EP1160431A2 - Entraínement pour le modèle réduit d'un hélicoptère - Google Patents

Entraínement pour le modèle réduit d'un hélicoptère Download PDF

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Publication number
EP1160431A2
EP1160431A2 EP01112293A EP01112293A EP1160431A2 EP 1160431 A2 EP1160431 A2 EP 1160431A2 EP 01112293 A EP01112293 A EP 01112293A EP 01112293 A EP01112293 A EP 01112293A EP 1160431 A2 EP1160431 A2 EP 1160431A2
Authority
EP
European Patent Office
Prior art keywords
drive unit
turbine
unit according
shaft
transmission
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
Application number
EP01112293A
Other languages
German (de)
English (en)
Other versions
EP1160431B1 (fr
EP1160431A3 (fr
Inventor
Christoph Protte
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
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
Application filed by Individual filed Critical Individual
Priority to DE20122107U priority Critical patent/DE20122107U1/de
Publication of EP1160431A2 publication Critical patent/EP1160431A2/fr
Publication of EP1160431A3 publication Critical patent/EP1160431A3/fr
Application granted granted Critical
Publication of EP1160431B1 publication Critical patent/EP1160431B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • A—HUMAN NECESSITIES
    • A63—SPORTS; GAMES; AMUSEMENTS
    • A63H—TOYS, e.g. TOPS, DOLLS, HOOPS OR BUILDING BLOCKS
    • A63H29/00—Drive mechanisms for toys in general
    • A63H29/22—Electric drives
    • 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
    • A63H29/00—Drive mechanisms for toys in general

