WO2003080433A1 - Dispositif de commande d'un helicoptere - Google Patents

Dispositif de commande d'un helicoptere Download PDF

Info

Publication number
WO2003080433A1
WO2003080433A1 PCT/BE2003/000051 BE0300051W WO03080433A1 WO 2003080433 A1 WO2003080433 A1 WO 2003080433A1 BE 0300051 W BE0300051 W BE 0300051W WO 03080433 A1 WO03080433 A1 WO 03080433A1
Authority
WO
WIPO (PCT)
Prior art keywords
rotor
mentioned
rotor blades
helicopter
steering
Prior art date
Application number
PCT/BE2003/000051
Other languages
English (en)
Other versions
WO2003080433A8 (fr
Inventor
Alexander Van De Rostyne
Original Assignee
Alexander Van De Rostyne
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
Application filed by Alexander Van De Rostyne filed Critical Alexander Van De Rostyne
Priority to EP03714560A priority Critical patent/EP1487698A1/fr
Priority to AU2003218919A priority patent/AU2003218919A1/en
Publication of WO2003080433A1 publication Critical patent/WO2003080433A1/fr
Publication of WO2003080433A8 publication Critical patent/WO2003080433A8/fr

Links

Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H30/00—Remote-control arrangements specially adapted for toys, e.g. for toy vehicles
    • A63H30/02—Electrical arrangements
    • A63H30/04—Electrical arrangements using wireless transmission
    • 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

