EP0957264B1 - Combinaison d'un démarreur de moteur à combustion et d'un générateur d'électricité pour aéronefs - Google Patents

Combinaison d'un démarreur de moteur à combustion et d'un générateur d'électricité pour aéronefs Download PDF

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Publication number
EP0957264B1
EP0957264B1 EP99106945A EP99106945A EP0957264B1 EP 0957264 B1 EP0957264 B1 EP 0957264B1 EP 99106945 A EP99106945 A EP 99106945A EP 99106945 A EP99106945 A EP 99106945A EP 0957264 B1 EP0957264 B1 EP 0957264B1
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EP
European Patent Office
Prior art keywords
starter
gear
generator
combustion engine
aircraft
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
Application number
EP99106945A
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German (de)
English (en)
Other versions
EP0957264A3 (fr
EP0957264A2 (fr
Inventor
Joachim Dr.-Ing. Wernicke
Hartmut Dipl.-Ing. Euer
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.)
EMT Ingenieurgesellschaft Dipl Ing Hartmut Euer mbH
Original Assignee
EMT Ingenieurgesellschaft Dipl Ing Hartmut Euer mbH
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Publication date
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Publication of EP0957264A2 publication Critical patent/EP0957264A2/fr
Publication of EP0957264A3 publication Critical patent/EP0957264A3/fr
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Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02N—STARTING OF COMBUSTION ENGINES; STARTING AIDS FOR SUCH ENGINES, NOT OTHERWISE PROVIDED FOR
    • F02N11/00—Starting of engines by means of electric motors
    • F02N11/04—Starting of engines by means of electric motors the motors being associated with current generators

