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

Abstract

The invention provides an aircraft fuselage and a method for releasing a fuel tank from the interior of the aircraft fuselage in an emergency situation, and an aircraft. The aircraft fuselage (1) comprises: an outer structure (3); a mounting device (4) configured to releasably secure a carriage device (6) for carrying the fuel tank (2) inside the outer structure (3); and a first openable release door (5) separating the interior from the exterior of the external structure (3), where the first release door (5) is positioned relative to the mounting means (4) such that the fuel tank (2) is released by the first release door (5) when the mounting means (4) releases the carriage means (6). An aircraft (100) comprises such an aircraft fuselage (1).

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] For aircraft, especially in long-range flights, it is necessary for the aircraft to carry an additional fuel supply in addition to the fuel supply normally required and installed in the aircraft. This additional fuel is usually carried in additional tanks external to the aircraft, or more specifically, additional tanks may be attached to the lower surface of the wing section for convenience and aerodynamic reasons. These tanks may be released or lowered to reduce the load and drag factor on the aircraft, or they may be released or dropped 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 the aircraft with a generally aerodynamically smooth, streamlined outer surface.

[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 open fuel flow communication between the jettisonable fuel tank and the aircraft's engine.

[0005] For example, document US 4 306 693 A describes an improved fuel tank system for an aircraft and more specifically 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 of the invention.

[0008] According to a first aspect of the invention, an aircraft fuselage is provided for releasing a fuel tank from the interior of the aircraft fuselage in an emergency. The aircraft fuselage comprises an external structure and a mounting device. The mounting device is configured to releasably fix a carriage device for carrying the fuel tank inside the external structure. Furthermore, the aircraft fuselage comprises a first openable release door, which separates the interior of the external structure from the exterior, wherein the first release door is positioned relative to the mounting device such that when the mounting device releases the carriage device, the fuel tank is released through the first 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. In addition, the aircraft comprises a carriage device for carrying a fuel tank. The carriage device is releasably fixed to the interior of the external structure by a mounting device. In particular, the aircraft is configured as a passenger aircraft or a cargo aircraft.

[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 first release door, which separates the inside of an external structure of the aircraft fuselage from the outside. Furthermore, the method comprises disconnecting a carriage device for carrying the fuel tank, wherein the carriage device is releasably fixed to the inside of the external structure relative to the mounting device by a mounting device, so that the carriage device releases the aircraft fuselage through the opened first release door.

[0011] The basic concept of the present invention is to separate the fuel tank, in particular the liquid hydrogen tank, in an emergency situation that cannot be stopped, such as a hydrogen leak. This enables the fuel tank to be automatically removed from the aircraft and 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 tank can be installed in any position in the aircraft fuselage, such as the front, middle, rear or cargo compartment. In particular, the fuel tank is stored in an internal tank compartment of the external structure that is separated from other areas of the aircraft fuselage. The carriage device is not limited to carrying fuel tanks, but can also carry any other items, such as boxes. A system for separating a carriage device carrying a fuel tank, 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 to provide 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 safely handle this problem, 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, the first openable release door or pop-up panel is located on a lateral side of the outer structure, in particular, so that the fuel tank slides out of the aircraft fuselage by a lateral force relative to the longitudinal axis of the aircraft fuselage.

[0016] According to some other aspects of the invention, the mounting device comprises a rail system for guiding the carriage device. Optionally, the rail system may comprise rollers or similar elements for improving the sliding of the carriage device.

[0017] According to some other aspects of the present invention, the mounting device includes a reversible quick release element, which locks the carriage device in a fixed state and is electromechanically, magnetically, hydraulically or pneumatically driven to release the carriage device. Therefore, the quick release element can be operated automatically and / or semi-automatically. For example, a hydrogen detection system can be positioned at the mounting device and / or the first release door or connected to the mounting device and / or the first release door, and when a hydrogen leak is detected, the hydrogen detection system can enable the quick release element and the first release door. In addition, the quick release element and / or the first release door can be enabled or controlled by an enabling system or a control and steering unit, respectively.

[0018] According to some other aspects of the invention, the first openable release door is hinged to the external structure and is opened by a hydraulic, electromechanical or pneumatic pivot mechanism, wherein the hinge axis of the hinged release door substantially corresponds 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 be opening at very high altitudes and / or at maximum flight speeds.