Definitions

  • the present invention concerns a device for steering a helicopter.
  • Such helicopters are driven, as is known, by at least one main rotor comprising several adjustable rotor blades and which provides for the buoyant force of the helicopter.
  • the rotor blades are hinge-mounted around their longitudinal axis, whereby the pivot angle is adjustable, such that the buoyant force that is created during the rotation of the rotor can be adjusted.
  • the rotor blades depending on the position in which the pilot moves his steering elements, are adjusted differently, individually and in a cyclic manner, so that they each develop a different buoyant force, as a result of which the helicopter is asymmetrically loaded, and, as a consequence, a moment of force is created which makes the • helicopter heel over in the required direction and makes the helicopter move in this direction.
  • a device with mechanical transmission means between the above-mentioned control elements of the pilot and the adjusting mechanism of the rotor blades are adjusted differently, individually and in a cyclic manner, so that they each develop a different buoyant force, as a result of which the helicopter is asymmetrically loaded, and, as a consequence, a moment of force is created which makes the • helicopter heel over in the required direction and makes the helicopter move in this direction.
  • the present invention aims to remedy the above-mentioned and other disadvantages .
  • the invention concerns a device for steering a helicopter, comprising at least one rotor formed of several rotor blades provided crosswise on the rotor shaft and which are hinge-mounted around their longitudinal axis; at least one steering element for flying forward and backwards and a steering element for flying sidewards; and finally transmission means between these steering elements and the rotor blades for hinge-mounting the rotor blades around their longitudinal axis, characterised in that these transmission means comprise electric drive means provided on the rotor.
  • the drive means preferably consist of one or several electric motors and the transmission means comprise an electric universal joint connected between the motors and the steering elements, so that the device can be realised in a simple and thus cost-efficient manner.
  • the invention is also particularly suitable to be applied on a remote-controlled model helicopter with two adjustable rotor blades .
  • the device in this case comprises one or several converters generating a stress signal which is proportional to the movement of the control elements of the remote control
  • the above- mentioned universal joint mainly consists of a part which is fixed in relation to the body of the helicopter on the one hand, provided co-axially around the rotor shaft and having an insulating core provided with four contact shoes on the outside, and of a rotating part having two sliding contacts provided diametrically opposed to each other on the rotor shaft on the other hand.
  • Such a remote-controlled model helicopter is very easy and cheap to realise, as opposed to the known model helicopters which are also very complex and which make use of expensive servomotors, gyroscopes, accelerometers and microprocessors for their steering, together with the necessary expensive software.
  • a model helicopter makes use of standard and cheap components, namely an electric motor, one or several voltage converters and a universal joint that is easy to realise.
  • figure 1 schematically represents a helicopter in perspective, equipped with a device according to the invention
  • figure 2 represents the part indicated by F2 in figure
  • figure 3 represents a disassembled view of the part represented in figure 2;
  • figure 4 represents a section according to line IV-IV in figure 2;
  • figure 5 represents a section according to line V-V in figure 4;
  • figure 6 represents the part indicated by F6 in figure
  • figure 7 represents a section according to line VII-
  • figure 8 represents a side view of the helicopter from figure 1 ;
  • figure 9 represents a section according to line IX-IX in figure 1;
  • figure 10 represents a section as in figure 9, but for another position;
  • figure 11 represents a diagram of the successive positions of the rotor blades of the helicopter;
  • figure 12 represents a view as in figure 8, but for another position;
  • figure 13 represents a variant of the embodiment of a device according to the invention;
  • figure 14 represents a top view of yet another embodiment of a device according to the invention.
  • Figure 1 represents a helicopter 1 which is equipped with a device according to the invention.
  • the helicopter 1 is in this case a model helicopter steered by means of a conventional remote control with a transmitter part 2, connected wireless to a receiver part 3 in. the helicopter 1, and whereby the transmitter part 2 is among others provided with a steering element 4 in the shape of a toggle or the like which can be moved in two directions in relation to a neutral position in order to steer the forward or backward flying, and a similar steering element 5 for flying sideways .
  • the helicopter 1 mainly consists of a body 6 and a rotor 7 provided upon it, which in this case is provided with rotor blades 8, namely two rotor blades 8A and 8B.
  • the rotor 7 has a rotor shaft 9 which is bearing-mounted in a bearing bush 10 fixed to the body 6 and which is driven at its lower end by means of a drive formed for example of a motor 11 and a reduction gearbox 12.
  • a fork-shaped support 13 is provided centrally on the top end of the rotor shaft 9, having two legs 14 which are parallel to the rotor shaft 9 and a cross piece 15 connecting the two legs 14 and which is fixed crosswise on the rotor shaft 9.
  • a rocker arm 16 with a central, hollow part whereby said rocker arm 16 is mounted on said support 13, such that it can freely pivot around a geometric oscillatory axis Y-Y, by means of two coaxial shafts 17 and 18 respectively, provided in the above- mentioned legs 14 of the support 13, such that they can freely rotate through the passages 19 therein, and which are fixed on two parallel walls 20 of the rocker arm 16 situated opposite to one another, for example because they are provided in a bore in these walls 20 by means of a press fit.
  • the rotor blades 8 are in this case fixed on the above- mentioned flanges 22 in a fixed manner, for example by means of a press pen 23, provided through the passage 24 of the flange 22, such that the rotor blades 8A-8B, as represented in figure 9, enclose a specific adjustment angle H in relation to a plane of symmetry 22A of the plate-shaped flanges 22, such that the rotor blades 8A and 8B are erected such that their front edge 25, which is the front tip of the rotor blades 8, is always directed in the sense of rotation of the rotor 7.
  • drive means 26 which, in this case, consist of an electric motor 27 fixed on the cross piece 15 and which is coupled to the rocker arm 16 by means of a gear wheel transmission 28, whereby this gear wheel transmission 28 consists of a first gear wheel 28A fixed on the shaft of the motor 27 and a second gear wheel 28B working in conjunction with it which is fixed to the above- mentioned shaft 17 of the rocker arm 16.
  • an electric motor 27 is used for the drive means 26, other electric drive means which can provide for a torque or a force, such as actuators, servomotors or the like are not excluded.
