AT517540B1 - FLIGHT UNIT - Google Patents

Abstract

Aircraft with at least two main rotors (11, 12) arranged coaxially with one another and at least two drive devices (7, 8, 20, 21), wherein the aircraft further comprises • a middle part (1) for accommodating persons and freight, to which middle part (1 ) connect the at least two drive devices (7, 8), • a disc-shaped platform (4), which surrounds the middle part (1) at least in sections and is firmly connected thereto, • two magnetically, and preferably non-contact, on the middle part (1) mounted rotor disks (5, 6) on whose insides the main rotors (11, 12) are adjustably mounted, which rotor disks (5, 6) are arranged on both sides of and parallel to the platform (4), • rotor openings (22, 23) the rotor disks (5, 6) for the inlet and outlet of air; platform openings (13, 14) for receiving the air discharged through the rotor openings (22, 23) into the interior of the platform, and at least four with the platform m connected ejection nozzles (15) for discharging from the rotor discs (5,6) in the platform (4) inflowing air to the environment, • wherein the rotor discs (5,6) by means of the drive means are driven in opposite directions rotationally.

Description

description

FLIGHT UNIT

FIELD OF THE INVENTION

The invention relates to an aircraft with at least two coaxially arranged main rotors and at least two drive means.

STATE OF THE ART

Aircraft of various designs are well known in the art and are referred to by the collective term "aircraft". Aircraft heavier than air are subdivided into power-driven (such as airplanes and rotorcraft) and non-propelled aircraft, with essentially only powered aircraft being used to transport people and goods.

In aircraft, the required buoyancy is usually generated when flying by forward movement in the air, with wings cause a dynamic buoyancy. In rotary-wing aircraft this lift (and in helicopters also the propulsion force) is effected by at least one rotor rotating about a vertical axis.

Representatives of these two aircraft variants require for their operation fuel-powered engines (usually in the form of gas turbine engines) - in aircraft usually jet engines cause the necessary for the forward thrust and helicopters, the rotor is nowadays usually by means of a wave engine in rotational motion.

Since the fuel consumption of a helicopter with the same load on the flight path is usually well above that of a wing aircraft, are used in passenger and freight transport - especially at greater distances - mainly aircraft.

As undeniable as the high level of comfort that traveling by plane brings with it, is the fact that air traffic is considered today as climate-damaging transport sector at all. According to the European Environment Agency (EEA), car and air traffic worldwide contribute 21 percent to the production of greenhouse gases. In the EU countries, air traffic alone increased by 96 per cent between 1990 and 2003.

Not only in terms of climate protection alternative concepts in aviation are in demand, but also against the background of the inevitable and imminent closing of the sources of fossil fuels. For example, a four-jet 400-ton jumbo jet on a flight from Toronto to Frankfurt consumes around 150,000 liters of kerosene. In general, neither climate protection nor energy saving is an important concern of aviation research and development.

Also occur in the operation of aircraft dissipative effects, which cause a considerable part of the energy supplied in the form of heat is released to the environment and thus lost.

OBJECT OF THE INVENTION

It is therefore an object of the subject invention to provide an alternative aircraft, which avoids at least a portion of the dissipative effects occurring during flight or uses for energy.

PRESENTATION OF THE INVENTION

This object is achieved in an aircraft according to the invention with at least two coaxially arranged main rotors and at least two drive means, characterized in that the aircraft also has a central part for accommodating persons and freight, at which central part connect the at least two drive means, a disc-shaped Platform, which surrounds the middle part at least in sections and is fixedly connected to it, two magnetically, and preferably non-contact, mounted on the central part rotor disks, on whose inner sides the main rotors are adjustably mounted, which rotor disks are arranged on both sides of and parallel to the platform, Rotor openings of the rotor disks for the inlet and outlet of air, platform openings for receiving the air discharged through the rotor openings into the interior of the platform, and at least four ejector nozzles connected to the platform for discharging from the ro Door discs in the platform inflowing air to the environment comprises, wherein the rotor disks are driven in rotation by means of the drive means in opposite directions.

It is provided in the middle part space for accommodating people and cargo. In addition, this center section also houses instruments needed to operate and control the aircraft, as well as control equipment and the cockpit. The adjoining the center part drive means drive on both sides of and parallel to the platform mounted rotor disks in opposite directions to rotate. Since these rotor disks are mounted magnetically, and preferably without contact, on the middle part, no energy is lost in the form of friction between rotor disks and the bearing of the rotor disks at the middle part. Also, this type of storage avoids the danger of a resonance disaster. The main rotors of the aircraft arranged in the interior of the two rotor disks in each case adjoining the platform serve, on the one hand, to draw in air via the rotor openings arranged on the outer sides of the rotor disks, preferably in the form of boundary layer suction, into the interior of the rotor disks and to discharge this air the platform via the provided for receiving the air platform openings, and on the other hand to generate buoyancy by rotation. The air drawn in from the outside can be discharged to the environment in the horizontal movement of the aircraft to generate thrust by means of the ejection nozzles.

In a preferred embodiment of the aircraft, it is provided that at least one upper and one lower air conveyor flap is arranged on the outer side of each of the two rotor disks, which at least one upper and lower air conveyor flap are controllable off and folded.

