Aircraft fuselage and method for releasing a fuel tank from the inside of an aircraft

Abstract

The invention provides an aircraft fuselage (1) for releasing a fuel tank (2) from inside an aircraft fuselage (1) in an emergency, a method (M) for releasing a fuel tank (2) from inside an aircraft fuselage (1) in an emergency, and an aircraft (100) comprising such an aircraft fuselage (1). The aircraft fuselage (1) comprises: an outer structure (3); a mounting device (4) configured to releasably secure the fuel tank (2) inside the external structure (3); and an openable release door (5) separating the interior from the exterior of the external structure (3), where the release door (5) is positioned relative to the mounting device (4) such that the fuel tank (2) is released by the release door (5) when the mounting device (4) releases the fuel tank (2).

Description

Technical Field

[0001] The invention relates to a device for releasing a fuel tank from inside an aircraft fuselage in an emergency and to an aircraft fuselage. The invention also relates to an aircraft comprising such an aircraft fuselage and to a method for releasing a fuel tank from inside an aircraft fuselage in an emergency. Background Art

[0002] In addition to the fuel supply that is usually required and installed in the aircraft, the aircraft often needs to carry an additional fuel supply, especially in long-range flights. This additional fuel is usually carried in additional tanks outside the aircraft or, more specifically, can be attached to the lower surface of the wing section for convenience and aerodynamic reasons. These tanks can be released or dropped, thus reducing the load and drag factor on the aircraft or for safety reasons.

[0003] Various types of jettisonable fuel tank arrangements are known. Most prior art types of jettisonable fuel tank arrangements have been constructed and positioned relative to an aircraft body or fuselage to provide a generally aerodynamically smooth, streamlined outer surface to the aircraft.

[0004] Typically, the jettisonable fuel tank is connected to a spare fuel tank arrangement carried by the aircraft, and wherein the valve arrangement is used to normally maintain an open fuel flow communication between the jettisonable fuel tank and the engine of the aircraft.

[0005] For example, document US 4306693 A describes an improved fuel tank system for an aircraft, and more particularly, describes a disposable fuel tank arrangement and its associated self-sealing valve arrangement. The disposable fuel tank can be dropped when the contained fuel is exhausted.

[0006] In existing aircraft, those known jettisonable fuel tanks may be difficult to upgrade. Summary of the invention

[0007] According to the invention, this problem is solved in each case by the subject-matter of the main aspects.

[0008] According to a first aspect of the invention, an aircraft fuselage is provided for releasing a fuel tank from inside the aircraft fuselage in an emergency. The aircraft fuselage comprises an external structure and a mounting device. The mounting device is configured to releasably secure the fuel tank inside the external structure. Furthermore, the aircraft fuselage comprises an openable release door that separates the inside of the external structure from the outside, wherein the release door is positioned relative to the mounting device such that when the mounting device releases the fuel tank, the fuel tank is released through the release door.

[0009] According to a second aspect of the invention, an aircraft is provided comprising an aircraft fuselage according to the first aspect of the invention. Furthermore, the aircraft comprises a fuel tank which is releasably secured by mounting means inside the external structure, for example in an internal tank compartment.

[0010] According to a third aspect of the invention, there is provided a method for releasing a fuel tank from inside an aircraft fuselage in an emergency. The method comprises opening a release door that separates the inside of an external structure of the aircraft fuselage from the outside. Furthermore, the method comprises disconnecting a fuel tank that is releasably fixed to the inside of the external structure by a mounting device relative to the mounting device, so that the fuel tank releases the aircraft fuselage through the opened release door.

[0011] The basic concept of the present invention is to separate fuel tanks, in particular liquid hydrogen tanks, in an emergency situation that cannot be stopped, such as a hydrogen leak. The fuel tanks can be automatically removed from the aircraft and can be moved to a safe distance. It should be emphasized that the present invention can be applied on the ground as well as in flight. The fuel tanks can be installed in any position in the aircraft fuselage, such as the front, middle, rear or cargo compartment. In particular, the fuel tanks are stored in an internal tank compartment of the external structure that is separated from other areas of the aircraft fuselage. For example, the mounting device or the tank fitting can be integrated in the aircraft fuselage respectively. A system for separating fuel tanks, in particular a hydrogen tank separation system, is provided. The fuel tank can have a generally cylindrical shape or any similar shape.

