Aerial vehicle

Abstract

The invention relates to an aerial vehicle (1), in particular an unmanned aerial vehicle, comprising: a receiving space (2) for receiving at least one cargo box (3); an electric accumulator (4) arranged in the receiving space (2); a movement device (6) for moving the electric accumulator (4) within the receiving space (2); and a data processing apparatus (5) which is configured to identify a center of gravity of the aerial vehicle (1) and, on the basis of the result of the identification, to cause a movement of the electric accumulator (4) within the receiving space (2).

Description

[0001] March 13, 2026

[0002] 1

[0003] aircraft

[0004] The invention relates to an aircraft, in particular an unmanned aircraft, a system comprising such an aircraft and a method for adjusting the center of gravity of an aircraft. #

[0005] A wide variety of aircraft are known, differing, among other things, in their propulsion systems. Jet-powered aircraft are very common. Recently, electric propulsion systems have been increasingly used in aircraft, both unmanned and manned.

[0006] Regardless of the propulsion system, the stability and controllability of an aircraft depend significantly on its center of gravity (CTG). The CTG influences both stability and controllability. A CTG that is too far forward can increase stability, but this can lead to higher drag and a higher stall speed. A CTG that is too far aft improves maneuverability but reduces stability, making the aircraft more difficult to control. Furthermore, a CTG that is outside permissible limits can lead to dangerous flight conditions, such as uncontrollable spins or difficulties during landing. The CTG is also relevant to the aircraft's fuel consumption. An optimal CTG can reduce the need for control corrections and results in smoother flight, thus lowering fuel consumption.The center of gravity also influences the aircraft's aerodynamic properties, including lift and drag, and thus its overall flight performance. The precise position of the center of gravity is determined by the aircraft's load and fuel and must remain within the manufacturer's specified limits to ensure safe and efficient flight.

[0007] During flight operations, the aircraft's center of gravity changes. This is due, among other things, to fuel consumption. Therefore, there is a need to adjust the aircraft's center of gravity before and / or during flight operations to ensure stability and controllability.

[0008] The object of the invention is therefore to provide an aircraft in which the center of gravity can be adjusted in a simple manner. 13.03.2026

[0009] 2

[0010] The task is solved by an aircraft, in particular an unmanned aircraft, with a receiving compartment for receiving at least one cargo box,

[0011] an electrical storage device located in the recording room,

[0012] a moving device for moving the electrical storage device within the receiving space and

[0013] a data processing device configured to determine the center of gravity of the aircraft and, depending on the result of the determination, to effect a procedure of electrical storage within the recording space.

[0014] Furthermore, an object of the invention is to provide a method for adjusting the center of gravity of an aircraft, in which the center of gravity adjustment is carried out in a simple manner.

[0015] The problem is solved by a method for adjusting the center of gravity of an aircraft, wherein a center of gravity of the aircraft is determined and, depending on the result of the determination, a control signal is sent to a movement device to move an electrical storage device in a receiving space of the aircraft.

[0016] The aircraft according to the invention has the advantage that the aircraft's center of gravity can be easily adjusted by moving the electrical storage device using the movement mechanism. This allows, for example, fuel consumption during flight operation to be easily taken into account. Furthermore, no complex structural modifications to the aircraft are necessary for adjusting the center of gravity; instead, the adjustment is achieved by moving the electrical storage device within the housing, which, as explained below, can be implemented structurally in a simple manner.

[0017] The aircraft's cargo space corresponds to an interior defined by the aircraft fuselage. Cargo and other components, such as the aircraft's electrical storage system, can be arranged within this space. As detailed below, the aircraft may be designed such that the cargo and / or other components are fixed in place. This means that the cargo and / or other components are not moved to adjust the center of gravity. 13.03.2026

[0018] 3

[0019] An electrical storage system is an energy technology device that stores electrical energy. This electrical energy can be made available on demand. For example, it can power other components, such as generators to drive rotors, during takeoff or landing of the aircraft. Electrical energy can also be provided during flight operations. The electrical storage system can be a battery or a battery pack. It can also be designed so that it can be recharged by a generator during flight. This enables a high degree of system autonomy and allows for multiple takeoff and landing cycles without an external power supply.

[0020] The traversing device serves to move the electrical storage device spatially within the receiving space. Accordingly, the traversing device is operatively connected to the electrical storage device via a drive mechanism.

[0021] The data processing device is used for processing data. It can have at least one processor or be a single processor. Furthermore, the data processing device can have other components, such as memory, input and output devices, and communication interfaces with other technical devices. The data processing device can have a printed circuit board or be a printed circuit board.

[0022] A cargo box is a container used to hold cargo. Cargo boxes can be rectangular in shape. They typically have standardized dimensions.

