EP2604319A1 - Dispositif de couplage destiné à un hélicoptère modèle télécommandé doté d'une double hélice coaxiale et contrarotative - Google Patents

Dispositif de couplage destiné à un hélicoptère modèle télécommandé doté d'une double hélice coaxiale et contrarotative Download PDF

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Publication number
EP2604319A1
EP2604319A1 EP10855757.0A EP10855757A EP2604319A1 EP 2604319 A1 EP2604319 A1 EP 2604319A1 EP 10855757 A EP10855757 A EP 10855757A EP 2604319 A1 EP2604319 A1 EP 2604319A1
Authority
EP
European Patent Office
Prior art keywords
steering engine
servo steering
tail motor
operating system
engine operating
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.)
Withdrawn
Application number
EP10855757.0A
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German (de)
English (en)
Other versions
EP2604319A4 (fr
Inventor
Kanghan Ni
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Individual
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Individual
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Priority claimed from CN2010202913219U external-priority patent/CN201760098U/zh
Priority claimed from CN2010102528131A external-priority patent/CN101912688B/zh
Application filed by Individual filed Critical Individual
Publication of EP2604319A1 publication Critical patent/EP2604319A1/fr
Publication of EP2604319A4 publication Critical patent/EP2604319A4/fr
Withdrawn legal-status Critical Current

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    • 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
    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H27/00—Toy aircraft; Other flying toys