[0012] A particular advantage of the solution according to aspects of the invention is that fuel tanks, which usually contain hazardous fluids, such as those that are prone to flammability or explosion, can be handled more safely in an aircraft. When a problem with a fuel tank occurs that cannot be handled in the aircraft, the entire fuel tank can be removed from the aircraft, thereby providing safe further flight and / or landing.

[0013] Another advantage is that hydrogen can be stored in fuel tanks and used as fuel for aircraft.Since liquid hydrogen can be explosive when combined with air, and only a small amount of energy is required to ignite the hydrogen, the present invention provides a solution to handle it safely, especially in emergency situations.

[0014] Advantageous embodiments and further developments emerge from the description with reference to the figures.

[0015] According to some aspects of the invention, a release door capable of opening is positioned on the bottom side of the external structure. In particular, the fuel tank is allowed to fall from the aircraft fuselage by gravity. For example, the release door comprises two bottom doors. The release door or the two bottom doors are respectively positioned below the fuel tank.

[0016] According to some other aspects of the present invention, the mounting device comprises an enclosure that at least partially encloses a shell surface of the fuel tank, which means that the shell surface is completely radially surrounded by the enclosure.

[0017] Furthermore, the mounting device may fix the fuel tank on the longitudinal axis of the fuel tank.Therefore, the mounting device may comprise an attachment element located at a front end region and / or a rear end region of the fuel tank relative to the longitudinal axis.

[0018] According to some other aspects of the invention, the enclosure includes a reversible quick release element, which locks the enclosure in a fixed state and is driven electromechanically, magnetically, hydraulically or pneumatically to open the enclosure. Therefore, the quick release element can be operated automatically and / or semi-automatically. For example, the quick release element is driven by a spindle drive. The quick release element can be positioned between the fuel tank and the release door. The quick release element releases the enclosure and therefore releases the fuel tank.

[0019] For example, the hydrogen detection system can be positioned at the mounting device and / or the release door or connected to the mounting device and / or the release door so that when a hydrogen leak is detected, the hydrogen detection system can activate the quick release element and the release door. In addition, the quick release element and / or the release door can be activated or controlled by the activation system or by the control and steering unit, respectively.

[0020] According to some other aspects of the present invention, the enclosure comprises a plurality of links connected to each other by a locking pin, wherein the reversible quick release element is configured as a reversible quick release pin connecting two links of the plurality of links. The quick release pin can be driven by a spindle drive to unlock / release the two links connected by the quick release pin.

[0021] According to some other aspects of the invention, the enclosure is configured as a strip having at least two parts connected to each other by a reversible quick-release element.For example, the strip may be configured like a belt.

[0022] In some embodiments, a plurality of links may be combined with a belt, wherein a quick release element is provided to release the belt or the plurality of links. Furthermore, the enclosure may include support blocks, rails or the like for enclosing the fuel tank.

[0023] According to some further aspects of the invention, the release door capable of opening is hinged to the external structure and is opened by a hydraulic pivot mechanism, an electromechanical pivot mechanism or a pneumatic pivot mechanism, wherein the hinge axis of the hinged release door corresponds approximately to the longitudinal axis of the aircraft fuselage. For example, the release door is configured as a conventional landing gear door, wherein the size and functionality of the release door can be scaled according to any requirements. Such requirements may exist at very high altitudes and / or at maximum flight speeds.

[0024] Alternatively, the hinge axis of the hinged release door is substantially perpendicular to the longitudinal axis of the aircraft fuselage.The release door may also be equipped with a lock for locking the release door.

[0025] According to some other aspects of the invention, the release door that can be opened is configured to be reclosable, in particular reclosable during flight. Therefore, the aerodynamic properties of the aircraft fuselage are not affected by the protruding release door and / or the uncovered opening.

[0026] Optionally, at least a section of the aircraft fuselage may be lined with a refractory lining for blocking flames.Alternatively or additionally, at least a section of the inner side of the outer structure may comprise a flame deflector shield.

[0027] According to some other aspects of the invention, the fuel tank is fluidly connected to a standard fuel supply and delivery line of the aircraft when secured by the mounting device. The fuel tank supplies fuel to the engine of the aircraft. The fuel tank can be configured as a cryogenic tank for storing hydrogen or other cryogenic fluids. The standard fuel supply and delivery line can be coupled to the fuel tank in the front end region or the rear end region of the fuel tank. For example, the front end region corresponds to the front end of a cylindrically shaped fuel tank.

