Fuselage structure for aircraft, method of assembling fuselage structure and aircraft comprising fuselage structure

Abstract

The invention provides an aircraft fuselage structure (100) comprising a first fuselage section (101) and a second fuselage section (102) connected to the first fuselage section (101), the second fuselage section (102) comprising at least one first fuselage cabin (105a, 105b) extending the first fuselage section (101) in the longitudinal direction, the first fuselage section (101) and the first fuselage cabin (105a) comprising a circumferential flange (111), the invention relates to a first fuselage section (101) and a first fuselage cabin (105a, 105b) which are arranged at the longitudinal ends (120a, 120b) of the first fuselage section (101) and the first fuselage cabin (105a, 105b) and extend radially into the first fuselage section (101) and the first fuselage cabin (105a), a plurality of fastening means being provided to extend through a counter flange (111) of the first fuselage section (101) and the first fuselage cabin (105a) during assembly to achieve a press-fit connection therebetween, the first fuselage cabin (105a) provides a storage space for the at least one tank structure (107a, 107b); the invention also provides a method of assembling an aircraft fuselage structure (100) and an aircraft comprising a fuselage structure (100).

Description

Technical Field

[0001] The present invention relates to an aircraft fuselage structure, a method for assembling the fuselage structure, and an aircraft including the fuselage structure.

[0002] Although the invention can be used in a variety of applications, it will be explained in more detail in conjunction with aircraft and the problems on which it is based. However, the described apparatus and methods are equally applicable to vehicles in all sectors of the transportation industry, such as road vehicles, rail vehicles, or watercraft. Background Technology

[0003] Hydrogen-powered aircraft represent a key technology for reducing emissions during aviation, necessitating technological modifications to the systems used in such aircraft. One such system is the energy storage system or tank installed within the aircraft's fuselage. Some aircraft utilize articulated hinges or doors that allow the loading and removal of components such as large, cylindrical cryogenic hydrogen tanks, but employ a design principle based on a combination of locking or latching mechanisms and articulated doors. Because these aircraft are designed for routine opening and closing of doors using hinges or latches, relatively heavy components are used, and the articulated doors are not designed for continuous load transfer. Therefore, the use of this design for planned installation and / or removal of major aircraft components (such as tanks or tank structures) is limited, as this would significantly impact aircraft performance in terms of weight and could potentially lead to unnecessary increases in product costs. Summary of the Invention

[0004] In this context, one object of the present invention is to find an aircraft fuselage structure and a method for assembling the fuselage structure, thereby facilitating the assembly, disassembly and reassembly of the fuselage for the installation and removal of tanks, particularly liquid hydrogen tanks, during production and during maintenance or replacement in operation, thus minimizing the associated process time and thereby ensuring continuous load transfer during operation.

[0005] This objective is achieved by an aircraft fuselage structure having the features of claim 1, a method for assembling the fuselage structure having the features of claim 10, and an aircraft including a fuselage having the features of claim 15.

[0006] According to a first aspect of the invention, an aircraft fuselage structure is provided, comprising: a first fuselage segment and a second fuselage segment connected to the first fuselage segment, the second fuselage segment including at least one first fuselage compartment extending longitudinally from the first fuselage segment, the first fuselage segment and the fuselage compartment including circumferential flanges disposed at longitudinal ends of the first fuselage segment and the fuselage compartment and extending radially within the first fuselage segment and the first fuselage compartment, wherein, during assembly, a plurality of fastening devices are provided to extend through the flanges for mating of the first fuselage segment and the fuselage compartment to achieve a press-fit connection between the first fuselage segment and the first fuselage compartment, and wherein the first fuselage compartment provides storage space for at least one tank structure. The advantage of this is that it provides space for the arrangement of tank structures, particularly hydrogen tank structures, within the fuselage, thereby allowing easy assembly of the fuselage segment before or after tank installation, wherein the fuselage structure can continuously transfer loads within the assembled fuselage.

[0007] Another aspect of the invention relates to a method for assembling an aircraft fuselage structure, particularly a fuselage structure according to the invention. The method includes the following steps: providing a first fuselage section; providing a first fuselage compartment for a second fuselage section; aligning the first fuselage section and the first fuselage compartment in a circumferential plane to connect the first fuselage compartment to the first fuselage section to extend the first fuselage section longitudinally along the aircraft fuselage; connecting the first fuselage compartment to the first fuselage section by a plurality of fastening devices; and arranging a tank structure within the first fuselage compartment; the plurality of fastening devices extending through flanges for mating at the mutually facing longitudinal ends of the first fuselage compartment and the first fuselage section.