  • the above-mentioned motor 26 is electrically connected to the receiver part 3 of the above-mentioned remote control, by means of an electric universal joint 29 provided on the rotor shaft 9 and which is itself connected to two converters 30 and 31 respectively, converting the signals from the receiver part 3 of the remote control in two separate stress signals which are proportional to the movements of the two above- mentioned control elements 4-5 respectively.
  • the above-mentioned universal joint 29 is provided with a part 29A that is fixed in relation to the body 6, consisting of an insulating ring-shaped core 32 which is provided co-axially around the rotor shaft 9 and which is provided with four contact shoes on the outside, two opposite contact shoes 33 and two other opposite contact shoes 34 respectively, rotated 90° in relation to one another.
  • the opposite contact shoes 33-34 form contact pairs which are connected to the above-mentioned converters 30-31 by means of conductors 35-36 respectively.
  • the universal joint 29 is further provided with a rotating part 29B consisting of a lath 37 provided diagonally on the rotor shaft 9 in a centred manner, whereby a sliding contact 38 is hinge-mounted on each far end of this lath 37 on a shaft 39 which is parallel to the rotor shaft, and whereby these sliding contacts 38 are held against the outside of the above-mentioned fixed part 29A by means of a spring which is not represented in the figures.
  • the above-mentioned sliding contacts 38 are each connected to a connection contact 41 of the above-mentioned motor 27 by means of a conductor 40.
  • the working of the device is as follows: hile the rotor 7 is being driven by the motor 11, the rotor blades 8 move through the air, as a result of which, as is known, since they enclose a specific angle of incidence, B and C respectively, in relation to the plane of rotation 42 in which they move, they are subjected to a buoyant force or what , is called a lift which is perpendicular to the above-mentioned plane of rotation 42.
  • the aforesaid angles of incidence B and C of the rotor blades 8A and 8B are equal to one another and moreover equal to the above-mentioned adjustment angle H, so that the lifts, indicated with LA and LB respectively, of the two rotor blades 8A and 8B will be equal, as a result of which no moment is exerted on the rotor 7 and a situation is created, for example, as represented in figure 10, whereby the common buoyant force L is in balance with the weight G of the helicopter 1, as a result of which it will for example stay hanging on the spot.
  • the steering element 4 of the remote control is pushed forward in order to make the helicopter 1 fly forward, the converter 30 will generate a positive voltage applied on the contact shoes 33 via the conductors 35.
  • the thus obtained voltage gradient between the contact poles 41 of the motor 27 is schematically represented in the upper diagram of figure 11 as a function of the position of for example the rotor blade 8A over an entire revolution of the rotor 7, whereby 0° corresponds to the most forward directed position of this rotor blade 8A, as represented in figure 1.
  • the motor 27 is excited, so that the rocker arm 16, as represented in figure 10, is rotated over a certain angle in proportion to the voltage applied, and thus in proportion to the movement of the steering element 4, for example in the direction indicated by the sense of rotation E.
  • this angular displacement of the rocker arm 16 has for a result that the angle of incidence A of the rotor blade 8A becomes smaller, and thus smaller than the neutral adjustment angle H, whereas the angle of incidence B of the rotor blade 8B simultaneously and to an equal extent becomes larger, and thus larger than the neutral adjustment angle H, so that for the above- mentioned positions corresponding to 0° and 180°, the lift LA of the rotor blade 8A in this case gets larger, whereas the lift LB of the rotor blade 8B gets smaller to the same extent, so that the common lift L remains as large as before, but as a result of which a moment of force is created which makes the rotor 7 and thus also the entire helicopter 1 heel over forward, as represented in figure 12.
  • the lift L which is always perpendicular to the plane of rotation 42 thus obtains a forward directed component LV which makes the helicopter 1 fly forward.
  • a forward directed component LV which makes the helicopter 1 fly forward.
  • the converter 30 When this steering element 4 is pulled backward, the converter 30 will generate a negative signal, as , a result of which the rocker arm 16, each time the rotor blades 8 mainly extend in the longitudinal direction of the helicopter 1, will tilt in the opposite sense compared to the preceding case, so that this time the lift of the rotor blade 8 situated at the front becomes larger, whereas the lift of the rear rotor blade ,8 becomes smaller, so that in this case the helicopter 1 will heel over backward and will also fly backward.
  • the converter 31 will this time generate a voltage applied to the contact poles 41 of the motor 27 each time the rotor blades 8 are directed sideways, so that in this case, according to an analogous argumentation, the rotor will heel over to the left, so that the helicopter 1 is steered to the left.
  • control elements 4-5 can be used in combination to make the helicopter 1 move in a slanting manner.
  • the rotational speed of the motor 11 can be altered in a conventional manner, by operating an additional control element 43 on the remote control, so that the receiver part 3 can control said motor 11 via the conductor 44.
  • Figure 13 represents a variant of a device according to the invention, whereby the rocker arm 16 is not driven directly by the motor 27 in this case, but indirectly by making use of the aerodynamic operation of two additional vanes 45 fixed on either side of the rocker arm 16 on a common shaft 46 which is provided on the rocker arm 16 in a rotating manner and which extends crosswise to the above-mentioned rotor blades 8A-8B.
  • a gear wheel segment 47 working in conjunction with a gear wheel 48 of the motor 27.
  • the vanes 45 are rotated in a particular direction, so that one vane 45 develops a buoyant force and the other vane 45 develops a downward force, such that a moment of force is obtained which makes the rocker arm 16 tilt in a certain direction, as a result of which, in the same manner as in the preceding embodiment, the rotor blades 8A and 8B are loaded asymmetrically and the helicopter 1 is heeled over in a certain direction.
  • additional vanes 45 is advantageous in that they can develop a great moment of force, such that a motor 27 with a smaller torque can be used to drive the rocker arm 16.
  • vanes 45 Another advantage of these vanes 45 is that they have a stabilising effect on the helicopter 1, such that no extra stabilising equipment with gyroscopes, accelerometers and the like is required.
  • Figure 14 represents yet another variant of a device according to the invention, whereby the rotor 7 is equipped with rotor blades 8 in this case which are provided on a rotor head 49 in a rotating manner, joint with the rotor shaft 9, and whereby separate drive means.26 are provided for each rotor blade 8 , each for example in the shape of a motor 27 and a gear wheel transmission 28.
  • all rotor blades 8 can be steered separately, either in common so as to increase or reduce the lift, or according to a cyclic movement, as in the preceding embodiments, to steer the helicopter 1 in a particular direction. It is clear that another type of electric universal joint is required for this, which can be easily realised by a craftsman of the related technical domain.

