EP1066194A1 - Propulsion system for an aircraft - Google Patents

Propulsion system for an aircraft

Info

Publication number
EP1066194A1
EP1066194A1 EP99906012A EP99906012A EP1066194A1 EP 1066194 A1 EP1066194 A1 EP 1066194A1 EP 99906012 A EP99906012 A EP 99906012A EP 99906012 A EP99906012 A EP 99906012A EP 1066194 A1 EP1066194 A1 EP 1066194A1
Authority
EP
European Patent Office
Prior art keywords
drive
aircraft
motors
drive system
drive shaft
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.)
Pending
Application number
EP99906012A
Other languages
German (de)
French (fr)
Inventor
Alexander Frick
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.)
Frick Aerotech AG
Original Assignee
Frick Aerotech AG
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 Frick Aerotech AG filed Critical Frick Aerotech AG
Priority to EP99906012A priority Critical patent/EP1066194A1/en
Publication of EP1066194A1 publication Critical patent/EP1066194A1/en
Pending legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/08—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions characterised by the transmission being driven by a plurality of power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60K—ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES
    • B60K5/00—Arrangement or mounting of internal-combustion or jet-propulsion units
    • B60K5/08—Arrangement or mounting of internal-combustion or jet-propulsion units comprising more than one engine

Definitions

  • the present invention relates to a drive system for an aircraft, in particular an aircraft, which is kept in flight by air currents generated by an impeller compressor, with a drive motor arrangement and transmission means to the lift / propulsion units of the aircraft.
  • the problem can e.g. can be solved by using two completely independent motors. For reasons of weight, this was only possible for larger performances.
  • a relatively complex double ignition is required for drive systems with only one internal combustion engine, but this is only effective against certain faults in the ignition system.
  • the object of the present invention was to create a drive system which was able to avoid the previous problems. - 2 -
  • the solution according to the invention has shown that the safety of the new concept can be increased significantly compared to single-engine aircraft without the costs becoming prohibitively high. Thanks to the drive system designed according to the invention, the size of the individual motor can be selected so that both resp. all engines together give the required total output. The costs for such engines would still be very high if they were only built for aircraft. However, since the individual motor is also suitable for other purposes (e.g. driving small motor vehicles, such as motorcycles), it is possible to produce quantities that keep the costs for the individual motor unexpectedly low.
  • the drive system according to the invention is suitable for smaller aircraft in which, for reasons of weight and cost, two conventional motors are out of the question and are replaced by two or more independent light motors which are arranged directly next to one another and act mechanically synchronized with one another on a common drive shaft.
  • What is essential here is the inevitable or automatic decoupling of a possibly failing motor from the common drive shaft. At least one onward flight sufficient for an emergency landing is guaranteed after the failed engine is disconnected. This is possible because of the remaining performance - 3 -
  • FIG. 1 shows a side view, purely schematically, of a drive system according to the invention
  • FIG. 2 is a bottom view of the arrangement of FIG .. 1
  • the propulsion system according to the invention shown in the drawing is suitable for small VTOL aircraft or engines for which two separate engines were previously out of the question for reasons of weight and cost.
  • the drive system shown in FIGS. 1 and 2 serves to drive an impeller compressor 1 with an air duct 2 (part of a push pipe system) for light VTOL aircraft.
  • an impeller compressor 1 for the drive of the impeller 3
  • two small internal combustion engines 4 and 5 are provided, which are synchronized with one another via a mechanical connection, for example a toothed belt 6.
  • Each of the two internal combustion engines 4, 5 has small overall dimensions (for example approx. 500 x 250 x 300 mm) for the intended purpose.
  • the motors 4, 5 arranged directly next to one another have an identical structure and the same output.
  • the motors 4, 5 each drive a common drive shaft 9 for the compressor 1 via a separate drive connection 7, 8 (eg toothed belt) (the drive can take place from the shaft 9, for example via a belt drive 10, onto the shaft 11 of the impeller 3 ).
  • a separate drive connection 7, 8 eg toothed belt
  • the performance of the two motors 4, 5 is designed so that flight operations are possible. Should one of the two motors 4, 5 fail, the performance of the second motor is sufficient at least for an emergency landing.
  • the drive connections between the motors 4, 5 and the shaft 9 can be interrupted via predetermined breaking points in a connecting link, automatic couplings and the like (at any point between the motor output and engagement with the shaft 9).
  • the drive connection is interrupted automatically, e.g. when a braking force occurs (torque-dependent control) in the connection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Transportation (AREA)
  • Output Control And Ontrol Of Special Type Engine (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Vehicle Engines Or Engines For Specific Uses (AREA)
  • Control Of Turbines (AREA)
  • Retarders (AREA)
  • Transmission Devices (AREA)

Abstract

The invention relates to a propulsion system comprising at least two independent internal combustion engines (4, 5) which are positioned directly next to each other and synchronized and which each act on a common drive shaft (9). Means are provided for in each separate propulsion connection (4 to 9 or 5 to 9) which cut said connection when there is a significant drop in power (rated breaking points, automatic decoupling).