[0023] In a specific embodiment, the data processing device can initiate a movement of the electrical storage device if the specified center of gravity lies outside a predetermined center of gravity range. Conversely, the data processing device cannot initiate a movement of the electrical storage device if the specified center of gravity lies within the predetermined center of gravity range. The data processing device can transmit a control signal to the movement device for moving the electrical storage device. The predetermined center of gravity range can be stored in an electrical memory. This center of gravity range can be specified by the aircraft manufacturer. As a result, it is easily known whether the center of gravity lies within the predetermined center of gravity range and / or within which range the center of gravity should be adjusted. 13.03.2026

[0024] 4

[0025] The aircraft may have at least one fuel tank, which is used to hold hydrogen. Alternatively, the fuel tank may contain another type of fuel. The data processing device can receive data characterizing the fuel weight and use this data to determine the center of gravity. "Characterize" in this context means that the received data includes weight information or information from which the weight can be calculated. This applies regardless of whether the data characterizes the weight of a fuel tank or the weight of the cargo box. The data processing device can receive the data before flight operations.The fuel weight is known before flight operations, so the fuel tank usually does not need to be weighed; instead, the data can be transmitted by entering the weight via an input device of the data processing unit.

[0026] The data processing device can receive and / or determine data that characterizes fuel consumption. Based on this data, the data processing device can then recalculate the center of gravity. This preferably occurs during flight operations. Depending on the result of the determination, the electrical storage device can be moved. Thus, any weight changes occurring during flight operations due to fuel consumption can be taken into account when adjusting the center of gravity. The data processing device determines whether a center of gravity adjustment is necessary due to fuel consumption. If so, the data processing device initiates a movement of the electrical storage device so that the center of gravity is again within the specified center of gravity range.Fuel flow can be measured, and fuel consumption can be determined taking this flow rate into account. Alternatively, fuel consumption can be determined using stored characteristic curves of the consumer, such as a fuel cell and / or an engine. These characteristic curves can be stored in an electronic memory.

[0027] In a special configuration, the cargo space can be arranged so that either the cargo or the fuel tank can be placed in one section of the cargo space. This allows for particularly flexible use of the aircraft. The aircraft can carry more cargo or cargo boxes on shorter flights. At the same time, the aircraft can also be used for longer flights. In this case, the aircraft contains more fuel tanks than for shorter flights. As a result, the number of [unclear - possibly "fuel tanks"] used can be [unclear - possibly "13.03.2026"].

[0028] 5

[0029] Fuel tank capacity depends on the flight route. Consequently, the number of cargo boxes to be carried also depends on the flight route.

[0030] The cargo box and the fuel tank can be identical in three dimensions: longitudinal, lateral, and vertical. In other words, the cargo box and the fuel tank have the same dimensions. One difference between the fuel tank and the cargo box is that the fuel tank has a filler neck. The filler neck can be arranged such that, when the fuel tank is inserted longitudinally, it connects to a fuel line located in the aircraft via a connecting device. The filler neck can also have at least one additional connecting element that is actuated after the filler neck engages the connecting device to ensure a secure connection between the fuel tank and the fuel line.

[0031] The fuel line connection device can be a quick-connect fitting. The additional connecting element can be configured to rotate or otherwise actuate it after the fuel nozzle engages the connection device, thus creating a secure connection between the fuel nozzle and the connection device. Actuation of the additional connecting element can occur from above or below along the aircraft's vertical axis.

[0032] The data processing device can receive data characterizing the weight of a cargo box located in the cargo space. For this purpose, the aircraft may have a weighing device for measuring the weight of the cargo box. The weighing device may be located within the aircraft. It may be configured to transmit the measured cargo weight to the data processing device. The weighing device may be positioned within the aircraft such that it determines the weight of one or more cargo boxes. In this configuration, the weighing device does not measure the total weight of the aircraft.

[0033] The weight of the cargo box is referred to as the load weight. For this purpose, the weighing device is connected to the data processing device via a data connection. A "data connection" is understood to be a connection in which data can be exchanged between the connected components in at least one direction. This process can be used for all 13.03.2026

[0034] 6

[0035] The weight of the cargo boxes is repeated. This means that after the weighing process of the data processing device, the weight of all cargo boxes is known.

[0036] The data processing device can determine the aircraft's center of gravity based on the received data. As previously described, the received data relates to the weight of a cargo box or the weight of all cargo boxes. Additionally, the data processing device can take into account the weight of at least one fuel tank and the weight of the electrical storage device when determining the center of gravity.

[0037] The weight of the electrical storage device can be stored in an electrical memory. Furthermore, the geometry and / or dimensions of the electrical storage device can be stored in the electrical memory. In this case, the weight of the electrical storage device is known to the data processing device and therefore does not need to be transmitted. Similarly, the weight of the fuel tank when full is known to the data processing device and therefore does not need to be transmitted. Likewise, the geometry and / or dimensions of the cargo box and / or the fuel tank are known to the data processing device.

[0038] If multiple fuel tanks are used, the number of fuel tanks can be communicated to the data processing device. For determining the center of gravity, the weight of other components in the aircraft, such as a frame described in more detail below, can also be taken into account. Furthermore, the geometry and / or dimensions of the aircraft and / or the individual components are known to the data processing device, or such data is transmitted to the data processing device. As a result, the aircraft's center of gravity can be calculated easily without requiring the data processing device to receive a large amount of data.

[0039] The weighing device can have at least two weighing elements spaced apart to measure the load weight at different points. Based on the values ​​determined by the at least two weighing elements, the data processing device calculates the total weight of the load box. A first weighing element can be located at one end of the load and a second at the other end, with the load end and the load end aligned on a longitudinal axis.

