Carrying device, propulsion arrangement, aircraft and method for providing a carrying device for a propulsion system of an aircraft

Abstract

The invention relates to a carrying device, a propulsion arrangement, an aircraft and a method for providing a carrying device for a propulsion system of an aircraft. In order to provide a more efficient carrying device for a propulsion system, a carrying device is provided, comprising at least three wall elements, a thrust unit interface and a wing interface. The at least three wall elements are arranged for being part of a protection shell enclosing at least a part of a fuel cell stack, which fuel cell stack powers a propulsion unit of the propulsion system. The thrust unit interface is configured for holding the propulsion unit. The wing interface is configured for mounting the carrying device to a wing of the aircraft. Both the thrust unit interface and the wing interface are connected to the at least three wall elements by an attachment. The attachment provides a direct load introduction from the thrust unit interface and the wing interface to a plane of at least one of the three wall elements.

Description

Technical Field

[0001] This invention relates to support structures for propulsion systems, and more specifically, to load-bearing devices, propulsion arrangement structures, aircraft, and methods for providing load-bearing devices. Background Technology

[0002] Propulsion systems, such as those used in aircraft, are typically enclosed by a support structure also known as a pod. The pod transfers the thrust of the propulsion system to the aircraft. Therefore, a pod can comprise a load-transferring frame consisting of longitudinal and planar elements. However, alternative propulsion systems may have different constructions, which could lead to incompatibility with conventional pod structures. Summary of the Invention

[0003] Therefore, it may be necessary to provide a more efficient load-bearing device for the propulsion system.

[0004] The objective of this invention is achieved through the technical solution of the main aspects of this invention; other embodiments are incorporated in the secondary aspects of this invention. It should be noted that the aspects of this invention described below are also applicable to carrier devices, propulsion arrangement structures, aircraft, and methods for providing carrier devices.

[0005] According to the present invention, a carrier for a propulsion system of an aircraft is provided. The carrier has a main structure comprising at least three wall elements, a thrust unit connector, and a wing connector. The at least three wall elements are arranged as part of a protective shell for enclosing at least a portion of a fuel cell stack, which powers the thrust unit of the propulsion system. The thrust unit connector is configured to hold the thrust unit. The wing connector is configured to mount the carrier to the wing of the aircraft. Both the thrust unit connector and the wing connector are connected to the at least three wall elements via attachments, wherein the attachments provide direct load introduction in the plane from the thrust unit connector and the wing connector to at least one of the three wall elements.

[0006] As an advantage, the protective shell can be used as a structural component of the load-bearing device. As an advantage, the protective shell, i.e., at least three wall elements, can be combined with the thrust unit joint and wing joint of the load-bearing device as a primary structural component. As an advantage, the protective shell or at least three wall elements can be used as a substitute for the anti-torsion box of the load-bearing device, a component of the anti-torsion box, or as a supplement to the anti-torsion box of the load-bearing device. As a result, weight is reduced, and the FC stack is equivalent to the heaviest component of the propulsion arrangement structure including the load-bearing structure.

[0007] According to one example, the attachment is arranged to provide direct load introduction at at least one of the three wall elements in a direction parallel to the plane of at least one wall element.

[0008] As an advantage, it allows for better introduction of loads onto the plane of the wall element.

[0009] According to one example, the thrust unit joint and / or wing joint includes a truss providing longitudinal force transmission members. Attachments are provided as at least one connection point. The at least one connection point is configured to receive the longitudinal force transmission members and distribute their point loads across at least one of at least three wall elements.

[0010] As an advantage, the combination of longitudinal force transmission components and surface force transmission components allows for optimization of the weight of longitudinal force transmission components through surface force transmission components.

[0011] As an advantage, at least three wall elements can replace the truss components and the anti-torsion box components. As an advantage, at least three wall elements form part of the truss structure of the anti-torsion box. As an advantage, at least three wall elements can replace the components of the anti-torsion box. As an advantage, the protective shell forms the anti-torsion box.

[0012] According to one example, the device also includes a sealing wall element. The sealing wall element is configured to isolate the lower portion of the fuel cell stack within the protective casing, as well as at least three wall elements, from the surrounding environment in a way that prevents gas leakage. The sealing wall element can be connected to at least three wall elements such that the sealing wall element is isolated from load paths within the at least three wall elements.

[0013] As an advantage, it protects the critical power source of the FC reactor from the loads of the load-bearing device. As another advantage, the enclosure's closed-wall elements can have thinner walls while not bearing loads, and the enclosure can therefore be designed with reduced weight.

[0014] According to one example, the device also includes at least one fireproof wall element, wherein the at least one fireproof wall element separates the fuel cell stack from the thrust unit joint and / or wing joint, and the at least one fireproof wall element is configured for fire protection.