At low to medium rotational speeds of the two rotor discs and low altitude, the at least two air conveyor flaps, depending on their current position relative to the direction of movement of the aircraft, be expanded to produce additional propulsion in the direction of movement. This is preferably done periodically at each individual revolution of the two rotor disks. Thus, the unfolded air conveyor flaps produce no thrust in the direction of movement of the aircraft in the opposite direction, they are folded at the appropriate position relative to the direction of movement of the aircraft again.

In a further preferred embodiment of the aircraft according to the invention, it is provided that each of the two rotor disks comprises a drive device, which as the first magnetic drive and / or second magnetic drive, which first and second magnetic drive in each case an electromagnetic support, guidance and drive system comprises, is executed.

The magnetic drives are thus even part of the lower or upper rotor disk and are powered by - described in more detail below - battery blocks with power. In this case, the first magnetic drive of the upper or lower rotor disk is preferably arranged on an inner side of the upper or lower rotor disk directed in the opposite direction to the middle part and serves primarily for the counter-rotating drive of the two rotor disks. The second magnetic drive is preferably arranged along a circumferentially extending in the outer region of the upper and lower rotor disk along the radial direction and serves in normal operation of the aircraft primarily for the storage of the rotor disks on the platform. In case of failure or malfunction or if necessary, however, the second magnetic drive can act as an emergency drive or as an additional drive.

To store the rotor disks particularly stable, cost and energy efficient at the central part or on the platform, it provides a further preferred embodiment of the aircraft according to the invention, that the rotor disks are magnetically supported by the first magnetic drive to the central part and by means of the second magnetic drive are magnetically mounted on the platform.

In order to enable a non-contact, yet stable magnetic bearing of the rotor disks on the central part or on the platform, the effect of the support and guiding system based on the principle of electromagnetic (EMS) or electrodynamic (EDS) levitation.

In a further preferred embodiment of the aircraft according to the invention, it is provided that at least four mutually paired, radially movably held battery blocks are arranged in each rotor disk to supply the magnetic drives with power.

In addition to the immediately obvious function of supplying the magnetic drives with power, the battery blocks still fulfill the important task of balancing the upper and lower rotor disk. For this purpose, they are held radially movable within the respective rotor disk, wherein their movement is induced on the one hand by the rotation of the rotor disks and on the other hand can also be controlled separately, so that any imbalance resulting from inhomogeneous mass distribution within the upper or lower rotor disk can be compensated. It may also be provided that for short-term storage of excess energy flywheels are arranged on the battery blocks.

Therefore, it is provided in a further preferred embodiment of the aircraft according to the invention, that the at least four battery blocks in the interior of the rotor disk are arranged to be movable radially outwardly extending magnetic struts.

As a result, a simple and reliable control of the movement of the arranged on the magnetic struts battery blocks is possible. At the same time, these magnetic struts can also fulfill a structuring function within the upper or lower rotor disk.

In a further preferred embodiment of the aircraft according to the invention it is provided that the at least four battery blocks each comprise at least one battery, preferably a plurality of batteries, and a linear generator, which linear generator is designed such that it can control the kinetic energy of the controllable outwardly moving battery blocks converted into electrical energy and this supplies the battery or the batteries.

As a result, due to the rotational movement of the upper and lower rotor disk on the magnetic struts radially outwardly moving battery blocks braked and their braking energy - as in magnetic levitation already common - converted into electrical energy and used to recharge the batteries.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the at least two drive means are separately operable to control the opposite rotational movement of the two rotor discs separately.

As with helicopters with two coaxial rotors also, the torques generated by the rotation of the two rotor discs cancel each other at the same speed of the two rotor discs, whereby both the middle part and the platform firmly connected to the middle platform no rotation around the Yaw axis of the aircraft. On the other hand, a yawing of the aircraft can be specifically caused by different speeds of the upper and lower rotor disk.

In a further preferred embodiment of the aircraft according to the invention, it is provided that each rotor blade of the main rotors is held about its longitudinal axis rotatably in the rotor discs.

The position of each rotor blade can be adjusted separately, preferably electronically, whereby essentially two purposes are met. Firstly, it is possible to change the position of all the rotor blades of one or both main rotors together and thus to regulate the lift caused by the main rotors. Secondly, by cyclic or non-uniform rotor blade adjustment, the change in the buoyancy in a certain portion of a rotor circuit surface can be caused, resulting in a tilting of the aircraft and this changes its direction of movement.

In particular, at the transition from the vertical movement in the horizontal movement of the aircraft according to the invention an adjustability of the orientation of all rotor blades of the arranged in the lower rotor main rotor is essential, since in horizontal flight movement of the dynamic buoyancy generated primarily on the functioning as a rotor surface rotor disks and the main rotors from this point onwards - as described below - are primarily there to first scoop large air masses into the rotor disks and subsequently into the platform.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the two rotor disks in each case one of the platform near the rotor region, in each of which one of the main rotors is arranged, a subsequent to the rotor region flow area, in which the magnet struts together Battery blocks are arranged and which flow area is flowed through by the sucked by the rotor movement via the rotor openings air, and have a radially outside the rotor area arranged edge tip area.

