Electronic arrangement for an aircraft and method for providing such an electronic arrangement

Abstract

Electronic arrangement for an aircraft (1), which - a structural section (5) of a structure of an aircraft (1), which - a stiffening arrangement (8) of interconnected elongated longitudinal and transverse stiffening elements (6, 7), - an outer skin (9) arranged on one side of the stiffening arrangement (8) and attached to the longitudinal and transverse stiffening elements (6, 7), wherein a surface of the outer skin (9) facing away from these forms an outer surface (11) of the structural section (5), and - has one or more skin fields (12), each of which is a section of the outer skin (9) defined between two immediately adjacent longitudinal stiffening elements (6) and two immediately adjacent transverse stiffening elements (7), and - comprising one or more structural elements (15), each of which has a frame (16) and one or more electronic components (20a-c, 26, 27) attached to the frame (16), wherein in at least one of the skin panels (12) in the outer skin (9) an opening (13) is formed that is completely arranged in the skin panel (12) and for each of the skin panels (12) with one of the openings (13) a separate associated structural element (15) is provided, which is designed and detachably attached with its frame (16) to the outer skin (9) in the corresponding skin panel (12) on the side of the outer skin (9) opposite the outer surface (11) in such a way that it closes the corresponding opening (13) in such a way that the skin panel (12) has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the direction of extension of the outer skin (9) in the skin panel (12) as the same skin panel (12) without the corresponding opening (13), wherein the frame (16) of at least one of the structural elements (15) has a through-opening (24) which connects a side of the frame (16) located on the side of the outer surface (11) with an opposite side of the frame (16) and through which at least one of the electronic components (20a-c, 26, 27) of the respective structural element (15) passes at least partially, wherein each of these structural elements (15) has at least one second sealing device which is designed and arranged in such a way as to prevent air from passing through the through-opening (24) of the frame (16).

Description

[0001] The present application relates to an electronic arrangement for an aircraft or an aircraft comprising a structural section of a structure of an aircraft with a stiffening arrangement of interconnected elongated longitudinal and transverse stiffening elements and an outer skin and an electronic component.

[0002] Aircraft typically have one or more antennas or other electronic devices that can establish a radio link between the aircraft and external devices or participants on the ground or in the air, such as other aircraft or satellites, or that perform other functions, such as sensors or laser devices.

[0003] In the prior art, such antennas or other electronic devices are mounted externally on the fuselage, often by creating a minimal opening in the outer skin, so that they protrude from the fuselage into the surrounding air. This increases the aircraft's drag, which in turn increases fuel consumption. Furthermore, for each aircraft type, each electronic device, and each position of the electronic device, the aerodynamic pressure and suction forces (also known as aeroloads) acting on the outer surfaces of the electronic device must be recalculated, resulting in significant calculation and certification costs. In addition, some antenna elements or other electronic devices are attached to the fuselage via a base plate, which is relatively heavy and, together with the actual antenna element, contributes to the overall weight of the fuselage.the actual other electronic device is exposed to the ambient air.

[0004] DE 10 2018 109 723 A1 discloses an antenna arrangement for an aircraft. The antenna arrangement comprises a structural section of an aircraft, an antenna element, a cover transparent to radio waves, and a structural element. The structural section has an arrangement of interconnected elongated longitudinal and transverse stiffening elements and an outer skin, which is arranged on one side of the arrangement of longitudinal and transverse stiffening elements and is attached to the longitudinal and transverse stiffening elements. A surface of the outer skin facing away from these stiffening elements forms an outer surface of the structural section. An opening is formed in the outer skin, which is closed by the cover. In the area of ​​the opening, at least one of the longitudinal stiffening elements and / or at least one of the transverse stiffening elements has a break in which the structural element is arranged and which allows the respective longitudinal or transverse stiffening element to pass through.The cross-stiffening element is divided into two sections on opposite sides of the break.

[0005] US 6,047,925 A discloses a glide path antenna for receiving information transmitted from the ground, including altitude guidance for final approach. The glide path antenna is integrated into the rear nose landing gear door and utilizes the electrical properties of the graphite / epoxy composite door.