[0028] According to some other aspects of the invention, the aircraft further includes a second fuel tank that is separate from the fuel tank and integrated into a wing of the aircraft.

[0029] Alternatively, the aircraft may include a hybrid engine configured to be driven by different fuels supplied from a fuel tank and a second fuel tank via a standard fuel supply and delivery line. For example, the fuel tank may store hydrogen and the second fuel tank may store kerosene. Alternatively, the fuel tank and the second fuel tank may store the same fuel.

[0030] According to some other aspects of the present invention, the method further comprises closing the release door after the fuel tank has been released from the aircraft fuselage. In particular, the release door is closed during flight at a normal flight speed or at a reduced flight speed. In addition, the release door can be closed at any desired altitude.

[0031] According to some other aspects of the invention, the fuel tank falls from the aircraft fuselage through the open release door under the action of gravity. Therefore, the fuel tank can be separated downwardly away from the aircraft fuselage. The open release door can include two bottom doors. For example, the bottom door is driven in a fully open position.

[0032] Additionally, the step of disconnecting may include activating shutoff valves for fluidly closing the fuel tank and standard fuel supply and delivery lines.

[0033] According to some other aspects of the invention, the method further includes switching the fuel supply from the fuel tank to a second fuel tank that is independent of the fuel tank and is not released.

[0034] Optionally, the method may begin with the step of detecting a leak in the fuel tank.For example, the leak may be detected by a user or by a hydrogen detection system located at or coupled to the fuel tank. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The invention is explained in more detail below based on an exemplary embodiment indicated in a schematic diagram, in which:

[0036] Figure 1 A schematic diagram of an aircraft fuselage is shown for releasing a fuel tank from inside the aircraft fuselage in an emergency according to an embodiment of the present invention;

[0037] Figure 2 Shown according to Figure 1 A schematic diagram of an aircraft fuselage with an open release door and a fixed mounting device;

[0038] Figure 3 Shown according to Figure 1 and Figure 2 A schematic diagram of an aircraft fuselage with an open release door and a released mounting device;

[0039] Figure 4 Shown according to Figure 1 , Figure 2 and Figure 3 A schematic diagram of an aircraft fuselage with a re-closed release door;

[0040] Figure 5 A schematic diagram of an aircraft according to another embodiment of the present invention is shown;

[0041] Figure 6 A flow chart showing a method for releasing a fuel tank from inside an aircraft fuselage in an emergency situation according to another embodiment of the present invention is shown. DETAILED DESCRIPTION

[0042] The accompanying drawings are intended to convey a further understanding of embodiments of the present invention. The accompanying drawings illustrate embodiments and are used in conjunction with the specification to explain the principles and concepts of the present invention. Many advantages of other embodiments and cited advantages appear according to the accompanying drawings. The elements of the accompanying drawings are not necessarily shown in proportion relative to each other. Terms indicating directions such as, for example, "at the top", "at the bottom", "at the left", "at the right", "above", "below", "horizontally", "vertically", "at the front", "at the rear" and similar statements are only used for illustrative purposes and are not used to limit generality to a specific configuration as shown in the figures.

[0043] In the figures of the drawings, elements, features and components that are identical, have the same function and have the same effect are each provided with the same reference numerals, unless otherwise stated.

[0044] Figure 1 , Figure 2 , Figure 3 and Figure 4 A schematic diagram of an aircraft fuselage 1 is shown for releasing a fuel tank 2 from inside the aircraft fuselage 1 in an emergency situation according to an embodiment of the invention.

[0045] The aircraft fuselage 1 comprises an external structure 3, mounting means 4, an openable release door 5, an enclosure 6 and a reversible quick-release element 7. The external structure 3 may comprise frames and longitudinal beams.

[0046] The mounting device 4 or tank fitting, respectively, is configured to releasably fix the fuel tank 2 inside the outer structure 3, in particular in the inner tank compartment. The tank fitting 4 comprises an enclosure 6, which at least in sections, here in the lower section and in the side sections, surrounds the shell surface of the fuel tank 2. In addition, the tank fitting 4 comprises three liners. The upper section of the fuel tank 2 is sectionally surrounded by the three liners.