[0015] As an advantage, a safer load-bearing device is provided. As an advantage, a lighter and fire-resistant load-bearing device is provided.

[0016] According to one example, the protective casing includes a bottom insertion chamber, allowing the fuel cell stack to be inserted from the bottom surface of the protective casing.

[0017] As an advantage, it facilitates the replacement of fuel cells without compromising the structural stability of the supporting device.

[0018] According to the present invention, a propulsion arrangement structure is also provided. This arrangement structure includes a support device according to one of the foregoing examples, a propulsion system having a thrust unit and at least one fuel cell stack. The propulsion system is supported by the support device. At least one fuel cell stack is housed by a protective casing. At least one fuel cell stack is connected to the thrust unit to provide power for driving the thrust unit.

[0019] As an advantage, a lighter and more stable propulsion arrangement structure was achieved.

[0020] According to the present invention, an aircraft is also provided. The aircraft includes: a frame having a fuselage and at least one wing; and at least one propulsion arrangement structure according to a previous example. The at least one propulsion arrangement structure is mounted to at least one wing via a wing joint to apply thrust to the frame to move the aircraft.

[0021] As an advantage, lighter aircraft result in lower energy consumption.

[0022] According to the present invention, a method is provided for providing a support device for a propulsion system of an aircraft, the support device having a main structure. The method includes the following steps:

[0023] - Provide at least three wall elements,

[0024] - Provide thrust unit couplings, and

[0025] - A wing joint is provided, wherein at least three wall elements are arranged as part of a protective shell for enclosing at least a portion of a fuel cell stack that powers a thrust unit of a propulsion system, wherein the thrust unit joint is configured to hold the thrust unit, wherein the wing joint is configured to mount a load-bearing device to the wing of an aircraft, and wherein both the thrust unit joint and the wing joint are connected to the at least three wall elements by attachments, wherein the attachments provide direct load introduction in the plane from the thrust unit joint and the wing joint to at least one of the three wall elements.

[0026] Depending on the type of propulsion system, such as a turboprop engine, different construction components are used as the main load-bearing structure. Some use frames and rods. Some use a torsion box consisting of panels at the top, with the frame and rods placed within it. This main structure bears all thrust and propeller loads during all normal conditions and carries the internal components. In an electric propulsion system powered by a fuel cell, the heaviest component in such a pod is the fuel cell stack. Due to operational constraints, the fuel cell stack should also be kept enclosed. The main objective is to retain the necessary components for fuel cell operation and to reduce the overall system weight by combining the two main components, the torsion box and the fuel cell enclosure / enclosure.

[0027] According to one aspect, a support structure for an aircraft propulsion unit is provided. The support structure or pod is typically composed of a frame structure with longitudinal elements or a combination of longitudinal and planar elements, providing rigidity against torsional loads on the propulsion unit; it is therefore also referred to as a "torsion box." Alternative propulsion systems have higher loads and are limited by components whose function is irreplaceable. Therefore, the aim is to retain these necessary components and use them in place of the longitudinal and planar elements to still provide the necessary rigidity against torsional loads while reducing weight.

[0028] On one hand, the fuel cell protective shell is provided as a major structural component of the aircraft.

[0029] According to one aspect, a fuel cell protective shell with the following dual functions is provided: protecting the enclosed fuel cell and providing structural support for the propulsion unit.

[0030] According to one aspect, a fuel cell enclosure pod is provided.

[0031] These and other aspects of the invention will become readily understood and elucidated with reference to the embodiments described below. Attached Figure Description

[0032] Exemplary embodiments of the present invention will now be described with reference to the following figures:

[0033] Figure 1 An example of a support device is shown schematically.

[0034] Figure 2 Another example of a support device is shown.

[0035] Figure 3 Another example of a support device and an example of a propulsion arrangement structure are shown.

[0036] Figure 4 An example of an aircraft is shown.

[0037] Figure 5 The basic steps of an example of a method for providing a load-bearing device for the propulsion system of an aircraft are shown. Detailed Implementation

[0038] Certain embodiments will now be described in more detail with reference to the accompanying drawings. In the following description, similar reference numerals are used for similar elements, even in different drawings. The descriptions provided, such as detailed constructions and elements, are intended to aid in a comprehensive understanding of the exemplary embodiments. Furthermore, well-known functions or structures are not described in detail, as such details would obscure the embodiments due to unnecessary detail. Additionally, expressions such as “at least one of…” when preceding a list of elements modify the entire list of elements, rather than modifying individual elements in the list.

