Aircraft equipped with a battery block

Abstract

The invention relates to an aircraft (1) comprising a battery block (2) for the energy supply of the aircraft (1). The battery block (2) is placeable in a battery compartment (4) of the aircraft (1). The battery compartment (4) is arranged in a volume formed by a fuselage (5) of the aircraft (1) and is accessible from the outside through a receiving opening (6) in the fuselage (5). The battery block (2) is retractable in the battery compartment (4) through the receiving opening (6). The receiving opening (6) is arranged on an upward-facing top surface (7) of the fuselage (5) when the aircraft (1) is in normal use. The battery block (2) is introduceable in the battery compartment (4) by movement of the battery block (2) along an insertion axis (9) oriented substantially parallel to the direction of gravity (8). The battery block (2) has a gripping device (17) that is accessible from outside the aircraft (1) when the battery block (2) is properly installed in the battery compartment (4).

Description

[Technical field]

[0001] The present invention relates to an aircraft comprising a battery block for the energy supply of the aircraft, the battery block being positionable in a battery compartment of the aircraft, the battery compartment being arranged in a volume formed by the fuselage of the aircraft and being accessible from the outside through a storage opening in the fuselage, the battery block being storable in the battery compartment through the storage opening. [Background technology]

[0002] Vertically taking off aircraft, for example so-called quadrocopters, are known as aircraft for the transportation of small cargo. Quadrocopters are aircraft that use four rotors or propellers arranged in one plane and acting vertically downwards to generate lift. The thrust of quadrocopters is generated by the inclination of the rotor planes. Depending on the drive power, these aircraft can transport a certain payload over a certain distance. The range is then limited by the available battery capacity, depending on the drive power and the payload.

[0003] Typically, the energy supply of the aircraft is realized via replaceable battery blocks, and a depleted battery block is replaced by a new charged battery block, which allows a rapid continuation of flight operations without the need for long charging times with a fixedly built-in battery block. The battery block is typically inserted into a battery compartment from the side, which can be closed by a flap, which can protect the secondary batteries from falling or environmental influences during flight operations. After the battery block is inserted into the battery compartment, electrical connection lines attached to the battery block can be connected to the aircraft, thereby forming an electrical connection.

[0004] The insertion of the battery block into the battery compartment from the side can be laborious and time-consuming. In particular, the handling of the battery block during the lateral insertion into the battery compartment requires great care and sufficient experience, since the battery block usually has a large weight. Since aircraft are mostly constructed with a lightweight structure, an incomplete insertion of the battery block can shift the center of gravity of the aircraft to such an extent that the aircraft with the battery block can tip to the side. Furthermore, the electrical connection of the battery block with the aircraft and the subsequent closing of the flap require additional time. Similarly, the laborious handling of the battery block when removing it from the battery compartment or when disconnecting the electrical connection between the battery block and the aircraft leads to additional time when replacing the battery block.

[0005] In other known aircraft, the installation of a battery block on the underside of the aircraft is planned. This type of storage of the battery block may require time-consuming removal of attachments attached to the underside of the aircraft, such as cable winches, transport containers or mounting devices. Furthermore, for good access to the underside of the aircraft, the aircraft must be placed in an upside-down position, which, depending on the size and design of the aircraft, is associated with a high expenditure of force and time. The replacement of a battery block attached to the underside of the aircraft is thus likewise significantly more laborious and time-consuming. Summary of the Invention [Problem to be solved by the invention]

[0006] It is therefore an object of the present invention to provide an aircraft with a battery block which can be particularly quickly and simply removed from and installed in the aircraft. [Means for solving the problem]

[0007] The above problem is solved in the present invention by the fact that the storage opening is arranged on the upward-facing upper surface of the fuselage when the aircraft is in normal use, the battery block can be introduced into the battery compartment by moving the battery block along an insertion axis oriented approximately parallel to the direction of gravity, and the battery block has a gripping device that is accessible from outside the aircraft when the battery block has been introduced into the battery compartment in the normal manner. Effect of the Invention

[0008] For this reason, the battery block can be introduced particularly simply into the battery compartment by lowering it down due to gravity. Since the battery block is introduced into the battery compartment from above, the aircraft can remain upright during the installation of the battery block, and there is no need to turn the aircraft upside down. This allows a particularly simple and quick installation of the battery block into the battery compartment.