[0019] According to some other aspects of the invention, the aircraft fuselage further comprises a second openable release door, which is positioned on the opposite side of the outer structure relative to the first release door. Thus, the fuel tank can also be released via the second release door. Releasing the fuel tank via the first release door or the second release door can be selected by the control unit or the user, in particular the pilot. Basically, the second release door can be constructed and hinged like the first release door.

[0020] According to some other aspects of the invention, at least one of the first openable release door and the second openable release door is configured to be reclosable, in particular reclosable during flight. Thus, the aerodynamic properties of the aircraft fuselage are not affected by the protruding release door and / or the uncovered opening.

[0021] Optionally, at least a portion of the aircraft fuselage may be lined with a refractory lining for flame containment. Alternatively or additionally, at least a portion of an inner portion of the outer structure may include a flame deflector shield. Alternatively or additionally, a flameless pressure relief device for flame containment may be disposed on an inner portion of at least one of the first openable release door and the second openable release door and configured to cover an opening in the outer structure when the first release door or the second release door is open.

[0022] Flameless vents combine the technology of explosion venting and flame arresting. A flameless vent may include a vent panel, a flanged housing, and a flame arrester element. The general principle is that during the early stages of an explosion, the explosion vent cover opens and burning and unburned dust and flames enter the flame arrester element. The flame is prevented from propagating beyond the flameless vent by dissipating energy (heat) in the element, thereby reducing the burning fuel to below its ignition temperature. The dust is mostly retained within the catcher element, and the gases from the explosion are discharged through the device into the external atmosphere surrounding the flameless vent.

[0023] There are several types of flameless pressure relief devices. In addition, there are passive flameless pressure relief devices, which basically include a cylindrical member closed at one end and opened at the other end. The surface of the flameless pressure relief device can be made of various mesh layers, in particular made of high-temperature stainless steel mesh. The flameless pressure relief device can be bolted to the explosion-proof vent on the container, wherein the open end of the flameless pressure relief device overlaps the vent orifice. Through the net and due to the heat absorption of the flame filter, the dust will be retained in the compartment; the flame from the explosion will be extinguished when it passes through the net. Only the post-combustion gas from the explosion is allowed to be safely discharged. The advantages of flameless pressure relief are flame extinguishing, dust retention, elimination of the need for explosion pressure relief piping, and minimization of the pressure relief release area required for indoor pressure relief. This means that the three-dimensional net arrangement acts as a heat sink for interrupting the explosion in the mid-flow and an absorber of the pressure wave and dust that would normally be ejected by the pressure relief explosion.

[0024] According to some other aspects of the invention, the fuel tank, when secured by the mounting device, is fluidly connected to the standard fuel supply and delivery lines of the aircraft. The fuel tank supplies fuel to the engines of the aircraft.

[0025] According to some other aspects of the invention, the carriage device comprises an acceleration device for ejecting the carriage device together with a fuel tank fixed to the carriage device. Optionally, the carriage device may comprise rollers or similar elements for improving the sliding of the carriage device on the rail system.

[0026] According to some other aspects of the present invention, the acceleration device is configured as a solid propellant rocket or a solid rocket booster, respectively.

[0027] A solid propellant rocket or solid rocket is a rocket with a rocket engine that uses a solid propellant such as a fuel, particularly a plastic or resin material, and an oxidizer, particularly a nitrate or perchlorate. The solid fuel and oxidizer are uniformly mixed and filled into the rocket. A liner is provided between the shell and the propellant. The purpose of the liner is to protect the shell because high temperatures will be generated during the combustion process. The solid particle mass burns in a predictable manner to produce exhaust gases. The nozzle size is calculated to maintain the design chamber pressure while generating thrust from the exhaust gases. Once ignited, a simple solid rocket cannot be shut down because the solid rocket contains all the ingredients required for combustion in the chamber, and all the ingredients are burned in the chamber. More advanced solid rockets can be throttled, and can also be extinguished, and then ignited again by controlling the nozzle geometry or by using a pressure relief port. In addition, pulse rockets that can be burned in stages and can be ignited on command are available. Modern designs can also include maneuverable nozzles for guidance, avionics, recovery hardware such as parachutes, self-destruct mechanisms, APUs, controllable tactical motors, controllable steering and attitude control motors, and thermal management materials.

[0028] The advantage of a solid propellant rocket is that the forces for accelerating the carriage device do not need to be supported by the aircraft fuselage. Therefore, the forces for accelerating the carriage device are not transmitted to the external structure and the aircraft fuselage is not pushed away. In an embodiment with a second release door, the second release door can be opened in addition to the first release door so that the exhaust gases can better leave the aircraft fuselage.