[0008] The advantage of this approach is that the integration of the fuselage structure with the tank structures and systems allocated to the fuselage, particularly the hydrogen tank system, can be completed quickly and efficiently. It avoids concealed installation of the tanks and only requires a single structural opening in the fuselage structure. Another advantage of this method is that the tank structures are easily accessible during assembly or disassembly, significantly reducing manufacturing and maintenance time and associated costs.

[0009] Furthermore, the rear section of the fuselage is connected to the longitudinal end of the second fuselage section by a plurality of fastening devices extending through flanges provided at the longitudinal ends of the second fuselage section and the rear section facing each other.

[0010] Another aspect of the invention relates to an aircraft comprising the fuselage structure of the invention, wherein a first fuselage section is preferably configured as a pressurized cargo hold or passenger cabin, a second fuselage section is configured as an unpressurized tank compartment, and pressure bulkheads are arranged between the first and second fuselage sections. This arrangement offers the advantage of easy access to the tanks and tank structures, resulting in reduced manufacturing and maintenance workload. The fuselage structure also allows for reduced unused space at specific locations within the fuselage that require access for the installation, removal, and maintenance of the tank structures within the fuselage. Access to the installation space is possible through the open fuselage structure, allowing for rapid removal and reinstallation of the tank structures without modification or repair of the fuselage structure. As another advantage, in airline operations, downtime for maintenance or replacement of the tank structures is reduced because the fuselage structure can be removed without modification, with the fuselage structure of the invention described herein significantly facilitating disassembly.

[0011] Advantageous embodiments and further developments will become clear from the further dependent claims and from the description with reference to the accompanying drawings.

[0012] According to another aspect of the invention, the at least one tank structure is configured as a pressurized hydrogen storage tank structure. Its advantage lies in that the fuselage structure according to the invention provides efficient utilization of available space, thereby increasing the storage capacity for hydrogen, particularly liquid or gaseous hydrogen, required for hydrogen-powered aircraft.

[0013] According to one embodiment of the present invention, the circumferential surface of the first fuselage compartment forms a shell, also referred to as the outer skin of the fuselage, and flanges are attached to the skin in a form-fit manner. This has the advantages that flanges for axial and shear load transfer can be incorporated during the manufacture of the fuselage compartment or fuselage section, and the flanges can be adapted to the corresponding geometry and design of the compartment. Therefore, the manufacturing efficiency of the main fuselage structure is improved, and the manufacturing steps and related workload required for adaptation are reduced.

[0014] According to another embodiment of the invention, the first fuselage compartment has a circular or non-circular configuration and is aligned with the first fuselage section in a circumferential plane. This has the advantage that this arrangement allows for the combination of circular or non-circular fuselage compartments with similar or different shapes to achieve a fuselage structure that can accommodate tank structures of similar or different shapes, particularly for storing hydrogen within the fuselage. This maximizes the use of available space within the fuselage and increases storage capacity.

[0015] According to another embodiment of the invention, the fastening device is configured as one of a tension bolt and a tapered shear bolt, wherein the fastening device can be alternately arranged circumferentially within the flange. One advantage of this embodiment is that the combination of tension bolts evenly distributed around the entire perimeter of the cabin enables assembly and disassembly, allowing axial loads occurring between fuselage sections or cabins during aircraft operation to be transferred in a distributed rather than discrete manner. The tapered shear bolts provide a self-centering function to compensate for elastic deformation of the fuselage and cabin due to different loading conditions, such as different lifting methods of the fuselage cabin, the presence or absence of tank structures on the fuselage cabin, and whether in a connected or disassembled state. This self-centering function allows the fuselage sections and cabins to adapt their shapes to each other during connection operations without requiring any measurement, adjustment, or modification of the cabin. Once the fuselage sections or cabins are connected, the tapered shear bolts can also be used to transfer shear loads occurring during aircraft operation from the fuselage cabins of the second fuselage section to the first fuselage section and / or to additional fuselage cabins within the second fuselage section. Because of the tension bolt tightening assembly, shear transfer can also occur through friction between the flanges. In this case, tapered shear bolts can facilitate shear transfer while still providing self-centering functionality for aligning the fuselage compartment with the fuselage section.

[0016] According to another embodiment of the invention, the first fuselage compartment of the second fuselage section defines an internal space whose shape substantially corresponds to the shape of the tank structure, wherein the tank structure includes at least one of two side-by-side storage tanks and a storage tank extending longitudinally along the second fuselage section. This has the advantage of achieving the highest possible efficiency in maximizing the volume of the tank structure, particularly for hydrogen storage, within the fuselage compartment and improving accessibility to the tank structure. Preferably, the tank structure includes multiple pipelines, particularly inlet and outlet pipelines, which are guided along one of the inner or outer surfaces of the aircraft fuselage. An advantage of the invention is the ability to quickly and efficiently install and remove the tank structure and associated tank equipment, which is particularly important for the operation of the hydrogen storage system. The open connection of the fuselage compartment allows access to the mechanical and electrical interfaces of the tank structure, particularly the tank structure for hydrogen storage. During assembly, when the fuselage section is open and accessible, it is possible to route tank structure feed lines (fuel distribution lines, fuel discharge lines, electrical harnesses, and fluid transport lines for the heat and cooling systems) through the main structure, especially the outer fuselage skin or shell, thereby improving the manufacturing efficiency and quality of fuselage structure assembly.

