DE102019205849B4 - Method for carrying out a starting process of an aviation automobile, as well as a system for operating a corresponding aviation automobile - Google Patents

Abstract

A method for starting a flight automobile (2), in which starting energy is generated for the flight automobile (2), characterized in that an air stream (4) is provided with an energy generator (3) which is separate from the flight automobile (2) ) is generated as external starting energy for at least one propeller (9) of the flying vehicle (2), the air flow (4) acting on a propeller (9) of the flying vehicle (2) and directed towards the propeller (9) so that through the air flow (4) the speed of the propeller (9) is increased.

Description

The invention relates to a method for carrying out a starting process of a flight automobile, in which starting energy is generated for the flight automobile. The invention also relates to a system for operating a corresponding aircraft.

The DE 10 2016 123 254 A1 discloses a rotary wing aircraft with a rotor and a propeller, also referred to as a gyroplane or autogyro or gyrocopter. A take-off and landing device for the rotary-wing aircraft has a stationary carrier on which a guide can pivot about a horizontal axis between a take-off position and a landing position. A drive for transmitting an acceleration force to the rotary wing aircraft is arranged at its outer end region, which acceleration force can thereby be generated independently of an on-board drive of the rotary wing aircraft. For this purpose, a coupling has a circumferential contact surface which forms a positive pole of an electrical contact, and a further front-side contact surface which forms the negative pole. Such helicopters require a relatively large amount of starting energy.

US 2018/0 065 734 A1 discloses a system for pre-rotating a gyrocopter. A restraint is positioned to at least restrict the lateral and vertical movement of a gyrocopter. A transmission device is coupled to an energy source, the transmission device being releasably couplable to a pre-rotator carried by the gyrocopter.

In the U.S. 4,700,912 A it is stated that a vertical take-off and landing of an aircraft is supported by means of a huge air column. The air column is pushed through movable louvers that direct the aircraft onto the air column. A pressure differential occurs on top of the column of air to center an aircraft on the column of air. To illuminate the column of air, a salt mist is introduced into the column and a laser source vibrates the crystals of the salt, radiating energy from the column that can be detected and displayed by an approaching aircraft.

The object of the present invention is to provide a method and a system with which a starting process of a flight automobile can be designed more efficiently and in particular thereby the range of a flight operation of the flight automobile can be increased.

This object is achieved by a method and a system according to the independent patent claims. Useful further developments result from the subclaims.

One aspect of the invention relates to a method for carrying out a starting process of a flight automobile, in which starting energy is generated for the flight automobile, an air flow being generated as external starting energy with an energy generator which is designed separately from the flight automobile. The air flow acts in a directed manner on a propeller of the aircraft and flows towards the propeller, so that the speed of the propeller is increased by the air flow. As a result of the starting energy generated by the separately arranged energy generator, the energy of the internal energy storage device of the flying automobile can be saved, in particular during the starting process of the flying automobile. As a result, in particular the energy store or the stored energy of the energy store of the flight automobile can be used exclusively for flight operation of the flight automobile. In particular, the range during flight operation of the flight automobile can thereby be significantly increased. This is particularly advantageous if the flight automobile has an electric drive. Electrical energy can then be saved during the starting process.

Corresponding flight automobiles require a relatively large amount of starting energy for a starting process. In particular, a large amount of electrical energy of the flight automobile is consumed for the starting process of an upcoming flight operation if the flight automobile has an electric drive. Since an, in particular electrical, energy storage device of the flight automobile has only a limited capacity, a large amount of stored energy can already be consumed during the starting process. As a result, only less electrical energy is available for flight operations, which reduces the range. This is improved by the invention.

A flight automobile is to be understood as a means of transport that serves both as an aircraft and as an automobile. In particular, an aviation automobile is a means of transport for several people, which is designed in a combination of an aircraft and a land vehicle. It includes the functions of an aircraft as well as a land vehicle in order to take part in urban and rural individual road traffic like any other vehicle. In particular, in contrast to an airplane, the aviation automobile is a vehicle that is approved for use in road traffic.