[0006] CN 2 04 696 229 U discloses an integrated antenna design for aircraft construction. It is an antenna for permanent mounting on an aircraft. The mounting hole is internally fitted with an antenna element. The connector is inserted into the mounting hole. The antenna is connected at one end, and the electronic device is connected at the other. The antenna element is firmly attached to the connecting strip plate by bolts and plate nuts. The connecting strip plate is riveted to the long purlin and the fuselage fairing. The frame is connected to the purlin by a long, vertical fixed connection.

[0007] US 8,063,837 B1 discloses a system comprising an interposer. The interposer may include a mounting plate for attaching the interposer to the fuselage of an aircraft. The interposer may be connected to the fuselage to form a seal for maintaining pressure within the aircraft. The system may also include an antenna module. The antenna module may comprise a ground plane, an aircraft antenna, and a radar dome. The ground plane may be connected to the aircraft antenna and may be configured to allow the antenna module to be mounted to the interposer. The radar dome may be connected to the ground plane to form a housing for the antenna. The antenna module may be detachably connected to the interposer. The system may also include a connection for electrically connecting the antenna module to the aircraft's electronics.The antenna module can be separated from the interposer without destroying the seal formed between the interposer and the fuselage.

[0008] In other configurations, antenna elements of such antennas or components of other electronic systems were integrated directly into the outer skin of the aircraft fuselage by being designed as a layer of a multi-layered outer skin. However, maintenance and subsequent replacement of such antennas after manufacturing are complex, and their transmitting and receiving characteristics, as well as other functions, can be impaired by deformation of the fuselage or outer skin that occurs during aircraft operation.

[0009] It is therefore an object of the present invention to provide an electronic arrangement for an aircraft which is simple and cost-effective in design, can be easily configured to enable low air resistance of the aircraft, is easy to install and maintain and has a low weight, an aircraft with such an electronic arrangement and a method for providing such an electronic arrangement.

[0010] This problem is solved by an electronic arrangement for an aircraft having the features of claim 1, by an aircraft having the features of claim 10, and by a method having the features of claim 12. Advantageous embodiments of the electronic arrangement, the aircraft, and the method are the subject of the respective dependent claims.

[0011] According to the present invention, an electronic arrangement for an aircraft is provided, comprising a structural section of the aircraft—or more precisely, a structural section of a structure or substructure of the aircraft—and one or more structural elements, each of which has a frame, preferably rigid, and one or more electronic components attached to the frame of the respective structural element. Each of the structural elements may also have a cover to protect the electronic components. If the electronic components include an antenna element, such a cover is preferably designed to be transparent to radio waves emitted by the antenna element during operation and to radio waves that can be received by or are to be received by the antenna element.

[0012] The structural section, which may be, for example, a fuselage section of the aircraft or a section of the vertical stabilizer or wing structure of the aircraft, comprises a stiffening arrangement of interconnected elongated longitudinal and transverse stiffening elements. The stiffening arrangement of interconnected elongated longitudinal and transverse stiffening elements includes several, preferably parallel, elongated longitudinal stiffening elements and several, preferably parallel, elongated transverse stiffening elements.The longitudinal stiffening elements run at an angle to the transverse stiffening elements, with the longitudinal stiffening elements preferably extending longitudinally along the fuselage when the structural section is installed in an aircraft, and the transverse stiffening elements preferably extending circumferentially along the fuselage when the structural section is installed in an aircraft. The longitudinal stiffening elements are also referred to as stringers, and the transverse stiffening elements as frames. The longitudinal and transverse stiffening elements are preferably interconnected in a lattice-like arrangement, forming a lattice structure.

[0013] The structural section also features an outer skin, which is arranged on one side of the stiffening arrangement of longitudinal and transverse stiffening elements—or on one side of the corresponding grid arrangement—and attached to the longitudinal and transverse stiffening elements. This attachment can be direct, without any further elements between the outer skin and the respective longitudinal or transverse stiffening element, or indirect, via intermediate elements, and can differ for different longitudinal and transverse stiffening elements. For example, the outer skin may rest directly on and be attached to the longitudinal stiffening elements, while clips are arranged between the transverse stiffening elements and the outer skin, through which the outer skin is attached to the transverse stiffening elements. In any case, one of the longitudinal and transverse stiffening elements forms aThe extended surface of the outer skin, facing away from the arrangement of longitudinal and transverse stiffening elements, forms an outer surface of the structural section and, when the structural section is installed in an aircraft, of the entire aircraft. In other words, the outer skin is arranged and attached to the longitudinal and transverse stiffening elements in such a way that a first surface of the outer skin faces the stiffening arrangement of longitudinal and transverse stiffening elements, and a second surface of the outer skin, opposite the first, forms an outer surface of the structural section that, when the structural section is installed in an aircraft, faces the surroundings of the aircraft.