[0039] Figure 1 An example of the support device 10 is shown schematically. (For use with...) Figure 1 The carrier 10 of the propulsion system 12 of the aircraft (not shown) has a main structure 14, which includes at least three wall elements 16, a thrust unit joint 18, and a wing joint 20. The at least three wall elements 16 are arranged as part of a protective shell 22 for enclosing at least a portion 24 of a fuel cell stack 26, which powers the thrust unit of the propulsion system 12. The thrust unit joint 18 is configured to hold the thrust unit. The wing joint 20 is configured to mount the carrier 10 to the wing of the aircraft. Both the thrust unit joint 18 and the wing joint 20 are connected to the at least three wall elements 16 via an attachment 28. The attachment 28 provides direct load introduction from the thrust unit joint 18 and the wing joint 20 into the plane 30 of at least one of the three wall elements 16.

[0040] The carrier 10 may also be referred to as a pod, basket, or nacelle. The carrier 10 relates to a base for mounting the propulsion system 12 to the aircraft, so that the propulsion system 12 can apply its thrust to the aircraft and is unaffected by the aerodynamic conditions of the aircraft's propulsion.

[0041] The term "propulsion system" encompasses energy supply, energy converters, and energy-thrust converters.

[0042] In one example, as a functional component, the propulsion system 12 includes a fuel supply device, a fuel cell stack 26 as part of a fuel cell system, and a thrust unit, such as a propeller or jet engine, powered by the electrical energy of the fuel cell stack 26.

[0043] In one example, the fuel is hydrogen or any other hydrogen-carrying molecule, such as methanol or other hydrocarbons.

[0044] The term "primary structure" refers to the framework of the load-bearing device 10, which is crucial for maintaining the structural integrity of the aircraft and withstanding the aerodynamic forces encountered during flight. The primary structure 14 is designed to handle the main flight loads, including weight, drag, thrust, shear force, bending moment, torque, pressure, and tension. While the primary structure 14 is critical to the operation of the aircraft, alterations to it are highly regulated processes and must strictly adhere to aviation standards.

[0045] In one example, the turboprop engine uses different types of main structures14. Some use only frames and rods, while others use a torsion box at the top, with the frames and rods placed within it. Figure 1 Not shown in the diagram. This main structure 14 bears all thrust and propeller loads during all normal conditions and carries the internal components.

[0046] The term "wall element" refers to structural components primarily used to enclose spaces, provide protection, and support loads.

[0047] In one example, at least one wall element 32 is configured to support the load acting on the load-bearing device 10 during a hard landing of the aircraft. Figure 1 Not shown in the image.

[0048] In one example, the load-bearing device 10 is configured to support the load that occurs during a hard landing of the aircraft.

[0049] In one example, at least a portion 24 of the fuel cell stack 26 is configured as an upper or lower component of the fuel cell stack 26. Figure 1 Not shown in the image.

[0050] The term "thrust unit" refers to a self-contained system that generates thrust for propelling a vehicle or aircraft. A thrust unit provides the force required to move an object forward. A thrust unit includes engine elements powered by energy from a fuel cell stack 26, which move volumetric displacement elements, such as thrusters, to generate thrust for the thrust unit.

[0051] The term "thrust unit joint" refers to the connection between a thrust unit and the structure it propels. The thrust unit joint safely transmits thrust while also accommodating connections between engine components and displacement components and energy converters.

[0052] The term "wing joint" refers to the connection between the wing of an aircraft and the load-bearing device 10. The wing joint securely connects the lift-generating load-bearing device 10 to the rest of the aircraft. The wing joint 20 also transfers the forces and loads of the load-bearing device 10 to the aircraft structure.

[0053] In one example, the wing joint 20 is connected to the wing box of the aircraft. Figure 1 Not shown in the image.

[0054] In one example, wing joint 20 is attached to the aircraft's wing spars. Figure 1 Not shown in the image.

[0055] The term "protective housing" refers to chambers, enclosures, cavities, storage devices, spaces, housings, enclosures, shells, boxes, housings, outer shells, closures, protective fabrics, tubes, sleeves, and sheaths designed to protect the delicate and sensitive components of the fuel cell stack 26 from various environmental factors. The protective housing 22 is used to contain any gases, hydrogen, oxygen, or fluids leaking from the fuel cell stack 26 and to retain these gases within the enclosure of the protective housing 22.

[0056] In one example, the protective shell 22 is for preventing hydrogen gas leakage because hydrogen is a small molecule gas that is highly diffusive relative to fractures, cracks and tears in the material.

[0057] In one example, the protective shell 22 is a component of the carrier device 10, such as Figure 1 As shown in the image.

[0058] In one example, the support device 10 is a combined structure formed by the protective shell 22 and the anti-torsion box of the support device 10.

[0059] In one example, the load-bearing device 10 is a combined structure consisting of a protective shell 22 and a truss formed by a thrust unit joint 18 and a wing joint 20. Figure 1 Not shown in the image.