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  • Engineering & Computer Science (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Toys (AREA)

Abstract

L'invention concerne un dispositif de commande d'un hélicoptère, comprenant au moins un rotor (7) formé de plusieurs pales (8) disposées en croix sur l'arbre de rotor (9) et articulées autour de leur axe longitudinal ; au moins un élément de commande (4) de vol vers l'avant ou vers l'arrière, et un élément de commande (5) de vol latéral ; ainsi que des moyens de transmission entre ces éléments de commande (4-5) et les pales de rotor (8) pour l'articulation des lames de rotor (8) autour de leur axe longitudinal, caractérisé en ce que lesdits moyens de transmission comprennent des moyens d'entraînement électriques (26) prévus sur le rotor (7).
PCT/BE2003/000051 2002-03-25 2003-03-24 Dispositif de commande d'un helicoptere WO2003080433A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP03714560A EP1487698A1 (fr) 2002-03-25 2003-03-24 Dispositif de commande d'un helicoptere
AU2003218919A AU2003218919A1 (en) 2002-03-25 2003-03-24 Device for steering a helicopter

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
BE2002/0214A BE1014724A6 (nl) 2002-03-25 2002-03-25 Inrichting voor de besturing van een helikopter.
BE2002/0214 2002-03-25

Publications (2)

Publication Number Publication Date
WO2003080433A1 true WO2003080433A1 (fr) 2003-10-02
WO2003080433A8 WO2003080433A8 (fr) 2004-05-27

Family

ID=28047797

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/BE2003/000051 WO2003080433A1 (fr) 2002-03-25 2003-03-24 Dispositif de commande d'un helicoptere

Country Status (4)