[0040] 7

[0041] are related to the aircraft. In other words, the two ends are opposite each other with respect to the longitudinal axis of the aircraft. Accordingly, the weighing device has at least the same length, or substantially the same length, as the cargo box along the longitudinal axis.

[0042] The cargo weight can be measured before flight operations. This offers the advantage that the center of gravity can be adjusted before takeoff. Furthermore, the cargo weight can be measured during flight operations. This allows for adjustments to the center of gravity that may be necessary because the cargo has shifted from its original position during flight.

[0043] In a special configuration, the electrical storage device can be arranged in a plane perpendicular to a longitudinal axis of the aircraft and encompassing a vertical axis. The electrical storage device can be positioned in an area above or below the cargo, relative to the aircraft's vertical axis. If multiple electrical storage devices are present, they can be moved to different areas within the cargo space. This allows for the deployment of an aircraft in which the cargo space is optimally utilized with components, eliminating any empty space.

[0044] The traversing device can be configured to move the electrical storage device, in particular exclusively, along the longitudinal axis of the aircraft. The traversing device can be designed to move the electrical storage device, in particular exclusively linearly. The traversing device can be supported by the fuselage of the aircraft.

[0045] In a special configuration, the aircraft may have a frame that defines the cargo space in which the cargo can be arranged. The frame may be rectangular and have several interconnected frame members. The frame can serve to hold one or more cargo boxes. It also provides the option of attaching a rail required for moving the electrical storage device. The rail may be attached to the frame's guide rod, or the guide rod itself may be designed as a rail. Furthermore, the frame serves to absorb wing loads and stabilize the cargo within the aircraft. The frame defines a portion of the cargo space. 13.03.2026

[0046] 8

[0047] The electrical storage device can be located outside the frame. In particular, the electrical storage device can be positioned offset from the frame along the aircraft's vertical axis. Alternatively, the electrical storage device can be located within a space defined by the frame. In this case, the electrical storage device moves within the frame.

[0048] The traversing device can include a movable bracket on which the electrical storage device is mounted. Furthermore, the traversing device can include at least one guide rod, and in particular two guide rods, for guiding the electrical storage device, and especially the bracket. The guide rod can, as described above, have a rail for the mounting of the electrical storage device or be designed as a rail itself. The at least one guide rod, and in particular the two guide rods, can be an integral part of the frame. This offers the advantage that the traversing device can be designed compactly. The guide rod can correspond to a frame member extending along the longitudinal axis of the aircraft. Another advantage of such a design is that weight is saved because a separate guide rod is not required.The guide rod(s) can have any suitable cross-sectional shape, such as cylindrical, dovetail, square, or specially designed profiles, to ensure smooth, stable movement of the bracket. The guide rod(s) support the movement and keep the bracket aligned as it moves.

[0049] The moving device can include a drive unit that is functionally connected to the mounting and / or electrically connected to the electrical storage device. The functional connection is designed such that movement of the drive unit results in movement, in particular linear movement, of the mounting. The electrical connection means that the drive unit can be supplied with electrical energy from the electrical storage device. This electrical energy can alternatively or additionally be supplied by a fuel cell, in particular a hydrogen fuel cell, or a generator.

[0050] The traversing device can have a linear motion system. For example, the traversing device can have a threaded rod that is rotated by a drive unit. The drive unit can have a drive motor. The threaded rod can be operatively connected to the bracket, such that rotation of the threaded rod by the drive motor causes a linear movement of the bracket along the longitudinal axis of the aircraft. (March 13, 2026)

[0051] 9

[0052] The drive unit precisely controls the movement of the bracket, thus enabling accurate positioning of the electrical storage device.

[0053] The bracket is mounted to the threaded rod and designed to hold the electrical storage device. The bracket is also capable of supporting any other type of payload, such as sensors, cameras, or other equipment. The bracket's position is adjusted based on the load's position to maintain the center of gravity within a defined range for optimal stability.

[0054] An alternative design of the traversing device can also incorporate a linear motion system. This linear motion system differs in that it uses one or more belts. These belts run along the body and are driven by the drive unit. Adjustable mechanisms tension the belts to ensure smooth, backlash-free operation. The rotary motion of a pulley driven by the drive unit is converted into a linear motion, causing the bracket containing the electrical storage device to move along the belt.

[0055] Using multiple belts offers the advantage of evenly distributing the load. It also provides redundancy for critical applications. Furthermore, it can improve the overall stability and reliability of the traversing device.

[0056] The belts can be made of various materials, such as reinforced rubber, polyurethane with steel or Kevlar reinforcements, or lightweight composite fibers, depending on the application requirements. The guide pulleys of the traversing mechanism and the mounting bracket are made of lightweight metals, such as aluminum, or composite materials to keep the overall weight of the aircraft low.

[0057] Both previously described embodiments of the electrical storage device feature guide rails for guiding the holder of the electrical storage device and the drive device for driving the threaded rod or at least one belt.

[0058] In one embodiment, the travel distance of the electrical storage device can correspond to at least one length of the frame in the longitudinal direction of the aircraft. This results from the fact that the travel distance is defined by the length of the guide rods, which are part of the frame. However, 13.03.2026

[0059] 10

[0060] It is possible that part of the guide rod protrudes along the longitudinal axis of the frame. In this case, the travel distance is longer than the longitudinal direction of the frame. Alternatively, it is possible that the travel distance is shorter than the length of the frame in the longitudinal direction of the aircraft.