Description

Antriebssystem für ein FluggerätPropulsion system for an aircraft
Die vorliegende Erfindung betrifft ein Antriebssystem für ein Fluggerät, insbesondere ein Fluggerät, welches durch von einem Flügelradkompressor erzeugte Luftströme im Flug gehalten wird, mit einer Antriebsmotoranordnung und Übertragungsmitteln an die Auftrieb-/Vortriebaggregate des Fluggerätes.The present invention relates to a drive system for an aircraft, in particular an aircraft, which is kept in flight by air currents generated by an impeller compressor, with a drive motor arrangement and transmission means to the lift / propulsion units of the aircraft.
Beim Antrieb von Fluggeräten werden an den bzw. die Motoren höchste Anforderungen bezüglich Betriebssicherheit gestellt.When driving aircraft, the highest demands are placed on the engine (s) with regard to operational safety.
Das Problem kann z.B. dadurch gelöst werden, dass zwei völlig unabhängige Motoren eingesetzt werden. Aus Gewichtsgründen kam das bis heute nur für grössere Leistungen in Frage.The problem can e.g. can be solved by using two completely independent motors. For reasons of weight, this was only possible for larger performances.
Bei Antriebssystemen mit nur einem Verbrennungsmotor wird eine relativ aufwendige Doppelzündung verlangt, welche jedoch nur gegen gewisse Störungen im Zündungssystem wirksam ist .A relatively complex double ignition is required for drive systems with only one internal combustion engine, but this is only effective against certain faults in the ignition system.
Bei einmotorigen Antriebssystemen ist ein merklicher Leistungsabfall praktisch gleichbedeutend mit Totalausfall.In the case of single-engine drive systems, a noticeable drop in performance is practically synonymous with total failure.
Für VTOL-Fluggeräte, insbesondere mittels Luft- bzw. Gasströmen im Flug gehaltene Fluggeräte kleinerer Abmessungen, kam bisher nur ein einzelner Motor für den Antrieb in Frage. Ein Motoraus- fall war auch hier gleichbedeutend mit Totalausfall und damit Absturz. Auch hier stand aus Gewichtsgründen und insbesondere Kostengründen die Lösung mit zwei separaten Motoren nicht zur Diskussion.For VTOL aircraft, in particular aircraft of smaller dimensions that are kept in flight by means of air or gas flows, only a single motor for propulsion has so far been considered. An engine failure was synonymous with total failure and thus a crash. Here too, the solution with two separate motors was out of the question for reasons of weight and, in particular, cost.
Aufgabe der vorliegenden Erfindung war es nun, ein Antriebssy- stem zu schaffen, welches die bisherigen Probleme vermeiden konnte . - 2 -The object of the present invention was to create a drive system which was able to avoid the previous problems. - 2 -
Bei einem Antriebssystem der eingangs definierten Art konnte die gestellte Aufgabe erfindungsgemäss durch die Merkmale gemäss dem kennzeichnenden Teil von Anspruch 1 gelöst werden.In a drive system of the type defined at the outset, the object was achieved according to the invention by the features according to the characterizing part of claim 1.
Besondere Ausführungsformen des erfindungsgemässen Antriebssy- stems sind in den abhängigen Ansprüchen definiert .Particular embodiments of the drive system according to the invention are defined in the dependent claims.
Die erfindungsgemässe Lösung hat überraschenderweise gezeigt, dass mit dem neuen Konzept im Vergleich zu einmotorigen Fluggeräten die Sicherheit wesentlich erhöht werden kann, ohne dass dabei die Kosten untragbar hoch werden. Dank dem erfindungsge- mäss ausgebildeten Antriebssystem kann die Grosse des einzelnen Motors so gewählt werden, dass beide resp. alle Motoren zusammen die geforderte Gesamtleistung ergeben. Die Kosten für solche Motoren würden trotzdem sehr hoch ausfallen, wenn diese nur für Fluggeräte gebaut würden. Da sich der einzelne Motor aber auch für andere Zwecke (z.B. Antrieb kleiner Motorfahrzeuge, wie Motorräder) eignet, lassen sich Stückzahlen produzieren, welche die Kosten für den einzelnen Motor unerwartet tief halten.Surprisingly, the solution according to the invention has shown that the safety of the new concept can be increased significantly compared to single-engine aircraft without the costs becoming prohibitively high. Thanks to the drive system designed according to the invention, the size of the individual motor can be selected so that both resp. all engines together give the required total output. The costs for such engines would still be very high if they were only built for aircraft. However, since the individual motor is also suitable for other purposes (e.g. driving small motor vehicles, such as motorcycles), it is possible to produce quantities that keep the costs for the individual motor unexpectedly low.