Definitions

  • the invention relates to a device for starting an internal combustion engine Using an electrical starter and converting mechanical power to electrical Electricity using a generator for aircraft powered by the internal combustion engine according to the preamble of claim 1.
  • a device according to the preamble of claim 1 from US-A-4 708 030.
  • Aircraft powered by an internal combustion engine are known in practice. Such For example, aircraft engines are started using an electric starter. To When the internal combustion engine is started, the starter becomes mechanical by means of a clutch separated from the shaft of the aircraft engine. Aircraft are usually powered from pre-charged on-board batteries. For aircraft that are designed for long flight times is common an electric generator is provided, which recharges the on-board batteries.
  • the disadvantage is in the known device that both the electric starter and the generator have relatively high weight and thereby the weight of the aircraft as a whole increase. The high weight of the starter and generator is due to the required magnet and Attributed to coil materials.
  • the range and flight duration, especially of unmanned aerial vehicles Aircraft, for example for the remote-controlled extraction and transmission of aerial photographs, depends heavily on the weight of these aircraft. To maximize range and flight duration, the flight weight of the aircraft must be kept as low as possible.
  • the invention has for its object to a device of the type mentioned create, which has a lower weight.
  • the starter / generator unit Due to the integrated design of the starter / generator unit, it is able to Execute double function.
  • the unit can be used as a starter to start the internal combustion engine of the aircraft powered by this and as a generator, for example for charging the On-board batteries are used. So while in the prior art for performing the Function "starting the internal combustion engine” and the function “converting mechanical Power in electrical current "two separate electrical components are needed, comes the Device according to the invention with a single unit, which perform both functions can. With the help of a suitable gearbox, this starter / generator unit is permanent connected to the internal combustion engine.
  • the transmission is a manual transmission with a certain Reduction for starter operation and a specific reduction for generator operation educated. Low speeds usually occur when the aircraft engine is started Connection with a high required starting torque while in generator operation high speeds of the engine shaft of the aircraft engine on the starter / generator unit working in generator operation are to be transferred. With the help of the manual transmission it is possible to both for the starter as well as for the generator operation an optimal coupling between the To create starter / generator unit and the internal combustion engine driving the aircraft.
  • the manual transmission proposed according to the invention thus enables Gearbox with constant step-up or step-down optimization of both applications, so that the The device according to the invention can work optimally so that in starter operation a sufficient high starting torque is available and an impermissibly high one in generator mode Speed load of the starter / generator unit is excluded.
  • a gearbox with constant step-up or step-down can only be one of the two applications, i.e. the Starter operation or generator operation, be optimally designed so that either is not sufficient high torque for starting the internal combustion engine is available or the anyway high speed of the internal combustion engine in generator mode to an impermissibly high Speed of the starter / generator unit would lead.
  • the manual transmission has several clutches, preferably one clutch each to switch the gearbox to starter or generator operation, with the Couplings using a force flow direction sensor, preferably a torque sensor, are controllable.
  • This is a Manual transmission created, controlled by the direction of power flow on the one hand from the Starter / generator unit for the internal combustion engine, on the other hand from the internal combustion engine to Starter / generator unit automatically to one of two preselected gear ratios or Sets reductions.
  • the other translation / reduction is by the respective other clutch switched inactive.
  • the starter / generator unit is one Collector DC motor, preferably a rare earth magnet DC motor, the Rare earth magnet according to an advantageous development of the invention, a neodymium-iron-boron magnet is.
  • a rare earth magnet DC motor preferably a rare earth magnet DC motor
  • the Rare earth magnet according to an advantageous development of the invention, a neodymium-iron-boron magnet is.
  • Such magnets are other permanent magnet materials both in the energy product as well as superior in stability, so that such a DC motor extremely can be constructed compactly and at the same time has a high efficiency. On such a DC motor of small size offers a high despite its low weight Torque.
  • the transmission is According to an advantageous development of the invention, a constant gear with a fixed, constant translation or reduction.
  • This makes the weight of the invention Device and thus the aircraft as a whole further minimized, since such Transmission has a lower weight than a manual transmission.
  • rare earth magnet dc motor can have a single reduction value and select and design a constant gearbox so that a permanently functional one Compromise in terms of starter or generator operation with extreme at the same time light weight can be realized. Due to the proposed gear with fixed or Constant translation or reduction can therefore be compared to using a suitable one constructively designed gearbox a weight advantage can be achieved.
  • the invention Preferred device thus has the particular advantage that equipped aircraft during the flight the internal combustion engine driving the aircraft can be switched off and on again and again so that flightless phases can be realized. This is for the inconspicuous extraction of electronic aerial photographs with unmanned aerial vehicles Motor glider aircraft of particular importance.
  • the device 1 essentially has an integrated starter / generator unit 3 and the internal combustion engine 2, which are connected to one another via a transmission 4 are.
  • the starter / generator unit 3 is designed such that it is both electrical and Starter for the internal combustion engine 2 and also as a generator, for example for charging the On-board batteries, not shown, of the aircraft, not shown, can work.
  • the Internal combustion engine 2 is, for example, a piston internal combustion engine, the aircraft, for example an unmanned motor glider.
  • the starter / generator unit 3 is connected to the transmission 4 and via a shaft 5 the transmission 4 is connected to the internal combustion engine 2 by means of a motor shaft 6.
  • the Internal combustion engine 2 also has a propeller shaft 7, which is firmly connected to it Propeller 10 drives.
  • the aircraft can also carry screws instead of propeller 10 exhibit.
  • this is Transmission 4 as a manual transmission 11 with a specific, preselected reduction for the Starter operation and a specific, preselected reduction for generator operation trained, the respective reduction ratios are selected so that the starter / generator unit 3 in starter mode the torque required to start the Combustion engine 2 reached and in generator operation with an at least still permissible Speed is applied.
  • the manual transmission 11 has two clutches 12, 13, one each Clutch for switching gear 4 to starter mode and for switching gear 4 on generator operation, on, the clutch 13 at one end with a gear part 14 and at the other end with the motor shaft 6 of the internal combustion engine 2 and the clutch 12 at one end is coupled to a gear part 15 and at the other end to the starter / generator unit 3. It is clear that the aforementioned elements cooperate in such a way that the gear part 14 also with the shaft 5 of the unit 3 and the transmission part 15 also with the motor shaft 6 of the Internal combustion engine 2 are connected.
  • the gearbox can be a gear, toothed belt or friction belt gear, for example.
  • the clutches 12, 13 can be electromagnetic clutches, for example.
  • the power flow direction sensor 16 is preferably a Torque sensor with inductive power supply and inductive, d. H. non-contact, Signal leakage.
  • the torque sensor determines the torque direction and is only evaluated with regard to this torque direction.
  • the torque sensor has For example, a mechanical spring-loaded torque direction switch, which radial or axial position of a movable element depending on the torque direction for example, with the help of a groove guide and thereby an intervention or disengaging the couplings 12, 13.
  • the arrangement and interpretation of the Couplings 12, 13 is selected according to the invention so that the components of the associated Gear parts 14, 15 are not subjected to impermissibly high speeds or moments become.
  • the inventive Device can work in an optimal operating range.
  • the unit 3 applies a torque sufficient to start the internal combustion engine and can be transferred to the internal combustion engine and that the unit is not included in generator mode operating at impermissibly high speeds.
  • a gearbox with constant Ratio of starter operation realized that the starter speed to Reaching a sufficient torque to the motor shaft 6 or to the internal combustion engine 2 is stepped down.
  • this reduction would work as a translation in generator mode act that the already high speed of the internal combustion engine 2 or the motor shaft 6th further increased and thereby particularly stress the unit 3 in generator operation and with a would impermissibly high speed.
  • the constant Gear unit 3 would be operated in the permissible speed range, on the other hand but there would be a risk that the unit 3 due to its required small and light Type do not apply the torque required to start the internal combustion engine can.
  • the starter / generator unit 3 is a Rare earth magnet DC motor, the rare earth magnet preferably a neodymium-iron-boron magnet is.
  • the elements scandium, yttrium and lanthanum become rare earth metals and the 14 elements following the lanthanum.
  • the rare earth metals are located in the periodic table in the third group and count among the transition metals.
  • the rare earth elements are also called lanthanoids or lanthanides.
  • the transmission 4 as a manual transmission 11 shown in the figure or as a constant transmission fixed translation / reduction.
  • the aforementioned force flow direction sensor 16 can alternatively also be arranged on the motor shaft 6 his. It is clear that the output signal of this sensor clutches 12, 13 in complementary switching controls so that under no operating conditions both clutches intervene at the same time.
  • a fixed reduction gear d. H. a gear with constant reduction
  • the shaft 5 is, for example, with a starter Small diameter gear and the motor shaft 6 with a gear large diameter that meshes with the small diameter gear wheel, connected.
  • the motor shaft 6 is then with the gear wheel small diameter and the shaft 5 with the large diameter gear wheel connected.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Ignition Installations For Internal Combustion Engines (AREA)

