EP1160431B1 - Antriebseinheit für einen Modellhubschrauber - Google Patents
Antriebseinheit für einen Modellhubschrauber Download PDFInfo
- Publication number
- EP1160431B1 EP1160431B1 EP01112293A EP01112293A EP1160431B1 EP 1160431 B1 EP1160431 B1 EP 1160431B1 EP 01112293 A EP01112293 A EP 01112293A EP 01112293 A EP01112293 A EP 01112293A EP 1160431 B1 EP1160431 B1 EP 1160431B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- drive unit
- turbine
- unit according
- shaft
- gearbox
- 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.)
- Expired - Lifetime
Links
Images
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 hull at whose Center area bearing points for the detachable attachment of a Carrier are formed, which a rotor shaft, a transmission and stores a drive.
- model making are a variety of designs known by drive units for model helicopters. These typically include two-stroke combustion model engines, as used in surface aircraft models.
- the invention is based on the object, a drive unit for a model helicopter of the type mentioned to create which using a turbine with simple Construction and reliable handling in a model helicopter can be used.
- the drive unit according to the invention is characterized by a Series of significant benefits.
- the horizontal arrangement of the turbine on the one hand possible, the flow direction of the turbine of the model helicopter to adapt to the original models of helicopters and in particular the hull design according to the model perform. This applies in particular to the inlet area and the air supply to the turbine.
- the turbine shaft on a Carrier is stored, which carries the gearbox. This is a ensures safe allocation between the turbine and the transmission.
- the storage of the turbine shaft on the carrier is more preferred Way by means of a preloaded bearing. This is in favorable design at the free end of the turbine shaft mounted so that the gearbox is located at the rear of the warehouse Field of the turbine shaft can be flanged. By this measure, the overall stability of the arrangement increases.
- the transmission is according to the invention preferably in three stages trained, it can be used as a belt transmission, as a gear transmission or be designed as a friction gear.
- the transmission has a reduction of 100,000 rpm to 1,200 to 1,800 rpm.
- a clutch arranged to provide a separation between the transmission and to make the rotor, especially if it to malfunction of the transmission or turbine comes. In this case, the model helicopter by autorotation of the rotor are landed safely.
- the turbine with a speed-limiting device is provided.
- This can for example include a controller for a fuel pump.
- the model helicopter includes a main rotor and a tail rotor.
- a turbine 2 is used horizontally in the direction of flow and thus also in Flight direction behind a vertically mounted rotor shaft 1 is arranged.
- a turbine shaft 3 of the turbine 2 is in the flow direction extended forward and is by means of a warehouse 6 mounted on a support 5.
- the carrier 5 includes both the storage of a transmission 4 as also the rotor shaft 1.
- the turbine shaft 3 is on a yoke plate 10th 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 includes disc springs.
- the yoke plate 10 is connected to a front support plate 8, which is part of the carrier 5.
- a rear support plate 9 serves for further support of the turbine. 2
- a bearing cage 12 provided, on which by means of bearings 13 and 14, the rotor shaft 1 is stored.
- the rotor shaft 1 carries 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 between the front and the rear support plate 8, 9 is mounted and with an output 18 for the Tail rotor is provided.
- FIGs 4 and 5 respectively show the carrier plates 8 and 9th
- the carrier 5 is formed as a whole is that he at articulation points of the hull in the usual way is attachable, leaving the drive unit as an entire unit taken in a simple manner from the model helicopter can be.
- the clutch 7 is designed so that in case of damage or a stoppage of the turbine and the transmission of the Tail rotor with the main rotor continue to be firmly connected, so that a safe landing of the model helicopter by autorotation is possible.
- a turbine speed is 100,000 rev / min based.
- FIG. 6 to 8 show a wide embodiment of the Drive unit according to the invention. Same parts are with the same reference numerals as in the previous figures Mistake.
- the third gear stage is formed by the bevel gears 15; 16, wherein the bevel gear 15 is arranged coaxially with the rotor shaft 1 is while the bevel gear 16 on an auxiliary shaft 17th sitting.
- the auxiliary shaft 17 is connected to a centrifugal clutch 31 connected, which in turn releasably connected to the wheel 30 stands.
