RU2802265C2 - Drive, in particular for the main rotor of an aircraft with a main rotor - Google Patents

Abstract

FIELD: aircrafts.

SUBSTANCE: drive unit for driving the main rotor of an aircraft with a main rotor, contains a planetary gear, which includes several satellites. Each gear planet has a planet gear with teeth, and these planet gears are located inside the planetary gear concentric to the central axis, so that the rotating shaft of the propeller of the aircraft is driven by the planets or the sun gear. A first electric drive is integrated into at least one planet gear, whereby an internal drive is formed inside the planetary gear so that the screw shaft is driven by the first drive.

EFFECT: increased compactness of the drive.

13 cl, 21 dwg

Description

The present invention relates to a drive unit, in particular for driving the main rotor of an aircraft with a main rotor according to the preamble of independent claim 1.

In addition, the present invention relates to a hybrid drive with a drive unit according to the invention, in particular for driving the main rotor of an aircraft with a main rotor, and also relates to an aircraft with a main rotor, containing the specified hybrid drive, respectively, the specified drive unit.

Drive units are known from the prior art for a wide variety of applications in drive systems or energy production. Such drive units often contain so-called planetary gears or related, comparable gears.

By definition, planetary gears are so-called planetary gears (due to the rotation of the planetary gears (planetary gears) around the sun gear), which essentially contain a centrally located sun gear, at least one, but larger part of several planetary gears (satellites), a planet carrier connected to the planetary gears, as well as a ring gear located outside, equipped with internal teeth, respectively, located outside, equipped with internal teeth, a gear ring. The advantages of using planetary gears lie in the diverse transmission possibilities, as well as in the uniform and distributed power transmission.

Planetary gears are used in drive units in various fields of technology, such as, for example, in wind turbines, in the automotive industry, respectively, in cars, ship drives, in aviation, etc.

From US 9,797,504 B2, for example, the use of a planetary gear for a wind turbine is known. With the wind-induced (respectively, driven by the wind) rotation of the main rotor shaft of the wind turbine, the transmission is carried out by means of a planetary gear, respectively, the conversion of the low speed and high torque on the main rotor shaft into a high speed and low torque of the generator.

In aircraft with a main rotor, in particular in the field of helicopter construction, the drive unit for driving the main rotor often comprises a gear (reducer) of the main rotor of the helicopter, respectively, made in the form of a planetary gear or similar gear, respectively, the main gear. This type of transmission of the main rotor of the helicopter has received a predominant distribution, since due to this a reliable design becomes possible.

Such planetary gears used in the field of drive systems have the disadvantage that the space required for their installation is enormous, and in addition, this can lead to an undesirable complication of the design of the drive unit.

The present invention aims to provide a compact and simplified drive unit for a wide variety of applications, in particular for driving the main rotor of a main rotor aircraft.

This task is solved by means of a drive unit with features of independent claim 1, by means of a hybrid drive with features of independent claim 5, respectively, by means of an aircraft with a main rotor with features of independent claim 6 of the claims.

According to the invention, a first drive, in particular an electric drive, is integrated into at least one planetary gear, whereby an internal drive is formed inside the planetary gear.

In the sense of the present invention, said at least one satellite is itself designed as a drive, respectively, essentially forms the first drive. As a significant difference from the already known application of planetary gears (for example, from US 9,797,504 B2), it can be noted that, according to this invention, the planetary gear (due to said at least one made as a planetary gear) can now work as a drive unit, accordingly, an internal drive is formed inside the planetary gear.

In the sense of the present invention, only one single satellite can operate as a drive, respectively, can be designed as a drive, and preferably for optimal power distribution all satellites work as a drive. It is therefore particularly advantageous if the drive unit according to the invention comprises a control unit designed in such a way that the drives integrated in the satellites are synchronized with each other. Further, these planet-integrated drives can be configured to be mechanically, electrically or hydraulically disconnected from each other by means of a suitable clutch to prevent possible transmission blockage due to incorrect operation of one or more drives. In the sense of the present invention, said control is implemented as a standard control for electric synchronous motors with control logic and power electronics LEE (also called "inverter"). This control logic (motor controller) generates appropriate signals that drive the inverter, which then energizes the appropriate windings of the synchronous motor to achieve continuous rotation at a given frequency and torque. Synchronization of electric synchronous motors is carried out by determining the position and speed of rotation of the armature, and for each electric synchronous motor is performed individually by calculating the control signals. In this sense, a suitable view is shown in Fig.6.

According to one preferred modification of the present invention, the drive unit may also comprise a single, i.e. made in the form of a single solid structural part, the carrier of the planetary gear, and this carrier of the planetary gear contains at least one, preferably a plurality of receiving holes for satellites.

Other preferred embodiments are described in the dependent claims.

Preferably, the satellite wheels are stationary and rotatably mounted about their respective axes of the satellite wheels, wherein said stationary satellite wheels are surrounded by an internally toothed ring rotatable about the central axis of the drive assembly, and this toothed ring is rotatably mounted such that the shaft, in in particular the main rotor shaft is driven by means of a toothed ring driver fixed on the toothed ring and on the shaft, in particular on the main rotor shaft. This creates a related, comparable form of planetary gear. Such stationary satellite wheels have the advantage that the power supply of the drive integrated in these satellite wheels is facilitated by electrical supply lines.