The flight automobile can for example be built up from several individual sub-modules. These sub-modules can be assembled in a modular manner. For example, there is Aviation automobile made up of three sub-modules, one sub-module being the base module which contains a vehicle chassis with, for example, an autonomous vehicle control and / or wheels. In particular, the base module is a self-propelled module on the ground. Another sub-module can be a capsule with a receiving volume for people and / or objects. The sub-module can thus be a passenger compartment or a cargo space. The capsule is used in particular as a vehicle interior for passenger transport. The third sub-module can be a quadcopter module, as a result of which the aircraft can move in the air. In particular, these sub-modules of the flight automobile can be assembled or disassembled in a modular manner, depending on the current need for transportation on the ground or in the air. It can be provided that the flight automobile, when operated as a land vehicle, has only the capsule and as the base module. During flight operations, it can be provided that the flight automobile has only the capsule and the quadcopter module.

In particular, the energy generator is a unit stationed on the ground. An energy generator can be, for example, an energy generation unit or an energy generation device. The energy generator can be a compressor, for example.

The air flow is preferably generated by the energy generator until the aircraft takes off from the ground. In particular, while the air flow hits the propeller, the flight automobile is in a not yet lifted state or in a state on the ground. The speed of the propeller can be increased with the aid of the air flow, which is directed in the direction of the propeller of the aircraft. In particular, the speed of the propeller is increased or brought to a corresponding value until the aircraft takes off from the ground. The air flow can be changed in particular while it is flowing onto the propeller. In particular, the air flow is adapted depending on the current or the speed to be reached. If the speed of the propeller increases, the air flow can be reduced accordingly. With the aid of the air flow flowing to the propeller, internal starting energy from an internal drive, in particular an electric drive, for driving the at least one propeller of the aircraft can be dispensed with, at least in phases during the starting process.

An advantageous embodiment of the invention provides that the propeller of the flight automobile is brought from a standstill to a base speed with the air flow. Before the flight automobile is started, it is in a state of rest in which the propeller has a speed of zero. In particular, the propeller of the flight automobile is at a standstill when the external starting energy begins to act on it. With the help of the directed air flow on the propeller of the flight automobile, the speed of the propeller can be brought from zero to a predefined base speed. For example, the base speed is the speed at which the flight automobile is immediately before it is lifted off the ground. The base speed is in particular the speed that is generated by the external starting energy, so that the internal energy of the aircraft can be saved.

It is preferably provided that a drive of the flight automobile, in particular an electric drive, with which drive energy is generated internally for the propeller, only supplies drive energy for the propeller when a base speed of the propeller is reached by the air flow of the energy generator. As soon as the propeller of the flight automobile has been brought to the base speed with the help of the air flow generated by the energy generator, the actual internal drive of the flight automobile is started in an advantageous embodiment. The base speed is, in particular, lower than a take-off speed at which the flight automobile goes into flight operation and thus takes off from the ground. For example, the current speed of the propeller is evaluated with a sensor unit and, as soon as it reaches the value of the base speed, a signal is transmitted to the drive of the aircraft so that it can drive the propeller with the drive energy. For example, the energy generator can be switched off or deactivated when the drive of the flight automobile is started.

Particularly when a propeller has to be driven from a standstill, a particularly large amount of drive energy or starting energy is required. In this situation in particular, the invention is very advantageous in order to save internal energy of the aircraft, in particular internal electrical energy of an electric drive.

In an advantageous embodiment of the invention, it is provided that the air flow is generated by the energy generator at least until the flying vehicle lifts off a standing surface of the flying vehicle. As soon as the flight automobile takes off from a parking position or a position on the ground, a signal is transmitted to the energy generator so that the energy generator can be deactivated. In particular, the energy generator is automatically deactivated or switched off when the aircraft is lifted off. In particular, the airflow is so long generated by the energy generator until the aircraft takes off from the ground, from a parking area or a runway from a standstill to flight operation. In particular, the flight behavior of the flight automobile is not possibly adversely affected by an actively generated air flow immediately after take-off.

In an exemplary embodiment of the invention it is provided that the air stream flows downward from above, directed at the propeller. In particular, the energy generator is automatically removed from a flight path of the aircraft when the aircraft takes off upwards. For example, the air stream can flow from above down onto the propeller with the aid of an outlet nozzle of the energy generator and thus bring the propeller to a desired speed. So that the outlet nozzle of the energy generator or the energy generator does not interfere with flight operations or a starting process of the aircraft, the energy generator is automatically removed from the flight path of the aircraft as soon as the propeller of the aircraft has reached the base speed. In particular, when the drive is activated, the drive of the automobile immediately sends a signal to the energy generator, so that the energy generator is informed that the automobile will immediately lift off the ground or the standing surface. The energy generator can be automatically removed from the flight path of the aircraft depending on the signal sent by the drive. For example, this can be carried out by a swivel mechanism of the energy generator. In this way, the energy generator and the aircraft in particular can be protected from possible damage or collisions.