[0017] According to another embodiment of the invention, the first fuselage section is configured as a pressurized cabin, the second fuselage section is configured as an unpressurized cabin, and pressure bulkheads are provided, which can be arranged between the first and second fuselage sections. The advantage of this is that it provides different and separate cabins within the fuselage, thereby allowing the fuselage to be adapted to specific aircraft applications and associated space requirements.

[0018] According to another embodiment of the invention, the second fuselage section includes at least one additional fuselage compartment that extends longitudinally beyond the first fuselage compartment and is aligned with it in a circumferential plane. The at least one additional fuselage compartment also includes a circumferential flange disposed at a longitudinal end of the at least one additional fuselage compartment and extending radially within it. During assembly, multiple fastening devices are provided to extend through the flanges of the first fuselage compartment and the at least one additional fuselage compartment for mating, thereby achieving a press-fit connection between these fuselage compartments. The advantage of this is that, utilizing the aforementioned advantages, the second fuselage section can extend further longitudinally toward the rear end of the aircraft. Therefore, the fuselage structure also allows for the integration of more tanks within the fuselage in a convenient and quick assembly manner.

[0019] According to another embodiment of the invention, the fuselage structure further includes a rear end section disposed at the longitudinal end of the second fuselage section, the rear end section including a circumferential flange disposed at a longitudinal end of the rear end section facing the second fuselage section and extending radially within the rear end section. Thus, during assembly, multiple fastening devices are provided to extend through the flange for mating between the rear end section and the second fuselage section to achieve a press-fit connection between the second fuselage section and the rear end section. The advantage of this is that, utilizing the aforementioned advantages of the flanges and fastening devices, the fuselage can be completed or closed by connecting the rear end section to the second fuselage section or forming a hull of the second fuselage section, thereby allowing for easy and quick assembly and disassembly of the fuselage structure with minimal effort.

[0020] According to another embodiment of the method, the fastening device is configured as one of tension bolts and tapered shear bolts, wherein the plurality of fastening devices can be arranged alternately along the circumference of the flange. The advantage is that the combination of tension bolts and tapered shear bolts evenly distributed around the entire perimeter of the cabin enables assembly and disassembly, allowing axial loads occurring between fuselage sections or cabins during aircraft operation to be transferred in a distributed rather than discrete manner. The tapered shear bolts also provide a self-centering function to compensate for elastic deformation of the fuselage cabin due to different loading conditions, such as different lifting methods of the fuselage cabin, whether the fuselage cabin has a tank structure installed or not, and whether it is in a connected or disassembled state. This self-centering function allows the cabin and / or fuselage section to adapt their shapes to each other during connection operations without any measurement, adjustment, or modification of the cabin itself. Once the cabins are connected, the tapered shear bolts can also be used to transfer shear loads occurring during aircraft operation from one cabin to another. Shear transfer can also occur through friction between the flanges due to the tension bolt tightening assembly. In this configuration, tapered shear bolts facilitate shear transfer while still providing self-centering functionality for aligning the fuselage compartment with the fuselage section. During assembly, the tapered shear bolts are installed before the tension bolts. In the first assembly step, the tapered pin of the tapered shear bolt is inserted into the flange, extending through a hole in the flange. By tightening the tapered shear bolts, the fuselage compartment self-centers and pulls together. In the second assembly step, tension bolts are inserted into the remaining holes of the flange, alternating with the tapered shear bolts. The tension bolts are then tightened after the fuselage compartment or fuselage section is centered, ensuring a press-fit connection that allows axial loads to be transferred between the fuselage compartments or fuselage sections.

[0021] Alternatively, another tank structure can be arranged in the second fuselage section. The advantage of this is that it allows for efficient use of the space provided in the second fuselage section and increases storage capacity. However, thanks to the assembly and disassembly options of the fuselage sections, the fuselage structure of the present invention allows for complete access to the tank structure and associated supply lines during assembly and maintenance.

[0022] According to another embodiment of the method, the tank structure includes at least one of two tanks and a tank extending longitudinally along the second fuselage section, wherein arranging the tank structure includes arranging the tanks side by side and one after another. The advantage of this is that using tanks of similar or different shapes in the arrangement allows for maximizing volumetric efficiency by aligning the fuselage compartment and tank geometry, particularly for hydrogen tanks designed as pressure vessels with a circular shape to achieve optimal weight efficiency.