Das erfindungsgemässe Antriebssystem eignet sich für kleinere Fluggeräte, bei welchen aus Gewichts- und Kostengründen zwei konventionelle Motoren nicht in Frage kommen und durch zwei oder mehrere unabhängige leichte Motoren, die direkt nebeneinander angeordnet, mechanisch miteinander synchronisiert auf eine gemeinsame Antriebswelle wirken, ersetzt werden. Wesentlich dabei ist die zwangsläufige bzw. automatische Abkopplung eines gegebenenfalls ausfallenden Motors von der gemeinsamen Antriebswelle. Zumindest ein für eine Notlandung ausreichender Weiterflug ist nach Abkopplung des ausfallenden Motors gewährleistet. Dies ist möglich, weil die Leistung des verbleibenden - 3 -The drive system according to the invention is suitable for smaller aircraft in which, for reasons of weight and cost, two conventional motors are out of the question and are replaced by two or more independent light motors which are arranged directly next to one another and act mechanically synchronized with one another on a common drive shaft. What is essential here is the inevitable or automatic decoupling of a possibly failing motor from the common drive shaft. At least one onward flight sufficient for an emergency landing is guaranteed after the failed engine is disconnected. This is possible because of the remaining performance - 3 -
Motors nicht durch Verluste durch den nicht mehr betriebstüchtigen Motor beeinträchtigt wird.Motors is not affected by losses caused by the motor that is no longer operational.
Die Erfindung wird nachstehend anhand eines in der Zeichnung dargestellten Ausführungsbeispiels noch etwas näher erläutert .The invention is explained in more detail below with reference to an embodiment shown in the drawing.
Es zeigt :It shows :
Fig. 1 eine Seitenansicht, rein schematisch, eines erfindungs- gemässen Antriebssystems und1 shows a side view, purely schematically, of a drive system according to the invention and
Fig. 2 eine Ansicht von unten auf die Anordnung nach Fig. 1.2 is a bottom view of the arrangement of FIG .. 1
Das in der Zeichnung gezeigte erfindungsgemässe Antriebssystem eignet sich für kleine VTOL-Fluggeräte bzw. Triebwerke, für welche bisher aus Gewichts- und Kostengründen zwei separate Triebwerke nicht in Frage kamen.The propulsion system according to the invention shown in the drawing is suitable for small VTOL aircraft or engines for which two separate engines were previously out of the question for reasons of weight and cost.
Das in den Fig. 1 und 2 gezeigte Antriebssystem dient dem Antrieb eines Flügelradkompressors 1 mit Luftkanal 2 (Teil eines Schubrohrsystems) für leichte VTOL-Fluggeräte. Für den Antrieb des Flügelrades 3 sind zwei kleine Verbrennungsmotoren 4 und 5 vorgesehen, welche über eine mechanische Verbindung, z.B. Zahnriemen 6, miteinander synchronisiert sind. Jeder der beiden Verbrennungsmotoren 4, 5 weist für den angestrebten Zweck ge- ringe Gesamtabmessungen auf (z.B. ca. 500 x 250 x 300 mm) . Die unmittelbar nebeneinander angeordneten Motoren 4, 5 weisen einen identischen Aufbau und gleiche Leistung auf. Die Motoren 4, 5 treiben über jeweils eine eigene Antriebsverbindung 7, 8 (z.B. Zahnriemen) eine gemeinsame Antriebswelle 9 für den Kom- pressor 1 an (der Antrieb kann von der Welle 9 z.B. über einen Riementrieb 10 auf die Welle 11 des Flügelrades 3 erfolgen) . - 4 -The drive system shown in FIGS. 1 and 2 serves to drive an impeller compressor 1 with an air duct 2 (part of a push pipe system) for light VTOL aircraft. For the drive of the impeller 3, two small internal combustion engines 4 and 5 are provided, which are synchronized with one another via a mechanical connection, for example a toothed belt 6. Each of the two internal combustion engines 4, 5 has small overall dimensions (for example approx. 500 x 250 x 300 mm) for the intended purpose. The motors 4, 5 arranged directly next to one another have an identical structure and the same output. The motors 4, 5 each drive a common drive shaft 9 for the compressor 1 via a separate drive connection 7, 8 (eg toothed belt) (the drive can take place from the shaft 9, for example via a belt drive 10, onto the shaft 11 of the impeller 3 ). - 4 -
Die Leistung der beiden Motoren 4, 5 ist so ausgelegt, dass damit der Flugbetrieb möglich ist. Sollte einer der beiden Motoren 4, 5 ausfallen, genügt die Leistung des zweiten Motors zumindest für eine Notlandung.The performance of the two motors 4, 5 is designed so that flight operations are possible. Should one of the two motors 4, 5 fail, the performance of the second motor is sufficient at least for an emergency landing.
Damit dies aber bei der beschränkten Leistung der Motoren 4, 5 gewährleistet ist, muss bei Ausfall eines Motors dessen Antriebsverbindung zur gemeinsamen Antriebswelle 9 des Auftrieb- /Vortriebaggregates (Kompressor 1) unterbrochen werden, so dass der arbeitende Motor nicht zusätzlich Leistung verliert, um den nicht mehr betriebstüchtigen Motor "mitzubetreiben" .So that this is ensured with the limited power of the motors 4, 5, if one motor fails, its drive connection to the common drive shaft 9 of the buoyancy / propulsion unit (compressor 1) must be interrupted, so that the working motor does not lose additional power in order to no longer operational engine "to operate".
Der Unterbruch der Antriebsverbindungen zwischen den Motoren 4, 5 und der Welle 9 kann über Sollbruchstellen in einem Verbindungsglied, automatische Kupplungen und dergleichen erfolgen (an irgendeiner Stelle zwischen Motorausgang und Eingriff auf die Welle 9) .The drive connections between the motors 4, 5 and the shaft 9 can be interrupted via predetermined breaking points in a connecting link, automatic couplings and the like (at any point between the motor output and engagement with the shaft 9).
Der Unterbruch der Antriebsverbindung erfolgt automatisch, z.B. bei Auftreten einer Bremskraft (drehmomentabhängige Steuerung) in der Verbindung. The drive connection is interrupted automatically, e.g. when a braking force occurs (torque-dependent control) in the connection.