It is preferably provided that the energy generator is brought under the propeller and is coupled to a propeller carrier, which carries the propeller, and the air stream flows directly onto the propeller from below. In this way it can be prevented, for example, that the energy generator stands in the way of the aircraft when the vehicle is lifted off or that it interferes with it. In particular, the outlet nozzle of the energy generator or the energy generator is placed below the propeller of the aircraft. In particular, the energy generator or the outlet nozzle is placed in such a way that the air flow is directed directly to flow towards the propeller of the aircraft. In particular, the energy generator or the outlet nozzle can be coupled to the propeller carrier of the aircraft. For example, the outlet nozzle can have the same diameter as a diameter of an annular propeller housing which encircles the propeller as a radial ring. This means that the air flow can only flow towards the propeller and no air flow is unnecessarily lost as it flows into an area outside the propeller. A particularly high efficiency of the external starting energy is achieved. Because the propeller housing and the outlet nozzle are in direct contact with one another, a flow channel is also formed which directs the air flow in a directed manner onto the propeller.

In a further advantageous embodiment of the invention it is provided that a flow channel through which the air flow is directed onto the propeller is formed by a propeller housing of the propeller unit and the coupled energy generator. For example, the energy generator can be coupled to the propeller housing of the aircraft in such a way that there is no longer any air gap or space between the coupled energy generator and the propeller housing. In this way it can be achieved that a very high proportion of the air flow flows towards the propeller. As a result, optimal efficiency can be achieved for the air flow generated by the energy generator and for the starting process using the external energy of the aircraft. By forming the flow channel, the air flow can flow in a targeted manner onto the propeller. This also prevents part of the air flow from acting outside the propeller. A very low-loss flow onto the propeller is thereby achieved.

It is preferably provided that the air flow flows towards the propeller parallel or essentially directed to an axis of rotation of the propeller, about which the propeller rotates. This directed flow of air against the propeller enables the propeller to be set in motion efficiently. As a result, the efficiency of the starting process can in particular be increased and the air flow of the energy generator can be optimally used for driving the propeller. In particular, the base speed of the propeller can be reached quickly due to the parallel air flow. As a result, the starting process of the flight automobile can be designed efficiently.

In an advantageous embodiment of the invention, it is provided that the air flow is guided with a line system of the energy generator from a generator source of the energy generator to the propeller. The energy generator can be, for example, a compressor with a pressure vessel. With the help of the pipe system, the air flow can be placed at the exact position for ideal flow to the propeller without major losses. In particular, the air flow can be either from above onto the propeller or from below onto the with the line system Flow towards the propeller. For example, the outlet nozzle for the outlet of the air flow in the direction of the propeller can be mounted at one end of the line system. The power system can be, for example, a pipe system or a hose system. For example, the line system can consist of a flexible material, so that, depending on the type of aircraft or aircraft type, the respective propeller of the aircraft type can be easily and extensively flowed against the air flow.

Another aspect of the invention relates to a system for operating an aviation automobile, with an aviation automobile and a separate energy generator for generating an air flow and a line system for transporting the air flow generated, the system for carrying out a method according to the above aspect or an advantageous embodiment is trained. In particular, the method is carried out with the system. In particular, the system can be used to use an aircraft that is designed for flight operations or road operations. The flight automobile comprises at least one propeller, in particular at least two, in particular up to four propellers. The propeller is arranged on the aircraft via a propeller carrier. A propeller is preferably surrounded by a propeller housing, which in particular has a ring-like design. The propeller is encircled and protected around the axis of rotation. The energy generator is, in particular, a separate energy generator from the aircraft. It can be permanently stationed on the ground or be mobile. With the help of the energy generator, which has a compressor, for example, an air flow can be provided as external starting energy for a starting process of the flight automobile. The energy generator can have a line system with which the air flow is guided. For example, an outlet nozzle can be attached at the end of the line system, which allows the air flow to flow onto the propeller either from bottom to top or from top to bottom. For example, the outlet nozzle of the line system of the energy generator can be designed to be pivotable. As a result, in the case of a flow direction from top to bottom onto the propeller when the flying automobile is lifted off, the outlet nozzle can be removed or pivoted away from a trajectory of the flying automobile.