- the formed by the bevel gears 15, 16 bevel gear (third Gear stage) can be designed and arranged differently be.
- the direction of rotation of another bevel gear 32 which sits on a tail rotor shaft 33, changeable. It is thus possible, a rotation change for the main rotor and to provide the tail rotor.
- the turbine rotates for example at a speed of 85000 min -1
- the tail rotor shaft has a speed of 5886 min -1
- the main shaft rotates at 1260 min -1. It goes without saying that these speed specifications are exemplary approx.
- Overall, there is thus a total transmission ratio of the transmission of i 67.29.
- the first stage has a ratio of 3.8: 1, while the second stage has a ratio of 3.8: 1.
- the ratio is 4.66: 1.
- an electric starter 34 may be provided be firmly connected to the drive unit according to the invention is.
- the reference numeral 35 denotes a shaft coupling, that of the connection between the turbine shaft 3 and the transmission serves. Furthermore, on the rotor shaft 1, a freewheel 36 provided.
- FIGS. 6 to 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 allow.
- a carriage 39 is provided for tensioning the belt drives, on which the intermediate shaft 21 is mounted. By lateral Moving the carriage 39 can tension the timing belt 25; 26. For this purpose, the carriage 39 Slotted holes in which are guided, which against a Cross member 40 are clamped.
Landscapes
- Toys (AREA)
- Catching Or Destruction (AREA)
Description
- Fig. 1
- eine schematische Teil-Seiten-Ansicht der erfindungsgemäßen Antriebseinheit,
- Fig. 2
- eine vereinfachte Teil-Seiten-Ansicht, analog der Darstellung der Figur 1,
- Fig. 3
- eine stirnseitige Ansicht, der in Figur 2 gezeigten Anordnung unter Darstellung des Getriebes,
- Fig. 4
- eine Ansicht einer hinteren Trägerplatte des Trägers,
- Fig. 5
- eine Ansicht einer vorderen Trägerplatte des Trägers,
- Fig. 6
- eine perspektivische Ansicht, teils im demontierten Zustand, eines Ausführungsbeispiels der erfindungsgemäßen Antriebseinheit,
- Fig. 7
- eine Seitenansicht, teils im Schnitt, der in Fig. 6 gezeigten Antriebseinheit, und
- Fig. 8
- eine stirnseitige Ansicht der in den Figuren 6 und 7 gezeigten Antriebseinheit.
Claims (12)
- Antriebseinheit für einen Modellhubschrauber mit einem Rumpf und einem in den Rumpf einbaubaren Träger (5), welcher eine Rotorwelle (1), ein Getriebe (4) und eine Antriebseinheit lagert, dadurch gekennzeichnet, dass die Antriebseinheit eine horizontal angeordnete Turbine (2) umfasst, deren Turbinenwelle (3) im Einlaufbereich der Turbine (2) verlängert ist und mit dem Riementriebe umfassenden Getriebe (4) verbunden ist.
- Antriebseinheit nach Anspruch 1, dadurch gekennzeichnet, dass die Turbinenwelle (3) an dem Träger (5) gelagert ist, der das Getriebe (4) trägt.
- Antriebseinheit nach Anspruch 2, dadurch gekennzeichnet, dass die Turbinenwelle (3) mittels eines vorgespannten Lagers (6) an dem Träger (5) gelagert ist.
- Antriebseinheit nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, dass das Getriebe (4) in Durchströmungsrichtung vor der Turbine (2) angeordnet ist.
- Antriebseinheit nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die Turbine (2) in Durchströmungsrichtung hinter der Rotorwelle (1) eingebaut ist.
- Antriebseinheit nach einem der Ansprüche 1 bis 5, dadurch gekennzeichnet, dass das Getriebe (4) dreistufig ausgebildet ist.
- Antriebseinheit nach einem der Ansprüche 1 bis 6, dadurch gekennzeichnet, dass das Getriebe (4) eine Untersetzung von 100.000 U/min auf 1.200 bis 1.800 U/min hat.