[0029] In addition, the solid propellant rocket can be configured to provide a sustained acceleration so that the carriage is ejected a long distance from the aircraft fuselage while the aircraft fuselage is on the ground, and the carriage falls to the ground after being released from the aircraft fuselage. Thus, when the carriage is a long distance away, the explosion of the fuel tank will not damage the aircraft fuselage.

[0030] According to some other aspects of the invention, the carriage device includes at least two solid propellant rockets, which are located at opposite end regions of the carriage device and are oriented to opposite directions, so that the carriage device can be accelerated in two opposite directions.

[0031] For example, the aircraft may further include a second fuel tank that is independent of the fuel tank and integrated into the wing of the aircraft. For example, the fuel tank is configured as a cryogenic tank for storing hydrogen. For example, the second fuel tank is configured for storing kerosene.

[0032] 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.

[0033] According to some other aspects of the present invention, the method further comprises closing the first release door after the fuel tank has been released from the aircraft fuselage. In particular, the first release door is closed during flight at a normal flight speed or at a reduced flight speed. In addition, the first release door can be closed at any desired altitude.

[0034] According to some other aspects of the invention, the disconnection includes accelerating the carriage device relative to the aircraft fuselage by the acceleration device. Therefore, the carriage device can be ejected / ejected from the aircraft fuselage. In particular, when the acceleration device is configured as a solid propellant rocket, the solid propellant rocket will be ignited and the fuel tank carriage device will be ejected from the aircraft fuselage.

[0035] Optionally, the method may begin with the step of detecting a fuel tank leak. For example, the leak may be detected by a user or a hydrogen detection system located at or coupled to the fuel tank.

[0036] In some embodiments, the method further comprises switching the fuel supply from the fuel tank to a second fuel tank that is independent of the fuel tank and is not released. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] The invention is explained in more detail below based on an exemplary embodiment indicated in a schematic diagram, in which:

[0038] 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;

[0039] Figure 2 A schematic diagram showing a carriage device carrying two fuel tanks according to another embodiment of the present invention;

[0040] Figure 3 A schematic diagram of an aircraft fuselage according to another embodiment of the present invention is shown, wherein: Figure 2 The carriage device is released;

[0041] Figure 4 Shows Figure 3 A schematic diagram of an aircraft fuselage, wherein the carriage device has been ejected / ejected from the aircraft fuselage;

[0042] Figure 5A schematic diagram showing a solid propellant rocket according to another embodiment of the present invention when it is used to accelerate a carriage device;

[0043] Figure 6 A schematic diagram of an aircraft according to another embodiment of the present invention is shown;

[0044] Figure 7 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

[0045] 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.

[0046] In the figures of the drawings, elements, features and components which are identical, have the same function and have the same effect are each provided with the same reference numerals, unless stated otherwise.

[0047] Figure 1 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.

[0048] The aircraft fuselage 1 comprises an outer structure 3, a mounting arrangement 4, a first openable release door 5, a rail system 7, a reversible quick release element 8 and a second release door 9. The outer structure 3 may comprise frames and stringers.

[0049] The mounting device 4 is configured to releasably fix a carriage device 6 for carrying a fuel tank 2 inside the outer structure 3, in particular in the inner tank compartment. Here, the illustrated carriage device 6 carries two fuel tanks 2, for example but not limited to this number. In addition, the mounting device 4 comprises a rail system 7 for guiding the carriage device 6. Optionally, the rail system 7 may comprise rollers (not shown) or similar elements for improving the sliding of the carriage device 6. In particular, the rail system 7 is configured as a conventional cargo platform for storing cargo containers or the like.

[0050] In addition, the mounting device 4 includes a reversible quick release element 8, which locks the carriage device 6 in a fixed state and is electromechanically or hydraulically driven to release the carriage device 6. Therefore, the quick release element 8 can be operated semi-automatically. For example, a hydrogen detection system (not shown) can be positioned at the mounting device 4 and / or the first release door 5 or connected to the mounting device 4 and / or the first release door 5, and when a hydrogen leak is detected, the hydrogen detection system can enable a signal for informing the pilot. The quick release element 8 and the first release door 5 can be enabled by the pilot. After being enabled by the pilot, the carriage device 6 is automatically released through the first release door 5.