[0061] The traversing device and / or the frame can be designed such that the electrical storage unit is movable within a range of 10-90% of the aircraft's total length. As described above, the electrical storage unit is movable along the longitudinal axis of the aircraft. The weight of the electrical storage unit can range from 5% to 60% of the aircraft's empty weight. The possible travel distance and the weight of the electrical storage unit allow for adjustment of the aircraft's center of gravity.

[0062] The electrical storage system can be moved during flight operations. This offers the advantage that the center of gravity can be adjusted during flight. The movement of the electrical storage system can depend on fuel consumption and / or the time elapsed since takeoff.

[0063] A system comprising an aircraft according to the invention and an external weighing device for weighing the cargo and / or the aircraft is particularly advantageous, wherein the external weighing device is configured to communicate the measured weight to the data processing device. The external weighing device can be located outside the aircraft. In particular, the external weighing device can be located in a floor. Accordingly, the weight of the cargo can be measured automatically during the loading of the aircraft. "External" means that the weighing device is not part of the aircraft. The external weighing device can be connected to the aircraft's data processing device via data transmission. In particular, the external weighing device and the data processing device can communicate wirelessly with each other.

[0064] In this configuration, the data processing unit can receive data characterizing the cargo weight before the cargo is arranged in the aircraft's cargo hold. This occurs when the cargo boxes are weighed by the external weighing system. The data is used to determine the aircraft's center of gravity. In a configuration where the aircraft has the weighing system integrated, data characterizing the cargo weight can be received after the cargo is arranged in the aircraft's cargo hold. In this configuration, the cargo weight data can also be received on March 13, 2026.

[0065] 11

[0066] This data is received during flight operations. This makes it possible to determine whether the cargo box and / or the cargo inside the cargo box has moved during flight operations.

[0067] As described above, the weight of each cargo box to be placed in the receiving compartment can be determined. The data processing device can determine the position of the cargo boxes within the receiving compartment after receiving data characterizing the weight of the cargo boxes to be placed in the aircraft. In particular, the data processing device can determine the sequence in which the cargo boxes are to be placed in the receiving compartment. Accordingly, the loading process of the cargo boxes is simplified. The cargo boxes can be fixed in place by fixing points on the frame. The fixing is such that the cargo boxes cannot move relative to the fuselage of the aircraft. The frame is positioned in the receiving compartment in such a way that it cannot move relative to the fuselage of the aircraft.Since the order of the cargo boxes in the frame is known, the weight distribution is also known and the center of gravity can be measured accurately and easily.

[0068] A data processing device with means for carrying out a method according to the invention is particularly advantageous. A computer program comprising instructions that, when executed by a computer, cause it to carry out the method according to the invention is also particularly advantageous. The computer can be the aforementioned data processing device. Furthermore, a computer-readable data carrier on which the computer program is stored is provided. A data carrier signal that transmits the computer program is also advantageous.

[0069] The invention is schematically represented in the figures, with identical or equivalent elements generally being designated with the same reference numerals. This shows:

[0070] Fig. 1 shows a side section view of an aircraft according to the invention.

[0071] Fig. 2 is a sectional view from the front along line AA from Fig. 1.

[0072] Fig. 3 shows a top view of the aircraft, with part of the aircraft shown in a sectional view.

[0073] Fig. 4 shows a perspective view of the moving device and a frame.

[0074] Fig. 5 shows an external weighing device for measuring the aircraft. 13.03.2026

[0075] 12

[0076] Fig. 6a shows an external weighing device for measuring a cargo box.

[0077] Fig. 6b shows a representation of the aircraft into which two fuel tanks and a cargo box are loaded.

[0078] Fig. 7 shows a flowchart for a design in which one or more cargo boxes are weighed with a weighing device before loading.

[0079] Fig. 8 shows a flowchart for a version in which the aircraft is weighed before flight operations.

[0080] Fig. 9 shows a flowchart for a version in which the aircraft is in flight operation.

[0081] An aircraft 1, shown in Figure 1, has a cargo compartment 2 for receiving cargo boxes 3. The cargo boxes 3 are boxes containing goods. In the case shown in Figure 1, two cargo boxes 3 are arranged in the cargo compartment 2. The cargo boxes 3 are arranged in a frame 10, which is located within the cargo compartment 2. The frame 10 is shown in Figure 4 and serves, among other things, to stabilize the cargo boxes 2. A fuel tank 7 is also located in the cargo compartment 2. The cargo compartment 2 is bounded by the fuselage of the aircraft 1.