[0009] According to the invention, the battery compartment is arranged in the fuselage in such a way that the total centre of gravity of the aircraft remains unchanged before and after the installation of the battery block in the aircraft. This allows a permanently anti-tip stop of the aircraft. When the change of the battery block is carried out manually, it is not necessary to hold or fix the aircraft to prevent it from tipping over. This allows a quick change of the battery block, so that flight operations can be resumed particularly quickly.

[0010] According to the invention, the battery compartment is configured in such a way that a battery block introduced into the battery compartment from above through the receiving opening can be fixed therein in a form-fitting manner. Advantageously, the battery compartment is configured in a pocket-shaped manner, so that a battery block introduced into the pocket-shaped battery compartment remains in its lowermost position in the battery compartment due to gravity. This ensures that the battery block is reliably accommodated in the battery compartment when the aircraft is in normal use.

[0011] By means of the gripping device, the battery block can be introduced into and removed from the battery compartment in a particularly comfortable and fast manner. The gripping device can advantageously be configured as a handle-type grip, which has a gripping area, in which the gripping device or the battery block can be gripped. In order to achieve a particularly low flow resistance during flight operation, the gripping device can be configured according to the invention as a cavity with an undercut, which is built into the battery block cover, so that the gripping device protruding from the fuselage of the aircraft does not influence the flow resistance. The gripping device configured as a cavity is advantageously configured in such a way that fingers, hands or a gripping device can be inserted into said gripping device and the battery block can be gripped by means of the undercut. In the case of particularly heavy battery blocks, a handle-type grip is preferred for the convenience of transporting the battery block.

[0012] In an advantageous embodiment of the inventive idea, the battery block is shaped like a rectangular parallelepiped. In this case, the battery block is advantageously also shaped elongated, so that the direction of introduction of the battery block into the battery compartment is particularly easily recognizable. Optionally, according to the invention, the battery block can also have a circular cross section and be shaped elongated, so that the direction of introduction of the battery block into the battery compartment is known, whereby introduction of the battery block in all directions with respect to a rotational movement of the battery block about its longitudinal axis is possible.

[0013] Advantageously, the end face of the battery block facing the aircraft has a cross-sectional area corresponding to the receiving opening, so that the battery block can be inserted particularly simply into the receiving opening at the end face facing the aircraft. When the battery block is moved along the insertion axis towards the battery compartment, the outer face of the battery block abuts against the receiving opening, which causes a guidance of the battery block. This allows a particularly simple and fast introduction of the battery block into the battery compartment.

[0014] In an advantageous configuration of the invention, the aircraft comprises at least two battery blocks arranged one behind the other in the longitudinal direction and in the flight direction of the aircraft. By using a plurality of battery blocks to operate the aircraft, a high total battery capacity can be achieved, as a result of which particularly long flight operations are possible. According to the invention, instead of a single battery block of large capacity, typically with large dimensions and a large weight, two or more battery blocks of relatively small capacity are used. As a result, the shift of the total center of gravity caused by the forces due to the weight of the plurality of battery blocks can be adjusted particularly well due to the corresponding arrangement of the battery blocks in the fuselage. Due to the plurality of battery blocks arranged one behind the other in the longitudinal direction and in the flight direction of the aircraft, a shift of the center of gravity to one side of the aircraft during flight operation of an aircraft with only one battery block can be avoided. As a result, a particularly stable flight operation is possible due to the arrangement of the plurality of battery blocks according to the invention. Furthermore, a lateral shift of the total center of gravity of the aircraft during the installation of the battery blocks is avoided. Since two or more battery blocks are accessible according to the invention from the top surface of the aircraft, a particularly simple and quick change of the battery blocks is possible.