In principle, however, within the framework of the present invention, a planetary gear set in the form of an epicyclic gear train is also possible, in which the satellite wheels are not stationary, i.e. installed with the possibility of rotation, respectively, circulation around the sun gear. For example, according to one such preferred embodiment, the power supply to the drives integrated in the satellites could be via slip rings.

In principle, all embodiments of the first drive integrated in said at least one satellite are possible, this first drive being, for example, a drive configured as a thermodynamic prime mover. It is particularly preferred if the first drive is designed as an electrically variable speed and torque motor, in particular as an electrically driven synchronous motor with an internal rotor part. In the sense of the present invention, alternatively, an electrically variable speed and torque motor can also mean, for example, an asynchronous motor, a synchronous reluctance motor, a cross-flow motor or the like.

Alternatively, within the scope of the present invention, a variant of an electric synchronous motor with an external rotor is also possible, wherein the external rotor of the electric synchronous motor is connected to the satellite wheel without being able to rotate. For example, an outer rotor could be connected to a non-rotating ring gear such that the planet wheel and the outer rotor of an electric synchronous motor lie in the same plane and form a single unit. In this sense, Figs. 5a-5d show a corresponding view.

Preferably, the first drive is an electric drive, respectively, an electric motor, wherein said at least one satellite comprises a fixed stator part, a rotating rotor part, in particular an inner rotor part, and at least one satellite wheel fixed indirectly or directly on the rotor part with external teeth, and this satellite with the planetary carrier is held inside the planetary gear, kinematically interacting with the sun gear and / or a rotating shaft.

It is especially preferred if the planetary gear of the drive according to the invention comprises at least three planets, more preferably three to six planets. By using at least three planet gears, a stable planetary gear structure can be guaranteed. By using more than three satellites, a modular design is advantageously achieved and different power levels can be produced at low cost from a technological point of view. A further advantage is that the high power consumption due to the modular design can be distributed over several stages with lower electrical power, whereby the resulting larger surface area is physically and technologically advantageous in dissipating heat losses from the motor and from the control. The electric drive, additionally distributed over several stages, is even better protected from a complete failure of the common drive in the event of failure of the said second drive, which is made as a thermodynamic prime mover.

In principle, this drive unit according to the invention can only comprise at least one, preferably a plurality of first electric drives, each integrated in the satellites, and can thus be designed as a fully electric drive unit. A further aspect of the present invention concerns, however, a hybrid drive comprising a drive unit according to the invention, wherein the first drive, in particular an electric drive, can be mechanically connected to a second drive configured as a thermodynamic prime mover.

Another aspect of the present invention relates to a rotor aircraft comprising a drive unit according to the invention or a hybrid drive according to the invention.

Preferably said at least one, preferably said plurality of first electric drives, in particular said electric synchronous motor with an internal rotor part, is designed and sized such that the main rotor and/or tail rotor of the main rotor aircraft, in particular, the helicopter can be powered autonomously without additional drive, and thus a rotorcraft with a fully electric drive unit is obtained. In the sense of the present invention, autonomous electric drive is understood to mean that, depending on the dimensions, any mechanical power can be delivered. With regard to the mechanical power of the independent electric drive, preferably at least 150 kW is achieved, more preferably between 200 kW and 700 kW, more preferably between 300 kW and 600 kW, particularly preferably around 600 kW. By way of example, with an electric drive of about 600 kW at a low speed of 371 rpm, a high torque of about 15'500 Nm or more can be obtained.

Preferably, the first, in particular electrical, drive can be mechanically connected to the second drive, designed as a thermodynamic prime mover, in particular due to the fact that the central sun gear can be driven by the second drive unit. Preferably, the second drive assembly may be in mechanical communication with a second drive configured as a thermodynamic prime mover or another electric drive, such as an internal combustion engine, a turbine engine, a positive ignition engine, a diesel engine, a fuel cell drive, or the like. Said at least electric drive and said second drive are connected via a planetary gear so that the electric drive can support the second drive when the main rotor and/or the tail rotor is driven and vice versa, thereby forming a hybrid drive.

Preferably, the shaft or the drive shaft of the drive unit according to the invention is the propeller shaft of the main rotor aircraft according to the invention, this propeller shaft being made in two parts and comprising a support leg and an outer leg, the outer leg being made as a hollow body mounted with the possibility of rotation around the central axis relative to the support column, concentrically surrounding this support column, and moreover, the outer column interacts with the transmission of the helicopter rotor, made as a planetary gear, and the specified support column in an aircraft with a main rotor can be installed permanently and without the possibility of turning, so that said outer strut can be connected in a non-rotatable manner to the main rotor and can be driven by a helicopter rotor transmission configured as a planetary gear.

Thanks to such a composite (two-piece) design of the drive shaft, respectively, the shaft of the screw, a main rotor drive with a particularly high smoothness of operation can be obtained. By such a division into a pedestal and an outer pedestal, the pressure from the rotatable pedestal is received, which is then taken over by the non-rotating part, respectively the pedestal, so that a drive with high running smoothness is obtained. In the future, it has been advantageously found that less cyclic bending occurs during the driving of the main rotor, and therefore less fatigue occurs than with single-piece drive shafts or propeller shafts. In addition, an extremely compact layout can be provided, which, for example, in the hollow space of the support leg, allows cables, control rods to accommodate the swashplate located above the propeller blade coupling device, and other structural parts from the drive side to the main rotor side. For example, electrical supply lines for powering the rotating system, such as de-icers for propeller blades, for lamps in propeller blades, or electrical actuators for a fly-by-wire control system, may also be located here.

