly that is installed in frame 2 bottoms comprises the preceding wheel 10 of being located at frame 2 front portions and is located at an offside wheel 11 of both sides, frame 2 middle part.
As shown in Figure 3, be provided with the chamber that battery 1 and signal receiver 9 are installed in frame 2 middle parts; Middle part signal receiver 9 upper fixed of frame 2 have a permanent seat 12, permanent seat 12 top cross are provided with bar cover 13, kink has the left and right cantilever lever of laterally being located at frame 2 both sides 4,5 that inserts from its both sides in this bar cover 13, the equal in length of left and right cantilever lever 4,5, its pivot center is on the same straight line, the rotor mechanism that is fixed in left and right cantilever lever 4,5 ends becomes to be symmetrical arranged, and left and right cantilever lever 4,5 is provided with and is equipped with clamping frame 14.
As shown in Figure 3, rotor mechanism comprises a motor fixed cover, be located at the motor 8 in the motor fixed cover, be located at motor gear 15 on this motor drive shaft, with the big gear wheel 16 of the parallel motor drive shaft axis of these motor gear 15 ingear rotation axiss, comprise that also top is equipped with the rotor shaft 18 of rotor 17 and balanced component.The motor fixed cover is by last, following motor fixed cover 19,20 butt joints are formed, last motor fixed cover 19 is provided with the connecting bore of main shaft fixed cover 21 and grafting cantilever lever, rotor shaft 18 is set in the axis hole and main shaft fixed cover 21 of big gear wheel 16, its end is resisted against on the main shaft block 23 that is positioned at main shaft fixed cover 21 bottoms, rotor shaft 18 is a flush fit with big gear wheel 16, the motor drive shaft of motor 8 is exposed to outside the motor fixed cover, on the rotor shaft 18 21 of big gear wheel 16 and main shaft fixed covers, 23 of main shaft fixed cover 21 and main shaft blocks are equipped with the plain bearing 24 of radial force.When rotor mechanism was installed, inserted in the connecting bore of cooresponding upward motor fixed cover 19 left and right cantilever lever 4,5 ends, makes two groups of rotor mechanisms realize being connected with left and right cantilever lever 4,5 respectively.
In the present embodiment, rotor 17 is reached the contiguous block 25 that two blades are connected as a single entity and is constituted by two blades.Rotor 17 is fixed on the rotor cover 26 by contiguous block 25, and rotor cover 26 is fixed on rotor shaft 18 tops, and both belong to flush fit.Overlap 26 tops at rotor and be provided with Connection Block 27, contiguous block 25 sidewalls are provided with ball pin.Balanced component comprises trammel beam 28, and is fixed in two bob-weights 29 at trammel beam 28 two ends, and the place is provided with set collar 30 in the middle of the trammel beam 28, and set collar 30 both sides are provided with ball pin in trammel beam 28, and set collar 30 is connected through bolt and Connection Block 27.Simultaneously 17 of trammel beam 28 and rotors interconnect through the 3rd sling 31, the 3rd sling 31 is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, one on two bulb buttons are connected with ball pin on the trammel beam 28, and another is connected with ball pin on the contiguous block 25.The balance of helicopter is by the trammel beam 28 common balances of both sides, and trammel beam 28 is 30 degree with the angle of blade.
Shown in Fig. 1,3, connecting rod mechanism comprises the lifting rocking arm 32 that is fixed on the cantilever lever, be located at the actuating arm 33 on the steering wheel output shaft, 33 of lifting rocking arm 32 and actuating arms are connected through second sling 34, and second sling 34 is by one section steel wire and be fixed in buckleing with lifting rocking arm 32 and two bulbs of actuating arm 33 pivotallys attached respectively of steel wire two ends and form.Steering wheel when work drive link mechanism kinematic, the steering wheel output shaft drives actuating arm 33 and rotates, and the stressed drive lifting rocking arm of second sling 34 32 is around the cantilever lever rotational, and cantilever lever rotates together in company with lifting rocking arm 32 simultaneously.With the difference of steering wheel output shaft rotation direction, but make the cantilever lever conter clockwise or clockwise rotate, under connecting rod mechanism drove, cantilever lever rotated counterclockwise rotor mechanism is turned forward, and promptly rotor 17 turns forward; Cantilever lever clockwise rotates rotor mechanism is receded, and promptly rotor 17 recedes.In the present embodiment, two lifting rocking arms 32 that are fixed on the left and right cantilever lever 4,5 respectively are provided with a ball pin, left and right cantilever lever 4,5 interconnects by first sling 35, first sling 35 is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, two bulb deduction of points not and the ball pin on two lifting rocking arms 32 be connected.