In this case, each of a rotor rotor housing a region of the upper and lower rotor disk, which is closest to the platform. In this area, apart from the rotor blades, no further elements are arranged. The high rotational speed of the main rotors already causes a compression of the air sucked in via the rotor openings in the rotor area.

The adjoining the rotor region and arranged between this and the curved rotor disk outer surface flow area of the upper and lower rotor disk has arranged on the magnetic struts battery blocks includes - described later - air and water pipes and any power and control lines, and is flowed through by the intake via the respective main rotor air, which is also used for cooling the battery blocks and the first and / or second magnetic drive.

The edge tip region is located on the peripheral outer surface of the respective rotor disk and is strongly heated due to the high temperature caused by friction at this peripheral outer surface. This high temperature in the edge tip region can - as described below - also be used for energy.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the edge tip region has a first chamber and a second chamber, wherein the first chamber is used to collect water from the environment, and the second chamber directly to the inside of the rotor disk connects and is connected via a valve to the first chamber.

According to the invention it is provided that when flying through clouds or areas with high humidity moisture in the form of water droplets can enter together with the intake air through the rotor openings first in the flow area and then in the rotor area of the upper and lower rotor disk. Due to the centrifugal force, the collected water passes into the first chamber of the edge tip region, where it is collected and can pass further into the second chamber through negative pressure arising in the second chamber. The number of existing chambers is not necessarily limited to two chambers. So something can consist of the first chamber itself from a variety of chambers.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the two rotor disks each have a capillary tube system, which capillary tube system is connected to the second chamber, along the outer surfaces of the rotor disk in the direction of central part and opens into the flow area of the rotor disk.

Water which has entered the second chamber of the edge tip region, after having been heated by the high temperature prevailing in the edge tip region, can be utilized by means of the capillary tube system to heat the curved outer surface of the respective rotor disk and then reintroduced into the throughflow region of the rotor disk become.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the second chamber is divided into a plurality, preferably eight, separate sections, each section having a discharge valve for delivering water vapor to the environment.

These discharge valves can either be arranged freely and independently of one another pivotably or substantially tangentially to the peripheral outer surface of the respective rotor disk. Optionally, a portion of the highly heated water in the form of water vapor can be delivered to the environment via the pivotable discharge valves - both to generate propulsion and to increase / decrease the rotational speed of the respective rotor disk. According to the invention, a part of these discharge valves can also be used to increase / reduce the rotational speed of the rotor disks, while the remaining discharge valves are each aligned so that they can be used to generate propulsion.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the edge tip region has at least one thermoelectric generator, preferably a plurality of thermoelectric generators, to charge the batteries with the current generated by the / the thermoelectric generator / thermoelectric generators ,

Due to the friction between the air surrounding the aircraft and the peripheral outer surface of the rotating rotor disk, there is great heat development in the edge tip region of the rotor disk. With the help of thermocouples whose reference junction is in each case arranged, for example, in the flow area of the rotor disk and whose measuring point is arranged in each case in the edge tip region of the rotor disk, the invention provides that this heat is converted into electrical energy. As a result, such a thermocouple acts as a thermoelectric generator. Several such thermal generators can be connected in series to increase the efficiency of a thermopile. The recovered electrical energy can be used to recharge the batteries.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the surface of at least one rotor disk is at least partially covered with solar cells to charge the batteries with the electricity generated by the solar cells.

This is another way to extend the maximum possible flight time. The electrical energy generated by the solar cells can be returned to the batteries and thus used for recharging. The arrangement of the solar cells on the surface of the at least one rotor disk must be done in coordination with the rotor openings and the aerodynamic requirements, which are set by the function as a supporting surface in horizontal locomotion to the rotor disk. In a further preferred embodiment of the aircraft according to the invention, it is provided that the platform has at least one receiving volume, preferably a plurality of separate receiving volumes, which / which receiving volume / receiving volumes for air on the platform openings is accessible.

By the rotating main rotors air from the environment of the aircraft via the rotor openings in the platform facing away from the outer surfaces of the rotor disks is first passed into the interior of the rotor disks and then into the receiving volume of the platform. To generate propulsion, this air can subsequently be discharged back to the environment by means of the ejection nozzles.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the at least one receiving volume means for compression and / or combustion of the air, which is located in the receiving volume has.

To generate thrust or propulsion, it may be provided according to the invention that air, which is conveyed by means of the main rotors first into the interior of the rotor disks and subsequently into the at least one receiving volume of the platform, compressed and after injection of fuel ( Kerosene) - burned before it is discharged through the ejection nozzles. The means for compression can be designed as low-pressure compressor and / or high-pressure compressor, which may each consist of a plurality of successively arranged paddle wheels. As known from gas turbine engines of the prior art, the compressed air streams are thereby passed through at least one combustion chamber, where it is mixed with a spray and ignited. The compressors can be driven by a turbine stage connected downstream of the combustion chamber. Finally, the hot gas mixture can be discharged by means of the ejection nozzles to the environment and thereby thrust or propulsion are generated.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the platform openings and / or the rotor openings can be closed and opened separately.

As a result, on the one hand, the amount of air sucked in via the rotor openings can be regulated, and, on the other hand, the aerodynamic behavior of the aircraft can be changed.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the at least four ejection nozzles are separately aligned.