[0015] In order that the air resistance generated by the aircraft in a horizontal flight attitude is particularly low, in an advantageous configuration of the aircraft according to the invention, the battery block has a battery block cover, the outer contour of which is adapted to the fuselage shape of the fuselage surface of the aircraft surrounding the receiving opening and closes flush with the fuselage surface of the fuselage in the assembled state of the battery block. The battery block cover is arranged according to the invention directly on one end face of the battery block. As a result, the volume occupied by the battery block in the battery compartment is particularly well utilized and particularly large battery blocks can be used. Advantageously, according to the invention, it can also be optionally arranged that the battery block cover is arranged at a distance from the end face of the battery block. In addition, the battery block cover can be designed as a component, for example of thin-walled construction and adapted to the fuselage shape, which is arranged on the battery block via spacer elements or mounting elements. In this case, the battery block cover can be manufactured from a material that corresponds to the material of the fuselage. Aircraft fuselages are generally manufactured from fiber composite plastics, which have high stiffness and strength and at the same time low weight. Since the production of components from fiber composite plastics is often very time-consuming and cost-intensive, the battery block cover may optionally be produced according to the invention from a material different from the material of the aircraft fuselage. For example, the battery block cover may be produced as a sheet of metal material or from an injection-moldable plastic. In order that the shape of the battery block cover can be particularly advantageously adapted to the shaping of the aircraft, the battery block cover may be produced according to the invention by an additive production method, for example 3D printing.

[0016] In order to prevent liquids, for example rainwater, from penetrating into the battery compartment, in one advantageous embodiment of the invention the battery block cover has sealing means in the region of its outer contour which, in the assembled state of the battery block, abuts against the fuselage in the region of the fuselage surface and closes the battery compartment in a liquid-tight manner, so that the battery block and the volume formed by the aircraft fuselage are protected from external environmental influences, for example precipitation or dust.

[0017] In an advantageous embodiment of the inventive idea, the aircraft comprises at least one electrical contact device with two electrical contact elements for forming an electrical connection between the battery block and the aircraft for the energy supply and / or data transmission of the aircraft, the first electrical contact element being arranged on the outer surface of the battery block and the second electrical contact element being arranged on the inner surface of the battery compartment, in such a way that the electrical connection is formed when the battery block is properly introduced into the battery compartment. Advantageously, the first electrical contact element is arranged on the end surface of the battery block that faces into the battery compartment when the battery block is inserted, so that the electrical connection is only formed when the battery block is completely introduced into the battery compartment. According to the invention, the presence of the electrical connection between the battery block and the aircraft may be monitored by a control unit of the aircraft. In addition, the contact device may carry out a data transmission of status information of the battery block, such as the current capacity, the current charge state or the current operating conditions, such as the current power call or temperature. By monitoring the correct installation of all battery blocks, a more reliable flight operation is possible.

[0018] In one advantageous configuration of the aircraft according to the invention, the gripping device is pivotally mounted on the battery block cover on the side of the battery block cover facing away from the battery block, so that the gripping device can be raised or raised outward for the removal or transportation of the battery block, so that the gripping device can be particularly well gripped in the gripping area.

[0019] In order to keep the flow resistance that may be generated by the gripping device during flight operation particularly low, in an advantageous configuration of the inventive idea, the battery block cover and / or the fuselage surface have a cavity corresponding to the gripping device, which can be arranged in the cavity in the non-operated state. In this case, the volume formed by the cavity is completely filled by the gripping device when the gripping device is folded inward. Advantageously, the surface of the gripping device that faces outward when the gripping device is folded inward is closed flush with the fuselage surface. As a result, vortexes or flow separations or stalls at the edges can be avoided during flight operation of the aircraft. This allows a low flow resistance of the aircraft during flight operation and, as a result, a particularly long service life of the aircraft.

[0020] In order to position the battery block in the battery compartment particularly securely, in an advantageous embodiment of the inventive idea, the battery block has a locking device, by means of which the battery block can be fixed in the battery compartment in a positive-locking manner when the battery block is introduced into the battery compartment in the correct way. The locking device can, for example, be configured as a snap hook which projects laterally from the battery block and which engages in a corresponding cavity arranged on the inner surface of the battery compartment when the battery block is inserted into the battery compartment. In this case, the locking device is configured according to the invention in such a way that the snap hook is held in the cavity by a spring force and can be pushed back in the direction opposite to the spring force to release the positive lock, so that the positive lock can be released and the battery block can be removed again from the battery compartment.