When the present invention flies, motor 8 is by signal receiver 9 controls, motor 8 energisings, the motor drive shaft rotation, motor gear 15 on the motor drive shaft drives big gear wheel 16 rotations, drives rotor 17 rotations with big gear wheel 16 friction tight rotor shaft 18, and rotor 17 can produce corresponding reactive torque when rotation at full speed, signal receiver 9 can send the rotating speed of different instruction with control motor 8, and the rotor 17 that is driven by motor 8 has respective change according to the different anti-torsion of motor 8 rotating speeds.When signal receiver 9 transmission instructions are carried out flicon to 8 pairs of helicopters of two motors.When the motor 8 in the signal receiver 9 transmission instruction control both sides rotor assemblies is worked with different rotating speeds, because of producing corresponding reactive torque, both sides rotor 17 varies in size, and helicopter is tilted to the left or to the right, reach the purpose that helicopter flight turns to.The lifting of model copter increases simultaneously or reduces by both sides motor 8 rotating speeds to be controlled.
When signal receiver 9 transmission instructions are carried out flicon to 6,7 pairs of helicopters of left and right steering wheel.When flying before the control helicopter, left and right steering wheel 6,7 drives actuating arm 33 simultaneously and rotates to rear side, and promptly left and right rotor 17 turns forward, and helicopter is flown forward; When flying behind the control helicopter, left and right steering wheel 6,7 drives actuating arm 33 simultaneously and rotates to the front side, and promptly left and right rotor 17 recedes, and helicopter is flown backward; As left and right steering wheel 6,7 one-tenth counter motions: steering wheel drive actuating arm 33 to rear side rotate, another drives actuating arm 33 and rotates to the front side, promptly a rotor 17 turns forward, another rotor 17 recedes, and can realize the control to the helicopter flight direction.
The present invention, lifting airscrew have only forward, recede two kinds of angles change, by to rotor forward, forward and backward flight or the direction of finishing helicopter that recede rotate.The lifting of model copter increases simultaneously or reduces by the both sides motor rotary speed to be controlled; And control the inclination of helicopter by controlling variation that two motor rotary speeds control anti-torsion, reach the purpose that helicopter flight turns to.Compared with prior art, the present invention has simplified the rotor operation, and the physical construction that drives the variation of rotor angle is simplified relatively, has reduced productive costs, has also reduced the helicopter operation difficulty, makes the beginner who does not have the manipulation basis also can handle the helicopter smooth flight.The mechanics of helicopter simply also makes the helicopter stability improve greatly simultaneously.
Claims (8)
1. four channel row two-bladed helicopter, comprise that inside is packaged with the frame of battery, laterally be located at the empennage of described frame afterbody, be located at the wheel assembly of described frame bottom, it is characterized in that: described frame both sides laterally are provided with two, and be connected with described frame can be around the left side of self rotational, right cantilever lever, a described left side, right cantilever lever respectively by one group of connecting rod mechanism respectively with the described left side of being located on the described frame that drives, right cantilever lever is around the left side of self rotational, the right standard rudder machine connects, a described left side, right cantilever lever end respectively is provided with one group of rotor mechanism, a motor and a described left side in described two groups of rotor mechanisms, the right standard rudder machine signal receiver interior with being located at described frame is connected, and described motor is a variable speed motor.
2. four channel row two-bladed helicopter according to claim 1, it is characterized in that: the middle part of described frame is provided with a permanent seat, described permanent seat top cross is provided with a bar cover, kink has the described left and right cantilever lever of laterally being located at described frame both sides that inserts from its both sides in this bar cover, the equal in length of described left and right cantilever lever, its pivot center is on the same straight line, and the described rotor mechanism that is fixed on the described left and right cantilever lever becomes to be symmetrical arranged.
3. four channel row two-bladed helicopter according to claim 2, it is characterized in that: described connecting rod mechanism comprises the lifting rocking arm that is fixed on the cantilever lever, be located at the actuating arm on the steering wheel output shaft, be connected through second sling between described lifting rocking arm and actuating arm, described second sling is by one section steel wire and be fixed in buckleing with described lifting rocking arm and two bulbs of actuating arm pivotally attached respectively of steel wire two ends and form.
4. four channel row two-bladed helicopter according to claim 3, it is characterized in that: two described lifting rocking arms that are fixed on the described left and right cantilever lever respectively are provided with a ball pin, described left and right cantilever lever interconnects by first sling, described first sling is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, two bulb deduction of points not and the ball pin on two described lifting rocking arms be connected.