Definitions

  • the present invention relates to a linkage device for a model helicopter, and more particularly to a linkage device for a remote control model helicopter with coaxial and counter rotating double-propeller.
  • the conventional remote control model helicopter with coaxial and counter rotating double-propeller mainly comprises a landing gear, a body, a receiver controlling device, a motor power transmitting device, a rotor lifting device, a flybar device and a forward and backward device.
  • the forward and backward device of a conventional four-channel model helicopter is embodied as an operating unit of a forward and backward servo steering engine in a servo steering engine controlling system which is realized by a manner that the servo steering engine drives a servo steering engine joystick; that the servo steering engine joystick further drives a swashplate to tilt; and that the swashplate further drives a rotor head via a rotor connecting rod to force a rotating plane of a lower rotor to tilt forwardly or backwardly.
  • the forward and backward device thereof has a disadvantage that, when the rotating plane of the lower rotor tilts forwardly and the helicopter flies forwardly, under the action of a centrifugal force of the flybar, the upper rotor would produce an opposite equal force tilting backwardly to counteract with the force driving the helicopter to fly forwardly; and vice versa.
  • this type of helicopter has relatively weak forces of flying forwardly and backwardly and is vulnerable to airflows; a strong wind may stop the helicopter.
  • the forward and backward device of a conventional three-channel model helicopter is embodied as a tail motor operating system which is realized by a manner that a tail motor rotates positively and reversely to drive a screw propeller to rotate positively and reversely, so as to generate forces to lower or raise a head thereof.
  • the conventional three-channel model helicopter also has the problem of the weak forces of flying forward and backward.
  • the tail motor is related with power matching, an appearance and a center of gravity, a volume, a size and a weight thereof are strictly limited, and thus the tail motor has a small power and provides very small motive forces; moreover, under the action of the centrifugal forces of the flybar, the rotating plane of the upper rotor tilts opposite to a tilting direction of the body and a force of the tilting adequately counteracts with the force lowering or raising the head thereof generated by the positive and negative rotations of the tail motor, so that the body thereof is unable to effectively generate torque to lower or raise the head; and thus the conventional three-channel helicopter is unable to fly in outdoor winds.
  • An object of the present invention is to provide a linkage device for a remote control model helicopter with coaxial and counter rotating double-propeller having a good resistance to winds, so as to satisfy requirement for the model helicopter to fly fast against winds outdoors.
  • the linkage device of the present invention adopts following technical solutions.
  • the linkage device comprises a servo steering engine operating system, a tail motor operating system and a receiver controlling device.
  • the servo steering engine operating system comprises a forward and backward servo steering engine operating unit and a leftward and rightward servo steering engine operating unit.
  • the receiver controlling device is connected to both the servo steering engine operating system and the tail motor operating system and able to control the forward and backward servo steering engine operating unit and the tail motor operating system to link simultaneously.
  • the receiver controlling device is for controlling the forward and backward servo steering engine operating unit and the tail motor operating system to link simultaneously to control the forward and backward servo steering engine operating unit and the tail motor operating system to act simultaneously when the model helicopter flies forwardly and backwardly.
  • the forward and backward servo steering engine operating unit comprises a forward and backward servo steering engine, a servo steering engine joystick, a swashplate, a rotor head connecting rod, a rotor head and rotors.
  • the forward and backward servo steering engine is installed on a body of the model helicopter; a first end of the servo steering engine joystick is installed on the forward and backward servo steering engine and a second end thereof is connected to the swashplate; a first end of the rotor end connecting rod is installed on the swashplate and a second end thereof is installed on the rotor head; the rotors are installed on the rotor head.
  • the tail motor operating system comprises a tail motor frame, a tail motor, a screw propeller and tail motor fasteners.
  • the tail motor frame is fixed on a back of the body; the tail motor is fixed on the tail motor frame via the tail motor fasteners; and the screw propeller is fixed on the tail motor.
  • the tail motor operating system further comprises a tail motor manual switch connected to the receiver controlling device.
  • the receiver controlling device comprises a radio frequency (RF) signal circuit, a micro controller unit (MCU) and a motor driving circuit, wherein the MCU is connected to the servo steering engine operating system; the motor driving circuit is connected to the tail motor operating system; after receiving a controlling instruction, the RF signal circuit is processed by the MCU and then sends controlling signals into the servo steering engine operating system and the motor driving circuit.
  • RF radio frequency
  • the present invention combines a conventional three-channel model helicopter with a conventional four-channel model helicopter via the receiver controlling device, and controls a lower rotor to tilt via the forward and backward servo steering engine operating unit of the servo steering engine operating system to counteract with reaction forces of an upper rotor; meanwhile, the tail motor operating system receives an instruction of the receiver controlling device that the tail motor drives the screw propeller to rotate positively or reversely to generate an upward force or a downward force without restrictions which acts on the body of the helicopter to form and keep a relatively big angle tilting forwardly or backwardly, when rotating planes of the upper rotor and the lower rotor also form and keep an identically big angle, in such a manner that the upper rotor and the lower rotor rotate to generate a relatively big force pushing forwardly or backwardly to provide a relatively strong forwardly or backwardly driving force for the helicopter to reach effects of a strong resistance to winds and a fast flying speed, so as to satisfy needs of flying against the winds outdoors.
  • 1-forward and backward servo steering engine 2-tail motor; 3-screw propeller; 4-receiver controlling device; 5-tail motor manual switch; 6-RF signal circuit; 7-MCU; 8-motor driving circuit; 9-servo steering engine joystick; 10-swashplate; 11-rotor head connecting rod; 12-rotor head; 13-rotor; 14-tail motor frame; 15-tail motor fastener; 16-leftward and rightward servo steering engine.
  • a linkage device for a remote control model helicopter with coaxial and counter rotating double-propeller comprises a servo steering engine operating system (only a forward and backward servo steering engine 1 and a leftward and rightward servo steering engine 16 showed), a tail motor operating system (only a tail motor 2 and a screw propeller 3 showed) and a receiver controlling device 4.