[0021] In an advantageous embodiment of the invention, the locking device is in an interacting relationship with the gripping device such that the locking device can be operated by a pivoting movement of the gripping device. As a result, the battery block can be locked or unlocked and the battery block can be pulled out of the battery compartment by manual operation of the locking device with only one hand. This allows the locking process to be performed particularly simply and quickly. According to the invention, the gripping device can be pivoted to the battery block cover and has a handle-shaped grip on its outward side and a locking device on its opposite side of the gripping mechanism. In this case, the locking device can be designed in the form of a hook, which in the operated state, i.e. with the gripping device folded inwards, engages in a corresponding cavity arranged in the aircraft, so that a form-locking locking of the battery block in the battery compartment is performed. Advantageously, the gripping device is pivoted to the battery block cover in such a way that the distance between the pivoting point and the locking device is smaller than the distance between the pivoting point and the gripping area. As a result, the gripping device can be operated particularly lightly with a correspondingly large lever.

[0022] Further advantageous configurations of the inventive idea will now be explained on the basis of an embodiment shown in the drawing. [Brief description of the drawings]

[0023] [Figure 1] FIG. 1 is a schematic diagram of an aircraft according to the present invention with one battery block installed in the battery compartment. [Diagram 2] FIG. 2 is a schematic diagram of a battery block cover. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0024] FIG. 1 shows a schematic diagram of an aircraft 1 according to the invention, which accommodates two battery blocks 2 for the energy supply of the aircraft 1. In the aircraft 1 according to the invention shown in FIG. 1, two battery blocks 2 can be arranged one after the other in the longitudinal direction of the aircraft 1 and in the direction of flight 3, with a first battery block 2 being inserted into a battery compartment 4 of the aircraft 1 which is forward in the direction of flight 3, and the rear battery compartment 4 in the direction of flight 3 does not have a battery block 2. The battery compartment 4 is arranged in a volume formed by the fuselage 5 of the aircraft 1 and is accessible from the outside through an access opening 6 in the fuselage 5. The battery block 2 can be stored in the battery compartment 4 through the access opening 6. In this case, the access opening 6 is arranged on an upward-facing upper surface 7 of the fuselage 5 when the aircraft 1 is in normal use, so that the battery block 2 can be introduced into the battery compartment 4 by a movement of the battery block 2 along an insertion axis 9 oriented approximately parallel to the direction of gravity 8. The battery compartment 4 is pocket-shaped, so that the battery block 2 introduced into the pocket-shaped battery compartment 4 remains in its lowermost position therein due to gravity. The aircraft 1 is equipped with an electrical contact device for establishing an electrical connection between the battery block 2 and the aircraft 1 for the energy supply of the aircraft 1. A first electrical contact element 10, not shown in FIG. 1, is arranged on the end face 11 of the battery block 2 facing the battery compartment 4, and a second electrical contact element 12 is arranged on the inner face 13 of the battery compartment 4, so that the electrical connection is only established as soon as the battery block 2 is fully inserted into the battery compartment 4. In the inventive configuration of the battery block 2, the battery block 2 has a battery block cover 14. An outer contour 15 of the battery block cover 14 is adapted to the fuselage shape of a fuselage surface 16 of the aircraft 1 surrounding the receiving opening 6. In the assembled state of the battery block 2, it closes flush with the fuselage surface 16.The battery block 2 has a gripping device 17, which is accessible from outside the aircraft 1 when the battery block 2 is properly installed in the battery compartment 4. In the non-operated state, the gripping device 17 can be accommodated by a cavity built into the battery block cover 14, so that the flow resistance generated by the fuselage surface during flight operation is particularly low.

[0025] FIG. 2 shows a schematic view of the battery block cover 14, which is arranged on one end face 11 of the rectangular parallelepiped battery block 2. The outer contour 15 of the battery block cover 14 is adapted to the fuselage shape of the fuselage surface 16 of the aircraft 1 surrounding the receiving opening 6 and closes flush with the fuselage surface 16 of the fuselage 5 in the assembled state of the battery block 2. The battery block cover 14 is constructed as a component part of thin-walled construction adapted to the fuselage shape. The grip device 17 of the battery block cover 14 is constructed as a handle-shaped grip and has a gripping area 18 in which the grip device 17 or the battery block 2 can be gripped. The grip device 17 is shown in the folded-out state in FIG. 2. The battery block 2 has a locking device 19 by means of which the battery block 2 can be fixed in the battery compartment 4 in a form-locking manner when the battery block 2 is introduced into the battery compartment 4 as specified. The locking device 19 is in an interacting relationship with the gripping device 17 such that the locking device 19 can be operated by a pivoting movement of the gripping device 17. This allows the battery block 2 to be locked or unlocked and the battery block 2 to be pulled out of the battery compartment 4 by manual operation of the locking device 19 with only one hand. The gripping device 17 is pivoted to the battery block cover 14 and has, on its outwardly facing side, a handle-shaped grip with a gripping area 18. The locking device 19 is arranged on the side of the gripping device 17 that is located opposite the gripping area 18. In this case, the gripping device 17 is pivoted to the battery block cover 14 in such a way that the distance between the pivoting point 20 and the locking device 19 is smaller than the distance between the pivoting point 20 and the gripping area 18. The first electrical contact element 10 is arranged on the end face 11 of the battery block 2 facing the battery compartment 4, so that the electrical connection between the battery block 2 and the aircraft 1 is only formed as soon as the battery block 2 is fully inserted into the battery compartment 4.