[0082] Aircraft 1 also has a fuel tank 7. The fuel tank 7 is also located within frame 10 and is stabilized by it. The fuel tank 7 and the cargo boxes 3 are arranged offset from each other along a longitudinal axis L of aircraft 1. The fuel tank 7 has the same dimensions as the cargo box 3. Thus, depending on the application, it is possible that more than one fuel tank 7 is located in the receiving space 2 and / or frame 10. However, the number of cargo boxes 3 is reduced by the same amount by which the number of fuel tanks 7 increases. In this case, the fuel tank 7 is located in the receiving space 2 instead of the cargo box 3. This means that either the fuel tank 7 or the cargo box 3 is located in a receiving area. The cargo boxes can have dimensions of 40 x 60 x 40 cm.After at least one cargo box 3 and / or at least one fuel tank 7 has been inserted into the frame, the cargo box 3 and / or the fuel tank 7 can be secured. Once secured, the cargo box 3 and / or the fuel tank can no longer move relative to the frame 10.

[0083] Furthermore, aircraft 1 has an electrical storage device 4 located in the receiving compartment 2. The electrical storage device 4 serves to supply electrical components, such as at least one drive motor for rotors, of aircraft 1 with electrical power.

[0084] 13

[0085] Energy. The electrical storage device 4 can be moved within the receiving space 2 relative to the fuselage of the aircraft 1. Furthermore, the electrical storage device 4 can be moved relative to the frame 10. The aircraft 1 also has a moving device 6, which is shown in more detail in Figure 4. The moving device 6 serves to move the electrical storage device 4 within the receiving space 2.

[0086] The aircraft 1 also has a data processing unit 5. The data processing device 5 is configured such that, depending on the received data, it determines a center of gravity of the aircraft 1 and, depending on the result of the determination, initiates a process of the electrical storage device 4 within the recording space 2.

[0087] The data processing unit 5 is connected to a traversing unit 6, in particular to a drive unit 13 of the traversing unit 6, via data transmission. Thus, after determining the center of gravity, the data processing unit 5 can, if necessary, transmit a control signal to the drive unit 13 to initiate a movement of the electrical storage device 4 within the receiving space 2. The electrical storage device 2 is thereby moved to a position in which the center of gravity of the aircraft 1 is located within a predefined center of gravity range.

[0088] Furthermore, the data processing unit 5 is connected to a weighing unit 8. The weighing unit 8 is located inside the aircraft 1 and transmits the measured weight values ​​to the data processing unit 5, which are required for determining the aircraft's center of gravity. The weighing unit 8 has two load cells 9 arranged to measure the weight of a single cargo box 3. The load cells 9 are spaced apart from each other along the longitudinal axis L. Thus, the two load cells measure the weight of the cargo box 3 at two points. Before loading the aircraft, the weight of all cargo boxes 3 is measured using the weighing unit. The fuel tank weight 7 before flight and / or the weight of the remaining components of the aircraft 1 are known and therefore do not need to be measured.

[0089] Figure 2 shows a sectional view from the front along line AA from Fig. 1. The frame 10 has several frame rods 10a, 10b, 10c, 10d which are connected to each other. The electrical storage device 4 is arranged along a vertical axis H above the frame 4. (The last sentence appears to be a fragment and is omitted.)

[0090] 14

[0091] The electrical storage device 4 is arranged on a bracket 11, which can be moved relative to the frame 10. The electrical storage device 4 and the bracket 11 can be made of multiple parts. In an embodiment not shown, the electrical storage device 4 and the bracket 11 can be made of a single piece. The bracket 11 is slidably mounted on the frame. In particular, the bracket is slidably mounted on two guide rods 12, wherein, as can be seen from Figure 3, the guide rods 12 each correspond to a frame member of the frame 10, which extends along the longitudinal axis L of the aircraft 1.

[0092] Figure 3 shows a top view of the aircraft 1, with a portion of the aircraft 1 shown in a sectional view. The aircraft 1 can be an unmanned aerial vehicle, in particular a drone. The frame 10 extends along the longitudinal axis L of the aircraft 1 within the receiving space 2. The electrical storage device 4 is arranged at one end of the frame 10 in Figure 3. The electrical storage device 4 can be moved linearly along the longitudinal direction L of the frame 10.

[0093] Fig. 4 shows a perspective view of the traversing device 6 and a frame 10. The traversing device 6 serves to linearly move the electrical storage device 4 along the guide rods 12. The electrical storage device 4 is arranged on the support 11, which is supported by the opposing guide rods 12 and is slidably mounted on them. The guide rods 12 run parallel to each other and extend along the longitudinal direction L.

[0094] The traversing device 6 has a drive unit 13 comprising a drive motor 15 and several guide rollers 16a. The drive motor 15 serves to drive the guide rollers 16, which are arranged at one end of the frame 10. The traversing device 6 also has two belts 17, each belt 17 being guided around a guide roller 16a at one end. Both belts 17 are also guided around a different guide roller 16b at their other ends. The other two guide rollers 16b are arranged at opposite ends of the frame 10. As a result, the guide rollers 16a and the other guide rollers 16b are arranged along the longitudinal axis L at opposite ends of the frame 10.

[0095] The traversing device 6 is operatively connected to the bracket 11 in such a way that a rotation of the deflection pulleys 16a driven by the drive motor 15 causes a movement of the belts and thus the 13.03.2026

[0096] 15

[0097] The bracket 11 moves in a linear direction. In this process, the bracket 11, and thus the electrical storage device 4, moves along the longitudinal direction L.