  • the receiver controlling device 4 is respectively connected to the forward and backward servo steering engine 1, the leftward and rightward servo steering engine 16 and the tail motor 2 via electric wires and able to control the forward and backward servo steering engine 1 and the tail motor 2 to link simultaneously to control the forward and backward servo steering engine operating unit and the tail motor operating system to act simultaneously when the helicopter flies forwardly and backwardly.
  • the screw propeller 3 is installed on the tail motor 2.
  • a tail motor manual switch 5 is installed on the electric wires connecting the tail motor 2 and the receiver controlling device 4 to control whether the tail motor operating system accepts and executes acting instructions from the receiver controlling device 4.
  • Fig. 2 shows circuit principles of the receiver controlling device 4 which comprises a RF signal circuit 6, an MCU 7 and a motor driving circuit 8, wherein the MCU 7 is connected to the forward and backward servo steering engine 1 and the leftward and rightward servo steering engine 16; and the motor driving circuit 8 is connected to the tail motor 2.
  • the RF signal circuit 6 After receiving a first controlling instruction of flying forwardly or backwardly, the RF signal circuit 6 is processed by the MCU 7 and sends two groups of controlling signals into the forward and backward servo steering engine 1 and the motor driving circuit 8; a first group comprises pulse position modulation (PPM) signals for controlling the forward and backward servo steering engine 1 to act according to the first controlling instruction of flying forwardly or backwardly; a second group comprises pulse width modulation (PWM) signals for synchronously controlling the motor driving circuit 8 to drive the tail motor 2 to act according to the first controlling instruction of flying forwardly or backwardly.
  • PPM pulse position modulation
  • PWM pulse width modulation
  • the tail motor manual switch 5 can be turned off, when a signal route to reach the tail motor 2 is cut off and the tail motor 2 is idle, so as to satisfy needs of flying without winds.
  • the RF signal circuit 6 is processed by the MCU 7 and sends the first group of PPM signals into the leftward and rightward servo steering engine 16 to control the leftward and rightward servo steering engine 16 to act according to the second controlling instruction of flying leftwardly or rightwardly.
  • Fig. 3 shows an installing structure of the linkage device of the present invention.
  • the servo steering engine operating system is installed on an upper part of a body, comprising the forward and backward servo steering engine operating unit and the leftward and rightward servo steering engine operating unit which is provided at backside and not showed, wherein the forward and backward servo steering engine operating unit comprises the forward and backward servo steering engine 1, a servo steering engine joystick 9, a swashplate 10, a rotor head connecting rod 11, a rotor head 12 and rotors 13.
  • the forward and backward servo steering engine 1 is installed on the body; a first end of the servo steering engine joystick 9 is installed on the forward and backward servo steering engine 1 and a second end thereof is installed on the swashplate 10; a first end of the rotor end connecting rod 11 is installed on the swashplate 10 and a second end thereof is installed on the rotor head 12; the rotors 13 are installed on the rotor head 12.
  • the tail motor operating system provided on a tail part of the body, comprises a tail motor frame 14, a tail motor 2, a screw propeller 3 and tail motor fasteners 15.
  • the tail motor frame 14 is fixed on a back part of the body; the tail motor 2 is fixed on the tail motor frame 14 via the tail motor fasteners 15; and the screw propeller 3 is fixed on the tail motor 2.
  • the receiver controlling device 4 is provided in a front part of the body.
  • the receiver controlling device 4 After receiving a synchronous controlling instruction of flying forwardly or backwardly, the receiver controlling device 4 sends synchronous action signals into the forward and backward servo steering engine 1 and the tail motor 2, and then the forward and backward servo steering engine operating unit and the tail motor operating system act simultaneously.
  • a specific process is as follows.
  • the forward and backward servo steering engine 1 drives the servo steering engine joystick 9;
  • the servo steering engine joystick 9 drives the swashplate 10 to tilt;
  • the swashplate 10 drives the rotor head 12 via a rotor head connecting rod 11 to force a rotating plane of a lower rotor 13 to tilt forwardly or backwardly.
  • the tail motor 2 drives the screw propeller 3 to positively rotate synchronously to generate a downward force to lift the tail part of the helicopter and lower the head of the helicopter and instantly the helicopter gains force components tilting forwardly to fly forwardly;
  • the tail motor 2 drives the screw propeller 3 to reversely rotate synchronously to generate an upward force to press the tail part of the helicopter downwardly and lift the head and instantly the helicopter gains force components tilting backwardly to fly backwardly.
  • the tail motor manual switch 5 can be turned on and off according to practical needs to control whether the tail motor 2 is synchronously linked with the forward and backward servo steering engine 1.
  • the forward and backward servo steering engine 1 drives the rotating plane of the lower rotor 13 to tilt forwardly or backwardly under instructions, but the tail motor 2 is idle, so as to suit for flying indoors or without winds.
  • a tail motor circuit can be turned off via wireless instructions to realize flying without winds when the tail motor operating system and the forward and backward servo steering engine operating unit are unable to link simultaneously, i.e., the tail motor operating system is idle and the forward and backward servo steering engine operating unit acts.
  • the receiver controlling device 4 After receiving the synchronous controlling instruction of flying leftwardly or righwardly, the receiver controlling device 4 sends action signals to the leftward and rightward servo steering engine 16 and instantly the leftward and rightward servo steering engine operating unit acts to force the helicopter to fly leftwardly or rightwardly.
  • Table 1 350 helicopter types test frequency flying tests of model helicopters against winds of each scale conclusion scale 0 scale 1 scale 2 scale 3 scale 4 status of the flight speed status of the flight speed status of the flight speed status of the flight speed 350 two-channel helicopter 5 3 m/s stable & controllable 0 m/s going with winds & losing control 0 m/s going with winds & losing control 0 m/s unable to take off 0 m/s unable to take off suitable for flying indoors 350 three-channel helicopter 5 6m/s stable & controllable 4 m/s stable & controllable 2 m/s bumpy & hardly controllable 0 m/s going with winds & losing control 0 m/s unable to take off suitable for flying indoors or in outdoor breeze 350 four-channel helicopter 5 7 m/s stable & controllable 5 m/s stable & controllable 3 m/s bumpy & controllable 0 m/s going with winds & losing control 0 m/s going
  • the model helicopter using the linkage device of the present invention flies faster than the conventional model helicopter; in a condition of winds below scale 4, the model helicopter using the linkage device of the present invention flies faster than the conventional model helicopter and has better stability and controllability than the conventional model helicopter, especially in relatively strong winds of scale 3 to scale 4, the conventional model helicopter totally lose control while the model helicopter using the linkage device is still able to fly against winds.