According to an alternative preferred embodiment of the rotor aircraft according to the invention, the shaft or the propeller shaft can also be made in one piece (in one piece) and thus can have other advantages, in particular in connection with a particularly simple and compact design. .

Preferably, the drive shaft may be connected to a drive gear in a non-rotating manner, which drive gear may be rotatably supported on a support leg by at least one radial bearing, and by a central sun gear connected to the drive gear without cranking capability, rotation of at least one satellite wheel (in particular, the lower satellite wheel in a two-stage transmission) on the side facing the sun gear of the corresponding planetary carrier around the corresponding axis of the planetary gear is ensured, and at least one satellite wheel (in particular, the upper satellite wheel coordinated with the lower satellite wheel in a two-stage transmission) is covered by a toothed ring with internal teeth rotating around the central axis. Between the gear ring and the outer leg, a gear ring driver can be placed or molded, respectively, acting as a force-transmitting device, so that the rotational movement of the drive gear can drive the outer leg and the rotor associated with the outer leg without the possibility of turning. .

Preferably, in the rotor aircraft according to the invention, the drive unit according to the invention comprises a source of electrical energy, in particular a battery, the first drive being in the form of an electric drive of the hybrid drive according to the invention, in a non-rotatably coupled state between the electric drive and the second drive configured as a thermodynamic prime mover, and during operation of the second drive, said at least one first electric drive, preferably a plurality of first electric drives, can operate as a generator to generate additional power for the battery.

Preferably, in a rotorcraft according to the invention, in particular a helicopter, a rectifier, in particular in the form of a blocking diode, is provided in the first electric drive, so that said storage battery can be charged when the electric drive is not in operation.

Preferably, in a rotorcraft according to the invention, the logic circuit of the control unit is designed in such a way that it further allows automatic mode change between generating torque to drive the propeller and additional energy recovery for the battery.

Preferred embodiments of the subject matter of the invention are described below in connection with the accompanying drawings. The drawings show the following.

1a is a longitudinal sectional view of a first preferred embodiment of the drive unit according to the invention with a two-stage planetary gear as a hybrid variant, in particular for driving the main rotor of a rotorcraft;

Fig. 1b is a plan view of a first preferred embodiment of the drive unit according to the invention with the transmission housing installed;

Fig. 1c is a perspective view of a first preferred embodiment of the drive unit according to the invention without a transmission housing;

Fig. 1d is a perspective view of a first preferred embodiment of a drive unit according to the invention with a transmission housing;

Fig. 2a is a longitudinal sectional view of a second preferred embodiment of the two-stage planetary gear drive unit according to the invention as a hybrid variant with an internal toothed ring with external teeth;

Fig. 2b is a plan view of a second preferred embodiment of the drive unit according to the invention with the transmission housing installed;

2c is a perspective view of a second preferred embodiment of the drive unit according to the invention without a transmission housing;

2d is a perspective view of a second preferred embodiment of the drive unit according to the invention with a transmission housing;

3a is a longitudinal sectional view of a third preferred embodiment of the drive unit according to the invention with a single-stage planetary gear as an all-electric drive option, in particular for driving the main rotor of a rotorcraft;

Fig. 3b is a plan view of a third preferred embodiment of the drive unit according to the invention with the transmission housing installed;

3c is a perspective view of a third preferred embodiment of the drive unit according to the invention without a transmission housing;

3d is a perspective view of a third preferred embodiment of the inventive drive unit with transmission housing;

4a is a longitudinal sectional view of a fourth preferred embodiment of the drive unit according to the invention with a single-stage planetary gear as a variant of a fully electric drive, and with an internal toothed ring with external teeth, in particular for driving the main rotor of an aircraft with a load-bearing screw;

Fig. 4b is a plan view of a fourth preferred embodiment of the drive unit according to the invention with the transmission housing installed;

4c is a perspective view of a fourth preferred embodiment of the drive unit according to the invention without a transmission housing;

4d is a perspective view of a fourth preferred embodiment of the drive unit according to the invention with a transmission housing;

5a is a longitudinal sectional view of a fifth preferred embodiment of the drive unit according to the invention with a single-stage planetary gear as a fully electric drive option and also as an external rotor option;

Fig. 5b is a plan view of a fifth preferred embodiment of the drive unit according to the invention with the transmission housing installed;

5c is a perspective view of a fifth preferred embodiment of the drive unit according to the invention without a transmission housing;

5d is a perspective view of a fifth preferred embodiment of the drive unit according to the invention with a transmission housing;

FIG. 6 is a functional block diagram of the drive power control of the first drives integrated in the satellites of the preferred embodiments of the drive assembly according to the invention.

FIG. 1a shows a longitudinal sectional view along the line A-A (see FIG. 1b) of a first preferred embodiment of the drive unit 1 according to the invention with a multi-stage, here two-stage, planetary gear PI, for example, for driving an aircraft main rotor not shown here apparatus with a rotor (see in this regard, in particular, Fig.3).