[0023] According to another embodiment, the method further includes the following steps: preferably connecting pipelines, particularly feed and discharge pipelines, to the tank structure before installing the tank structure into the fuselage; and guiding these pipelines along one of the inner or outer surfaces of the fuselage with the fuselage in an open state. This has the advantage of optimizing the use of available space within the fuselage and ensuring full access to the pipelines during assembly and disassembly of the fuselage during manufacturing and maintenance.

[0024] According to another embodiment, the method further includes the steps of: providing at least one additional fuselage compartment extending longitudinally along the first fuselage compartment before or after arranging the tank structure within the first fuselage compartment; aligning these fuselage compartments in a circumferential plane; and connecting the fuselage compartments by means of a plurality of fastening devices extending through flanges disposed at the mutually facing longitudinal ends of these fuselage compartments for mating. The advantage of this is that, depending on the requirements and configuration of the fuselage structure and the tank structure therein, the adaptation of the fuselage structure, particularly the longitudinal extension of the second fuselage section, can be achieved in an efficient and time-saving manner without incurring excessive workload during manufacturing and assembly.

[0025] According to another embodiment, the method further includes the steps of: providing a rear end section of the fuselage; and connecting the rear end section of the fuselage to the second fuselage section by a plurality of fastening devices extending through flanges disposed at the opposing longitudinal ends of the second fuselage section and the rear end section of the fuselage for mating. The advantage of this is that, utilizing the aforementioned advantages regarding flanges and fastening devices, the fuselage can be completed or enclosed by connecting the rear end section to the second fuselage section or forming a compartment of the second fuselage section. This facilitates easy and rapid assembly and disassembly of the fuselage structure while reducing workload. In a particular embodiment, the rear end section may form part of the first fuselage section or a further fuselage compartment connected to the first fuselage section, or form an insert fuselage compartment and be connected thereto using flanges and fastening devices in the manner described above. Attached Figure Description

[0026] The invention will be explained in more detail with reference to the exemplary embodiments shown in the accompanying drawings.

[0027] Figure 1a , 1b A schematic view of a fuselage structure according to an embodiment of the present invention is shown.

[0028] Figure 2a , 2b A schematic cross-sectional view of a fuselage structure according to an embodiment of the present invention is shown, wherein the tank structures are arranged in different ways within the fuselage structure.

[0029] Figure 3 Another embodiment of the fuselage structure according to the present invention is illustrated schematically;

[0030] Figure 4a , 4b A detailed view of a portion of the fuselage structure according to another embodiment of the present invention is shown;

[0031] Figure 5 A fuselage structure according to another embodiment of the present invention is shown; and

[0032] Figure 6 The steps of a method for assembling the fuselage structure of an aircraft according to an embodiment of the present invention are illustrated schematically. Specific Implementation

[0033] The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification. These drawings illustrate embodiments of the invention and, together with the description, serve to explain the principles of the invention. Other embodiments of the invention and many anticipated advantages of the invention will be readily understood as they become clearer with reference to the detailed description. Elements in the drawings are not necessarily drawn to scale relative to each other. In the drawings, unless otherwise stated, similar reference numerals denote similar or functionally similar components.

[0034] While specific embodiments are shown and described herein, those skilled in the art will understand that various alternatives and / or equivalent implementations may be used in place of the specific embodiments shown and described without departing from the scope of the invention. Generally, this application is intended to cover any modifications or variations to the specific embodiments discussed herein.

[0035] In the accompanying drawings, unless otherwise specified, the same elements, features and components having the same function and effect are given the same reference numerals.

[0036] Figure 1a , 1b A schematic view of a fuselage structure 100 according to an embodiment of the present invention is shown. The fuselage structure 100 includes a first fuselage section 101 and a second fuselage section 102 connected to the first fuselage section, wherein the second fuselage section 102 extends longitudinally toward the rear end section 103 of the aircraft fuselage 104 from the first fuselage section 101. Figure 1a In the middle, the second fuselage section 102 includes a fuselage compartment 105a connected to the first fuselage section 101 and the rear aft section 103, while Figure 1b In the second fuselage section, two fuselage compartments 105a and 105b are interconnected and located between the first fuselage section 101 and the rear aft section 103. The fuselage compartments 105a and 105b define a compartment 106 for accommodating tank structures 107a and 107b, particularly hydrogen storage tanks. Figure 1aIn the illustrated embodiment, two tank structures 107a and 107b are arranged side by side, wherein the second tank structure 107b is not visible. Figure 1a In this configuration, a tank system 108 is located near each tank 109 of tank structures 107a and 107b, and this tank system is arranged in the area of ​​the second fuselage section 102 facing the first fuselage section 101. Figure 1b In the illustrated embodiment, the storage tanks 109 are arranged one after another in the second fuselage section 102, and an additional storage tank 109 is located in the rear aft section 103 of the aircraft fuselage 104. Figure 1a The illustrated embodiment incorporates tank structures 107a and 107b, while... Figure 1b In the illustrated embodiment, a first fuselage compartment 105a is connected to a first fuselage section 101 and a tank structure 107a is arranged therein, and then a second fuselage compartment 105b is circumferentially connected to the first fuselage compartment.