[0060] In one example, the protective housing 22 includes more than three wall elements 16, such as four, five, seven, eight or more wall elements. Figure 1 Not shown in the image.

[0061] Wall elements can also be referred to as walls.

[0062] In one example, the wall elements of the protective shell 22 are arranged as cubes, such as... Figure 1 As shown in the image.

[0063] In one example, at least three wall elements 16 are arranged in a bent shape to form an enclosure for the fuel cell stack 26. Figure 1 Not shown in the image.

[0064] In one example, at least three wall elements 16 are arranged in a U-shape to form an enclosure for the fuel cell stack 26. Figure 1 Not shown in the image.

[0065] In one example, at least three wall elements 16 are arranged in a semi-cubic shape to form an enclosure for the fuel cell stack 26. Figure 1 Not shown in the image.

[0066] In one example, the wall elements of the protective shell 22 are arranged as polyhedra, such as tetrahedrons, cubes, pentahedrons, or hexahedrons. Figure 1 Not shown in the image.

[0067] In one example, Figure 1 As not shown, component 24 of fuel cell stack 26 is configured as an upper component of fuel cell stack 26, which relates to the FC stack and the component of carrier 10 pointing in the opposite direction of gravity in the main travel direction of carrier 10, i.e., the main travel direction of the aircraft on which carrier 10 is mounted.

[0068] In one example, direct loads can also be introduced along the planes of two, three, four, or more of the three wall elements 16. Figure 1 Not shown in the image.

[0069] The term "fuel cell" refers to a device that directly converts chemical energy into electrical energy. This process occurs through an electrochemical reaction between a fuel, such as hydrogen, and an oxidant, such as oxygen, without combustion.

[0070] The term "fuel cell stack" or "FC stack" refers to a collection of individual fuel cells connected together to increase total voltage and / or power output. Multiple cells are stacked in series to achieve higher voltage. Multiple cells can be connected in parallel to increase current. The stack is the core component of a fuel cell system.

[0071] "Fuel cell" can also be called FC.

[0072] In one example, the FC stack has an upper part and a lower part. The upper part points to the upper surface of the protective shell 22 or at least three wall elements 16, while the lower part points to the bottom surface of the protective shell 22 or at least three wall elements 16.

[0073] The term “attachment” refers to any object capable of providing a direct physical connection between the thrust unit joint 18, the wing joint 20, and at least three wall elements 16.

[0074] The term "direct" refers to the direct transfer of loads without intermediate components or significant distribution to the main supporting structure. This means that the path of force is more or less straight, without any detours or circuits.

[0075] The term "load introduction" refers to the manner in which loads are applied to structural elements or systems. Load introduction can indicate the location, magnitude, direction, and distribution of forces acting on a structure.

[0076] The term "direct load introduction" combines the terms "direct" load transfer and "load introduction," meaning that the load is applied immediately and is not significantly distributed to the primary structural elements designed to support it. The load path is short and relatively uncomplicated, with very few intermediate members. The load remains concentrated at or near the point of application.

[0077] The term "plane" refers to the face, surface, or front side of a wall element.

[0078] Figure 2 Another example of the load-bearing device 10 is shown. At least one of the three wall elements 16, 32, is configured as a planar force transmission element 34 to provide a direct load path between the thrust unit joint 18 and the wing joint 20, as shown by... Figure 2 As indicated by arrow 36. At least one wall element 32 has a plane 30 between the thrust unit joint 18 and the wing joint 20, which is aligned with the thrust unit as shown by... Figure 2 The direction of the main thrust, indicated by the middle arrow 38, is aligned.

[0079] The term "surface force transmission element" refers to a flat object that distributes point loads across a surface.

[0080] The term “between” refers to the position of at least one wall element relative to the thrust unit joint 18 and the wing joint 20.

[0081] The term "primary thrust direction" refers to the main direction in which a thrust element is designed to generate the force used for propulsion. The primary thrust direction is the predetermined line of action of the thrust.

[0082] In one example, the main thrust direction 38 defines the front and rear ends of the bearing device 10, such as Figure 2 As shown in the diagram. The rear end of the carrier 10 and the rear end of the FC stack are located behind the thrust unit in the thrust direction, wherein the thrust unit and the thrust unit joint 18 are located at the front end of the carrier 10, and the wing joint 20 is located at the rear end of the carrier 10. The plane 30 of at least one wall element 32 is disposed between the thrust unit joint 18 and the wing joint 20, and transmits the load from the front end of the carrier 10 to the rear end, wherein the force is distributed on the plane 30 of at least one wall element 32. Therefore, the thrust unit joint 18 and the wing joint 20 are located in opposite positions on the carrier 10, as shown in the diagram. Figure 2 As shown in the image.