Executed here as a two-stage planetary gear PI, the drive unit 1 according to the invention comprises a central sun gear 17 and several planet gears 4 adjacent to the outer teeth of the sun gear 17, not shown here. PI is concentric with sun gear 17 and central z axis. While the satellite 4 includes the lower satellite wheel 6, the upper satellite wheel 6' and connecting the satellite wheels 6; 6' without the possibility of turning the inner rotor part 11 to form two stages here of a two-stage planetary gear PI, as well as the stator part 12.

Shown here, the first preferred embodiment has a shaft 15, which is made of two parts, including a support column 13, as well as an outer column 14. Using the outer column 14, respectively, the shaft 15 can be driven, for example, the main rotor of an aircraft apparatus with a main rotor or a propeller or the like. The drive unit 1 according to the invention, which drives the shaft 15, can be used in a wide variety of technical fields. In other words, this gear or the planetary gear PI of the drive unit according to the invention can also be considered as a torque conversion gear 30 .

At the level, respectively, at the same axial position of the upper satellite wheels 6' is a toothed ring 19, rotating around the central axis z. This toothed ring 19 encloses all of the upper planetary gears 6', can be driven by the rotation of the upper planetary gears 6' and thus rotate around the central axis z. On the gear ring 19 there are internal teeth, not shown here, which engage with the external teeth 5 of the upper satellite wheels 6', not shown here (if they are made, as shown in Fig.1a, in a two-stage form).

The mechanical kinematic interaction between the upper satellite wheels 6' and the external rack 14 rotating around the central axis z is available to drive this outer rack 14 of the specified shaft 15.

In this, the first preferred embodiment, this mechanical interaction is implemented by connected without the possibility of rotation with the outer rack shaft 14 of the driver 20 of the gear ring. In other words, the toothed ring driver 20, which is also located on the toothed ring 19, functions as a force-transmitting device by which the rotation of the toothed ring 19 can be transmitted to the rotatable outer leg 14.

As can be seen in FIG. 1a, a first electric drive 2 is integrated into at least one satellite 4, here in particular an electric synchronous motor 10 with an internal rotor part 11, to form a first drive unit 1, so that the shaft 15 can be driven into rotation by means of the first drive 2. Acting as a stator of the synchronous motor 10, here essentially annular and provided with windings W, the stator part 12 is here placed in the carrier 5 of the planetary gear and is rigidly connected to the carrier 5 of the planetary gear. Working as a rotor of a synchronous motor 10, the rod-shaped inner rotor part 11 is connected without the possibility of turning with the upper and lower satellite wheels 6; 6'. The satellite 4, by means of the carrier 5 inside the planetary gear PI, interacts with the sun gear 17 and the rotating shaft 15, and is held stationary here.

In the electric synchronous motor 10 shown in FIG. 1a, the force of the synchronous motor 10 occurs in the air gap or in the magnetic gap M between the stator part 12 (stator) and the inner rotor part 11 (rotor).

As can be seen in FIG. 1a, a sun gear 17 designed as a hollow shaft is connected to the drive gear 24, this sun gear 17 having external teeth not shown here. The sun gear 17 and the drive gear 24 are mounted on the support column 13 for rotation around the central axis z. By means of the sun gear 17, the satellite wheel 6' can be rotated through the lower satellite wheel 6 about the respective axis P of the satellite wheel.

The drive gear 24 in turn is in communication with at least one drive branch 25 through the gear wheel 26 of the drive branch. Preferably here, this drive branch 25 is in mechanical interaction with another drive TK, not shown here, designed as a thermodynamic prime mover to form a hybrid drive, respectively, a hybrid variant, including the drive unit 1 according to the invention.

Below will be considered as an example the use of a hybrid version, according to the first preferred embodiment of the drive unit 1, to drive the main rotor of an aircraft with a main rotor (moreover, the second to fifth preferred embodiments are just as suitable for driving the main rotor rotorcraft).

In this case, said torque-converting transmission 30 of the drive unit 1 according to the invention can here be considered as a final drive made in the form of a planetary gear PI, respectively, a gear of a helicopter rotor of an aircraft with a main rotor.

Shaft 15, respectively, here the screw shaft is made of two parts, including a support post 13, as well as an outer post 14.

The helicopter propeller transmission has a central hollow space. In this central hollow space, a stationary and non-rotatable support post 13 is installed here. The central axis z simultaneously forms the longitudinal direction of the support post 13 and the axis of rotation of the outer post 14.

Mechanical kinematic interaction between here stationary and mounted with the possibility of rotation around its axis P satellite wheels 6;6' and rotating around the central axis z shaft 15, i.e. here including a support runoff 13, as well as a tubular outer rack 14, covering this support rack 13, is realized due to the fact that these stationary upper satellite wheels 6' are covered by a toothed ring 19 rotating around the central axis z with internal teeth, and this the gear ring 19 rotates so that the outer rack 14 of the specified shaft 15 can be rotated by means of the gear ring 20 fixed on the gear ring 19 and on the outer rack 14.