[0037] The fuselage structure 100 allows for the reduction of unused space within the aircraft fuselage, which inevitably requires access via an open fuselage access point to the installation site for the installation, removal, and maintenance of tank structures 107a and 107b within the aircraft fuselage 104. This assembly allows for the rapid removal and reinstallation of fuselage sections 105a and 105b without modification to the fuselage structure itself. Consequently, in airline operations, downtime for maintaining or replacing tank structures 107a and 107b is reduced because the second fuselage section 102 can be removed without requiring modifications. Figure 1a and 1b The fuselage structure 100 shown avoids concealed installation of the tanks 109 and tank systems 108. In cases where the system architecture requires more than one tank 109, unnecessary removal of installation components is avoided to allow for the removal of, for example, defective components. During the assembly of the fuselage structure 100 and the installation of the tank structures 107a, 107b, the open space inside the aircraft fuselage 104 effectively allows for the parallel execution of installation work for the tank structures 107a, 107b and the tank system 108. The fuselage structure 100 also improves accessibility to each tank structure 107a, 107b and associated tank system 108 due to the open fuselage compartments 105a, 105b. Work performed through the openings in the fuselage compartments 105a, 105b during assembly also provides operators with significantly better lighting and logistical conditions, as well as more ergonomic working positions during manufacturing.

[0038] Figure 2a and 2b A schematic cross-sectional view of the fuselage structure 100 of the present invention is shown, wherein tank structures 107a and 107b are arranged in different ways within the fuselage structure 100. Figure 2a Showing according to Figure 1a A cross-sectional view of the fuselage structure 100, and Figure 2b Corresponding to Figure 1b Examples of implementations. In Figure 1a The diagram shows two tank structures 107a and 107b arranged side by side, and fuselage compartments 105a and 105b having non-circular cross-sections. Figure 2b The fuselage compartment has a circular cross-section and accommodates a single tank structure 107a, 107b. The other tank structures 107a, 107b can be positioned longitudinally along the fuselage structure 100. Figure 2b Following the tank structure 107a shown. In both embodiments, tank structures 107a and 107b are mounted on a horizontally extending floor structure 110 within fuselage compartments 105a and 105b, thereby ensuring that tank structures 107a and 107b are safely and balancedly positioned within fuselage compartments 105a and 105b.

[0039] Figure 3 Another embodiment of the fuselage structure 100 according to the invention is schematically shown. The fuselage structure 100 includes a pressurized first fuselage section 101 serving as a cargo hold or passenger cabin, which is spaced apart from a second fuselage section 102 by a pressure bulkhead 121. The second fuselage section 102 is arranged circumferentially to the first fuselage section 101. The second fuselage section 102 consists of two fuselage compartments 105a and 105b, which are connected by flanges 111 extending radially within the fuselage compartments 105a and 105b and mating in the assembled state. The connection of the fuselage compartments 105a and 105b is achieved using tension bolts 112 and tapered shear bolts 113 inserted into the flanges 111. The tension bolts 112 and tapered shear bolts 113 will combine... Figure 4a and 4bA more detailed description follows. Two tank structures 107a and 107b are disposed within the second fuselage section 102, each including a pressurized hydrogen storage tank 109 and a hydrogen tank system 108 connected thereto. The two tank structures are positioned such that the hydrogen tank systems 108 of each tank structure 107a and 107b face each other. The hydrogen tank systems 108 are connected to multiple pipelines 114a and 114b, such as fuel distribution lines, fuel discharge lines, electrical wiring harnesses, and fluid transport lines for the thermal and cooling systems. The pipelines 114a and 114b are guided within the second fuselage section 102 and extend vertically relative to the longitudinal extension direction of the aircraft fuselage 104. The pipelines 114a and 114b are guided through the outer shell 115 of the aircraft fuselage 104, and the fuselage hulls 105a and 105b provide the main structure of the aircraft fuselage 104. Pipelines 114a and 114b, exiting the fuselage 104, are further guided along the outer shell 115 of the fuselage 104 and extend horizontally along the longitudinal direction of the aircraft to supply hydrogen to the aircraft's propulsion system. Because pipelines 114a and 114b are guided to the exterior of the second fuselage section 102, the use of internal space is optimized, and accessibility to pipelines 114a and 114b is improved. The modular configuration of the second fuselage section 102 allows for efficient and ergonomic operation during the assembly, disassembly, and maintenance of pipelines 114a and 114b via open fuselage compartments 105a and 105b.