- Antriebseinheit nach einem der Ansprüche 1 bis 7, dadurch gekennzeichnet, dass zwischen dem Getriebe (4) und der Rotorwelle (1) eine Kupplung (7) angeordnet ist.
- Antriebseinheit nach Anspruch 8, dadurch gekennzeichnet, dass die Kupplung (7) als Fliehkraftkupplung ausgebildet ist.
- Antriebseinheit nach Anspruch 9, dadurch gekennzeichnet, dass die Kupplung (7) als Freilaufkupplung für die Autorotation des Rotors ausgebildet ist.
- Antriebseinheit nach einem der Ansprüche 1 bis 10, dadurch gekennzeichnet, dass die Turbine (2) mit einer Drehzahl-Begrenzungseinrichtung versehen ist.
- Antriebseinheit nach Anspruch 11, dadurch gekennzeichnet, dass die Drehzahl-Begrenzungseinrichtung eine Steuerung für eine Treibstoffpumpe umfasst.
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 |
---|---|---|---|
DE10027081A DE10027081C1 (de) | 2000-05-31 | 2000-05-31 | Antriebseinheit für einen Modellhubschrauber |
DE10027081 | 2000-05-31 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP1160431A2 EP1160431A2 (de) | 2001-12-05 |
EP1160431A3 EP1160431A3 (de) | 2002-12-11 |
EP1160431B1 true EP1160431B1 (de) | 2005-12-21 |
Family
ID=7644287
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP01112293A Expired - Lifetime EP1160431B1 (de) | 2000-05-31 | 2001-05-18 | Antriebseinheit für einen Modellhubschrauber |
Country Status (4)
Country | Link |
---|---|
US (1) | US6484967B2 (de) |
EP (1) | EP1160431B1 (de) |
AT (1) | ATE313708T1 (de) |
DE (2) | DE10027081C1 (de) |
Families Citing this family (12)
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)
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 |
-
2000
- 2000-05-31 DE DE10027081A patent/DE10027081C1/de not_active Expired - Fee Related
-
2001
- 2001-05-18 DE DE50108428T patent/DE50108428D1/de not_active Expired - Lifetime
- 2001-05-18 EP EP01112293A patent/EP1160431B1/de not_active Expired - Lifetime
- 2001-05-18 AT AT01112293T patent/ATE313708T1/de active
- 2001-05-21 US US09/860,527 patent/US6484967B2/en not_active Expired - Lifetime
Also Published As
Publication number | Publication date |
---|---|
US20020017591A1 (en) | 2002-02-14 |
US6484967B2 (en) | 2002-11-26 |
ATE313708T1 (de) | 2006-01-15 |
EP1160431A3 (de) | 2002-12-11 |
DE50108428D1 (de) | 2006-01-26 |
EP1160431A2 (de) | 2001-12-05 |
DE10027081C1 (de) | 2002-01-24 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
DE2519152C2 (de) | Vorrichtung zum Anlassen von Flugzeugtriebwerken und zum Betreiben von Flugzeughilfsgeräten | |
DE602005000678T2 (de) | Turbomaschine mit einem Rezeptor und einem Niederdruckverdichter von einer Niederdruckturbine angetrieben | |
EP1160431B1 (de) | Antriebseinheit für einen Modellhubschrauber | |
DE2549771A1 (de) | Gasturbinentriebwerk mit konvertiblen zubehoerteilen | |
DE60018054T2 (de) | Zusätzlisches antriebssystem eines drehflügelflugzeuges | |
DE102005043615B4 (de) | Propellerantriebseinheit | |
DE3837736A1 (de) | Kombiniertes aussen- und notstromaggregat | |
DE3731463A1 (de) | Lufteinlass fuer ein turboprop-gasturbinentriebwerk | |
DE60003200T2 (de) | Integrierte antriebs- und getriebeeinheiten für drehflügel-luftfahrzeuge | |
DE102020117254A1 (de) | Gasturbinentriebwerk und Luftfahrzeug mit einem Gasturbinentriebwerk | |
DE1756138A1 (de) | Triebwerksanlage fuer Hubschrauber | |
DE2451059A1 (de) | Gasturbinentriebwerk | |
DE20122107U1 (de) | Antreibseinheit für einen Modellhubschrauber | |
DE102004008073B4 (de) | Ausfahrtriebwerk | |
DE102008018101A1 (de) | Strahltriebwerk mit mindestens einem Notantrieb | |
DE2733986A1 (de) | Triebwerk mit differentialgetriebe | |
DE20022355U1 (de) | Antriebseinheit für einen Modellhubschrauber | |
DE10151954A1 (de) | Segelflugzeug mit einem Triebwerk | |
DE1109533B (de) | Antriebsanordnung fuer Flugzeuge | |
AT410467B (de) | Gasturbine | |
DE19958058B4 (de) | Antriebseinheit für einen Modellhubschrauber | |
EP2948366B1 (de) | Schiffsantriebsanordnung | |
DE4010362C2 (de) | Triebwerk für flugfähige Modellhubschrauber | |
DE861209C (de) | Insbesondere an den Tragfluegeln eines Flugzeuges angeordnetes Heissluft-Strahltriebwerk mit zusaetzlichem Luftschraubenantrieb durch die Turbine des Triebwerks | |
DE102019109854A1 (de) | Fahrzeug |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
RIC1 | Information provided on ipc code assigned before grant |
Free format text: 7F 02B 75/34 A, 7A 63H 27/12 B, 7A 63H 29/00 B, 7F 02B 61/04 B |
|
17P | Request for examination filed |