[0098] Fig. 5 shows a representation of an external weighing device 14 for measuring the weight of the aircraft 1. "External" means that the weighing device 14 is located outside the aircraft 1. Analogous to the weighing device 8 located inside the aircraft 1, the external weighing device 1 has two load cells 9. The external weighing device 14 is connected to the data processing device 5 and transmits the measured value to the data processing device 5. The data processing device 5 calculates the center of gravity of the aircraft 1 using the transmitted value.

[0099] Fig. 6a shows an external weighing device 14 for measuring a cargo box 3. In contrast to the embodiment shown in Fig. 5, the external weighing device 14 serves to measure the weight of a cargo box 3. First, the weight of all cargo boxes 3 to be arranged in the cargo compartment 2 of the aircraft 1 can be determined. The measured values ​​are transmitted from the external weighing device 14 to the data processing device 5.

[0100] The data processing device 5 determines the position of the cargo boxes 3 in the receiving space 2 and / or the sequence in which the cargo boxes 3 are to be placed in the receiving space 2. The cargo boxes 3 can be placed into the receiving space 2 through an opening 17 of the aircraft 1. The aircraft 1 can be moved into the open position shown in Fig. 6 by folding down one end 18 of the aircraft.

[0101] The weighing device 14 shown in Figure 5 and Figure 6 can be arranged on or in the ground.

[0102] Fig. 6b shows a representation of the aircraft 1, into which two fuel tanks 7 and a cargo box 3 are loaded. The cargo box 3 and the fuel tank 7 have the same dimensions in all three spatial directions. Both the cargo box 3 and the fuel tanks are inserted into the cargo space 2 of the aircraft 1 along the longitudinal direction L.

[0103] Aircraft 1 has a fuel line 19 which has several connection devices 21. The fuel tank 7 has a filler neck 20 which is designed such that when the fuel tank 7 is moved along the longitudinal direction L, it connects to the connection device 13.03.2026

[0104] 16

[0105] 21 is connected. The connection is such that fuel can flow from fuel tank 7 into fuel line 19.

[0106] In the embodiment shown in Fig. 6b, a fuel tank 7, in particular the fuel inlet 20 of the fuel tank, is connected to the fuel line 19. Another fuel tank 7 is arranged outside the receiving space 2 and is therefore not yet connected to the fuel line 19.

[0107] Cargo box 3 has no fuel filler neck and therefore cannot be connected to fuel line 19.

[0108] Fig. 7 shows a flowchart for an embodiment in which one or more cargo boxes are weighed before loading using a weighing device 8, 14. The method can be carried out in an embodiment in which the weighing device 8 is located inside the aircraft 1, as well as in an embodiment in which an external weighing device 14 is present, i.e., the weighing device 14 is located outside the aircraft 1.

[0109] In a first step S1, the cargo box 3 is loaded with cargo and / or placed on a weighing device. This can be done manually or mechanically. In a second step S2, it is checked whether the cargo box is placed on the weighing device 8, 14. If this is not the case, the procedure is repeated. If the cargo box 3 is placed on the weighing device 8, 14, the weighing device 8, 14 measures the weight of the cargo box 3 in a third step S3. The cargo box 3 is weighed at a minimum of two points.

[0110] In a fourth step S4, the measured data are transmitted from the weighing device 8, 14 to the data processing device 5 and stored. In a fifth step S5, it is checked whether the weight of all cargo boxes 3 has been determined. If this is not the case, steps S1 to S5 are repeated until the condition is met. If the condition is met, the data processing device 5 calculates the center of gravity of the aircraft 1 in a sixth step S6. The center of gravity determination can take into account the weight of at least one fuel tank.

[0111] In a seventh step S7, the data processing device 5 determines whether, based on the received data, the electrical storage device 4 can be moved into a position so that the 13.03.2026

[0112] 17

[0113] The center of gravity must lie within a predefined center of gravity range. If this is not the case, a warning is issued in step eight (S8), and in step nine (S9), the cargo in cargo boxes 3 must be changed. The process then restarts at step one (S1).

[0114] If, in the seventh step S7, it is determined that the electrical storage device 4 can be moved into a position so that the center of gravity of the aircraft 1 lies within a specified center of gravity area, the data processing device 5 determines in a tenth step S10 in which order the cargo boxes 3 are to be loaded into the receiving space 2 and / or the cargo boxes 3 are loaded into the receiving space 2 in this order.

[0115] In an eleventh step, S11, a control signal is transmitted to the drive unit 13 to move the electrical storage device 4 into a position. The position of the electrical storage device 4 is selected such that the center of gravity of the aircraft 1 lies within the specified center of gravity range. In a twelfth step, S12, it is checked whether the electrical storage device 4 is positioned in the position determined by the data processing unit 5. "Determined position" refers to the position identified by the data processing unit 5 at which the center of gravity is located within the specified center of gravity range. If this is the case, in a thirteenth step, S13, it is checked whether further conditions of the aircraft 1 for flight operation are met.

[0116] If, in step thirteen S13, it was determined that all conditions are met, flight operations are started in step fourteen S14. The data processing device 5 then waits until the aircraft 1 has landed before the procedure is executed again. After landing, the procedure is restarted in step one S1.