[0083] In one example, at least three planes of at least three wall elements 16 are aligned with the main thrust direction 38 of the thrust unit between the thrust unit joint 18 and the wing joint 20, such as... Figure 2 As shown in the image.

[0084] In one example, at least three planes of at least three wall elements 16, which are bent or U-shaped, are aligned with the main thrust direction 38 of the thrust unit between the thrust unit joint 18 and the wing joint 20, as shown. Figure 2 As shown in the image.

[0085] In one example, at least three planes of at least three wall elements 16, which are bent or U-shaped, are aligned with the main thrust direction 38 of the thrust unit between the thrust unit joint 18 and the wing joint 20, wherein the curvature of the U-shape or bent shape points towards the upper part of the fuel cell stack 26, such as... Figure 2 As shown in the image.

[0086] As a result, the thrust is evenly distributed across the entire plane of at least one wall element.

[0087] As an advantage, it enables a more surface-based load introduction for the load-bearing device and reduces point loads. As an advantage, the entire surface of the protective shell is used for load distribution between the thrust unit joint 18 and the wing joint 20.

[0088] exist Figure 2 In the example, the attachment 28 is arranged to provide direct load introduction at at least one of the three wall elements 16, at a direction parallel to the plane 30 of the at least one wall element 32.

[0089] The term "direction parallel to a plane" refers to a line contained within a plane 30 of at least one wall element 32.

[0090] In one example, the attachment 28 is positioned at the edge of the wall element so that the force flow is not orthogonally introduced into the plane 30 of the wall element.

[0091] In one example, Figure 2 Not shown, the load includes at least one of the group consisting of thrust load, torsional load and vibration load.

[0092] As a result, excessive loads can be absorbed by the wall elements of the protective shell. As an advantage, the complexity of the load-bearing device is reduced, and the number of load-absorbing measures is decreased.

[0093] exist Figure 2 In the example, the attachment 28 is arranged at at least three wall elements 16, such that Figure 2 The torsional load, not shown, travels a longer direct path between the thrust unit joint 18 and the wing joint 20 compared to the thrust load.

[0094] The term “longer” refers to the length of the load path passing through the surface plane of the protective shell 22 or at least three wall elements 16.

[0095] In one example, the attachment 28 introduces loads only at the corners of the wall elements, such that torsional loads act on the diagonal of the plane of at least one wall element 32 or at least three wall elements 16.

[0096] As an advantage, torsional loads are absorbed more effectively by at least three wall elements 16 or at least one wall element 32 or protective shell 22.

[0097] exist Figure 2 In the example, the thrust unit joint 18 and / or wing joint 20 include a truss 40 providing a longitudinal force transmission member 42. An attachment 28 is configured with at least one connection point 44. The at least one connection point 44 is configured to receive the longitudinal force transmission member 42 and distribute its point load on at least one wall element 32 of at least three wall elements 16.

[0098] The term "truss" refers to a structural frame made of interconnected members arranged primarily in a triangular pattern, designed to provide strength and stiffness while minimizing weight. The members primarily bear axial forces rather than bending forces, which helps to construct a lighter structure compared to solid beams or other structures.

[0099] The term "longitudinal force transfer member" refers to a structural element designed to primarily bear forces acting along its longitudinal axis, i.e., its length. Longitudinal force transfer members transmit loads within a structure and, in particular, resist tensile and compressive forces. Longitudinal force transfer members 42 include frames, rods, columns, chords, and webs.

[0100] In one example, truss 40 includes a torsion-resistant box for supporting device 10.

[0101] The term "connection point" refers to the anchorage point of the longitudinal force transmission member 42, where the longitudinal force transmission member 42 can be fixed.

[0102] In one example, the truss 40 also includes a torsion box, and at least three wall elements 16 replace areas or portions of the torsion box. Figure 2 Not shown in the image.

[0103] In one example, the longitudinal force transmission member 42 is fixed by bolts at at least one connection point 44, such as Figure 2 As shown in the image.

[0104] In one example, at least one connection point 44 is constructed as a reinforcing anchor point for an element of the truss 40, the reinforcing anchor point being located at the corner of the wall element of the protective shell 22, such as... Figure 2 As shown in the image.

[0105] In one example, at least one connection point 44 is formed as an eyelet, the eyelet being located at at least one wall of at least three wall elements 16, such as Figure 2As shown in the image.

[0106] The term "point load" refers to a force concentrated at a specific coordinate.

[0107] In one example, at least one wall element 32 separates the anti-torsion box located between the thrust unit joint 18 and the wing joint 20.

[0108] exist Figure 2 In the example, at least one of the three wall elements 16, at least one wall element 32, provides an additional support portion 46 to replace the longitudinal force transmission element in the truss 40 of the thrust unit joint 18 and / or the wing joint 20.