As a result, the ejection direction of the air discharged by means of the ejection nozzles to the surroundings can be changed and thus the direction of the resulting thrust force can be influenced. In this way, the aircraft can also be rotated about its roll axis and about its tilt axis.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the rotor disks each comprise at least one airbag, preferably a plurality of airbags, which fill the flow area and / or the rotor area of the rotor disks in an operating state of the airbags.

To protect the persons and goods that may be located in the central part of the aircraft, these inventively provided airbags can fill in an emergency both the flow area and the rotor portion of the two rotor discs at least in sections.

In a further preferred embodiment of the aircraft according to the invention, it is provided that the two rotor disks for generating a dynamic buoyancy when moving the aircraft in a direction which is substantially parallel to the plane of the rotor disks, have different curvatures.

Characterized in that the outer side of the upper rotor disk is more curved than the outer side of the lower rotor disk, the two rotor disks act together as the wing of the aircraft and generate in its movement in a direction parallel to the plane of the platform, dynamic buoyancy.

BRIEF DESCRIPTION OF THE FIGURES

The invention will now be explained in more detail with reference to an embodiment. The drawings are exemplary and are intended to illustrate the inventive idea, but in no way restrict it or even reproduce it. 1 shows a schematic sectional view of the aircraft FIG. 2 shows detail A from FIG. 1 FIG. 3 shows detail B from FIG. 1 FIG. 4 shows detail C from FIG. 3 with upper air-conveying flap 16 folded in. FIG. 5 Detail C from FIG. 3 with upper air-conveying flap 16 unfolded FIG. 6 is a schematic plan view of upper rotor disk 5, wherein the upper outer surface of upper rotor disk 5 is not shown. [0062] FIG. 7 shows a schematic representation of the mode of operation of the air conveyor flaps 16, 17

WAYS OF CARRYING OUT THE INVENTION ACCORDING TO A CONCRETE EMBODIMENT

Fig. 1 shows a schematic view of the aircraft according to the invention. The horizontal sectional plane of the view in this case runs centrally through a central part 1, a landing leg 2, a platform 4, as well as through an upper 5 and a lower rotor disk 6.

The middle part 1 is designed approximately spherical in the concrete embodiment, wherein it is flattened in the region of its lower hemisphere. The Landebein 2 connects to this area. The platform 4 connects directly to the middle part 1, is connected to this stationary and surrounds the middle part 1 in sections. The middle part 1 has a viewing dome 3 in its upper hemisphere.

Above the platform 4, the upper rotor disk 5, below the platform 4, the lower rotor disk 6 is arranged. The two rotor disks 5, 6 surround the middle part in sections on all sides. The upper rotor disk 5 is mounted on the central part 1 by means of a first magnetic drive 7 of the upper rotor disk 5, the lower rotor disk 6 by means of a first magnetic drive 8 of the lower rotor disk 6.

In the specific embodiment, a battery block 9, 10 of the upper 5 and the lower rotor disk 6 are arranged on each side of the central part 1 in each of the two rotor disks 5, 6 respectively. The battery blocks 9, 10 are arranged displaceably on a respective one of a central region 36 (see Fig. 6) to an edge tip portion 19 (see Fig. 2) of the respective rotor disk 5, 6 extending magnetic strut 28 slidably.

On the side facing away from the platform 4 outside of the upper rotor disk 5 are upper

Air delivery valves 16 are arranged, which are shown here in an at least partially unfolded state. In addition, the aforementioned outer side has a multiplicity of rotor openings 22 of the upper rotor disk 5 (see, for example, FIG. 3).

The outer side facing away from the platform 4 of the lower rotor disk 6 has analogous to the upper air conveyor flaps 17 lower air conveyor flaps 17, and arranged in the region of the edge tip portion 19 damper valves 18. The stoppers 18 can be brought from a folded and substantially parallel to the said outer surface of the lower rotor disk 6 extending position in an unfolded and substantially normal standing on said outer surface position. In addition, the aforementioned outer side has a multiplicity of rotor openings 23 of the lower rotor disk 6 (see, for example, FIG. 3).

The second magnetic drive 20 of the upper rotor disk 5 and the second magnetic drive 21 of the lower rotor disk 6 are likewise arranged in the region of the edge tip region 19 of the upper rotor disk 5 and the lower rotor disk 6. The circle forming the circumference of the rotor disks 5 forms the same , 6 and the circle along which the second magnetic drive 20 of the upper rotor disk 5 and the second magnetic drive 21 of the lower rotor disk 6 is arranged, two concentric circles with radia slightly different in magnitude.

The running between the two rotor discs 5, 6 arranged platform 4 has in its interior over an upper 13 and lower platform openings 14 accessible receiving volume 35 (see, for example, Fig. 3) and is at least four of this receiving volume 35 with the environment of Aircraft connecting ejection nozzles 15 provided.

Fig. 2 shows the detail A of FIG. 1. In each case, a rotor blade 12 of the upper main rotor 11 and the lower main rotor 12 can be seen. The housing of the upper or lower rotor disk 5, 6 has in the region of these main rotors 11, 12 in each case a recess on its outer surface facing the platform 4. The rotor disks 5, 6 are thus open to the platform 4.