5. four channel row two-bladed helicopter according to claim 4, it is characterized in that: described rotor mechanism comprises a motor fixed cover, be located at the described motor in the described motor fixed cover, be located at the motor gear on this motor drive shaft, big gear wheel with the parallel described motor drive shaft axis of this motor gear ingear rotation axis, comprise that also top is equipped with the rotor shaft of rotor and balanced component, described motor fixed cover is provided with the connecting bore of main shaft fixed cover and grafting cantilever lever, this rotor shaft is set in the axis hole and described main shaft fixed cover of described big gear wheel, its end is resisted against on the main shaft block that is positioned at described main shaft fixed cover bottom, described rotor shaft and described big gear wheel are flush fit, the motor drive shaft of described motor is exposed to outside the described motor fixed cover, on the described rotor shaft between described big gear wheel and main shaft fixed cover, be equipped with the plain bearing of radial force between described main shaft fixed cover and main shaft block.
6. four channel row two-bladed helicopter according to claim 5 is characterized in that: described rotor is fixed in a rotor and puts, and this rotor cover is fixed on the rotor shaft top, is provided with Connection Block on described rotor cover top; Described balanced component comprises trammel beam, and is fixed in two bob-weights at these trammel beam two ends, and the place is provided with set collar in the middle of the described trammel beam, and these set collar both sides are provided with ball pin in described trammel beam, and described set collar is connected with described Connection Block; Interconnect through the 3rd sling between described trammel beam and rotor simultaneously, described the 3rd sling is buckled by one section steel wire and the bulb that is fixed in the steel wire two ends and is formed, and one on two bulb buttons are connected another described rotor connection with ball pin on the described trammel beam.
7. four channel row two-bladed helicopter according to claim 6 is characterized in that: described left and right cantilever lever is provided with and is equipped with clamping frame.
8. four channel row two-bladed helicopter according to claim 7 is characterized in that: described wheel assembly comprises the preceding wheel of being located at described frame front and is located at an offside wheel of described central rack both sides.
Priority Applications (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101237207A CN100534863C (en) | 2007-09-28 | 2007-09-28 | Four channel row two-bladed helicopter |
| US12/195,409 US20100323579A1 (en) | 2007-09-28 | 2008-08-20 | Four-channel transverse dual rotor helicopter |
| DE102008038434A DE102008038434A1 (en) | 2007-09-28 | 2008-08-20 | Helicopter with transverse double propeller, which can be operated in four frequency ranges |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101237207A CN100534863C (en) | 2007-09-28 | 2007-09-28 | Four channel row two-bladed helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101204991A true CN101204991A (en) | 2008-06-25 |
| CN100534863C CN100534863C (en) | 2009-09-02 |
Family
ID=39565519
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007101237207A Expired - Fee Related CN100534863C (en) | 2007-09-28 | 2007-09-28 | Four channel row two-bladed helicopter |
Country Status (3)
| Country | Link |
|---|---|
| US (1) | US20100323579A1 (en) |
| CN (1) | CN100534863C (en) |
| DE (1) | DE102008038434A1 (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN102514707A (en) * | 2011-12-22 | 2012-06-27 | 天津曙光敬业科技有限公司 | Electric bridge-type airframe structure of unmanned helicopter |
| CN103171764A (en) * | 2013-03-29 | 2013-06-26 | 北京航空航天大学 | Perpendicular/short-distance lifting warplane with two retractable rotor wings |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2952549B1 (en) * | 2009-11-13 | 2011-11-25 | Parrot | SUPPORT BLOCK FOR A ROTARY SAIL DRONE MOTOR |
| US8991758B2 (en) | 2013-05-13 | 2015-03-31 | Precisionhawk Inc. | Unmanned aerial vehicle |
| CN106542088A (en) * | 2016-04-29 | 2017-03-29 | 上海福昆航空科技有限公司 | Unmanned plane rotor folding and unfolding controlling organization and unmanned plane rotor extension and retraction system |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2987272A (en) * | 1959-04-29 | 1961-06-06 | Curtiss Wright Corp | Aircraft with a tiltable rotor system |
| US3246861A (en) * | 1964-03-30 | 1966-04-19 | Curci Alfred | Convertible aircraft |