Definitions

  • the invention relates to a drive unit for a Model helicopter according to the preamble of the main claim.
  • the invention relates to a drive unit for a model helicopter with a fuselage on its Middle area bearing points for the detachable attachment of a Carrier are formed, which is a rotor shaft, a gear and stores a drive.
  • a wide variety of design forms are from model making known from drive units for model helicopters. This typically include two-stroke model combustion engines, as they are also used in plane aircraft models.
  • the invention is based on the object of a drive unit for a model helicopter of the type mentioned to create which using a turbine at simple Construction and reliable handling in a model helicopter can be used.
  • the object is characterized by the features of Main claim solved, the sub-claims show further advantages on the design of the invention.
  • the drive unit according to the invention is characterized by a A number of significant advantages.
  • the horizontal arrangement of the turbine makes it one possible, the flow direction of the turbine of the model helicopter to adapt to the original models of helicopters and especially the hull design according to the model to execute. This applies in particular to the entry area and the air supply to the turbine.
  • the turbine shaft on one Carrier is mounted, which carries the transmission. This is one ensures safe assignment between the turbine and the gearbox.
  • the turbine shaft is more preferably supported on the carrier Way by means of a preloaded bearing. This is in favorable design at the free end region of the turbine shaft mounted so that the gearbox on the one behind the bearing Area of the turbine shaft can be flanged. This measure increases the overall stability of the arrangement.
  • the transmission is preferably three-stage according to the invention trained, it can be used as a belt transmission, as a gear transmission or be designed as a friction gear.
  • the transmission preferably has a reduction ratio of 100,000 rpm to 1,200 to 1,800 rpm.
  • a clutch arranged to separate the transmission and to be able to make the rotor, especially if it is malfunctions of the transmission or turbine is coming.
  • the model helicopter can be operated by autorotation of the rotor can be safely landed.
  • the turbine has a speed limiting device.
  • This can, for example include a controller for a fuel pump.
  • the fuselage of the model helicopter has been dispensed with to show in detail, as this in different Way can be designed and otherwise is known from the prior art.
  • the model helicopter includes a main rotor and a tail rotor.
  • FIGS. 1 and 2 there is a turbine 2 horizontally in the direction of flow and thus also in Flight direction arranged behind a vertically mounted rotor shaft 1.
  • a turbine shaft 3 of the turbine 2 is in the flow direction extended to the front and is supported by a bearing 6 mounted on a support 5.
  • the carrier 5 includes both the mounting of a gear 4 and also the rotor shaft 1.
  • the turbine shaft 3 is on a yoke plate 10 stored by means of the bearing 6.
  • the bearing 6 can be used as a shoulder ball bearing be formed, it is by means of a spring assembly 11 biased.
  • the spring assembly 11 comprises disc springs.
  • the yoke plate 10 is connected to a front carrier plate 8, which is part of the carrier 5.
  • a rear carrier plate 9 serves to further hold the turbine 2.
  • a bearing cage 12 provided on which the rotor shaft by means of bearings 13 and 14 1 is stored.
  • the rotor shaft 1 carries at its lower end a bevel gear 15 which is designed as a gear or as a friction wheel can be.
  • This bevel gear 15 meshes with another bevel gear 16, which is between the front and rear support plate 8, 9 is mounted and with an output 18 for the Tail rotor is provided.
  • a clutch 7 which acts as a one-way clutch is trained.
  • This in turn is connected with a wheel 19, which is part of a second gear stage forms.
  • a wheel 21 is on an intermediate shaft 20 stored, which in turn from the two carrier plates 8.9 is stored.
  • Another wheel 22, which on the Intermediate shaft 20 is attached forms part of a first Gear stage, its associated wheel 23 on the turbine shaft 3 sits.
  • the wheels 19, 21, 22, 23 as Gears or can be designed as friction wheels.
  • a belt transmission is provided, as it results from the representation of Figure 3.
  • the intermediate shaft 20 is mounted on a carriage 24 which relative to the carrier 5, in particular to the front Carrier plate 8 is slidable. This makes it possible to Adjust the belt tension accordingly.
  • FIGs 4 and 5 each show the carrier plates 8 and 9.
  • the carrier 5 is designed as a whole is that he is at articulation points of the trunk in the usual way can be fastened so that the drive unit as a whole unit taken from the model helicopter in a simple manner can be.
  • the clutch 7 is designed so that in the event of damage or a standstill of the turbine and the gearbox Tail rotor with the main rotor are still firmly connected, so that a safe landing of the model helicopter through autorotation is possible.
  • the turbine speed is Based on 100,000 rpm.
  • the drive unit by means of a flanged electric motor to start.
  • FIG. 6 to 8 show a wide embodiment of the drive unit according to the invention. Same parts are with same reference numerals as in the previous figures Mistake.
  • the third gear stage is formed by the bevel gears 15; 16, the bevel gear 15 being arranged coaxially to the rotor shaft 1 is, while the bevel gear 16 on an auxiliary shaft 17th sits.
  • the auxiliary shaft 17 is with a centrifugal clutch 31 connected, which in turn in detachable connection with the wheel 30 stands.
  • the bevel gear drive formed by the bevel gears 15; 16 (third Gear stage) can be designed and arranged differently his. This is the direction of rotation of another bevel gear 32, which sits on a tail rotor shaft 33, changeable. It is thus possible to change the rotation of the main rotor and to provide the tail rotor.
  • the turbine rotates at a speed of 85000 min -1
  • the tail rotor shaft has a speed of 5886 min -1
  • the main rotor shaft rotates at 1260 min -1 .
  • these speed data are examples of approximate data.
  • the first stage has a gear ratio of 3.8: 1
  • the second stage has a gear ratio of 3.8: 1.
  • the translation is 4.66: 1.
  • An electric starter 34 can be provided to start the turbine be firmly connected to the drive unit according to the invention is.
  • Reference number 35 denotes a shaft coupling, the connection between the turbine shaft 3 and the transmission serves. There is also a freewheel on the rotor shaft 1 36 provided.
  • FIGS 8 a total of two side plates 37 are provided, wherein one of the two side plates 37 for the purpose of clearer Representation was removed.
  • the two side plates 37 are connected by bearing struts 38, which also have additional functions, such as the attachment of bearings or the like.
  • a slide 39 is provided for tensioning the belt drives, on which the intermediate shaft 21 is mounted. By side Moving the carriage 39 can tension the timing belt 25; 26 take place.
  • the carriage 39 Elongated holes in which screws are guided, which against one Cross member 40 are clamped.