The platform 4 has the receiving volume 35, which is accessible via the upper 13 and lower platform openings 14. The pivotable ejection nozzle 15 connects the receiving volume 35 of the platform 4 with the surroundings of the aircraft.

Based on Fig. 3, which shows the detail B of Fig. 1, now the inner structure of the two rotor disks 5, 6 will be explained in more detail. The upper rotor disk 5 is therefore taken as an example and its internal structure shown in schematic form in detail.

The upper main rotor 11 of the upper rotor disk 5 is arranged to extend radially outwards in a rotor region 29. Each of the rotor blades 26 forming the upper main rotor 11 is rotatably arranged about a longitudinal axis 27 of the respective rotor blade 26. Above the rotor region 29, a flow-through region 30 connects, which is accessible from above via the rotor openings 22 of the upper rotor disk 5 from above and via the recess arranged in the region of the upper main rotor 11 in the housing of the upper rotor disk 5. The flow-through section can be equipped in sections with flow-through channels which have a slightly oblique course.

Within the flow area 30, magnetic struts 28 are arranged, which on the one hand serve as shaping elements for the housing of the upper rotor disk 5. On the other hand, the battery blocks 9 (9 ') are movably arranged on them.

The edge tip region 19 surrounds the rotor 29 and the throughflow region 30 on the circumferential side. It comprises a first chamber 31, which has an opening to the rotor 29 and the flow area 30, and a second chamber 32, which is connected on the one hand via a valve to the first chamber 31 and via a discharge valve 34 with the environment. A capillary tube system 33 extends from the second chamber 32 via the outer surface of the upper rotor disk 5 facing away from the platform and opens into the throughflow region 30 in the region of the central region 36 (see FIG. 6) of the upper rotor disk 5.

The lower rotor disk 6 has an analogous structure and also has the throughflow region 30, the rotor region 29 and the edge tip region 19, together with the elements arranged in these regions.

Fig. 4 shows in addition to the elements shown in Fig. 3, the upper air conveyor flap 16, which in the illustrated folded position flush with the platform 4 facing away from the outer surface of the upper rotor disk 5.

Fig. 5 shows the same view as Fig. 4, wherein the upper air conveyor flap 16 is now shown in the extended position. In this case, the upper air conveyor flap 16 projects beyond the outer surface of the upper rotor disk 5 facing away from the platform 4 in sections in the vertical direction.

6 shows a top view of the upper rotor disk 5, wherein the rotor blades 26 of the upper main rotor 11 are shown only in sections. In this case, the platform 4 facing away from the outer surface of the upper rotor disk 5 is not Darge for illustrative purposes.

The upper rotor disk 5, which is magnetically mounted on the center part 1 by means of the first magnetic drive 7, has 8 battery blocks 9 arranged in its middle region 36. These battery blocks 9 each have a linear generator 25 and 6 individual batteries 24. The second chamber 32 of the edge tip region 19 is subdivided into 13 separate sections in the embodiment shown.

7 shows a schematic representation of the at least one air conveyor flap 16, 17 on an outer side of at least one rotor disk 5, 6. Thus, for example, the upper air conveyor flap 16 in a rotation of the upper rotor disk 5 is pushed clockwise (for example, by pneumatic pulses) as soon as it has reached a position of about 45 ° in relation to the direction of flight. The air conveyor flap 16 is unfolded by the air resistance, which it experiences immediately, up to a standing substantially normal to the plane of the rotor disk 5 position and remains in this position until the air conveyor flap 16 has reached a position of about 135 ° with respect to the direction of flight , An anchorage fixing the air-conveying flap in its unfolded position is released at the latest at this time and the air-conveying flap 16 is - again by the air resistance - returned to its folded-in position. Analogously, this mechanism works for the rotating in the opposite direction lower rotor disk 6 and the associated air conveyor flap 17th

OPERATION OF THE INVENTION ACCORDING TO THE CONCRETE EMBODIMENT

In the following, the operation of the aircraft according to the invention will be explained with reference to the concrete embodiment described above. For this purpose, the operation of the aircraft is described starting with the take-off or take-off from the ground, about the horizontal flight to the landing.

Phase 1: Take off / take off In a start position, the aircraft according to the invention is supported by means of the extended landing leg 2 on a base area (for example a runway or a helipad). Crew, passengers and goods to be transported can be transported by means of a running inside the landing leg elevator in the middle part 1. At the base surface facing the outer leg wheels may be provided for locomotion of the aircraft on the ground rolling wheels.

To generate the lift required for take-off, the upper rotor disk 5 and the lower rotor disk 6 are set in an opposite rotational movement. The speed of the upper rotor disk 5 and the speed of the lower rotor disk 6 are exactly the same size. As a result, the torques exerted by the two rotor disks 5, 6 on the middle part 1 (and thus also on the platform 4 connected to the middle part 1) cancel each other out.

The rotor blades 26 of the upper main rotor 11 are set so that air is sucked through the rotor openings 22 of the upper rotor disk 5 in the interior of the upper rotor disk 5 by their movement. In this case, the sucked air first flows through the flow area 30 of the upper rotor disk 5, then reaches the rotor area 29 of the upper rotor disk 5 and is subsequently displaced into the receiving volume 35 of the platform 4 by the upper main rotor 11 via the open upper platform openings 13.