Claims

- 5 -Patentansprüche : - 5 patent claims:
1. Antriebssystem für ein Fluggerät, insbesondere ein Fluggerät, welches durch von einem Flügelradkompressor erzeugte Luft- ströme im Flug gehalten wird, mit einer Antriebsmotoranordnung und Ubertragungsmitteln an die Auftrieb-/Vortriebaggregate des Fluggerätes, dadurch gekennzeichnet, dass die Antriebsmotoranordnung mindestens zwei voneinander unabhängige, miteinander synchronisierte Motoren mit jeweils gleicher oder ähnlicher Leistung umfasst, von denen jeder auf eine gemeinsame Antriebs- welle der Auftrieb-/Vortriebaggregate wirkt, und dass Mittel vorgesehen sind, um bei Ausfall eines beliebigen der beiden Motoren dessen AntriebsVerbindung mit der gemeinsamen Antriebswelle zu unterbrechen.1. Drive system for an aircraft, in particular an aircraft which is kept in flight by air currents generated by an impeller compressor, with a drive motor arrangement and transmission means to the lift / propulsion units of the aircraft, characterized in that the drive motor arrangement comprises at least two mutually independent, Engines synchronized with each other, each with the same or similar power, each of which acts on a common drive shaft of the buoyancy / propulsion units, and that means are provided in order to interrupt the drive connection to the common drive shaft if any of the two motors fails.
2. Antriebssystem nach Anspruch 1, dadurch gekennzeichnet, dass die Unterbruchmittel in jeder der Antriebsverbindungen zwischen den unabhängigen Motoren und der gemeinsamen Antriebswelle aus einer Sollbruchstelle in der Antriebsverbindung bestehen.2. Drive system according to claim 1, characterized in that the interruption means in each of the drive connections between the independent motors and the common drive shaft consist of a predetermined breaking point in the drive connection.
3. Antriebssystem nach Anspruch 2, dadurch gekennzeichnet, dass die Unterbruchmittel in jeder der Antriebsverbindungen zwischen den unabhängigen Motoren und der gemeinsamen Antriebswelle aus einer vorzugsweise selbsttätig wirkenden Kupplung in der Antriebsverbindung bestehen.3. Drive system according to claim 2, characterized in that the interruption means in each of the drive connections between the independent motors and the common drive shaft consist of a preferably automatically acting clutch in the drive connection.
4. Antriebssystem nach einem der Ansprüche 1 bis 3 , dadurch gekennzeichnet, dass die unabhängigen Motoren Verbrennungsmotoren sind, von denen bei Ausfall eines Motors der Betrieb der übrigen Motoren ausreicht, um mit dem Fluggerät weiterzufliegen oder zumindest eine sanfte Landung durchzuführen. - 6 -4. Drive system according to one of claims 1 to 3, characterized in that the independent motors are internal combustion engines, of which, in the event of a motor failure, the operation of the other motors is sufficient to continue flying with the aircraft or at least to carry out a smooth landing. - 6 -
5. Antriebssystem nach einem der Ansprüche 1 bis 4, dadurch gekennzeichnet, dass die unabhängigen Motoren von identischer Bauart sind. 5. Drive system according to one of claims 1 to 4, characterized in that the independent motors are of identical design.
EP99906012A 1998-03-27 1999-03-09 Propulsion system for an aircraft Pending EP1066194A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP99906012A EP1066194A1 (en) 1998-03-27 1999-03-09 Propulsion system for an aircraft