[0109] The term "additional support portion" refers to a surface component of at least one wall element 32 that may replace a Z-shaped strut in a truss, or a web or chord member.

[0110] In one example, the additional support portion is formed to complement the shape of the truss 40. Figure 2 Not shown in the image.

[0111] As an advantage, the weight of the truss is further reduced. As an advantage, the load transfer between at least one wall element 32 and the truss is optimized, and parasitic loads are minimized. As an advantage, a more enclosed and complete main structure for the load-bearing device is achieved. As an advantage, the torsional deformation of the load-bearing device is further reduced.

[0112] exist Figure 2 In the example, at least one of the at least three wall elements 16, at least one wall element 32, includes a reinforcing element 48. The reinforcing element 48 is shaped to enhance the ability of at least one wall element 32 to resist torsional loads and thrust loads.

[0113] The term "reinforcing element" refers to elements used to enhance the structural integrity and durability of wall components.

[0114] In one example, at least one wall element 32 has a plane 30 provided with a truss structure formed of wall material, such as Figure 2 As shown in the image.

[0115] In one example, at least one wall element 32 has a honeycomb structure to improve stiffness. Figure 2 Not shown in the image.

[0116] In one example, the lateral support wall elements within the protective housing 22 are configured to support at least three wall elements 16. Figure 2 Not shown in the image.

[0117] In one example, the reinforcing element 48 is also configured as a wall in the truss 40 of the thrust unit joint 18 and the wing joint 20. Figure 2 Not shown in the image.

[0118] In one example, the reinforcing element 48 is shaped to enhance the ability of at least one wall element 32 to resist aerodynamic loads. Figure 2 Not shown in the image.

[0119] As an advantage, the stiffness of the protective shell 22 and at least three wall elements against torsional loads and forces is further improved.

[0120] In one example, at least three wall elements 16 are arranged in an inclined conical manner, wherein the tip of the cone points toward the thrust element.

[0121] In one example, some of the at least three wall elements 16 are shaped as diagonally tapering parallelograms extending toward the thrust element, such as... Figure 2 As shown in the image.

[0122] In one example, the connection area between at least three wall elements 16 is configured for load transfer while preventing gas leakage.

[0123] As an advantage, the protective casing is designed to prevent hydrogen leakage under high loads.

[0124] Figure 3 Another example of the carrier device 10 and an example of the propulsion arrangement structure 100 are shown. The device 10 includes a sealing wall element 50. The sealing wall element 50 is configured to isolate the fuel cell stack 26 within the protective housing 22 from the lower component 52 and at least three wall elements 16 in a gas-leakage-proof manner, thereby isolating it from the surrounding environment 54. The sealing wall element 50 can be connected to at least three wall elements 16 such that the sealing wall element 50 is isolated from load paths within the at least three wall elements 16.

[0125] The term "closed wall element" refers to a cover or enclosure of the protective shell 22 of the FC stack, used to seal the FC stack within the protective shell 22 comprising at least three wall elements 16. The cover or enclosure is applied from the bottom side of the carrier 10 and the FC stack, as this is the primary direction of entry for the FC stack into the carrier 10. The at least three wall elements 16 form the upper outer shell component, wherein the closed wall element 50 forms the lower outer shell component, as... Figure 3 As shown in the image.

[0126] In one example, the sealing wall element 50 is arranged as part of a protective shell 22 for enclosing at least a portion 24 of the fuel cell stack 26, such as Figure 3 As shown in the image.

[0127] In one example, the enclosed wall element 50 is configured as part of a protective shell 22 for enclosing at least a portion 24 of the fuel cell stack 26, such as Figure 3 As shown in the image.

[0128] In one example, the enclosure element 50 is configured as the bottom component or bottom surface of the protective shell 22 for enclosing at least a portion 24 of the fuel cell stack 26. The term "isolation" refers to the protective shell 22 that isolates the FC stack from the environment outside the carrier box, such as... Figure 3 As shown in the image.

[0129] In one example, the FC stack releases leaked hydrogen gas. This hydrogen gas needs to be collected, which is provided by a protective casing 22 to prevent gas leakage.

[0130] In one example, the FC stack can be removed from the carrier 10 by opening the closed wall element 50 and disassembling the FC stack.

[0131] The term "lower component" refers to the portion of the FC stack opposite to its upper component, with the lower component 52 pointing toward the ground and the direction of the enclosed wall element 50.

[0132] The term “surrounding environment” refers to the atmospheric environment, airport environment, or any environmental conditions in which the carrier 10 operates.

[0133] In one example, the enclosed wall element 50 includes an FC stack manifold element for gas supply and exhaust of the FC stack.

[0134] In one example, the closed-wall element 50 is a manifold element of the FC stack.