Claims (6)

  1. Dispositif pour faire démarrer un moteur à combustion interne (2) à l'aide d'un démarreur électrique, et pour transformer une puissance mécanique en courant électrique à l'aide d'un générateur, pour des aéronefs entraínés par le moteur à combustion interne (2), comportant une unité démarreur/générateur (3) intégrée qui est conçue de manière à fonctionner aussi bien comme démarreur que comme générateur, et qui est reliée au moteur à combustion interne par une transmission (4),
       la transmission (4) étant conformée en boíte de changement de vitesses (11) et comportant plusieurs accouplements (12, 13),
       caractérisé en ce que
       la transmission (4) comporte un accouplement actif (12; 13) respectif pour commuter la transmission (4) sur le mode démarreur ou pour commuter la transmission (4) sur le mode générateur.
  2. Dispositif selon la revendication 1, caractérisé en ce que la transmission (4) comporte une démultiplication déterminée pour le mode démarreur et une démultiplication déterminée pour le mode générateur.
  3. Dispositif selon la revendication 1 ou 2, caractérisé en ce que les accouplements (12, 13) peuvent être commandés au moyen d'un capteur de sens de flux des forces (16), de préférence un capteur de couple de rotation.
  4. Dispositif selon l'une des revendications précédentes, caractérisé en ce que l'unité démarreur/générateur (3) est un moteur à courant continu à collecteur.
  5. Dispositif selon la revendication 4, caractérisé en ce que le moteur à courant continu est un moteur à courant continu à aimant en terre rare, l'aimant en terre rare étant de préférence un aimant néodyme-fer-bore.
  6. Dispositif selon la revendication 5, caractérisé en ce que la transmission (4) est une transmission constante avec rapport constant fixe de multiplication ou de démultiplication.
EP99106945A 1998-05-15 1999-04-08 Combinaison d'un démarreur de moteur à combustion et d'un générateur d'électricité pour aéronefs Expired - Lifetime EP0957264B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19821997 1998-05-15
DE19821997A DE19821997A1 (de) 1998-05-15 1998-05-15 Vorrichtung zum Starten eines Verbrennungsmotors und zum Umwandeln von mechanischer Leistung in elektrischen Strom für Fluggeräte

Publications (3)

Publication Number Publication Date
EP0957264A2 EP0957264A2 (fr) 1999-11-17
EP0957264A3 EP0957264A3 (fr) 1999-12-08
EP0957264B1 true EP0957264B1 (fr) 2002-07-03

Family

ID=7867984

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99106945A Expired - Lifetime EP0957264B1 (fr) 1998-05-15 1999-04-08 Combinaison d'un démarreur de moteur à combustion et d'un générateur d'électricité pour aéronefs

Country Status (3)

Country Link
EP (1) EP0957264B1 (fr)
AT (1) ATE220176T1 (fr)
DE (2) DE19821997A1 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7687928B2 (en) * 2006-06-14 2010-03-30 Smiths Aerospace, Llc Dual-structured aircraft engine starter/generator
DE102007017332A1 (de) * 2007-04-11 2008-10-16 Flight - Design - GmbH Flugsportgeräte Luftfahrzeug

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4473752A (en) * 1982-05-27 1984-09-25 Lockheed Corporation Aircraft engine starting with synchronous ac generator
US4708030A (en) * 1985-03-18 1987-11-24 Sundstrand Corporation Multi-range starter-generator drive
FR2643520B1 (fr) * 1989-02-21 1991-04-26 Valeo Alternateur-demarreur avec dispositif d'accouplement automatique
DE19625022B4 (de) * 1995-06-28 2008-04-03 Volkswagen Ag Antriebsanordnung für ein Kraftfahrzeug und Verfahren zum Betreiben derselben

Also Published As

Publication number Publication date
EP0957264A3 (fr) 1999-12-08
DE19821997A1 (de) 1999-11-18
EP0957264A2 (fr) 1999-11-17
ATE220176T1 (de) 2002-07-15
DE59901898D1 (de) 2002-08-08

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