[0051] The first openable release door 5 separates the inner tank compartment of the outer structure 3 from the outside. The first release door 5 is positioned relative to the mounting device 4 so that when the mounting device 4 releases the carriage device 6, the fuel tank 2 is released through the first release door 5. Here, the first openable release door 5 is positioned on the lateral side 3a of the outer structure 3, Figure 1 In the embodiment of the invention, the lateral side is the right-hand side of the external structure 3, so that the fuel tank 2 slides out of the aircraft fuselage 1 by a lateral force relative to the longitudinal axis of the aircraft fuselage 1. Thereby, the first openable release door 5 is hinged to the external structure 3 and is opened by a hydraulic pivot mechanism. Here, the first release door 5 is illustrated 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 first release door 5 is configured as a conventional landing gear door, wherein the size and functionality of the first release door 5 can be scaled according to any requirements. In this example, the first release door 5 is hinged at an upper section of the first release door 5, so that the first release door 5 opens upwards.

[0052] The second openable release door 9 is positioned on the opposite side of the outer structure 3 relative to the first release door 5. Basically, the second release door 9 is constructed like the first release door 5. In particular, the second release door 9 has the same dimensions as the first release door 5 and is positioned relative to the mounting device 4 so that the fuel tank 2 can also be released through the second release door 9 when necessary. The release of the fuel tank 2 through the first release door 5 or the second release door 9 can be selected by the control unit or the user, in particular the pilot.

[0053] Like the above-described landing gear doors, the first release door 5 and the second openable release door 9 are designed to be reclosable, in particular reclosable during flight.

[0054] Figure 2 A schematic diagram of a carriage device 6 carrying two fuel tanks 2 according to another embodiment of the present invention is shown.

[0055] The exemplary carriage device 6 is configured to carry two fuel tanks 2 having a cylindrical shape. The two fuel tanks 2 are fixed to the carriage device 6 by a rod assembly or a frame, respectively. The carriage device 6 accordingly comprises two sliding beams or guide rails, which are configured to slide in a rail system, in particular in a rail system 7. The carriage device 6 is also configured to be fixed at the rail system 7 by the mounting device 4 in a releasable manner.

[0056] Preferably, the carriage device 6 comprises an acceleration device 14 for ejecting the carriage device 6 together with the fuel tank 2 fixed to the carriage device 6. The acceleration device 14 can be configured as a solid propellant rocket (see Figure 5 ).exist Figure 2 In the embodiment, the carriage device 6 comprises four acceleration devices 14, which are located at opposite end regions of the carriage device 6 and are oriented to opposite directions, so that the carriage device 6 can be accelerated in two opposite directions. For example, the two opposite directions correspond to the longitudinal axes of the two sliding beams. The four acceleration devices 14 are arranged at each end region of the two sliding beams.

[0057] Furthermore, the two sliding beams may comprise rollers 15 to improve the sliding of the carriage arrangement 6 .

[0058] Figure 3 and Figure 4 A method according to another embodiment of the present invention is shown. Figure 2 Schematic diagram of an aircraft fuselage 1 with a carriage device 6 .

[0059] Specifically, in Figure 3 middle, Figure 2 The carriage device 6 is released, wherein Figure 4 In the embodiment of the present invention, the carriage device 6 has been ejected / ejected from the aircraft fuselage.

[0060] Figure 3 and Figure 4 The aircraft fuselage 1 and Figure 1 The aircraft fuselage 1 of FIG. 1 differs in that a portion of the aircraft fuselage 1 is lined with a refractory lining 10 for retaining flames and a portion of the inner side of the outer structure 3 comprises a flame deflector shield 11. In particular, these portions correspond to the inner side of the first and second release doors 5, 9 and to the wall surrounding the carriage device 6.

[0061] In addition, a flameless pressure relief device 12 for maintaining flame is disposed inside both the first openable release door 5 and the second openable release door 9, and is configured to cover an opening 13 in the outer structure 3 when the first release door 5 or the second release door 9 is opened, such as Figure 3The flameless pressure relief device 12 at the first release door 5 is opened or destroyed when the carriage device 6 leaves the aircraft fuselage 1 through the opening 13. Figure 3 and Figure 4 In the illustrated case, the flameless pressure relief device 12 at the first release door 5 has been penetrated. The flameless pressure relief device 12 at the second release door 9 remains during the release of the carriage device 6 through the first release door 5.

[0062] Figure 5 A schematic diagram of a solid propellant rocket 14 according to another embodiment of the present invention is shown when it is used to accelerate the carriage device 6. The solid propellant rocket 14 is an example of an acceleration device 14 because it can be used, for example Figure 2 Slide device.