The rotor blades 26 of the lower main rotor 12 are compared to the position of the rotor blades 26 of the upper main rotor 11 so far as that by their movement air from the receiving volume 35 through the open lower platform openings 14 via the rotor portion 29 of the lower rotor disk 6 is sucked into the interior of the lower rotor disk 6. The sucked air is first displaced by the lower main rotor 12 in the flow area 30 of the lower rotor disk 6 and finally leaves the lower rotor disk 6 via the rotor openings 23 of the lower rotor disk 6 and the open air conveyor flaps 17th

In order to achieve additional buoyancy and additional air flow through the two main rotors 11, 12, the upper air conveyor flaps 16 are set such that they also suck in air and convey it into the interior of the upper rotor disk 5. The lower air conveyor flaps 17 are placed so that they displace the air flowing through the flow area 30 of the lower rotor disk 6 downwards.

When starting the receiving volume 35 of the platform 4 is only flowed through by the upper main rotor 11 in the receiving volume 35 displaced air before it is sucked by the lower main rotor 12 in the interior of the lower rotor disk 6. The ejection nozzles 15 are closed and thus do not emit air from the receiving volume 35 to the environment. Also, the receiving volume 35 flowing through the air is not further compressed or even burned.

The at the platform 4 facing away from the outside of the lower rotor disc 6 arranged stowage flaps 18 are placed at the start in the unfolded position to produce by means of the air displaced down an air cushion on ebendieser outside of the aircraft.

The position of the rotor blades 26 and the air conveyor flaps 16 and the jam flaps 18 is controlled by servomotors.

As a result of the rotation of the two rotor disks 5, 6, the battery blocks 9, 10, which are initially located in the middle region 26 of the respective rotor disk 5, 6, are moved outward in the direction of the edge tip region 19 of the respective rotor disk 5, 6. Their movement along the magnetic struts 28 is already magnetically braked and converted into electrical energy by means of the linear generators 25 and returned to the batteries 24.

As soon as the speed of the two rotor disks 5, 6 required for generating the lift necessary for lifting is reached, the aircraft lifts off the ground. The landing leg 2 is retracted immediately thereafter and remains during the flight in a retracted position in which it is flush with the middle part 1.

Phase 2: Transition to horizontal locomotion Either by cyclic pitch of the rotor blades 26 of the upper 11 and the lower main rotor 12 or by targeted shift of weight in one direction, the aircraft is now slightly inclined. The rotational speeds of the two rotor disks 5, 6 are preferably slightly increased.

The aircraft thereby gains a speed component in the horizontal direction. The amount of this speed component is influenced by the corresponding rotor blade position and rotational speed of the two main rotors 11, 12.

Phase 3: Horizontal Locomotion Once the aircraft has reached a predetermined velocity component in the horizontal travel direction, the blade position of the rotor blades 26 of the lower main rotor 12 is changed so that the rotor blades 26 of the lower main rotor 12 are substantially parallel to the rotor blades 26 of the upper main rotor 11 are provided.

Due to their opposing rotation, both main rotors 11, 12 now suck in air from the outer surface of the two rotor disks 5, 6 facing away from the platform 4 in each case and guide them into the receiving volume 35 of the platform 4. By means of the separately controllable and alignable ejection nozzles 15, the sucked air can be released from the receiving volume 35 to the environment and thus propulsion can be generated. Optionally, the aspirated air can be further compressed and heated by the means provided for the compression and combustion of the air before it leaves the platform 4 again via the ejection nozzles 15.

The rotation of the two main rotors 11, 12 is therefore no longer used from now on

Generation of dynamic buoyancy, but serves primarily to suck in sufficient air from the platform 4 remote from the outer surfaces of the rotor disks 5, 6, to produce by ejecting this air by means of the ejection nozzles 15 propulsion in the desired direction of flight. In order to achieve sufficiently large air flow for the generation of this thrust, not only via the rotor openings 22, 23 of the upper and lower rotor disk 5, 6, but also between the middle part 1 and lower 5, and upper rotor disk 6 arranged air intake slots in Area of the first magnetic drive 7, 8.

The dynamic Aufrieb is now generated by on the outer sides of the two rotor disks 5, 6 adjacent laminar air flows. For this purpose, as described above, the outer surface of the lower rotor disk 6 remote from the platform 4 has a smaller curvature than that of the upper rotor disk 5.

Thus, the two rotor discs 5, 6 act as a wing of the aircraft.

The jam flaps 18 are now folded and thus lie flat against the outer surface of the lower rotor disk 6 facing away from the platform 4.

Water which enters the rotor disks 5, 6 via the rotor openings 22, 23 in the course of the flight is collected in the edge tip region 19 of the respective rotor disk 5, 6, in particular in the first chamber 31. In the second chamber 32 there existing water due to the high heat development by friction between the air surrounding the aircraft and the outer surfaces of the edge tip portions 19 of the respective rotor disk 5, 6 is heated.