Landscapes

  • Toys (AREA)
  • Catching Or Destruction (AREA)
EP01112293A 2000-05-31 2001-05-18 Entraínement pour le modèle réduit d'un hélicoptère Expired - Lifetime EP1160431B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE20122107U DE20122107U1 (de) 2000-05-31 2001-05-18 Antreibseinheit für einen Modellhubschrauber

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10027081 2000-05-31
DE10027081A DE10027081C1 (de) 2000-05-31 2000-05-31 Antriebseinheit für einen Modellhubschrauber

Publications (3)

Publication Number Publication Date
EP1160431A2 true EP1160431A2 (fr) 2001-12-05
EP1160431A3 EP1160431A3 (fr) 2002-12-11
EP1160431B1 EP1160431B1 (fr) 2005-12-21

Family

ID=7644287

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01112293A Expired - Lifetime EP1160431B1 (fr) 2000-05-31 2001-05-18 Entraínement pour le modèle réduit d'un hélicoptère

Country Status (4)

Country Link
US (1) US6484967B2 (fr)
EP (1) EP1160431B1 (fr)
AT (1) ATE313708T1 (fr)
DE (2) DE10027081C1 (fr)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB0315419D0 (en) * 2003-07-02 2003-08-06 Westland Helicopters Compliant spacer
US7529247B2 (en) * 2003-09-17 2009-05-05 Rivulet Communications, Inc. Empirical scheduling of network packets
US7296767B2 (en) * 2005-05-31 2007-11-20 Sikorsky Aircraft Corporation Variable speed transmission for a rotary wing aircraft
US20090146001A1 (en) * 2007-12-11 2009-06-11 Shigetada Taya Power transmission system for an aircraft
US9879768B2 (en) * 2013-12-11 2018-01-30 Velos Rotors Llc Multi-electric motor driven synchronous gearbox assembly with motor failure mechanism
US11186363B2 (en) 2015-10-21 2021-11-30 Sikorsky Aircraft Corporation Electric propulsion system for a rotary wing aircraft
US9828089B2 (en) 2016-01-29 2017-11-28 Sikorsky Aircraft Corporation Rotor drive systems for rotorcraft
US10752343B2 (en) 2016-10-18 2020-08-25 Sikorsky Aircraft Corporation Electric propulsion system for a rotary wing aircraft
US10577090B2 (en) 2017-02-16 2020-03-03 Sikorsky Aircraft Corporation Electric propulsion system with overrunning clutch for a rotary-wing aircraft
US10676182B2 (en) 2017-07-20 2020-06-09 Sikorsky Aircraft Corporation Tilting coaxial rotor for a rotary wing aircraft
US10974824B2 (en) 2017-07-20 2021-04-13 Sikorsky Aircraft Corporation Electric powered direct drive rotor motor
US10407166B2 (en) 2018-01-08 2019-09-10 Sikorsky Aircraft Corporation Yaw moment supplement for directional control

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS582706B2 (ja) * 1977-09-06 1983-01-18 マブチモ−タ−株式会社 ヘリコプタ模型装置
US4222280A (en) * 1978-08-21 1980-09-16 Stewart Donald M Speed changing unit construction
US4829850A (en) * 1987-02-25 1989-05-16 Soloy Dual Pac, Inc. Multiple engine drive for single output shaft and combining gearbox therefor
DE4010362C2 (de) * 1990-03-30 1994-03-10 Peter Schroeppel Triebwerk für flugfähige Modellhubschrauber
DE4209046A1 (de) * 1992-03-20 1993-09-23 Kurt Schreckling Kleingasturbine, insbesondere zum antrieb von flugmodellen
US5782079A (en) * 1997-02-25 1998-07-21 Industrial Technology Research Institute Miniature liquid-fueled turbojet engine
FR2769586B1 (fr) * 1997-10-01 1999-11-19 Pierre Hardoin Hydropal - terrestre aerien hp 02
DE20001233U1 (de) * 2000-01-25 2000-08-03 Henseleit, Jan, 35649 Bischoffen Flugfähiger Modellhubschrauber mit einstufigem Kegelradantrieb des Hauptrotors

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Also Published As

Publication number Publication date
US20020017591A1 (en) 2002-02-14
EP1160431B1 (fr) 2005-12-21
ATE313708T1 (de) 2006-01-15
EP1160431A3 (fr) 2002-12-11
US6484967B2 (en) 2002-11-26
DE50108428D1 (de) 2006-01-26
DE10027081C1 (de) 2002-01-24

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