[0063] A solid propellant rocket 14 or solid rocket is a rocket having a rocket engine that uses solid propellants such as fuel and oxidizer. The solid propellant rocket 14 includes a nozzle 16, a pressure chamber 17, and an igniter 18. The solid particle mass burns in a predictable manner to produce exhaust gases. The size of the nozzle 16 is calculated to maintain the design chamber pressure while generating thrust from the exhaust gases. Once ignited, a simple solid rocket 14 cannot be shut down because the solid rocket 14 contains all the ingredients required for combustion within the pressure chamber 17, where all the ingredients are burned. Modern designs may also include steerable nozzles for guidance, avionics, recovery hardware such as parachutes, self-destruct mechanisms, APUs, controllable tactical motors, controllable steering and attitude control motors, and thermal management materials.

[0064] The advantage of the solid propellant rocket 14 is that the forces for the acceleration of the carriage device 6 do not need to be supported by the aircraft fuselage 1. Therefore, the forces for the acceleration of the carriage device 6 are not transmitted to the external structure 3, and the aircraft fuselage 1 is therefore not pushed away. In the embodiment with the second release door 9, in addition to the first release door 5, the second release door 9 can also be opened so that the exhaust gases can better leave the aircraft fuselage 1.

[0065] Figure 6 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.

[0066] Aircraft 100 comprises an aircraft fuselage, in particular according to Figure 1 , Figure 3 or Figure 4The aircraft fuselage 1 of the embodiment of the present invention is provided with a carriage device 6 for carrying a fuel tank. The carriage device 6 is releasably fixed in the interior of the outer structure 3, in particular in the inner tank compartment, by a mounting device 4. A first openable releasable door 5 is located on the lateral side 3a of the aircraft fuselage 1. For example, the first releasable door 5 is located on the left hand side of the aircraft 100 relative to the flight direction of the aircraft 100 and the longitudinal axis X.

[0067] Here, the aircraft 100 includes one carriage device 6, but is not limited to this number. The aircraft 100 may also include two or more carriage devices 6. For example, two or more carriage devices 6 are arranged one behind the other and / or one above the other, so that when the aircraft fuselage 1 includes a second openable release door 9, each carriage device 6 can be released from the aircraft fuselage 1 to two opposite lateral sides 3a, such as the left-hand side or the right-hand side.

[0068] The fuel tank is fluidly connected to the standard fuel supply and delivery lines of the aircraft 100 when secured by the mounting device 4. The fuel tank supplies fuel to the engines of the aircraft 100. The fuel may be, for example, kerosene or hydrogen. Thus, the fuel tank may be configured as a cryogenic tank for storing hydrogen.

[0069] In addition, the aircraft 100 includes a second fuel tank that is independent of the fuel tank and integrated into the wing of the aircraft 100. For example, the second fuel tank is configured to store kerosene. For example, the fuel tank can store hydrogen and the second fuel tank can store kerosene. Alternatively, the fuel tank and the second fuel tank store the same fuel.

[0070] Figure 7 1 shows a flow chart of a method M for releasing a fuel tank 2 from inside an aircraft fuselage 1 in an emergency according to another embodiment of the present invention. In particular, the fuel tank 2 is released from the aircraft fuselage 1 according to Figure 1 , Figure 3 or Figure 4 Released from inside the aircraft fuselage 1.

[0071] Method M includes the steps of detecting M0, switching M1, opening M2, disconnecting M3 and closing M4.

[0072] Method M may begin by detecting M0 a leak in fuel tank 2. The leak may be detected by a user or by a hydrogen detection system positioned at or coupled to fuel tank 2.

[0073] In the optional switching M1 step, the fuel supply from the fuel tank 2 is switched 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.

[0074] In the opening M2 step, the first release door 5 is opened. The first 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 enable the quick release element and the first release door. In addition, the quick release element and / or the first release door can be enabled or controlled by an enabling system or a control and steering unit, respectively. In the case where the aircraft fuselage 1 includes a second openable release door 9, the opening M2 step can also include opening the second release door 9. The first release door and the second release door can be opened together, which means that the first release door and the second release door can be opened simultaneously or one after another.

[0075] In the disconnection M3 step, the carriage device 6 for carrying the fuel tank 2 is disconnected. The carriage device 6 is fixed to the inside of the external structure 3 by the mounting device 4 in a releasable manner relative to the mounting device 4, so that the carriage device 6 releases the aircraft fuselage 1 through the opened first release door 5. In addition, the carriage device 6 can be accelerated relative to the aircraft fuselage 1 by the acceleration device 14. Therefore, the carriage device 6 can be ejected / sprayed from the aircraft fuselage 1. For example, the acceleration device 14 can be configured as a solid propellant rocket that is ignited.