The heated water can be forwarded on the one hand via the capillary tube system 33 for heating the outer sides of the rotor disks 5, 6. On the other hand, there is the possibility that the resulting from the strong heating of the edge tip portion 19 water vapor is discharged by means of the discharge valves 34 to the environment. By appropriate alignment of the discharge valves 34, the rotational movement of the respective rotor disk 5, 6 is supported and / or contributed to the generation of propulsion. Due to the resulting by the discharge of water or water vapor negative pressure in the second chamber 32, further water from the first chamber 31 is introduced into the second chamber 32 via the valve which connects the first chamber 31 with the second chamber 32.

If the water reserves are completely used up and no further water from the first chamber 31 is available, the thermoelectric generators of the edge tip region 19 can be used for energy.

The recovered electrical energy can be recycled to recharge the batteries 24 to the battery blocks 9, 10.

In this phase of the flight, the upper 16 and lower air conveyor flaps 17 are no longer used for generating dynamic buoyancy, but support the propulsion generation by targeted folding and unfolding (see Fig. 7). For example, when the upper rotor disk 5 is rotated, the upper air-conveying flaps 16 are pushed open clockwise (for example, by pneumatic impulses) as soon as they have reached a position of about 45 ° with respect to the direction of flight. The air conveyor flap 16 is unfolded by the air resistance, which it experiences immediately, up to a standing substantially normal to the plane of the rotor disk 5 position and remains in this position until the air conveyor flap 16 has reached a position of about 135 ° with respect to the direction of flight , An anchorage fixing the air-conveying flap in its unfolded position is released at the latest at this time and the air-conveying flap 16 is - again by the air resistance - returned to its folded-in position. This mechanism works analogously for the lower rotor disk 6 rotating in the opposite direction.

The maximum rotational speed of the two rotor disks 5, 6 depends, on the one hand, on the electrical energy of the batteries 24 available for their drive. On the other hand, due to the particularly robust arrangement of the rotor blades 26 in the two

Rotor disks 5, 6 much higher rotational speeds of the main rotors 11, 12 are made possible, as is the case with conventional rotorcraft.

As soon as a predetermined rotational speed of the rotor disks 5, 6 is reached, the air conveyor flaps 16, 17 are folded in order to prevent them from being damaged during operation.

Phase 4: Landing As in the case of conventional aircraft, the landing approach takes place on the outer sides of the rotor disks 5, 6 by means of a descent flight or gliding flight with the air flow present.

In order to reduce the horizontal component of the speed of the aircraft again, the ejection nozzles 15 are used to generate thrust in the direction of flight according to the operation described above.

The rotor blades 26 of the lower main rotor 12 are again brought into the opposite position described at the beginning in Phase 1, whereby the two main rotors 11, 12 provide again for the dynamic buoyancy of the aircraft. The ejection nozzles 15 are closed and the air, which is introduced by means of the first main rotor 11 in the receiving volume 35, flows through the receiving volume 35 only and is subsequently sucked by the lower main rotor 12 and ejected via the rotor openings 23 of the lower rotor disk 6.

By appropriate angle of attack of the rotor blades 26 of the upper and lower main rotors 11, 12 or by reducing the rotational speed of the two rotor disks 5, 6 of the descent is initiated. By means of the discharge valves 34 and / or cyclic rotor blade adjustment position correctors of the aircraft are made in the horizontal direction. Shortly before putting the aircraft on the ground the landing gear 2 is extended and the jam flaps 18 are extended. By magnetic braking of the rotor disks 5, 6, the kinetic energy of the rotor disks 5, 6 is converted into electrical energy and supplied to the batteries 24 for recharging. Excess energy, which can not be absorbed by the batteries 24, can be stored in the flywheels of the battery blocks 9, 10.

The battery blocks 9, 10 are again moved into the central region 36 of the respective rotor disk 5 or 6.

REFERENCE LIST 1 center section 2 landing leg 3 sighting dome 4 platform 5 upper rotor disk 6 lower rotor disk 7 first upper rotor disk drive 8 first lower rotor disk drive 9 battery block in upper rotor disk 10 battery block in lower rotor disk 11 upper main rotor 12 lower main rotor 13 upper deck opening 14 lower deck Platform opening 15 Discharge nozzle 16 Upper air-conveying flap 17 Lower air-conveying flap 18 Damping flap 19 Edge tip area 20 Second magnetic drive of the upper rotor disk 21 Second magnetic drive of the lower rotor disk 22 Rotor openings of the upper rotor disk 5 23 Rotor openings of the lower rotor disk 6 24 Battery 25 Linear generator 26 Rotor blade 27 Longitudinal axis of the rotor blade 28 Magnetic strut 29 Rotor area 30 Flow area 31 First chamber 32 Second chamber 33 Capillary tube system 34 Ejecting valve 35 Recording volume of the platform 4 36 Middle area of a rotor disc