[0040] Figure 4a and 4b A detailed view of a portion of a fuselage structure 100 according to another embodiment of the present invention is shown. Figure 4aThe diagram illustrates tapered shear bolts 113 used in the assembly of fuselage structure 100. The tapered shear bolts 113 include: a tapered pin 116 extending through a hole 117 provided in a flange 111 attached to fuselage compartments 105a, 105b; and shear bolt nuts 118 for securing and tightening the tapered shear bolts 113. The tapered shear bolts 113 are evenly distributed around the entire perimeter of fuselage compartments 105a, 105b and provide a self-centering function to compensate for elastic deformation of the fuselage compartments 105a, 105b that may occur due to different load conditions, such as different hoisting methods of fuselage compartments 105a, 105b, whether the fuselage compartments 105a, 105b are installed or not, and whether they are in a connected or disassembled state. The self-centering function allows the two fuselage bays 105a and 105b to adapt their shapes to each other during the connection operation without requiring any measurement, adjustment, or modification to the fuselage bays 105a and 105b themselves. Once the fuselage bays 105a and 105b are connected, the tapered shear bolts 113 can also be used to transfer shear loads generated during aircraft operation from one fuselage bay 105a or 105b to the other. Shear transfer can also occur through friction between flanges 111 due to the tightening assembly of the tension bolts 112. In this case, the tapered shear bolts 113 can facilitate shear transfer while still providing the self-centering function for aligning the fuselage bays 105a and 105b and the fuselage sections 101 and 102, for example, as... Figure 1a and 1b As shown in the image.

[0041] Figure 4b The tension bolt 112 extends through the aforementioned flange 111. After the fuselage compartments 105a, 105b or fuselage sections 101, 102 are aligned, the tension bolt nut 119 is tightened to ensure the press-fit connection of the fuselage compartments 105a, 105b or fuselage sections 101, 102, which can transmit axial loads between the fuselage compartments 105a, 105b and fuselage sections 101, 102.

[0042] Figure 5 A fuselage structure 100 according to another embodiment of the invention is shown, illustrating a portion of a circumferential mating portion between two fuselage compartments 105a, 105b. The fuselage compartments 105a, 105b are provided with flanges 111 extending radially inward into the fuselage compartments 105a, 105b, each flange 111 including a plurality of holes 117 aligned during assembly. These holes 117 are for accommodating the mating portion. Figure 4a and 4bThe alternating arrangement of tapered shear bolts 113 and tension bolts 112. Flanges 111 are connected to the longitudinal ends 120a, 120b of each fuselage compartment 105a, 105b or fuselage sections 101, 102, and are press-fitted, for example, riveted, to the outer peripheral structure of the fuselage compartment 105a, 105b. (See from...) Figure 4a and 4b As can be seen, flange 111 can also be configured to accommodate tapered shear bolts 113 and tension bolts 112. During assembly, in the first assembly step, the tapered pins 116 of the tapered shear bolts 112 are inserted into flange 111 and extend through holes 117 provided in the flange. By tightening the shear bolt nuts 118, fuselage compartments 105a and 105b are self-aligned and pulled together by the tapered pins 116. In the second assembly step, tension bolts 112 are inserted into the remaining holes 117 of flange 111 in an alternating arrangement with the tapered shear bolts 113. After the fuselage compartments 105a and 105b or fuselage sections 101 and 102 are aligned, the tension bolt nuts 119 are subsequently tightened, ensuring a press-fit connection of the fuselage compartments 105a and 105b or fuselage sections 101 and 102, thereby enabling the transmission of axial loads.

[0043] Figure 6The steps of a method for assembling an aircraft fuselage structure 100 according to an embodiment of the present invention are schematically illustrated. In a first step 201, a first fuselage compartment 105a of a first fuselage segment 101 and a second fuselage segment 102 is provided, and in a further step 202, the first fuselage compartment 105a is connected to the first fuselage segment 101 to extend the first fuselage segment 101 longitudinally along the aircraft fuselage 104. In step 203, tank structures 107a, 107b are arranged within the first fuselage compartment 105a, and in step 204, at least one second fuselage compartment 105b of the second fuselage segment 102 is provided. The first fuselage compartment 105a and the second fuselage compartment 105b are aligned in the orbital plane, and the at least one second fuselage compartment 105b is connected to the first fuselage compartment 105a by a plurality of fastening devices that extend through mating flanges 111 provided at the longitudinal ends 120a, 120b of the first and second fuselage compartments 105a, 105b facing each other. In a further assembly step 205, the tapered pin 116 of the tapered shear bolt 113 is inserted into the flange 111 and extends through a hole 117 provided in the flange, wherein the fuselage compartments 105a, 105b are self-centered and pulled together by tightening the shear bolt nut 118 of the tapered shear bolt 113. In a further step 206, tension bolts 112 are inserted into the remaining holes 117 of flange 111 in an alternating manner with tapered shear bolts 113, and tension bolt nuts 119 are tightened after the fuselage compartments 105a, 105b or fuselage sections 101, 102 are aligned to ensure a press-fit connection of the fuselage compartments 105a, 105b or fuselage sections 101, 102, thereby enabling the transmission of axial loads. After the fuselage compartments 105a and 105b of the second fuselage section 102 are assembled, in a further step 207, the rear end section 103 of the aircraft fuselage 104 is connected to the longitudinal ends 120a and 120b of the second fuselage section 102 by a plurality of fastening devices. The plurality of fastening devices extend through the mating flanges 111 provided at the longitudinal ends 102a and 102b of the second fuselage section 102 and the rear end section 103 facing each other, and are connected by tapered shear bolts 113 and tension bolts 112 in the assembly manner described above.