Effective date: 20030130 |
|
AKX | Designation fees paid |
Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
RIC1 | Information provided on ipc code assigned before grant |
Ipc: 7A 63H 27/133 B Ipc: 7A 63H 29/00 B Ipc: 7F 02B 61/04 B Ipc: 7F 02B 75/34 A |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: IT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT;WARNING: LAPSES OF ITALIAN PATENTS WITH EFFECTIVE DATE BEFORE 2007 MAY HAVE OCCURRED AT ANY TIME BEFORE 2007. THE CORRECT EFFECTIVE DATE MAY BE DIFFERENT FROM THE ONE RECORDED. Effective date: 20051221 Ref country code: FI Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20051221 Ref country code: IE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20051221 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: FG4D Free format text: NOT ENGLISH |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: EP |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FG4D Free format text: LANGUAGE OF EP DOCUMENT: GERMAN |
|
REF | Corresponds to: |
Ref document number: 50108428 Country of ref document: DE Date of ref document: 20060126 Kind code of ref document: P |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: DK Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20060321 Ref country code: SE Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20060321 Ref country code: GR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20060321 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: ES Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20060401 |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20060327 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: NV Representative=s name: BREITER + PARTNER AG PATENT - UND MARKENBUERO |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: PT Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20060522 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: BE Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20060531 Ref country code: MC Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20060531 |
|
REG | Reference to a national code |
Ref country code: IE Ref legal event code: FD4D |
|
ET | Fr: translation filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20060922 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PFA Owner name: PROTTE, CHRISTOPH Free format text: PROTTE, CHRISTOPH#JOHANN-WEGENER STRASSE 17 B#33129 DELBRUECK (DE) -TRANSFER TO- PROTTE, CHRISTOPH#JOHANN-WEGENER STRASSE 17 B#33129 DELBRUECK (DE) |
|
BERE | Be: lapsed |
Owner name: PROTTE, CHRISTOPH Effective date: 20060531 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LU Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20060518 Ref country code: TR Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20051221 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: CY Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT Effective date: 20051221 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20140520 Year of fee payment: 14 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 20140520 Year of fee payment: 14 Ref country code: FR Payment date: 20140516 Year of fee payment: 14 Ref country code: AT Payment date: 20140519 Year of fee payment: 14 Ref country code: CH Payment date: 20140522 Year of fee payment: 14 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MM01 Ref document number: 313708 Country of ref document: AT Kind code of ref document: T Effective date: 20150518 |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20150518 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: LI Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150531 Ref country code: CH Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150531 |
|
REG | Reference to a national code |
Ref country code: NL Ref legal event code: MM Effective date: 20150601 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: ST Effective date: 20160129 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: AT Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150518 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150518 Ref country code: NL Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150601 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: FR Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES Effective date: 20150601 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20200528 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 50108428 Country of ref document: DE |