As can be seen in FIG. 1a, at least one satellite 4 integrates a first electric drive 2, here in particular an electric synchronous motor 10 with an internal rotor part 11, to form a first drive unit 1, so that the outer leg 14 of the shaft 15 can be driven by means of the first drive 2. The stator part 12, working as a stator of the synchronous motor 10, is here placed in the carrier 5 of the planetary gear and is rigidly connected to the carrier of the planetary gear, while the rod-shaped inner rotor part 11, which works as a rotor of the synchronous motor 10, is connected without the possibility of turning with upper and lower satellite wheels 6; 6'.

The first preferred embodiment of the drive unit 1 according to the invention, shown in FIGS. 1a to 1d, suitable for a rotor aircraft or helicopter, has advantages in particular with regard to safety in this application. In the event of a single drive failure in such a multi-engine helicopter, the helicopter must be able to remain powered by the other remaining engines for a predetermined amount of time to bring the helicopter into safe flight and respond to an engine failure.

Preferably, in the first preferred embodiment shown in FIG. 1a, said drive branch 25 is also in mechanical engagement with another drive TK, not shown here, configured as a thermodynamic prime mover, to form a hybrid drive. In this case, in addition to the second drive TK, designed as a thermodynamic prime mover, the first, here electrical, drive 2, as well as the corresponding source of electrical energy, can perform additional mechanical work. Such hybrid-powered helicopters preferably offer an additional safety advantage over twin-engine helicopters powered only by fossil fuels, since, for example, if the fossil fuel supply system fails, they can switch to additional power supply.

By integrating the first drive 2, in particular an electric synchronous motor, into the satellites 4, an extremely compact hybrid drive for a twin-engine helicopter (eg in the sense of a helicopter of a different type) is obtained.

As can be seen in Fig. 1a, the support leg is designed here as a hollow body, so that structural parts, such as control rods for accommodating the swashplate located above the blade coupling device and/or cable management, can be located passing through in the direction of the central axis z through the support post 13 and the outer post 14. For example, here too, electrical supply lines for power supply can be placed on the rotating system, for example de-icers for the propeller blades, lamps in the propeller blades, or electrical actuators for the fly-by-wire control system.

From this point onwards, like reference numerals in the drawings refer to like components.

1b shows a plan view of a first preferred embodiment of the drive unit 1 according to the invention with the transmission housing G installed.

FIG. 1c shows a perspective view of a first preferred embodiment of the drive unit 1 according to the invention without a housing or with the housing removed. The first preferred embodiment shown in FIG. 1c here has four satellites 4 as an example.

FIG. 1d shows a perspective view of a first preferred embodiment of the drive unit 1 according to the invention with housing G. The drive unit 1 comprises a control unit ST, which is designed to synchronize the first drives 2 integrated in the satellites 4 with each other. This synchronization integrated into the satellites 4 of the first drives 2 is shown more precisely in Fig.6.

Further, these planet-integrated drives 2 can be configured to be mechanically, electrically or hydraulically disconnected from each other by means of a suitable clutch, not shown here, in order to prevent possible transmission blockage due to incorrect operation of one or more drives.

Further, according to Fig. 1d, said drive assembly 1 comprises a source of electrical energy, in particular the battery BS shown here, and wherein the first drive 2 here is in the form of an electric drive of said hybrid drive in a non-rotatably connected state between the first, here electric, drive 2 and a second drive TK, designed as a thermodynamic prime mover. During operation of the second drive TK, the first, here electrical, drive 2 can operate as a generator and provide additional energy recovery (generation) for the storage battery BS.

Preferably, in the first, in particular electric, drive 2, in particular in an electric synchronous motor with an internal rotor part 11, a rectifier is provided, in particular in the form of a blocking diode, whereby the storage battery BS can be charged when the electric drive is not in operation.

In addition, the control unit ST may be further provided with a logic circuit that enables automatic mode changeover between torque generation for driving the main rotor and additional energy recovery for the storage battery BS.

The first preferred embodiment shown in FIGS. 1a-1d, in other words the hybrid variant, includes the drive unit 1 according to the invention. By making the planetary gear PI two-stage, an optimum high gear ratio can preferably be set, while at the same time the advantages of a hybrid drive are achieved (for example , safety advantages when used in an aircraft with a main rotor).

According to one preferred modification of the present invention, this planetary gear can also be made more than two-stage, for example, three-stage, etc.

Fig. 2a shows a longitudinal sectional view along the line A-A (see Fig. 2b) of a second preferred embodiment of the drive unit 1 according to the invention with a two-stage planetary gear PI as a hybrid variant with an internal gear ring 18 with external teeth.

Executed here as a two-stage planetary gear PI, the drive unit 1 according to the invention comprises a central sun gear 17 and several planet gears 4 adjacent to the outer teeth of the sun gear 17, not shown here, and enclosing the sun gear 17, the pinion gears 4 being located inside the planetary gear PI concentric to the sun gear 17 and the central z axis.

As shown in Fig.2a, located inside, provided with external teeth, and also connected to the outer rack 14 without the possibility of rotation, the toothed ring 18 is here covered by the upper satellite wheels 6' and can be actuated in the same way due to the rotation of the upper satellite wheels 6' , and thus can be rotated about the central axis z and driven together with the outer leg 14. On the gear ring 18 there are external teeth, not shown here, which engage with the external teeth of the upper satellite wheels 6', not shown.