[0117] However, if in the twelfth step S12 it is determined that the electrical storage device 4 is not in the specified position, an error message is issued in a fifteenth step S15 indicating that the electrical storage device cannot be moved further. In a sixteenth step S16, the error code is cleared in the data processing device 5, and in a seventeenth step S17, all cargo boxes 3 are removed from the receiving chamber 2. The process then restarts at the first step S1. 13.03.2026

[0118] 18

[0119] If, in the thirteenth step S13, it is determined that flight operations of aircraft 1 are not possible, an error message is issued in the eighteenth step S18 stating that flight operations cannot be initiated. Subsequently, the sixteenth and seventeenth steps S16 and S17 are executed, and the procedure is restarted at the first step S1.

[0120] Fig. 8 shows a flowchart for a configuration in which the aircraft 1 is weighed before flight operations. In a first step T1, the loading boxes 3 are loaded into the aircraft 1 mechanically or automatically. In a second step T2, it is checked whether the aircraft is positioned on the external weighing device 8. If this is not the case, the procedure is repeated. If the aircraft 1 is positioned on the external weighing device 8, the external weighing device 8 measures the weight of the aircraft 1 in a third step T3.

[0121] In a fourth step, T4, the measured data are transmitted from the weighing device 8, 14 to the data processing device 5 and stored. In a fifth step, T5, the plausibility of the aircraft's weight is checked. This involves verifying whether the weight of the aircraft 1, including at least one fuel tank, and / or the cargo boxes 3, does not exceed a predefined maximum weight. If the weight does not exceed the maximum weight, the procedure continues in the sixth step, T7.

[0122] In the sixth step, T7, the data processing device 5 calculates the center of gravity of the aircraft 1. In a seventh step, T7, the data processing device 5 determines whether, based on the received data, the electrical storage device 4 can be moved to a position such that the center of gravity lies within a predefined center of gravity range. If this is not the case, a warning is issued in an eighth step, T8, and in a ninth step, T9, the cargo in the cargo boxes 3 must be changed. The procedure then starts again at the first step, T1.

[0123] If, in the fifth step T5, it is determined that the weight of aircraft 1 is not plausible, the eighth and ninth steps T8 and T9 are carried out and the procedure is started at the first step T1.

[0124] Steps T10 to T17 correspond to steps S10 to S17 from the procedure shown in Figure 7. Therefore, reference is made to the notation in Figure 7. 13.03.2026

[0125] 19

[0126] Fig. 9 shows a flowchart for an embodiment in which the aircraft 1 is in flight operation. In a first step F1, the aircraft takes off. A timer in the data processing device 5 is started and / or a flow measurement of the consumed fuel begins. The timer measures the time elapsed since takeoff. The flow measurement not only records the actual measured fuel consumption but also determines the cumulative fuel consumption.

[0127] In a second step, F2, it is checked whether a predetermined time has elapsed and / or a predetermined flow rate has been reached. If this is not the case, the second step, F2, is repeated.

[0128] If, in the second step F2, it is determined that the specified time has elapsed and / or the specified flow rate has been reached, the electrical storage device 4 is moved in a third step F3. This movement depends on a predefined function. This function contains a correlation between the elapsed time and / or flow rate and the position of the electrical storage device 4.

[0129] In a fourth step, F4, it is checked whether the electrical storage device 4 is arranged in a specific position. "Specific position" refers to the position determined by the data processing device 5, where the center of gravity is located within the specified center of gravity range. If this is the case, a fifth step, F5, checks whether the aircraft has landed.

[0130] If the aircraft 1 has landed, in a sixth step F6 a process of the electrical storage 4 is stopped and the process can be restarted in the first step F1.

[0131] If, in the fourth step F4, it is determined that the electrical storage device 4 is not in the specified position, an error message is issued in a seventh step F7, and the procedure continues with the sixth step F6. Thus, further processing of the electrical storage device 4 is discontinued.

[0132] If step five (F5) determines that aircraft 1 has not landed, the procedure continues in step two (F2). However, the input in step two (F2) is now an updated time and / or an updated flow rate. The updated time is 13.03.2026.

[0133] 20

[0134] The time elapsed since the start of the timer is understood. With the updated flow rate, the cumulative flow rate recorded since flight operations began is understood. The cumulative flow rate thus corresponds to the fuel consumption since the start of flight operations. 13.03.2026

[0135] Reference sign

[0136] 1 aircraft

[0137] 2 Recording room

[0138] 3 cargo

[0139] 4 Electrical storage

[0140] 5 Data processing device

[0141] 6. Moving device

[0142] 7 Fuel tank

[0143] 8 Weighing device

[0144] 9 weighing element

[0145] 10 frames

[0146] 10a-10d frame bar

[0147] 11 bracket

[0148] 12 Guide rod

[0149] 13 Drive unit

[0150] 14 external weighing devices

[0151] 15 Drive motor

[0152] 16 Pulley

[0153] 17 Opening

[0154] 18 End of the aircraft

[0155] 19 Fuel line

[0156] 20 fuel filler necks

[0157] 21 Connection device for fuel line

[0158] L Longitudinal axis

[0159] H vertical axis

Claims

March 13, 2026 22 Patent claims 1. Aircraft (1), in particular unmanned aircraft, with a receiving space (2) for receiving at least one cargo box (3), an electrical storage device (4) which is arranged in the receiving space (2), a moving device (6) for moving the electrical storage device (4) within the receiving space (2) and a data processing device (5) configured to determine the center of gravity of the aircraft (1) and, depending on the result of the determination, to effect a procedure of the electrical storage device (4) within the receiving space (2).