For example, the propeller carrier of the flight automobile can be designed to be pivotable, whereby the propeller or the propeller housing is rotatably mounted, so that a 180 ° movement of the propeller housing is possible. The flight automobile comprises in particular a drive or an aircraft engine, with which internal drive energy for the propeller can be generated, the drive energy for the propeller only being supplied by the drive when a base speed of the propeller has been reached by the air flow of the energy generator. The drive can be an electric drive or have an electric drive as a drive component.

The invention also includes developments of the system according to the invention which has features as they have already been described in connection with the further developments of the method according to the invention. For this reason, the corresponding developments of the system according to the invention are not described again here.

The invention also includes the combinations of the features of the described embodiments.

An exemplary embodiment of the invention is described below. For this purpose, the single figure shows a schematic representation of an external energy generator for an aircraft.

The exemplary embodiment explained below is a preferred embodiment of the invention. In the exemplary embodiment, the described components of the embodiment each represent individual features of the invention that are to be considered independently of one another, which also develop the invention independently of one another and are therefore to be regarded as part of the invention individually or in a combination other than the one shown. Furthermore, the described embodiment can also be supplemented by further features of the invention already described.

• Die Fig. zeigt ein System 1 zum Betreiben eines Flugautomobils 2. Dabei umfasst das System 1 das Flugautomobil 2 und einen dazu separaten Energieerzeuger 3 zum Erzeugen eines Luftstroms 4, als externe Startenergie. Das System 1 umfasst ein Leitungssystem 5 zum Transport des erzeugten Luftstroms 4 durch den Energieerzeuger 3. Bei dem Energieerzeuger 3 kann es sich beispielsweise um eine Energieerzeugungseinheit oder eine Energieerzeugungsvorrichtung handeln. Insbesondere kann der Energieerzeuger als ein Kompressor mit einer Erzeugerquelle ausgebildet sein.

In the figure, functionally identical elements are each provided with the same reference symbols.

• The figure shows a system 1 for operating a flight automobile 2 . The system includes 1 the flying car 2 and a separate energy generator 3 to generate an air flow 4th , as external starting energy. The system 1 includes a pipe system 5 for transporting the generated air flow 4th by the energy producer 3 . At the energy producer 3 it can be, for example, an energy generation unit or an energy generation device. In particular, the energy generator can be designed as a compressor with a generator source.

With the flying car 2 it is, for example, a modular flying car 2 which carry out flight operations or land or road operations can. In particular, the aviation automobile 2 also approved for road traffic. For example, the aviation automobile 2 a quadcopter module 6th , one capsule 7th and a basic module that is self-propelled on the ground 8th on. The capsule 7th serves in particular as a passenger transport module or as a storage module. Using the quadcopter module 6th can a flight operation of the flight automobile 2 be performed. The flying car 2 includes at least one propeller 9 , which in a propeller housing 10 is arranged.

The flying car 2 can have multiple propellers 9 include. For example, the aviation automobile 2 up to four propellers 9 on. The propeller 9 or the propeller housing 10 is via a propeller mount 11 with the flying car 2 or with the quadcopter module 6th of the aviation automobile 2 coupled or connected. By a propeller 9 , and in particular a propeller shaft, and in particular a propeller housing 10 and in particular by a propeller carrier 11 a propeller unit is formed.

In particular, the energy generator in question 3 an external starting energy for a starting process of the flight automobile 2 generated. This external starting energy is therefore not used by the aircraft 2 itself or not through an internal drive of the aircraft 2 generated. The energy generator is used as external starting energy 3 a stream of air 4th generated. The airflow 4th is particularly defined on the propeller 9 directed and flows this propeller 9 at. Through the airflow 4th can change the speed of the propeller 9 increase. In particular, the propeller 9 of the aviation automobile 2 with the airflow 4th be brought from a standstill to a base speed. For example, the base speed is less than a lift-off speed.

The flying car 2 has an internal drive 12 on, which is, for example, an aircraft engine. The drive 12 can be an electric drive. The drive 12 generates internal drive energy for the propeller 9 . The drive 12 in particular only then generates the drive energy required for the propeller 9 when through the airflow 4th of the energy generator 3 a base speed of the propeller 9 was achieved. The airflow 4th is preferably at least as long by the energy generator 3 generated until the aviation automobile 2 from a stand area 15th (for example a floor, a parking area, a runway or a parking position). In particular, during the start-up process of the flight automobile 2 the flying car 2 brought from a standstill or a parking position to flight operations. A shorter or longer period of time can also be provided in which the air flow 4th is produced. It can also be provided that the flow velocity or the mass flow of the air flow 4th during the flow against the propeller 9 can be changed. This can be dependent on the operating parameters of the flight automobile and / or on environmental parameters.