[0044] In the foregoing detailed description, various features have been combined together in one or more examples to simplify the disclosure. However, it should be understood that the above description is intended to be illustrative rather than restrictive. It is intended to cover all alternatives, modifications, and equivalents. Many other examples will become clear to those skilled in the art upon reading the foregoing specification. These embodiments were chosen and described in order to best explain the principles of the invention and its practical application, thereby enabling others skilled in the art to best utilize the invention and its various embodiments with various modifications suitable for the particular purpose contemplated.

[0045] Reference number list

[0046] 100 fuselage structure

[0047] 101 First Fuselage Section

[0048] 102 Second Fuselage Section

[0049] 103 backend segment

[0050] 104 aircraft fuselage

[0051] 105a and 105b fuselage

[0052] 106 compartments

[0053] 107a and 107b tank structures

[0054] 108-tank system

[0055] 109 storage tank

[0056] 110 Floor Structure

[0057] 111 flange

[0058] 112 tension bolt

[0059] 113 Conical shear bolt

[0060] Pipelines 114a and 114b

[0061] 115 Housing

[0062] 116 Tapered Pin

[0063] 117 holes

[0064] 118 Shear bolts and nuts

[0065] 119 Tension bolts and nuts

[0066] 120a, 120b longitudinal ends

[0067] 121 Pressure Chamber Bulkhead

[0068] 202 steps

[0069] 203 steps

[0070] 204 steps

[0071] 205 steps

[0072] 206 steps

[0073] 207 steps

Claims

1. A fuselage structure (100) for an aircraft, the fuselage structure comprising: A first fuselage section (101) and a second fuselage section (102) connected to the first fuselage section (101), the second fuselage section (102) including at least one first fuselage compartment (105a) extending longitudinally from the first fuselage section (101), the first fuselage section (101) and the first fuselage compartment (105a) including circumferential flanges (111) arranged at the longitudinal ends (120a, 120b) of the first fuselage section (101) and the first fuselage compartments (105a, 105b). The first fuselage section (101) and the first fuselage compartment (105a) are provided with a plurality of fastening devices for connecting flanges (111) extending through the first fuselage section (101) and the first fuselage compartment (105a) to achieve a press fit connection between the first fuselage section (101) and the first fuselage compartment (105a), and wherein the first fuselage compartment (105a) provides storage space for at least one tank structure (107a, 107b).

2. The fuselage structure (100) according to claim 1, wherein the at least one tank structure (107a, 107b) is configured as a pressurized hydrogen storage tank (109).

3. The fuselage structure (100) according to claim 1 or 2, wherein the circumferential surface of the first fuselage compartment (105a) forms the shell (115) of the aircraft fuselage (104), and the flange (111) is attached to the shell (115) in a form-fit manner.

4. The fuselage structure (100) according to any one of claims 1 to 3, wherein the first fuselage compartment (105a, 105b) has a circular or non-circular configuration and is aligned with the first fuselage section (101) in a circumferential plane.

5. The fuselage structure (100) according to any one of claims 1 to 4, wherein the fastening device is configured as one of a tension bolt (112) and a tapered shear bolt (113), wherein the fastening device can be alternately arranged in the flange (111) in the circumferential direction.

6. The fuselage structure (100) according to any one of claims 1 to 5, wherein a first fuselage compartment (105a) defines an internal space, the shape of which substantially corresponds to the shape of a tank structure (107a, 107b), wherein the tank structure (107a, 107b) comprises at least one of two side-by-side storage tanks (109) and a storage tank (109) extending longitudinally along the first fuselage compartment (105a), wherein the tank structure (107a, 107b) preferably comprises a plurality of pipelines (114a, 114b), particularly feed pipelines and discharge pipelines, the plurality of pipelines (114a, 114b) being guided along one of the inner or outer surfaces of the aircraft fuselage (104).