Claims

1. An aircraft (1) comprising a battery block (2) for energy supply of the aircraft (1), wherein the battery block (2) can be arranged within a battery compartment (4) of the aircraft (1), the battery compartment (4) is arranged within a volume formed by a fuselage (5) of the aircraft (1), is accessible from outside through a receiving opening (6) of the fuselage (5), and the battery block (2) can be stored within the battery compartment (4) through the receiving opening (6). In the aircraft (1), the receiving opening (6) is arranged on an upward-facing upper surface (7) of the fuselage (5) when the aircraft (1) is being used as prescribed, the battery block (2) can be introduced into the battery compartment (4) by movement of the battery block (2) along an insertion axis (9) oriented substantially parallel to the direction of gravity (8), the battery block (2) has a gripping device (17), and the gripping device (17) is approachable from outside the aircraft (1) when the battery block (2) is being introduced into the battery compartment (4) as prescribed. An aircraft (1) comprising a battery block (2) for energy supply of the aircraft (1), characterized in that.

2. The aircraft (1) according to claim 1, characterized in that the battery block (2) is configured in a cuboid shape.

3. The aircraft (1) according to claim 1 or 2, characterized in that the aircraft (1) comprises at least two battery blocks (2) arranged one behind the other in the longitudinal direction and the flight direction (3) of the aircraft (1).

4. 3. The aircraft (1) according to claim 1 or 2, characterized in that the battery block (2) has a battery block cover (14), the outer contour (15) of which is adapted to the fuselage shape of a fuselage surface (16) of the aircraft (1) surrounding the accommodation opening (6) and closes flush with the fuselage surface (16) of the fuselage (5) in the assembled state of the battery block (2).

5. 5. The aircraft (1) according to claim 4, characterized in that the battery block cover (14) has sealing means in the area of ​​the outer contour (15) which, in the assembled state of the battery block (2), abuts against the fuselage (5) in the area of ​​the fuselage surface (16) and closes the battery compartment (4) in a liquid-tight manner.

6. 3. The aircraft (1) according to claim 1 or 2, characterized in that the aircraft (1) comprises at least one electrical contact device having two electrical contact elements (10, 12) for forming an electrical connection between the battery block (2) and the aircraft (1) for the energy supply and / or data transmission of the aircraft (1), wherein a first electrical contact element (10) is arranged on an outer surface of the battery block (2) and a second electrical contact element (12) is arranged on an inner surface (13) of the battery compartment (4) such that the electrical connection is formed when the battery block (2) is introduced into the battery compartment (4) as specified.

7. 5. The aircraft (1) according to claim 4, characterized in that the grip device (17) is pivotally mounted to the battery block cover (14) on a side of the battery block cover (14) facing away from the battery block (2).

8. The battery block cover (14) and / or the fuselage surface (16) have a cavity corresponding to the gripping device (17), and the gripping device (17) can be arranged in the cavity in a non-operated state. The aircraft (1) according to claim 4, characterized in that.

9. The battery block (2) has a locking device (19), and when the battery block (2) is introduced into the battery compartment (4) as specified, the locking device (19) enables the battery block (2) to be fixedly arranged in the battery compartment (4) in a form-fitting manner. The aircraft (1) according to claim 1 or 2, characterized in that.

10. The locking device (19) is in an interaction relationship with the gripping device (17) such that the locking device (19) can be operated by the swinging movement of the gripping device (17). The aircraft (1) according to claim 9, characterized in that.

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