[0076] In another closing M4 step, the first release door 5 is reclosed after the fuel tank 2 has been released from the aircraft fuselage 1. In particular, the first release door 5 is closed during flight at a normal flight speed. In addition, the first release door 5 can be closed at any desired altitude. Therefore, the drive mechanism of the first release door 5 is designed to overcome higher loads.

[0077] 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 of the art.

[0078] 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.

[0079] 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.

[0080] Reference numerals list

[0081] 1 Aircraft body

[0082] 2 Fuel tanks

[0083] 3 External structure

[0084] 3a Lateral

[0085] 4 Installation

[0086] 5 First release gate

[0087] 6 Slide device

[0088] 7 Track System

[0089] 8 Reversible quick release element

[0090] 9 Second release gate

[0091] 10 Refractory lining

[0092] 11 Flame deflector shield

[0093] 12 Flameless pressure relief device

[0094] 13 Open

[0095] 14 Accelerator

[0096] 15 Roller

[0097] 16 Nozzle

[0098] 17 Pressure Chamber

[0099] 18 Ignition

[0100] 100 Aircraft

[0101] X longitudinal axis

[0102] M-method

[0103] M0 Detection

[0104] M1 Switch

[0105] M2 Open

[0106] M3 Disconnect

[0107] 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 a carriage device (6) for carrying a fuel tank (2) inside the outer structure (3); as well as A first openable release door (5) separates the interior of the outer structure (3) from the exterior, wherein the first release door (5) is positioned relative to the mounting device (4) so ​​that when the mounting device (4) releases the carriage device (6), the fuel tank (2) is released through the first release door (5).

2. The aircraft fuselage (1) according to claim 1, wherein: The first openable release door (5) is positioned on a lateral side (3a) of the outer structure (3).

3. Aircraft fuselage (1) according to claim 1 or 2, wherein: The mounting device (4) comprises a rail system (7) for guiding the carriage device (6).

4. Aircraft fuselage (1) according to one of the preceding claims, wherein: The mounting device (4) comprises a reversible quick-release element (8) which locks the carriage device (6) in a fixed state and is driven electromechanically, magnetically, hydraulically or pneumatically to release the carriage device (6).

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

6. Aircraft fuselage (1) according to one of the preceding claims, further comprising a second openable release door (9) which is positioned on the opposite side of the outer structure (3) relative to the first release door (5).

7. Aircraft fuselage (1) according to one of the preceding claims, wherein: At least one of the first openable release door (5) and the second openable release door (9) is configured to be reclosable, in particular reclosable during flight.

8. 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 carriage device (6) for carrying a fuel tank (2), wherein the carriage device (6) is releasably secured by the mounting device (4) in the interior (inner tank compartment) of the outer structure (3).

9. The aircraft (100) according to claim 8, wherein: The fuel tank (2) is fluidly connected to the aircraft's standard fuel supply and delivery lines when secured by the mounting device (4).

10. The aircraft (100) according to claim 8 or 9, wherein: The carriage device (6) comprises an acceleration device (14) for ejecting the carriage device (6) together with a fuel tank (2) fixed to the carriage device (6).

11. The aircraft (100) according to claim 10, wherein: The acceleration device (14) is configured as a solid propellant rocket.

12. The aircraft (100) according to claim 10 or 11, wherein: The carriage device (6) comprises at least two solid propellant rockets (14), which are located at opposite end regions of the carriage device (6) and are oriented in opposite directions, so that the carriage device (6) can be accelerated in two opposite directions.

13. A method (M) for releasing a fuel tank (2) from the interior of an aircraft fuselage, in particular an aircraft fuselage (1) according to one of claims 1 to 7, in an emergency situation, the method (M) comprising: opening (M2) a first release door (5) which separates the interior from the exterior of an outer structure (3) of an aircraft fuselage (1); as well as A carriage device (6) for carrying a fuel tank (2) is disconnected (M3), wherein the carriage device (6) is releasably fixed to the interior of the external structure (3) by a mounting device (4) relative to the mounting device (4), so that the carriage device (6) releases the aircraft fuselage (1) through the opened first release door (5).

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

15. The method (M) according to claim 13 or 14, wherein: The disconnection (M3) comprises accelerating the carriage device (6) relative to the aircraft fuselage (1) by means of an acceleration device (14).

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