Country Link
EP (1) EP1487698A1 (fr)
AU (1) AU2003218919A1 (fr)
BE (1) BE1014724A6 (fr)
WO (1) WO2003080433A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005100154A1 (fr) * 2004-04-13 2005-10-27 Wavefront Technology Pty Ltd Systeme pour tete de rotor et aube de rotor
US7662013B2 (en) 2006-01-19 2010-02-16 Silverlit Toys Manufactory Ltd. Helicopter with horizontal control
US7815482B2 (en) 2006-01-19 2010-10-19 Silverlit Toys Manufactory, Ltd. Helicopter
US7883392B2 (en) 2008-08-04 2011-02-08 Silverlit Toys Manufactory Ltd. Toy helicopter
US8002604B2 (en) 2006-01-19 2011-08-23 Silverlit Limited Remote controlled toy helicopter
US8052500B2 (en) 2008-11-25 2011-11-08 Silverlit Limited Helicopter with main and auxiliary rotors
US8308522B2 (en) 2006-01-19 2012-11-13 Silverlit Limited Flying toy
CN102811905A (zh) * 2010-03-23 2012-12-05 贝尔直升机泰克斯特龙公司 安装有倾斜盘的永磁交流发电机
US8357023B2 (en) 2006-01-19 2013-01-22 Silverlit Limited Helicopter
US8702466B2 (en) 2008-07-02 2014-04-22 Asian Express Holdings Limited Model helicopter

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3384184A (en) * 1966-07-06 1968-05-21 Buford J. Schramm Helicopter rotor hub
US4118143A (en) * 1977-03-29 1978-10-03 Franz Kavan Stabilizing and control device for two-bladed helicopter rotors
US4555219A (en) * 1984-08-23 1985-11-26 United Technologies Corporation Hub-mounted actuators for blade pitch collective control
WO2000027698A1 (fr) * 1998-11-05 2000-05-18 Nigel Howard Mckrill Moyeu de rotor pour aeronef a voilure tournante
EP1153829A2 (fr) * 2000-05-10 2001-11-14 ZF Luftfahrttechnik GmbH Dispositif de commande individuelle des pales du rotor

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3384184A (en) * 1966-07-06 1968-05-21 Buford J. Schramm Helicopter rotor hub
US4118143A (en) * 1977-03-29 1978-10-03 Franz Kavan Stabilizing and control device for two-bladed helicopter rotors
US4555219A (en) * 1984-08-23 1985-11-26 United Technologies Corporation Hub-mounted actuators for blade pitch collective control
WO2000027698A1 (fr) * 1998-11-05 2000-05-18 Nigel Howard Mckrill Moyeu de rotor pour aeronef a voilure tournante
EP1153829A2 (fr) * 2000-05-10 2001-11-14 ZF Luftfahrttechnik GmbH Dispositif de commande individuelle des pales du rotor

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2005100154A1 (fr) * 2004-04-13 2005-10-27 Wavefront Technology Pty Ltd Systeme pour tete de rotor et aube de rotor
US7662013B2 (en) 2006-01-19 2010-02-16 Silverlit Toys Manufactory Ltd. Helicopter with horizontal control
US7815482B2 (en) 2006-01-19 2010-10-19 Silverlit Toys Manufactory, Ltd. Helicopter
US8002604B2 (en) 2006-01-19 2011-08-23 Silverlit Limited Remote controlled toy helicopter
US8308522B2 (en) 2006-01-19 2012-11-13 Silverlit Limited Flying toy
US8357023B2 (en) 2006-01-19 2013-01-22 Silverlit Limited Helicopter
US8702466B2 (en) 2008-07-02 2014-04-22 Asian Express Holdings Limited Model helicopter
US7883392B2 (en) 2008-08-04 2011-02-08 Silverlit Toys Manufactory Ltd. Toy helicopter
US8052500B2 (en) 2008-11-25 2011-11-08 Silverlit Limited Helicopter with main and auxiliary rotors
CN102811905A (zh) * 2010-03-23 2012-12-05 贝尔直升机泰克斯特龙公司 安装有倾斜盘的永磁交流发电机

Also Published As

Publication number Publication date
WO2003080433A8 (fr) 2004-05-27
BE1014724A6 (nl) 2004-03-02
AU2003218919A1 (en) 2003-10-08
EP1487698A1 (fr) 2004-12-22
AU2003218919A8 (en) 2003-10-08

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