7. The fuselage structure (100) according to any one of claims 1 to 6, wherein the first fuselage section (101) is configured as a pressurized compartment, the second fuselage section (102) is configured as a non-pressurized compartment, and wherein a pressure bulkhead (121) is provided, the pressure bulkhead being disposed between the first fuselage section (101) and the second fuselage section (102).

8. The fuselage structure (100) according to any one of claims 1 to 7, wherein the second fuselage section (102) includes at least one additional fuselage compartment (105b), the at least one additional fuselage compartment extending longitudinally from the first fuselage compartment (105a) and aligned with the first fuselage compartment (105a) in a circumferential plane, the at least one additional fuselage compartment (105b) including a circumferential flange (111), the circumferential flange of the at least one additional fuselage compartment being arranged in the fuselage section (105a). At least one additional fuselage compartment (105b) extends radially at its longitudinal ends (120a, 120b) and within the at least one additional fuselage compartment (105b), and during assembly, a plurality of fastening devices are provided to extend through flanges (111) for mating through the first fuselage compartment (105a) and the at least one additional fuselage compartment (105b) to achieve a press-fit connection between the first fuselage compartment (105a) and the at least one additional fuselage compartment (105b).

9. The fuselage structure (100) according to any one of claims 1 to 8, wherein the fuselage structure further comprises a rear end section (103) disposed at a longitudinal end (120a, 120b) of the second fuselage section (102), the rear end section (103) comprising a circumferential flange (111) disposed at a longitudinal end (120a, 120b) of the rear end section (103) facing the second fuselage section (102) and extending radially within the rear end section (103), and providing a plurality of fastening devices for extending through the flange (111) of the rear end section (103) and the second fuselage section (102) for mating to achieve a press-fit connection between the second fuselage section (102) and the rear end section (103).

10. A method for assembling an aircraft fuselage structure (100), particularly a fuselage structure (100) according to any one of claims 1 to 9, the method comprising the following steps: A first fuselage section (101) and a first fuselage compartment (105a) of a second fuselage section (102) are provided. The first fuselage section (101) and the first fuselage compartment (105a) are aligned in a circumferential plane to connect the first fuselage compartment (105a) to the first fuselage section (101) to extend the first fuselage section (101) longitudinally along the fuselage (104). The first fuselage compartment (105a) is connected to the first fuselage section by a plurality of fastening devices. 101), tank structures (107a, 107b) are arranged within the first fuselage compartment (105a); the plurality of fastening devices are configured as one of tension bolts (112) and tapered shear bolts (113), arranged alternately along the circumference of flanges (111), extending through flanges (111) for mating at the longitudinal ends (120a, 120b) of the first fuselage compartment (105a) and the first fuselage section (101) facing each other.

11. The method of claim 10, wherein the tank structures (107a, 107b) comprise at least one of two storage tanks (109) and a storage tank (109) extending longitudinally along the second fuselage section (102), wherein arranging the tank structures (107a, 107b) comprises: The storage tanks (109) are arranged side by side and one after another.

12. The method according to claim 10 or 11, wherein the method further comprises the following step: Preferably, before the tank structures (107a, 107b) are installed into the first fuselage compartment (105a), the pipelines (114a, 114b), particularly the feed pipelines and discharge pipelines, are connected to the tank structures (107a, 107b), and the pipelines (114a, 114b) are guided along one of the inner or outer surfaces of the aircraft fuselage (104).

13. The method according to any one of claims 10 to 12, wherein, The method further includes the following steps: providing at least one additional fuselage compartment (105b) extending longitudinally along the first fuselage compartment (105a) before or after arranging the tank structures (107a, 107b) within the first fuselage compartment (105a); aligning the first fuselage compartment (105a) and the additional fuselage compartment (105b) in a circumferential plane; and connecting the first fuselage compartment (105a) and the additional fuselage compartment (105b) by a plurality of fastening devices extending through flanges (111) for mating provided at the longitudinally facing ends (120a, 120b) of the first fuselage compartment (105a) and the additional fuselage compartment (105b).

14. The method according to any one of claims 10 to 13, wherein, The method further includes the steps of: providing a rear end section (103) of the fuselage; and connecting the rear end section (103) of the fuselage to the second fuselage section (102) by means of a plurality of fastening devices extending through flanges (111) for mating located at the longitudinal ends (120a, 120b) of the second fuselage section (102) and the rear end section (103) of the fuselage facing each other.

15. An aircraft comprising a fuselage structure (100) according to any one of claims 1 to 9, wherein a first fuselage section (101) is preferably configured as a pressurized cargo compartment or passenger compartment, a second fuselage section (102) is configured as an unpressurized tank compartment, and a pressure tank wall is disposed between the first fuselage section (101) and the second fuselage section (102).

Images