[0014] Furthermore, the structural section has one or more skin panels, each of which is a section of the outer skin defined between two immediately adjacent longitudinal stiffening elements and two immediately adjacent transverse stiffening elements. In other words, each skin panel extends between the two facing inner lateral edges or surfaces of two immediately adjacent longitudinal stiffening elements and between the two facing inner lateral edges or surfaces of two immediately adjacent transverse stiffening elements.This also means that none of the skin panels are located in a break that divides one of the longitudinal stiffening elements or one of the transverse stiffening elements of the stiffening arrangement into two sections on opposite sides of the break, terminating at the respective skin panel. The skin panels are accordingly defined by the normal "cells" of a lattice arrangement formed by the stiffening arrangement. It is possible that the structural section has exclusively skin panels of this configuration, or that, in addition to the aforementioned skin panels, skin panels of a different configuration are also present.

[0015] The frame of each structural element—or of the structural element if only one is provided—can, for example, be made of aluminum and, in particular, be a milled aluminum component and can, for example, be plate-shaped. One or more, and preferably all, of the electronic components of each structural element are preferably arranged such that they are located wholly or partially on the same side of the frame as the outer surface of the structural section. The electronic components can be any type of electronic component or electronic device. In particular, one, several, or all of the electronic components can be, for example, an antenna element, antenna electronics, a sensor, a laser device or part of a laser device, or a communication device or part of a communication device.

[0016] In each case, one, several, or all of the aforementioned skin panels have an opening or through-hole formed entirely within the outer skin panel. This opening or through-hole can, for example, have a circular, oval, round, polygonal, rectangular, or square shape. Accordingly, the entire opening and its boundary are located completely within the respective skin panel, and no portion of the opening lies outside the skin panel, and in particular not in the area of ​​the longitudinal and transverse stiffening elements adjacent to the skin panel or neighboring skin panels. Therefore, the longitudinal and transverse stiffening elements in the area or vicinity of the skin panel are not modified by the electronics arrangement. Furthermore, a corresponding structural element is provided separately for each skin panel containing one of the openings.This element is designed and detachably attached to the outer skin in the corresponding skin field on the side of the outer skin opposite the outer surface, in such a way that it closes the corresponding opening. This ensures that the skin field exhibits at least the same pressure tightness and at least the same resistance to tensile, compressive, and shear forces acting in the direction of extension of the outer skin within the skin field, or in the plane defined by the outer skin within the skin field, as the same skin field without the corresponding opening—that is, the undisturbed skin field without the opening and the structural element attached to it. The resistance to tensile and compressive forces acting in the direction of extension of the outer skin within the skin field, or in the plane defined by the outer skin within the skin field, is...The strength against shear forces acting in the plane defined by the outer skin within the skin area can also be called normal strength and indicates a measure of the resistance that the outer skin offers to tensile and compressive forces acting parallel to the surface of the outer skin or tangentially to the outer skin, i.e., perpendicular to the thickness direction of the outer skin. The strength against shear forces acting in the extension direction of the outer skin within the skin area, or in the plane defined by the outer skin within the skin area, can also be called shear strength and indicates a measure of the resistance that the outer skin offers to shear forces acting parallel to the surface of the outer skin or tangentially to the outer skin, i.e., perpendicular to the thickness direction of the outer skin.

[0017] This means that the respective structural element is arranged so that it completely fills or covers the respective opening. It also means that the outer skin is connected to the respective structural element in the respective skin area in such a way that tensile, compressive, and shear forces acting on the outer skin within the skin area are transmitted through the structural element between opposite sides of the opening, in order to achieve at least the same overall strength against tensile, compressive, and shear forces acting in the direction of extension of the outer skin within the skin area, or in the plane defined by the outer skin within the skin area, as in an undisturbed skin area. The structural elements are therefore each such tensile, compressive, and shear force-transmitting element that is directly integrated into the outer skin.With regard to the transmission of these tensile, compressive, and shear forces, as well as pressure tightness, the structural element completely replaces the load-bearing parts of the outer skin that are missing due to the opening. Furthermore, when installed in an aircraft, the structural element absorbs the internal pressure prevailing inside the aircraft and, in particular, seals the respective opening pressure-tight from the aircraft's interior.