Claims (19)

claims 1. aircraft with at least two coaxially arranged main rotors (11,12) and at least two drive means (7,8,20,21), characterized in that the aircraft further comprises • a central part (1) for accommodating persons and freight, at which central part (1) the at least two drive devices (7, 8) connect, • a disc-shaped platform (4), which surrounds the middle part (1) at least in sections and is fixedly connected thereto, • two magnetically, and preferably non-contact, on rotor disks (5, 6) mounted on the middle part (1), on whose insides the main rotors (11, 12) are adjustably mounted, which rotor disks (5, 6) are arranged on both sides of and parallel to the platform (4), • rotor openings (22, 23) the rotor disks (5, 6) for the inlet and outlet of air, • platform openings (13, 14) for receiving the air discharged through the rotor openings (22, 23) into the interior of the platform, and at least four ejection nozzles (15) connected to the platform for discharging air flowing from the rotor disks (5, 6) into the platform (4) to the environment, wherein the rotor disks (5, 6) can be driven in rotation in opposite directions by means of the drive means , Wherein each of the two rotor disks (5,6) comprises a drive device, which as the first magnetic drive (7,8) and / or as a second magnetic drive (20,21), which first (7,8) and second (20,21 ) Magnetic drive in each case comprises an electromagnetic support, guiding and drive system, is executed, and • wherein the rotor discs (5,6) by means of the first magnetic drive (7,8) are magnetically mounted on the central part (1) and by means of the second magnetic drive (20,21) are magnetically mounted on the platform (4). 2. An aircraft according to claim 1, characterized in that at least one upper (16) and a lower air conveyor flap (17) on an outer side of each of the two rotor discs (5,6) are arranged, which at least one upper (16) and lower air conveyor flap ( 17) is controllable extended and retractable. 3. Aircraft according to claim 1 or 2, characterized in that in each rotor disc (5,6) at least four pairwise opposed, radially movably held battery blocks (9,10) are arranged to the solenoid drives (7,8) with power supply. 4. An aircraft according to claim 3, characterized in that the at least four battery blocks (9,10) in the interior of the rotor disc (5,6) are arranged to be controllably movable on radially outwardly extending magnetic struts (28). 5. An aircraft according to claim 3 or 4, characterized in that the at least four battery blocks (9,10) each comprise at least one battery (24), preferably a plurality of batteries (24), and a linear generator (25), which linear generator (25) is designed so that it converts the kinetic energy of the controllable outwardly moving battery blocks (9,10) into electrical energy and supplies it to the battery or the batteries. 6. Aircraft according to one of claims 1 to 5, characterized in that the at least two drive means (7,20, 8,21) are separately operable to separately control the opposite rotational movement of the two rotor discs (5,6). 7. Aircraft according to one of claims 1 to 6, characterized in that each rotor blade (26) of the main rotors (11,12) is held about its longitudinal axis (27) rotatably in the rotor discs (5,6). 8. Aircraft according to one of claims 4 to 7, characterized in that the two rotor discs (5,6) in their interior in each case one of the platform (4) near the rotor region (29), in which in each case one of the main rotors (11,12) is arranged, one to the rotor portion (29) adjoining the flow area (30) in which the magnetic struts (28) together with battery blocks (9,10) are arranged and which flow area (30) of the by the rotor movement over the rotor openings (22,23 Suctioned air is flowed through, and a radially outside of the rotor region (29) arranged edge tip region (19). 9. The aircraft according to claim 8, characterized in that the edge tip region (19) has a first chamber (31) and a second chamber (32), wherein the first chamber (31) serves to collect water from the environment, and the second Chamber (32) directly to the inside of the rotor disc (5,6) connects and is connected via a valve with the first chamber (31). 10. Aircraft according to claim 9, characterized in that the two rotor disks (5, 6) each have a capillary tube system (33), which capillary tube system (33) is connected to the second chamber (32), along the outer surfaces of the rotor disk (5, 6) in the direction of the central part (1) and in the flow area (30) of the rotor disc (5,6) opens. 11. An aircraft according to claim 9 or 10, characterized in that the second chamber (32) is divided into a plurality, preferably eight, separate sections, each section having a discharge valve (34) for discharging water vapor to the environment. 12. Aircraft according to one of claims 8 to 11, characterized in that the edge tip region (19) has at least one thermoelectric generator, preferably a plurality of thermoelectric generators, to the batteries (24) with that of the / the thermoelectric generator / thermoelectric Generators generate electricity to load. 13. Aircraft according to one of claims 5 to 12, characterized in that the surface of at least one rotor disc (5) is at least partially covered with solar cells to charge the batteries (24) with the electricity generated by the solar cells. 14. Aircraft according to one of claims 1 to 13, characterized in that the platform (4) has at least one receiving volume (35), preferably a plurality of separate receiving volumes (35), which / which receiving volume / receiving volumes (35) for air over the Platform openings (13,14) is accessible. 15. An aircraft according to claim 14, characterized in that the at least one receiving volume (35) means for compression and / or combustion of the air, which is located in the receiving volume (35) comprises. 16. Aircraft according to one of claims 1 to 15, characterized in that the platform openings (13,14) and / or the rotor openings (22,23) can be closed and opened separately. 17. Aircraft according to one of claims 1 to 16, characterized in that the at least four ejection nozzles (15) are separately alignable. 18. Aircraft according to one of claims 1 to 17, characterized in that the rotor discs (5,6) each comprise at least one airbag, preferably a plurality of airbags, which in an operating state of the airbags the flow area (30) and / or the rotor area ( 29) of the rotor disks (5,6) fill. 19. Aircraft according to one of claims 1 to 18, characterized in that the two rotor discs (5,6) for generating a dynamic buoyancy upon movement of the aircraft in a direction which is substantially parallel to the plane of the rotor discs (5,6) , have different curvatures.