| US6030177A (en) * | 1998-12-18 | 2000-02-29 | Sikorsky Aircraft Corporation | Drive system for a variable diameter tilt rotor |
| GB2409845A (en) * | 2004-01-08 | 2005-07-13 | Robert Graham Burrage | Tilt-rotor aircraft changeable between vertical lift and forward flight modes |
| US7946526B2 (en) * | 2004-11-05 | 2011-05-24 | Nachman Zimet | Rotary-wing vehicle system |
| US7658346B2 (en) * | 2005-02-25 | 2010-02-09 | Honeywell International Inc. | Double ducted hovering air-vehicle |
| US7871033B2 (en) * | 2008-04-11 | 2011-01-18 | Karem Aircraft, Inc | Tilt actuation for a rotorcraft |
-
2007
- 2007-09-28 CN CNB2007101237207A patent/CN100534863C/en not_active Expired - Fee Related
-
2008
- 2008-08-20 DE DE102008038434A patent/DE102008038434A1/en not_active Withdrawn
- 2008-08-20 US US12/195,409 patent/US20100323579A1/en not_active Abandoned
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101844617A (en) * | 2010-05-28 | 2010-09-29 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN101844617B (en) * | 2010-05-28 | 2013-06-12 | 南京航空航天大学 | Double-transverse-beam double-propeller helicopter with novel structure |
| CN102514707A (en) * | 2011-12-22 | 2012-06-27 | 天津曙光敬业科技有限公司 | Electric bridge-type airframe structure of unmanned helicopter |
| CN102514707B (en) * | 2011-12-22 | 2014-07-16 | 天津曙光敬业科技有限公司 | Electric bridge-type airframe structure of unmanned helicopter |
| CN103171764A (en) * | 2013-03-29 | 2013-06-26 | 北京航空航天大学 | Perpendicular/short-distance lifting warplane with two retractable rotor wings |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100534863C (en) | 2009-09-02 |
| DE102008038434A1 (en) | 2009-04-09 |
| US20100323579A1 (en) | 2010-12-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6719244B1 (en) | VTOL aircraft control using opposed tilting of its dual propellers or fans | |
| EP2340880B1 (en) | Dual-rotor model helicopter control system | |
| CN106915457B (en) | A kind of variable co-axial helicopter steerable system of the rotor inclinator depth of parallelism up and down | |
| CN110979651B (en) | Coaxial helicopter and control method | |
| WO2016004852A1 (en) | Vertical take-off and landing aircraft | |
| WO2015024044A1 (en) | Omni-directional thrust vectoring propulsor | |
| CN100534863C (en) | Four channel row two-bladed helicopter | |
| CN106428527A (en) | Dual-axis vector servo turning device with propeller and vertical take-off and landing unmanned aerial vehicle with fixed wings | |
| CN110294114B (en) | Gesture control system of coaxial double-oar aircraft | |
| CN110171568A (en) | One kind can hover flapping wing aircraft | |
| WO2015172558A1 (en) | Control method and control apparatus for variable-pitch aerial vehicle | |
| CN108528692A (en) | A kind of folded wing double-rotor aerobat and its control method | |
| CN110329497A (en) | The multi-rotor unmanned aerial vehicle and its control method of a kind of paddle face variable-angle | |
| CN107697279A (en) | Vert afterbody high-speed helicopter | |
| CN203094441U (en) | Improved four-rotor aircraft | |
| CN109455295B (en) | Rotor control device and rotor craft | |
| CN107380428A (en) | Dish-style rotor craft | |
| CN111003164A (en) | Coaxial tilting three-rotor-blade helicopter | |
| CN206202663U (en) | A kind of propeller twin shaft vector servo deviator and VTOL fixed-wing unmanned plane | |
| CN108791857A (en) | Universal shaft type full rigidity twin-rotor helicopter altogether | |
| CN211033009U (en) | Small coaxial dual-rotor unmanned aerial vehicle | |
| CN202128911U (en) | Remote-control electric side-by-side twin rotor helicopter model airplane | |
| CN100591400C (en) | Steering mechanism for model helicopter | |
| CN216805807U (en) | Rotor control device of tandem double-rotor unmanned helicopter | |
| CN201086823Y (en) | Rank double-oar minitype helicopter |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C56 | Change in the name or address of the patentee |
Owner name: SHENZHEN ART AVIATION TECHNOLOGY CO., LTD. Free format text: FORMER NAME: SHENZHEN ART-TECH R/C HOBBY CO., LTD. |
|
| CP03 | Change of name, title or address |
Address after: Two or three, 1, four floor, D4 building, Liyuan Industrial Estate, Shiyan community, Shiyan street, Shiyan City, Shenzhen, Guangdong, Baoan District 518000, China Patentee after: Shenzhen Art Aviation Technology Co., Ltd. Address before: 3, Shenzhen, Guangdong province Baoan District Shiyan street, D41 community center, 518000 industrial building Patentee before: Shenzhen Art-Tech R/C Hobby Co., Ltd. |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20090902 Termination date: 20170928 |