[0018] One, several, or all of the electronic components of each structural element are preferably arranged wholly or partially in the region of the opening—that is, completely or at least partially below the opening, if the outer surface of the structural section is defined as facing upwards or viewed perpendicularly to the opening—on the side of the outer skin opposite the outer surface. In other words, when the structural section is installed in an aircraft, the respective electronic component is located inside the aircraft with respect to the outer skin. Such an arrangement is particularly advantageous, for example, for electronic components in the form of antenna elements.

[0019] The described electronic arrangement has the advantage that, although the formation of the opening in a skin panel impairs or reduces its structural mechanical properties and the pressure tightness of the outer skin, these properties are restored or even improved compared to the state without the opening by the structural element. Since this is done separately for each skin panel with an opening, and the stiffening arrangement with the longitudinal and transverse stiffening elements remains unchanged, there is also no impairment of adjacent skin panels or the stiffening arrangement of longitudinal and transverse stiffening elements.This also makes it easy to design multiple adjacent skin panels in the described manner, without having to consider each skin panel individually. Therefore, there are no restrictions regarding the number and arrangement of adjacent skin panels that can be designed in this way. Furthermore, the electronics assembly is easy to install and maintain, and retrofitting it into an existing aircraft is straightforward. Additionally, it is optional and flexible for each skin panel to design the electronics assembly so that at least one of the electronic components, such as an antenna element, protrudes from the structural section or aircraft, or so that none of the electronic components protrude from the structural section or aircraft.In the latter case, no additional aerostatic loads act on the electronics arrangement during the operation of the aircraft in question, so that it can be implemented with a particularly low weight, the air resistance is not adversely affected, and the aircraft can have a better visual appearance.

[0020] In a preferred embodiment, each structural element has a first sealing device, such as a sealing ring, and the frame of each structural element has an annularly closed sealing surface. The frame of each structural element is then attached to the outer skin in the corresponding skin section such that the sealing surface is located on the side of the outer skin opposite the outer surface, faces an annularly closed section of the outer skin surrounding the respective opening in the respective skin section, and the first sealing device is arranged between this section of the outer skin and the sealing surface. This design allows for a particularly simple and reliable pressure-tight seal between the outer skin and the frame.

[0021] In a preferred embodiment, the structural elements each have a plurality of fastening elements, such as screws or other detachable fasteners. The frames of the structural elements then each have a corresponding plurality of bores adapted to accommodate the fastening elements for attaching the respective frame to the outer skin. The connection between the outer skin and the structural element is preferably direct, but can also be made via an intermediate element, such as a connecting bracket or clip. The fastening elements are thus part of the respective structural element and contribute to fulfilling the described requirements for the structural element's ability to form a pressure-tight seal and to transmit tensile, compressive, and shear forces.

[0022] According to the invention, the frame of one, several, or all of the structural elements has a through-opening that connects a side of the frame located on the outer surface with an opposite side of the frame, and through which at least one of the electronic components of the respective structural element passes completely or partially. This electronic component can, for example, be or include a transmitting and / or receiving electronic unit that transmits or receives radio signals with the aid of another electronic component in the form of an antenna element, or it can be a cable or a connector for electrical connection to an external unit. In each case, each of these structural elements has at least one second sealing device that is designed and arranged in such a way as to prevent air from passing through the through-opening of the frame.Each such second sealing device is preferably arranged between one of the electronic components and the frame of the respective structural element, which may, for example, be the same electronic component that passes through the opening of the frame or another electronic component of the respective structural element.

[0023] In a preferred embodiment, the frame of one, several, or all of the structural elements each has a section that annularly surrounds a receiving space in which one, several, or all of the electronic components of the respective structural element are wholly or partially arranged. The frame can, in particular, be trough-shaped or have a trough-shaped section, in which case the receiving space is formed by the interior of the trough. This design advantageously allows the electronic components to protrude only minimally, or not at all, from the opening above the outer surface of the outer skin within the skin area. In this embodiment, and also in other embodiments, it can be provided that an outer surface of at least one of the structural elements is flush with the outer surface of the outer skin within the respective skin area, so that the electronic arrangement does not increase, or does not significantly increase, air resistance.Parts of the outer surface of the structural element can then be formed entirely by the frame, entirely by one or more of the electronic components, or partially by the frame and partially by one or more of the electronic components. If the structural element in question has a cover as mentioned above, it is preferred that an outer surface of the cover is flush with the outer surface of the outer skin in the respective skin area, and that the outer surface of the structural element is thus partially formed by the cover of one or more of the structural elements.