[0047] In addition, the enclosure 6 includes a reversible quick release element 7, which locks the enclosure 6 in a fixed state and is electromechanically or hydraulically driven to open the enclosure 6. Therefore, the quick release element 7 can be operated semi-automatically. For example, a hydrogen detection system (not shown) can be positioned at the tank fitting 4 and / or the release door 5 or connected to the tank fitting 4 and / or the release door 5, so that when a hydrogen leak is detected, the hydrogen detection system can enable a signal for notifying the pilot. The quick release element 7 and the release door 5 can be enabled by the pilot. After being enabled by the pilot, the fuel tank 2 is automatically released through the release door 5.

[0048] Exemplarily, the enclosure 6 includes a plurality of links 8 and a plurality of locking pins 9. The plurality of links 8 are connected to each other by the locking pins 9. The reversible quick-release element 7 is configured as a reversible quick-release pin that connects two of the plurality of links 8. Here, the quick-release pin 7 is arranged at the lowest point of the tank fitting 4. In other words, for example, the quick-release pin 7 is arranged in the middle of the release door 5.

[0049] The release door 5 that can be opened separates the inner tank compartment from the outside of the outer structure 3. Here, the release door 5 comprises two door parts. The two door parts can be configured as double doors. The release door 5 is positioned relative to the mounting device 4 so that when the mounting device 4 releases the fuel tank 2, the fuel tank is released through the release door 5. Exemplarily, the two door parts each form a quarter of the aircraft fuselage 1. Therefore, with respect to the cross-sectional view, the release door 5 extends over the lower half of the aircraft fuselage 1.

[0050] Here, the release door 5 that can be opened is positioned on the bottom side 3a of the outer structure 3 - at Figure 2 and Figure 3 In the embodiment, the bottom side 3a corresponds to the lower side of the outer structure 3 - so that the fuel tank 2 falls from the aircraft fuselage 1 by gravity. Thereby, the release door 5 that can be opened is hinged to the outer structure 3 and is opened by a hydraulic pivot mechanism. Figure 2 and Figure 3 , the release door 5 is shown in a fully open state. The hinge axis of the hinged release door 5 corresponds approximately to the longitudinal axis of the aircraft fuselage 1. In particular, the release door 5 is configured as a conventional landing gear door, wherein the size and functionality of the release door 5 can be scaled according to any requirements. In this example, the release door 5 is hinged at the upper section of the release door 5 so that the release door 5 opens sideways.

[0051] exist Figure 2 In FIG. 1 , an aircraft fuselage 1 is schematically illustrated with an open release door 5 and a fixed mounting device 4 . Figure 2 The aircraft fuselage 1 and Figure 1 The aircraft fuselage 1 of FIG. 1 differs in that a section of the aircraft fuselage 1 is lined with a refractory lining 10 for retaining flames and a section of the inner part of the outer structure 3 comprises a flame deflector shield 11. In particular, these sections correspond to the inner part of the first release door 5 and the second release door 9 and the wall surrounding the fuel tank 2, for example the inner wall of the inner tank compartment.

[0052] Figure 3 Shown according to Figure 1 and Figure 2 An aircraft fuselage 1 with an opened release door 5 and a released tank fitting 4.

[0053] The release door 5 that can be opened is designed to be reclosable, in particular during flight. Therefore, the aerodynamic properties of the aircraft fuselage 1 are not affected by the following Figure 2 and Figure 3 The effects of the protruding release door 5 and / or the uncovered opening are presented in FIG. Figure 4 In, according to Figure 1 , Figure 2 and Figure 3The aircraft fuselage is shown with the release door 5 re-closed.

[0054] Figure 5 A schematic diagram of an aircraft 100 according to another embodiment of the present invention is shown. Specifically, the aircraft 100 is configured as a passenger aircraft or a cargo aircraft.

[0055] The aircraft 100 comprises an aircraft fuselage, in particular Figure 1 , Figure 2 , Figure 3 or Figure 4 The invention relates to an aircraft fuselage 1 and two fuel tanks 2. Each fuel tank 2 is releasably fixed in the interior of the outer structure 3, in particular in an inner tank compartment, by means of a mounting device 4. An openable release door 5 is positioned on the bottom side of the aircraft fuselage 1.

[0056] Here, the aircraft 100 includes two fuel tanks 2, but is not limited to this number. The aircraft 100 may also include one, three or more fuel tanks 2. For example, three or more fuel tanks are arranged one behind the other and / or close to each other, so that each fuel tank 2 can be released from the aircraft fuselage 1 individually.