[0135] In one example, the base component of the FC stack forms a closed-wall element 50.

[0136] In one example, at least three wall elements 16 and a closing wall element 50 of the protective casing 22 enclose the FC stack in a protective gas. Figure 3 Not shown in the image.

[0137] In one example, at least one wall element 32 and / or enclosed wall element 50 includes a passage for gas supply or exhaust for the FC stack or the chamber of the FC stack.

[0138] In one example, the exhaust passage can be located at the wall element to allow hydrogen gas to escape from the protective housing 22. Figure 3 Not shown in the image.

[0139] Return to reference Figure 2 The device 10 also includes at least one fire-resistant barrier element 56. The at least one fire-resistant barrier element 56 will... Figure 2 The fuel cell stack 26, which is not visible in the middle, is separated from the thrust unit joint 18 and / or the wing joint 20, and at least one fire wall element 56 is configured for fire protection.

[0140] The term "fireproof wall element" refers to a wall element that resists fire caused by fuel in the FC stack and thus protects critical infrastructure of the load-bearing device 10, such as the thrust unit and wing joint 20, and also protects the aircraft's wings from the effects of fuel cell fire.

[0141] In one example, at least one fireproof wall element 56 carries a load.

[0142] In one example, the fireproof wall element 56 resists the temperatures generated by a hydrogen fire. Figure 3 Not shown in the image.

[0143] exist Figure 3 In the example, the protective housing 22 includes a bottom insertion chamber 58, which allows the fuel cell stack 26 to be inserted from the bottom surface of the protective housing 22.

[0144] In one example, the load-bearing component of the support device 10 is located at the upper part of the fuel cell and is formed by the joint of the truss 40 and at least three wall elements 16 of the protective shell 22. To avoid disrupting this construction, the FC stack is inserted from the lower part 52 or the bottom side of the support device 10.

[0145] Figure 3 An example of a propulsion arrangement 100 is also shown. The propulsion arrangement 100 includes a support device 110 according to one of the foregoing examples, a propulsion system 120 having a thrust unit 122 and at least one fuel cell stack 124. The propulsion system 120 is supported by the support device 110. At least one fuel cell stack 124 is housed by a protective casing 126. At least one fuel cell stack 124 is connected to the thrust unit to provide power for driving the thrust unit.

[0146] In one example, the propulsion system 120 includes an electric thruster driven by a PEM fuel cell.

[0147] Figure 4 An example of an aircraft 200 is shown. The aircraft 200 includes: a frame 202 having a fuselage 204 and at least one wing 206; and at least one propulsion arrangement structure 210 according to the previous example. The at least one propulsion arrangement structure 210 is mounted to at least one wing 206 via a wing joint 212 to apply thrust to the frame 202 to move the aircraft 200.

[0148] Figure 5 The basic steps of an example of a method for providing a load-bearing device for a propulsion system of an aircraft are shown. The method 300 for providing a load-bearing device for a propulsion system of an aircraft includes the following steps:

[0149] - In the first step 302, at least three wall elements are provided.

[0150] - In the second step 304, a thrust unit connector is provided.

[0151] - In the third step 306, a wing connector is provided. At least three wall elements are arranged as part of a protective shell for enclosing at least a portion of a fuel cell stack that powers the thrust unit of the propulsion system. The thrust unit connector is configured to hold the thrust unit. The wing connector is configured to mount a load-bearing device to the wing of the aircraft. Both the thrust unit connector and the wing connector are connected to the at least three wall elements via attachments. These attachments provide direct load introduction in the plane from the thrust unit connector and the wing connector to at least one of the three wall elements.

[0152] In the example of the method, a portion of the truss of the bearing device is replaced by the wall element of the protective shell of the FC stack.

[0153] It should be noted that embodiments of the invention have been described with reference to different subjects. In particular, some embodiments are described with reference to method claims, while other embodiments are described with reference to apparatus claims. However, based on the above and following description, those skilled in the art will understand that, unless otherwise indicated, any combination of features related to different subjects is contemplated and disclosed with this application, in addition to any combination of features belonging to one type of subject matter. However, all features can be combined to provide synergistic effects beyond a simple superposition of features.

[0154] Although the invention has been illustrated and described in detail in the accompanying drawings and the foregoing description, such illustrations and descriptions are intended to be illustrative or exemplary, and not restrictive. The invention is not limited to the disclosed embodiments. Other variations of the disclosed embodiments can be understood and implemented by those skilled in the art when practicing the claimed invention through a study of the drawings, the disclosure, and the dependent claims.

[0155] In the claims, the word "comprising" does not exclude other elements or steps, and the indefinite article "a" or "one" does not exclude multiple. A single processor or other unit can perform the functions of several items recited in the claims. The mere fact that certain measures are recited in mutually different dependent claims does not indicate that a combination of these measures cannot be used to exert an advantage. Any reference numerals in the claims should not be construed as limiting the scope.