2. Aircraft (1) according to claim 1, characterized in that the data processing device (5) performs a method of the electrical storage device (4) when the determined center of gravity is outside a predetermined center of gravity range and / or does not perform a method of the electrical storage device (4) when the determined center of gravity is within the predetermined center of gravity range.

3. Aircraft (1) according to claim 1 or 2, characterized in that the aircraft (1) has at least one fuel tank (7) and the data processing device (5) receives data characterizing the fuel weight and uses the received data to determine the center of gravity.

4. Aircraft (1) according to claim 3, characterized in that the data processing device (5) receives and / or determines data that characterizes the fuel consumption and redetermines the center of gravity taking the data into account.

5. Aircraft (1 ) according to claim 3 or 4, characterized in that the receiving space is configured such that either the cargo box (3) or the fuel tank can be arranged in a receiving space section.

6. Aircraft (1) according to any one of claims 1 to 5, characterized in that the data processing device (5) receives data characterizing the weight of a cargo box (3) located in the receiving space (2) and determines the center of gravity depending on the received data. 13.03.2026 23 7. Aircraft (1) according to claim 6, characterized in that the aircraft has a weighing device (8) for measuring the weight of the cargo (3), wherein the weighing device (8) is configured to transmit the measured cargo weight to the data processing device (5).

8. Aircraft (1 ) according to claim 7, characterized in that the weighing device (8) has two weighing elements (9) which are spaced apart from each other in order to measure the cargo weight at different locations.

9. Aircraft (1) according to one of claims 1 to 8, characterized in that the electrical storage device (4) is arranged in a plane which is perpendicular to a longitudinal axis of the aircraft and which includes a vertical axis of the aircraft.

10. Aircraft (1) according to one of claims 1 to 9, characterized in that the traversing device (6) traverses the electrical storage device (4), in particular exclusively, along a longitudinal axis (L) of the aircraft (1), in particular linearly.

11. Aircraft (1 ) according to one of claims 1 to 10, characterized in that the aircraft (1 ) has a frame (10) which limits the receiving space (2) in which the cargo box (3) can be arranged.

12. Aircraft (1) according to one of claims 1 to 11, characterized in that the traversing device (6) has a movable support (11) on which the electrical storage device (4) is arranged.

13. Aircraft (1) according to one of claims 1 to 12, characterized in that the traversing device (6) has at least one guide rod (12), in particular two guide rods (12), for guiding the electrical storage device (4), in particular the holder (11).

14. Aircraft (1) according to claim 13, characterized in that the at least one guide rod (12) is a component of the frame (10). 13.03.2026 24 15. Aircraft (1) according to one of claims 1 to 14, characterized in that the traversing device (6) has a drive device (13) which is operatively connected to the support (11) and / or electrically connected to the electrical storage device (4).

16. Aircraft (1) according to one of claims 1 to 15, characterized in that a travel distance of the electrical storage device (4) corresponds to at least one length of the frame (10) in the longitudinal direction of the aircraft (1 ).

17. Aircraft (1 ) according to one of claims 1 to 16, characterized in that the electrical storage device (4) is movable in a range between 10-90% of the total length of the aircraft.

18. Aircraft (1 ) according to any one of claims 1 to 17, characterized in that the weight of the electrical storage device (4) is in a range between 5 and 60% of the empty weight of the aircraft (1 ).

19. System comprising an aircraft (1) according to any one of claims 1 to 18 and an external weighing device (14) for weighing the cargo box and / or the aircraft (1), wherein the external weighing device (14) is configured to communicate the measured weight to the data processing device (5).

20. Method for adjusting the center of gravity of an aircraft (1), in particular an unmanned aircraft (1), according to one of claims 1 to 18 or of an aircraft (1) in a system according to claim 19, wherein a center of gravity of the aircraft (1) is determined and, depending on the result of the determination, a control signal is transmitted to a movement device (6) for moving an electrical storage device (4) in a receiving space (2) of the aircraft (1).

21. The method of claim 20, characterized in that data characterizing the cargo weight are received before the cargo (3) is arranged in the receiving compartment (2) of the aircraft (1) and / or that data characterizing the cargo weight are received after the cargo is arranged in the receiving compartment (2) of the aircraft. 13.03.2026 22. Method according to claim 20 or 21, characterized in that after receiving the data characterizing the weight of the cargo boxes (3) to be arranged in the aircraft (1), the loading sequence of the cargo boxes (3) in the aircraft (1) is determined.

23. Method according to one of claims 20 to 22, characterized in that the electrical storage device (4) is moved during the flight operation of the aircraft (1).

23. Data processing device with means for carrying out a method according to one of claims 20 to 23.

24. Computer program product comprising instructions which, when the program is executed by a data processing device, in particular a computer, cause the data processing device (1), in particular the computer, to execute the method of one of claims 20 to 23.

25. Computer-readable data carrier on which the computer program product according to claim 24 is stored.

26. Data carrier signal that transmits the computer program product according to claim 24.

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