[0057] The two fuel tanks 2 are fluidly connected to the standard fuel supply and delivery lines of the aircraft 100 when fixed by the mounting device 4. The two fuel tanks supply fuel to the engines of the aircraft 100. For example, the fuel can be kerosene or hydrogen. Therefore, the fuel tanks can be configured as cryogenic tanks for storing hydrogen.

[0058] In addition, the aircraft 100 includes a second fuel tank, which is independent of the two fuel tanks and integrated into the wing of the aircraft 100. For example, the second fuel tank is configured to store kerosene. For example, the two fuel tanks 2 can store hydrogen and the second fuel tank can store kerosene. Alternatively, the two fuel tanks and the second fuel tank store the same fuel.

[0059] Figure 6 1 shows a flow chart of a method M for releasing a fuel tank from inside an aircraft fuselage in an emergency according to another embodiment of the present invention. In particular, the fuel tank 2 is released from the aircraft fuselage according to Figure 1 , Figure 2 , Figure 3 or Figure 4 Released from inside the aircraft fuselage 1.

[0060] Method M includes the steps of detecting M0, switching M1, opening M2, disconnecting M3 and closing M4.

[0061] The method M may begin by detecting a leak in the fuel tank 2 , shown at reference numeral M0 . The leak may be detected by a user or by a hydrogen detection system positioned at or coupled to the fuel tank 2 .

[0062] In the optional switching step M1, the fuel supply is switched from the fuel tank 2 to a second fuel tank independent of the fuel tank 2. Thus, the second fuel tank is not released. Of course, when the fuel tank 2 does not supply fuel at the moment of starting the method M, the fuel supply does not need to be switched from the fuel tank 2 to the second fuel tank.

[0063] In the step of opening M2, the release door 5 is opened. The release door 5 separates the interior of the outer structure 3 of the aircraft fuselage 1 from the exterior. For example, the hydrogen detection system can activate the quick release element and the release door. In addition, the quick release element and / or the release door can be activated or controlled by the activation system or by the control and steering unit, respectively.

[0064] In the step of disconnection M3, the fuel tank 2 is disconnected. The fuel tank 2 is releasably fixed to the interior of the external structure 3 by the mounting device 4, so that the fuel tank 2 is released from the aircraft fuselage 1 through the opened release door 5. In particular, the fuel tank 2 falls from the aircraft fuselage 1 through the opened release door 5 under the action of gravity. As a result, the fuel tank 2 can be separated downwardly away from the aircraft fuselage 1.

[0065] In another closing step M4, after the fuel tank 2 has been released from the aircraft fuselage 1, the release door 5 is closed again. In particular, the release door 5 is closed during flight at normal flight speeds. In addition, the release door 5 can be closed at any desired altitude. Therefore, the drive mechanism of the release door 5 is designed to overcome higher loads.

[0066] In the above detailed description, various features have been combined in one or more examples to improve the rigor of the illustration. However, it should be clear in this case that the above description is merely illustrative and not restrictive. It is intended to cover all alternatives, modifications and equivalents of the various features and exemplary embodiments. Considering the above description, many other examples will be immediately and directly clear to those skilled in the art based on their knowledge in the art.

[0067] The exemplary embodiments have been selected and described in order to be able to present the basic principles of the invention and their application possibilities in practice in the best possible way. Therefore, those skilled in the art can best modify and utilize the invention and its various exemplary embodiments with respect to the intended purpose of use. In the claims and the description, the terms "comprising" and "having" are used as neutral language concepts corresponding to the term "including". In addition, the use of the terms "a", "an" and "one" should not in principle exclude multiple features and components described in this way.

[0068] Although at least one exemplary embodiment of the present invention is disclosed herein, it should be understood that modifications, replacements, and alternatives may be obvious to those of ordinary skill in the art and may be made without departing from the scope of the present disclosure. The present disclosure is intended to cover any adaptation or variation of the exemplary embodiments. In addition, in the present disclosure, the terms "including" or "including" do not exclude other elements or steps, the terms "one" or "one" do not exclude plural numbers, and the term "or" means one or both. In addition, unless otherwise implied by the disclosure or context, the features or steps already described may also be used in combination with other features or steps, and in any order. The present disclosure is hereby incorporated by reference into the complete disclosure of any patent or application to which it claims interest or priority.