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  • Toys (AREA)
EP10855757.0A 2010-08-13 2010-12-28 Dispositif de couplage destiné à un hélicoptère modèle télécommandé doté d'une double hélice coaxiale et contrarotative Withdrawn EP2604319A4 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
CN2010202913219U CN201760098U (zh) 2010-08-13 2010-08-13 遥控共轴双桨反转模型直升机联动装置
CN2010102528131A CN101912688B (zh) 2010-08-13 2010-08-13 遥控共轴双桨反转模型直升机联动装置
PCT/CN2010/002183 WO2012019336A1 (fr) 2010-08-13 2010-12-28 Dispositif de couplage destiné à un hélicoptère modèle télécommandé doté d'une double hélice coaxiale et contrarotative

Publications (2)

Publication Number Publication Date
EP2604319A1 true EP2604319A1 (fr) 2013-06-19
EP2604319A4 EP2604319A4 (fr) 2014-01-01

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP10855757.0A Withdrawn EP2604319A4 (fr) 2010-08-13 2010-12-28 Dispositif de couplage destiné à un hélicoptère modèle télécommandé doté d'une double hélice coaxiale et contrarotative

Country Status (11)

Country Link
US (1) US20130137336A1 (fr)
EP (1) EP2604319A4 (fr)
JP (1) JP2013521021A (fr)
KR (1) KR20130045340A (fr)
AU (1) AU2010359022C1 (fr)
BR (1) BR112013002771A2 (fr)
CA (1) CA2807737A1 (fr)
RU (1) RU2013105159A (fr)
SG (1) SG187777A1 (fr)
WO (1) WO2012019336A1 (fr)
ZA (1) ZA201301817B (fr)

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Publication number Priority date Publication date Assignee Title
US9247787B2 (en) * 2012-10-24 2016-02-02 Peak Design, Llc Camera strap attachment mechanism and methods of use
US20140315464A1 (en) * 2013-04-23 2014-10-23 Kevork G. Kouyoumjian Remotely Controlled, Impact-Resistant Model Helicopter
US20140323009A1 (en) * 2013-04-24 2014-10-30 Top Notch Toys Limited Protective ring for toy helicopter
KR101528565B1 (ko) * 2013-12-11 2015-06-15 국립대학법인 울산과학기술대학교 산학협력단 소형 비행물체용 회전 동력장치 및 이를 설치한 소형 비행물체
CN107985567B (zh) * 2017-12-27 2024-03-12 中国科学院工程热物理研究所 一种基于有人机无人化改装的前轮转向操纵机构
CN107970622B (zh) * 2017-12-29 2024-03-15 王子铭 遥控模型飞机矢量电机座
CN108888969A (zh) * 2018-08-13 2018-11-27 江阴市翔诺电子科技有限公司 一种动力装置
CN109018425A (zh) * 2018-08-27 2018-12-18 成都飞机工业（集团）有限责任公司 一种低成本的小型无人机用舵机转接结构

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Publication number Priority date Publication date Assignee Title
US2571566A (en) * 1949-01-04 1951-10-16 John A Green Control system for multiple rotor helicopters
CN2761235Y (zh) * 2004-12-02 2006-03-01 邢英 玩具直升机
DE202006020074U1 (de) * 2006-12-15 2007-12-13 Silverlit Toys Inc., Walnut Helikopter
CN201398124Y (zh) * 2009-06-15 2010-02-03 倪康汉 三通道遥控共轴双桨模型直升机尾电机风冷散热装置

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Title
See also references of WO2012019336A1 *

Also Published As

Publication number Publication date
AU2010359022C1 (en) 2014-01-16
KR20130045340A (ko) 2013-05-03
US20130137336A1 (en) 2013-05-30
ZA201301817B (en) 2013-11-27
BR112013002771A2 (pt) 2016-06-07
AU2010359022A1 (en) 2012-11-08
AU2010359022B2 (en) 2013-09-19
CA2807737A1 (fr) 2012-02-16
SG187777A1 (en) 2013-03-28
JP2013521021A (ja) 2013-06-10
WO2012019336A1 (fr) 2012-02-16
RU2013105159A (ru) 2014-08-20
EP2604319A4 (fr) 2014-01-01

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