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP98105615A EP0945340A1 (en) 1998-03-27 1998-03-27 Driving system for an aircraft
EP98105615 1998-03-27
EP99906012A EP1066194A1 (en) 1998-03-27 1999-03-09 Propulsion system for an aircraft
PCT/CH1999/000109 WO1999050140A1 (en) 1998-03-27 1999-03-09 Propulsion system for an aircraft

Publications (1)

Publication Number Publication Date
EP1066194A1 true EP1066194A1 (en) 2001-01-10

Family

ID=8231664

Family Applications (2)

Application Number Title Priority Date Filing Date
EP98105615A Withdrawn EP0945340A1 (en) 1998-03-27 1998-03-27 Driving system for an aircraft
EP99906012A Pending EP1066194A1 (en) 1998-03-27 1999-03-09 Propulsion system for an aircraft

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP98105615A Withdrawn EP0945340A1 (en) 1998-03-27 1998-03-27 Driving system for an aircraft

Country Status (14)

Country Link
EP (2) EP0945340A1 (en)
JP (1) JP2002509841A (en)
KR (1) KR20010034656A (en)
CN (1) CN1293635A (en)
AU (1) AU2607499A (en)
BG (1) BG104795A (en)
BR (1) BR9909140A (en)
CA (1) CA2324447A1 (en)
HU (1) HUP0102323A3 (en)
IL (1) IL138550A0 (en)
NO (1) NO20004825L (en)
PL (1) PL343200A1 (en)
SK (1) SK13882000A3 (en)
WO (1) WO1999050140A1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102015105787A1 (en) * 2015-04-15 2016-10-20 Johann Schwöller Electric drive for an aircraft and hybrid system for an aircraft
CN105857623A (en) * 2016-03-28 2016-08-17 苏州妙旋无人机应用有限公司 Engine special for unmanned aerial vehicle

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR465209A (en) * 1913-11-22 1914-04-10 Porsche Ferdinand A Propeller control for air vehicles, in particular for airplanes
US1664399A (en) * 1923-08-07 1928-04-03 Brown Ellsworth Multiple-engine drive gear
US2505853A (en) * 1948-12-29 1950-05-02 Fairchild Engine & Airplane Output shaft coupling mechanism for multiple power plants
US4177693A (en) * 1978-06-22 1979-12-11 Avco Corporation Drive system
US4829850A (en) * 1987-02-25 1989-05-16 Soloy Dual Pac, Inc. Multiple engine drive for single output shaft and combining gearbox therefor

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO9950140A1 *

Also Published As

Publication number Publication date
KR20010034656A (en) 2001-04-25
BG104795A (en) 2001-06-29
NO20004825D0 (en) 2000-09-26
CN1293635A (en) 2001-05-02
BR9909140A (en) 2000-12-05
CA2324447A1 (en) 1999-10-07
EP0945340A1 (en) 1999-09-29
AU2607499A (en) 1999-10-18
NO20004825L (en) 2000-09-26
HUP0102323A3 (en) 2001-12-28
IL138550A0 (en) 2001-10-31
HUP0102323A2 (en) 2001-11-28
JP2002509841A (en) 2002-04-02
PL343200A1 (en) 2001-07-30
WO1999050140A1 (en) 1999-10-07
SK13882000A3 (en) 2001-06-11

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