[0069] Reference numerals list

[0070] 1 Device

[0071] 2 Fuel tanks

[0072] 3 External structure

[0073] 3a Bottom side

[0074] 4 Installation

[0075] 5 Release door

[0076] 6 Enclosures

[0077] 7 Reversible quick release element

[0078] 8+ links

[0079] 9 Locking pin

[0080] 10 Refractory lining

[0081] 11 Flame deflector shield

[0082] 100 Aircraft

[0083] X longitudinal axis

[0084] M-method

[0085] M0 Detection

[0086] M1 Switch

[0087] M2 Open

[0088] M3 Disconnect

[0089] M4 Close

Claims

1. An aircraft fuselage (1) for releasing a fuel tank (2) from inside the aircraft fuselage (1) in an emergency, the aircraft fuselage (1) comprising: External structure (3); a mounting device (4) configured to releasably secure the fuel tank (2) inside the outer structure (3); as well as A release door (5) that can be opened, the release door (5) separating the interior of the external structure (3) from the exterior, wherein the release door (5) is positioned relative to the mounting device (4) so ​​that when the mounting device (4) releases the fuel tank (2), the fuel tank (2) is released through the release door (5).

2. The aircraft fuselage (1) according to claim 1, wherein: The release door (5) that can be opened is positioned on the bottom side (3a) of the outer structure (3).

3. Aircraft fuselage (1) according to claim 1 or 2, wherein: The mounting device (4) comprises an enclosure (6), and the enclosure (6) at least partially encloses the shell surface of the fuel tank (2).

4. Aircraft fuselage (1) according to claim 3, wherein: The enclosure (6) comprises a reversible quick-release element (7) which locks the enclosure (6) in a fixed state and is driven electromechanically, magnetically, hydraulically or pneumatically to open the enclosure (6).

5. Aircraft fuselage (1) according to claim 4, wherein: The enclosure (6) comprises a plurality of chain links (8) connected to each other by locking pins (9), wherein the reversible quick-release element (7) is configured as a reversible quick-release pin connecting two chain links of the plurality of chain links (8).

6. Aircraft fuselage (1) according to claim 4, wherein: The enclosure (6) is configured as a strip having at least two parts connected to each other by the reversible quick-release element (7).

7. Aircraft fuselage (1) according to one of the preceding claims, wherein: The openable release door (5) is hinged to the external structure (3) and is opened by means of a hydraulic, electromechanical or pneumatic pivot mechanism, wherein the hinge axis of the hinged release door corresponds approximately to the longitudinal axis (X) of the aircraft fuselage (1).

8. Aircraft fuselage (1) according to one of the preceding claims, wherein: The release door (5) which can be opened is designed to be able to be closed again, in particular during flight.

9. An aircraft (100), in particular a passenger aircraft or a cargo aircraft, comprising: Aircraft fuselage (1) according to one of the preceding claims; as well as A fuel tank (2) is releasably fixed inside the outer structure (3) by the mounting device (4).

10. The aircraft (100) according to claim 9, wherein: The fuel tank (2) is fluidly connected to the standard fuel supply and delivery lines of the aircraft (100) when secured by the mounting device (4).

11. The aircraft (100) according to claim 9 or 10, further comprising a second fuel tank, which is independent of the fuel tank (2) and integrated into a wing of the aircraft (100).

12. A method (M) for releasing a fuel tank (2) from the interior of an aircraft fuselage, in particular from the interior of an aircraft fuselage (1) according to one of claims 1 to 8, in an emergency situation, the method (M) comprising: opening (M2) a release door (5) which separates the interior of an outer structure (3) of an aircraft fuselage (1) from the exterior; as well as Disconnecting (M3) a fuel tank (2) which is releasably fixed by means of a mounting device (4) inside the external structure (3) relative to the mounting device (4) allows the fuel tank (2) to be released from the aircraft fuselage (1) through the opening of the release door (5).

13. The method (M) according to claim 12, further comprising: After the fuel tank (2) has been released from the aircraft fuselage (1), the release door (5) is closed (M4).

14. The method (M) according to claim 12 or 13, wherein: The fuel tank (2) falls from the aircraft fuselage (1) through the opened release door (5) under the action of gravity.

15. The method (M) according to one of claims 12 to 14, further comprising: The fuel supply is switched (M1) from the fuel tank (2) to a second fuel tank which is independent of the fuel tank (2) and is not released.

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