FIG. 2b shows a plan view of a second preferred embodiment of the drive unit 1 according to the invention with the transmission housing G installed.

Fig. 2c shows a perspective view of a second preferred embodiment of the drive unit according to the invention without a transmission housing.

Fig. 2d shows a perspective view of a second preferred embodiment of the drive unit according to the invention with a transmission housing G.

Fig. 3a shows a longitudinal sectional view along the line A-A (see Fig. 3b) of a third preferred embodiment of the drive unit 1 according to the invention with a single-stage planetary gear PI, for example, for driving the main rotor of a main-rotor aircraft shown here.

As can be seen in FIG. 3a, the third preferred embodiment shown here omits the sun gear (as in the fourth preferred embodiment shown in FIGS. 4a-4d and respectively in the fifth preferred embodiment shown in FIGS. 5a-5d), which therefore corresponds to a gear similar to the PI planetary gear. This possible elimination of the sun gear has the advantage of reducing weight as well as reducing design complexity.

The use of such a single-stage planetary gear PI has the advantage that, in the third preferred embodiment shown here, it is not necessary to accommodate any outer gear housing G extending over two stages, and thereby integrated into the planetary gear 4, the first one, here embodied as an electric synchronous motor 10 s the inner rotor part 11 drive 2 can be better cooled. In particular, up to a certain power, the heat loss can be small enough to eliminate the liquid cooling circuit and therefore no liquid cooling is required, i.e. the existing air cooling by means of the ambient air around the satellites 4 already causes sufficient cooling. In addition, it turned out that with a modular design of an electric drive for several stages with low electric power, the indicated power without the necessary liquid cooling is higher than with a single, electric drive.

3b shows a top view of a third preferred embodiment of the drive unit according to the invention with the transmission housing G installed.

FIG. 3c shows a perspective view of a third preferred embodiment of the drive unit 1 according to the invention without a housing or with the housing removed. The third preferred embodiment shown here has six satellites 4 as an example.

Fig. 3d shows a perspective view of a third preferred embodiment of the drive unit 1 according to the invention with a transmission housing G.

Figures 3a-3d, referring to the third preferred embodiment with a single-stage PI planetary gear, show an all-electric version of the drive unit 1 according to the invention, and a hybrid version is also possible, including a drive unit 1 designed as a single-stage PI planetary gear. By single-stage planetary gear PI is meant that the planetary gears 4 only include the upper planetary gear 6' and thus have only one stage.

In principle, an even simpler embodiment of the drive according to the invention is also possible, whereby the torque can be transmitted not through the toothed ring 19 with internal teeth, but through the toothed ring 18, provided with external teeth (see Fig.2a-2d, respectively, Fig. .4a-4d).

4a shows a longitudinal sectional view of a fourth preferred embodiment of the drive unit 1 according to the invention with a single-stage planetary gear as an all-electric drive option, and with an internal toothed ring provided with external teeth, in particular for driving the main rotor aircraft with a main rotor.

As shown in Fig.4a, here the gear ring 18, located inside and provided with external teeth, and also connected to the outer rack 14 without the possibility of rotation, is covered by the upper satellite wheels 6' and can also be driven by the rotation of these upper satellite wheels 6 ' and rotate together with the outer column 14 around the central axis z.

4b shows a top view of a fourth preferred embodiment of the drive unit according to the invention with the transmission housing G installed.

Fig. 4c shows a perspective view of a fourth preferred embodiment of the drive unit according to the invention without a transmission housing.

4d shows a perspective view of a fourth preferred embodiment of the drive unit according to the invention with a transmission housing G.

Fig. 5a shows a longitudinal sectional view along the line A-A (see Fig. 5b) of a fifth preferred embodiment of the drive unit 1 according to the invention with a single-stage planetary gear PI as an all-electric drive option and also as an external rotor option.

As can be seen in Fig. 5a, at least one satellite 4 is integrated with the first, here an electric drive 2, here in particular an electric synchronous motor 10 with an external rotor part 16 to form the first drive unit 1.

Working as a stator of the synchronous motor 10, here, essentially an annular and equipped with windings W, the fixed stator part 12 is placed here in the rod-like element S and is rigidly connected to this rod-like element S, while here, working as the rotor of the synchronous motor 10, the outer rotor part 16 of the electric synchronous motor is connected here without the possibility of turning with the satellite wheel 6. The satellite wheel 6 and the outer rotor part 16 of the electric synchronous motor 10 lie here in the same plane, respectively, in the same axial position and form essentially a single block.

As can be seen in FIG. 5a, here the stationary satellite wheels 6' of the satellites 4 are, on the one hand, surrounded by an internally toothed ring 19 rotating around a central axis z and, on the other hand, an internally located, externally toothed toothed ring 18 is surrounded by satellite wheels 6', and with the help of a toothed ring 19 with internal teeth, an external rack 14 (not shown here) can be driven (see Fig. 5b), and with the help of a toothed ring 18 located inside, provided with external teeth, another can be driven, not shown here, the central drive shaft (see Fig. 5b). In other words, according to the fifth preferred embodiment, the two shafts can be driven with different gear ratios. In addition, in Fig.5a it is indicated that in the case of one here also possible implementation of a hybrid variant, said toothed ring 18 provided with external teeth can work as a sun gear 17.