Claims

1. A support device (10) for a propulsion system (12) of an aircraft, the support device (10) having a main structure (14) comprising: At least three wall elements (16); Thrust unit connector (18); as well as Wing joint (20); The at least three wall elements are arranged as part of a protective shell (22) for enclosing at least a portion (24) of the fuel cell stack (26), which provides power to the propulsion unit of the propulsion system. The thrust unit assembly is configured to hold the thrust unit. The wing joint is configured to mount the load-bearing device to the wing of the aircraft; and The thrust unit joint and the wing joint are both connected to the at least three wall elements via an attachment (28), wherein the attachment provides direct load introduction in the plane (30) from the thrust unit joint and the wing joint to at least one of the three wall elements (32).

2. The apparatus according to claim 1, wherein, At least one of the three wall elements is configured as a planar force transmission element (34) to provide a direct load path (36) between the thrust unit joint and the wing joint; and The plane of at least one wall element is aligned with the main thrust direction (38) of the thrust unit between the thrust unit joint and the wing joint.

3. The apparatus according to claim 1 or 2, wherein, The attachment is configured to provide direct load introduction at at least one of the three wall elements in a direction parallel to the plane of the at least one wall element.

4. The apparatus according to claim 1, 2 or 3, wherein, The load includes at least one of the following: Thrust load; Torsional load; and Vibration load.

5. The apparatus according to any one of the preceding claims, wherein, The attachments are arranged at the at least three wall elements such that the torsional load travels a longer direct path between the thrust unit joint and the wing joint compared to the thrust load.

6. The apparatus according to any one of the preceding claims, wherein, The thrust unit joint and / or the wing joint includes a truss (40) providing a longitudinal force transmission member (42); and The attachment is provided as at least one connection point (44), wherein the at least one connection point is configured to receive the longitudinal force transmission member and distribute the point load of the longitudinal force transmission member on at least one of the at least three wall elements.

7. The apparatus according to claim 6, wherein, At least one of the at least three wall elements provides an additional support portion (46) to replace the longitudinal force transmission element in the truss of the thrust unit joint and / or the wing joint.

8. The apparatus according to any one of the preceding claims, wherein, At least one of the at least three wall elements includes a reinforcing element (48), wherein the reinforcing element is shaped to enhance the ability of the at least one wall element to resist torsional loads and thrust loads.

9. The apparatus according to any one of the preceding claims further includes a sealing wall element (50); in, The enclosed wall element is configured to isolate the fuel cell stack in the protective shell from the lower component (52) and the at least three wall elements in a way that prevents gas leakage, thereby isolating it from the surrounding environment (54); and The closed wall element can be connected to at least three wall elements, thereby isolating the closed wall element from the load paths within the at least three wall elements.

10. The apparatus according to any one of the preceding claims further comprises at least one fireproof wall element (56), wherein, The at least one fireproof wall element separates the fuel cell stack from the thrust unit joint and / or the wing joint, and the at least one fireproof wall element is configured for fire protection.

11. The apparatus according to any one of the preceding claims, wherein, The protective casing includes a bottom insertion chamber (58) that allows the fuel cell stack to be inserted from the bottom surface of the protective casing.

12. A propulsion arrangement structure (100), comprising: The support device (110) according to any one of claims 1 to 11. The propulsion system (120) has a thrust unit (122) and at least one fuel cell stack (124). The propulsion system is supported by the bearing device. The at least one fuel cell stack is housed by a protective casing; and The at least one fuel cell stack is connected to the thrust unit to provide power for driving the thrust unit.

13. An aircraft (200), comprising: A frame (202) having a fuselage (204) and at least one wing (206); as well as At least one propulsion arrangement structure (210) according to claim 12. The at least one propulsion arrangement is mounted to the at least one wing via a wing joint (212) to apply thrust to the frame to move the aircraft.

14. A method (300) for providing a support device for a propulsion system of an aircraft, the support device having a main structure, the method (300) comprising the following steps: Provide (302) at least three wall elements; Provide (304) thrust unit connector; as well as Provided (306) a wing joint, wherein the at least three wall elements are arranged as part of a protective shell for enclosing at least a portion of a fuel cell stack that powers a thrust unit of the propulsion system, wherein the thrust unit joint is configured to hold the thrust unit, wherein the wing joint is configured to mount the load-bearing device to the wing of the aircraft, and wherein both the thrust unit joint and the wing joint are connected to the at least three wall elements by an attachment, wherein the attachment provides direct load introduction in the plane from the thrust unit joint and the wing joint to at least one of the three wall elements.

Images