It can be the airflow 4th from above on the propeller 9 directed downwards. This is shown in FIG. By the exemplary arrangement of the line system shown in dashed lines 5 respectively. The energy producer 3 can from a flight path of the flying automobile 2 automatically removed when the flying automobile 2 lifts upwards.

In particular, the energy producer 3 with its piping system 5 also under the propeller 9 as shown in fig. by the arrangement shown with a solid line.

The line system 5 can with an outlet area, in particular an outlet nozzle, in particular directly on the propeller housing 10 be coupled.

This allows the airflow 4th even better directed, with little loss and a short distance to the propeller 9 directed towards the stream.

The airflow 4th can via the line system 5 from the energy producer 3 either from bottom to top or from top to bottom the propeller 9 flow, both examples are shown in the figure. In particular, with an outlet nozzle 13 the airflow 4th directed at the propeller 9 stream towards. With the pipeline system 5 it can, for example, be a pipe system or a hose system. In particular, the outlet nozzle 13 so on the propeller housing 10 be coupled so that a flow channel is formed. This allows the airflow 4th particularly advantageously aimed at the propeller 9 stream towards.

The airflow 4th can preferably be directed parallel to an axis of rotation 14th of the propeller 9 the propeller 9 stream towards. The axis of rotation 14th is in particular the axis around which the propeller rotates 9 moved rotationally. For example, the propeller carrier 10 can be pivoted using a pivoting support arm. This can especially affect the propeller 9 be rotated 180 degrees. This allows the air flow to flow efficiently 4th on the propeller 9 can be achieved.

List of reference symbols

1

system

2

Aviation automobile

3

Energy producer

4th

Airflow

5

Line system

6th

Quadcopter module

7th

capsule

8th

Basic module

9

propeller

10

Propeller housing

11

Propeller carrier

12

drive

13

Outlet nozzle

14th

Axis of rotation

15th

Stand space

Claims (10)

A method for carrying out a starting process of a flying car (2), in which starting energy is generated for the flying car (2), characterized in that - with an energy generator (3) which is separate from the flying car (2), an air flow (4 ) is generated as external starting energy for at least one propeller (9) of the flying vehicle (2), wherein - the air flow (4) acts on a propeller (9) of the flying vehicle (2) and flows towards the propeller (9) so that through the air flow (4) the speed of the propeller (9) is increased. Procedure according to Claim 1 , characterized in that the propeller (9) of the flight automobile (2) is brought from a standstill to a base speed with the air flow (4). Method according to one of the preceding claims, characterized in that a drive (12) of the aircraft (2), with which drive energy is generated internally for the propeller (9), only supplies drive energy for the propeller (9) when through the air flow (4) of the energy generator (3) a base speed of the propeller (9) is reached. Method according to one of the preceding claims, characterized in that the air stream (4) is generated by the energy generator (3) at least until the flying vehicle (2) lifts off a standing surface (15) of the flying vehicle (2). Method according to one of the preceding claims, characterized in that the air flow (4) flows downwards from above onto the propeller (9) and the energy generator (3) is automatically removed from a trajectory of the flying car (2) when the flying car ( 2) lifts upwards. Method according to one of the preceding Claims 1 to 4th , characterized in that the energy generator (3) is brought under the propeller (9) and is coupled to a propeller carrier (11) which carries the propeller (9), and the air flow (4) from below to the propeller (9) ) directed towards it. Procedure according to Claim 6 , characterized in that a flow channel is formed by a propeller housing (10) and the coupled energy generator (3) through which the air stream (4) is directed onto the propeller (9). Method according to one of the preceding claims, characterized in that the air flow (4) directed parallel to an axis of rotation (14) of the propeller (9), about which the propeller (9) rotates, flows towards the propeller (9). Method according to one of the preceding claims, characterized in that the air flow (4) is guided with a line system (5) of the energy generator (3) from a generator source of the energy generator (3) to the propeller (9). System (1) for operating a flight automobile (2), with - an aviation automobile (2) and - a separate energy generator (3) for generating an air flow (4), - A line system (5) for transporting the generated air flow (4), the system (1) being designed to carry out a method according to one of the preceding claims.

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