FIG. 5b shows a plan view of a fifth preferred embodiment of the drive unit 1 according to the invention with the transmission housing G installed and also in kinematic engagement with the outer pillar 14, respectively, with the central drive shaft 27. As can be seen in FIG. 5b, the toothed ring 19 with internal teeth can, through a plurality of connecting elements V, be in kinematic interaction with the outer rack 14, respectively, with the shaft 15. Alternatively or additionally provided with external teeth, the toothed ring 18, respectively, the sun gear 17 can be in kinematic interaction through a plurality of connecting elements V with a central drive shaft 27, in particular as an embodiment of a hybrid drive.

Further, in Fig. 5b it is shown that in the case of a non-hybrid or all-electric drive, in the sense of another preferred modification, the internal toothed ring 18 provided with external teeth can be in kinematic engagement with the outer strut.

Fig. 5c shows a perspective view of a fifth preferred embodiment of the drive unit 1 according to the invention without the transmission housing, central drive shaft and outer strut. As shown in FIG. 5c, the planetary carrier 5 is here non-rotatable and permanently connected to the bottom element B, which functions as a support leg 13, via the consoles 9. In addition, here the support leg 13 comprises a centrally located, coaxial to the central axis z, tubular element R for another shaft fixed on the gear ring 18.

In addition, in Fig.5c it can be seen that here the carrier 5 of the planetary gear is made as a single continuous, essentially annular structural part, in which the satellites 4 are permanently held.

FIG. 5d shows a perspective view of a fifth preferred embodiment of the drive unit 1 according to the invention with a transmission housing G, however, without a central drive shaft and without an outer strut. As can be seen in Fig. 5d, here the consoles 9 simultaneously serve to secure the transmission housing G.

The fifth preferred embodiment of the drive unit 1 according to the invention, shown in FIGS. 5a-5d, has a particularly compact design, in which the accommodating, rotating outer leg 14 can be shortened by an externally toothed toothed ring 18 or by an internally toothed toothed ring 19 in this manner. that it can be placed essentially in the same axial position as the satellites 4. In the case of an application for an aircraft with a main rotor, the drive unit 1 could in principle be placed directly in the plane of the screw.

6 shows a functional block diagram of the drive power control of the first drives 2 integrated into the satellites P.

As shown by way of example in Fig. 1d, Fig. 2d, Fig. 3d, Fig. 4d and Fig. 5d, said drive unit 1 comprises a control unit ST, which is designed in such a way that it can be operated with each other and synchronized with each other. other integrated in the satellites P the first drives 2.

In the sense of the present invention, this control is implemented as a standard control for electric synchronous motors 10 with control logic and a power electronics unit LEE (here also referred to as "inverter"). This control logic (herein also referred to as "motor controller") generates appropriate signals that control the inverter, which then energizes the appropriate windings of the electric synchronous motor 10 to ensure continuous rotation at a given frequency and torque. Synchronization of electric synchronous motors 10 is possible by determining the position and speed of rotation of the armature, and for each electric synchronous motor 10 individually by calculating the control signals.

List of reference positions

1 drive unit

2 first drive

4 satellite

5 planet carrier

6; 6' lower/upper satellite wheel

7 electrical supply lines

9 consoles (for fixing planet carrier 5 on G gear housing)

10 electric synchronous motor

11 internal rotor part (electric synchronous motor)

12 stator part

13 support post

14 outdoor rack

15 shaft

16 external rotor part (electric synchronous motor)

17 sun gear

18 (located inside, equipped with external teeth) toothed ring

19 (located outside, equipped with internal teeth) toothed ring

20 gear ring leash

24 central drive gear

25 drive branch

26 gear drive branch

27 central drive shaft

30 torque converter gearbox

B bottom element

BS battery

G transmission housing

M magnetic gap

P axle of satellite wheel

PI planetary gear

R tubular element

S rod element

ST control unit

TK second drive designed as a thermodynamic prime mover

V connectors

W winding (stator part)

Claims (16)

1. Drive unit (1), in particular for driving the main rotor of an aircraft with a main rotor, comprising: planetary gear (PI), and this planetary gear (PI) includes several satellites (4), and each satellite (4) has at least one satellite wheel (6;6') with teeth, and these satellites (4) located inside the planetary gear (PI) concentric with the central axis (z), so that the rotatable shaft (15), in particular the propeller shaft of an aircraft with a main rotor, is made with the possibility of being driven by means of satellites (4) or sun gear (17) , characterized in that the first drive (2), in particular an electric drive, is integrated into at least one satellite (4), whereby an internal drive is formed inside the planetary gear (PI), so that said shaft (15) is made capable of being driven by the first drive ( 2). 2. The drive unit (1), in particular for driving the main rotor of a rotorcraft according to claim 1, characterized in that the first drive (2) is designed as an electric motor adjustable in speed and torque, in in particular as an electric synchronous motor (10) with an internal rotor part (11). 3. The drive unit (1), in particular for driving the main rotor of an aircraft with a main rotor, according to claim 1 or 2, characterized in that the first drive (2) is an electric drive, and said at least one satellite (4) contains a fixed stator part (12), a rotating rotor part, and at least one satellite wheel (6; 6') with external teeth fixed indirectly or directly on the rotor part, and this satellite (4) with the help of a carrier ( 5) planetary gear inside the planetary gear (PI) kinematically interacts with the sun gear (17) and/or with the rotating shaft (15). 4. Drive unit (1), in particular, for driving the main rotor of an aircraft with a main rotor, according to any of the previous paragraphs, characterized in that the satellite wheels (6; 6') are installed permanently and rotatable around their axes (P) of the satellite wheel, and that these stationary satellite wheels (6;6') are surrounded by a toothed ring (19) rotating around the central axis (z) with internal teeth, and / or located inside, equipped with external teeth, the toothed ring (18) is covered lower and/or upper satellite wheels (6;6'), and this toothed ring (19) and/or toothed ring (18) provided with external teeth is rotatable in such a way that the shaft (15), in particular the propeller shaft, can be driven by means of a gear ring fixed on the gear ring (19) and on the shaft (15), in particular on the screw shaft, the driver (20), and / or the shaft (15), in particular the screw shaft, can be driven by means of a toothed ring (18) provided with external teeth. 5. A hybrid drive comprising a drive unit (1) according to any one of the preceding claims, wherein the first, in particular electric drive (2) is mechanically connected to a second drive (TK) configured as a thermodynamic prime mover or as another electric drive, and outside the planetary gear (PI). 6. An aircraft with a main rotor, containing a drive unit according to any one of claims 1 to 4 or a hybrid drive according to claim 5. 7. An aircraft with a main rotor according to claim 6, characterized in that said at least one, preferably a plurality of first electric drives (2) are designed in such a way that the main rotor and/or tail rotor of the aircraft with a main rotor, in particular helicopter, can be driven autonomously without additional drive. 8. An aircraft with a main rotor with a hybrid drive (1) according to claim 6 or 7, characterized in that the first, in particular the electric drive (2) can be mechanically connected to the second, designed as a thermodynamic prime mover drive (TK), in particular, due to the fact that the central sun gear (17) can be driven by a second drive unit, and that this second drive unit is connected to a second drive (TK) designed as a thermodynamic prime mover and is in mechanical interaction, for example , with an internal combustion engine, a turbine engine, a positive ignition engine, a diesel engine or a fuel cell drive, so that said at least one first, in particular electric, drive (2) and said second drive (TK) are connected via a planetary gear (PI ), said electrical drive (2) can support the second drive (TK) when the main rotor and/or the tail rotor is driven and vice versa, thereby forming a hybrid drive. 9. An aircraft with a main rotor, in particular a helicopter, according to any one of claims 6 to 8, characterized in that the shaft (15) is a propeller shaft of an aircraft with a main rotor, and this propeller shaft is made of two parts and includes the support post (13), as well as the outer post (14), wherein the outer post (14) is made as a hollow body mounted with the possibility of rotation around the central axis (Z) relative to the support post (13), concentrically surrounding the support post (13) , and moreover, the outer strut (14) is configured to interact with the helicopter rotor gear, made as a planetary gear (PI), moreover, the support strut (13) can be installed permanently and without the possibility of turning in an aircraft with a main rotor, so that the outer strut ( 14) can be non-rotatably connected to the main rotor and can be driven by a helicopter propeller gear designed as a planetary gear (PI). 10. An aircraft with a main rotor, in particular a helicopter, according to claim 9, characterized in that the shaft, in particular the propeller shaft, can be connected to the drive gear (24) without the possibility of turning, and the drive gear (24) can be rotatably mounted on a support leg (13) by means of at least one radial bearing, and by means of a central sun gear (17) connected to the drive gear (24) without the possibility of rotation, rotation of at least one lower satellite wheel can be provided (6) on the side of the corresponding planetary carrier (5) facing the drive gear (24) around the corresponding axis (P) of the satellite wheel, and at least one related to the specified at least one lower satellite wheel (6), the permanently mounted upper satellite wheel (6') is surrounded by a toothed ring (19) with internal teeth rotating around the central axis (Z), and between the toothed ring (19) and the outer rack (14) a driver operating as a force-transmitting device ( 20) of the gear ring in such a way that from the rotational movement of the drive gear (24) the outer rack (14) and the main rotor associated with the outer rack (14) can be rotated without the possibility of turning. 11. An aircraft with a main rotor, in particular a helicopter, according to any one of claims 6 to 10, characterized in that the drive unit (1) contains a source of electrical energy, in particular a battery (BS), and wherein the first drive is in the form the electric drive (2) of said hybrid drive in a non-rotatable state between the first, in particular electric, drive (2) and the second drive (TK) made as a thermodynamic prime mover, and during operation of this second drive (TK) said first, the electric drive (2) can work as a generator for additional energy recovery for the storage battery (BS). 12. An aircraft with a main rotor, in particular a helicopter, according to claim 11, characterized in that a rectifier is provided in the first electric drive (2), in particular in the form of a blocking diode, due to which, in the idle mode of the electric drive (2), the battery battery (BS) can be charged. 13. An aircraft with a main rotor, in particular a helicopter, according to claim 11 or 12, characterized in that the logic circuit of the control unit (ST) provides an automatic change of mode between the generation of torque to drive the propeller and additional energy recovery for the battery (BS).

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