[0024] In a preferred embodiment, one, several, or all of the structural elements are designed such that each structural element can be removed from and attached to the outer skin as a single unit within the respective skin area, i.e., including all electronic components attached to the frame of the structural element, so that these components do not need to be detached from the frame for attaching or removing the structural element. In this case, the second sealing device, if present, can, for example, consist of or include a partial or complete encapsulation of epoxy resin or another sealing material. In any case, this further simplifies assembly.

[0025] In a preferred embodiment, the electronics arrangement comprises two or more skin fields and a corresponding plurality of structural elements, wherein two or more skin fields are preferably arranged adjacent to one another. The skin fields in question can, for example, be arranged in a row or in a two-dimensional matrix, with further skin fields optionally located between them or directly adjacent to one another. In any case, the structural elements associated with these skin fields are designed such that at least one of their electronic components is common to the structural elements and is attached to the frame of each of the structural elements. In other words, the respective electronic component then extends over several skin fields. In particular, such an electronic component can, for example, be a large-area antenna element whose dimensions are larger than those of the opening of a single skin field.than those of a single skin panel. Nevertheless, this embodiment also has the advantage that the stiffening arrangement does not need to be modified and that each skin panel can be considered separately with regard to the design and closure of the respective openings. The design of the electronics arrangement according to the invention generally makes it advantageously easy to provide electronic components, such as antenna elements, of different sizes, and in particular also relatively large electronic components, on or in an aircraft, such as on or in an aircraft fuselage.

[0026] In a preferred embodiment, the respective opening and the associated structural element in each skin panel are designed and dimensioned such that the attachment of the structural element's frame to the outer skin can be released and made from the outer surface (in particular by loosening or tightening screws or other fasteners of the respective structural element), and the structural element can be removed from the outer surface after the attachment has been released by tilting the frame and moving it outwards from the opening, or the structural element can be positioned in the attachment position from the outer surface before the attachment is made by tilting the frame and inserting it into the opening. Preferably, no work steps requiring access to the interior of the electronics assembly, i.e., inside the aircraft, are then necessary.Only if an electronic component extending across multiple skin fields is present, as explained above, might it be necessary to remove it from the corresponding structural elements in a preliminary step, requiring access to the inner side of the respective frames. Subsequently, the frames and any further electronic components of the individual structural elements can preferably be removed again in the manner described, solely through work steps from the outer surface.

[0027] In a preferred embodiment, the electronics arrangement is an antenna arrangement. One, several, or all of the electronic components of one, several, or all of the structural elements then constitute an antenna element. Such an antenna element can be or comprise a KU-, KA-, or L-band antenna, a phased-array antenna, or an electronically controlled antenna, and / or include a printed circuit board. The respective antenna element can be a single, one-piece antenna element or comprise an arrangement of several separate antenna elements that work together to transmit and / or receive radio waves. Alternatively, the electronics arrangement can be, for example, a laser device and / or a communication device. In these cases as well, preferably at least one of the electronic components can be an antenna element of the described configuration.

[0028] The electronics assembly according to one of the embodiments described above is, in its installed state, part of an aircraft. Therefore, according to the present invention, an aircraft with a structure and an electronics assembly according to one of the embodiments described herein is also provided. The structure has a plurality of longitudinal and transverse stiffening elements and an outer skin. The structural section is part of the structure; that is, in particular, the longitudinal and transverse stiffening elements of the structural section of the electronics assembly are part of longitudinal and transverse stiffening elements of the structure. If, for example, the structural section is a fuselage structure section, the aircraft has a fuselage and an electronics assembly according to one of the embodiments described herein. The fuselage then has a fuselage structure with a plurality of longitudinal and transverse stiffening elements and an outer skin. The fuselage structure section is part of the fuselage structure; that is,In particular, the longitudinal and transverse stiffening elements of the fuselage structure section of the antenna arrangement are part of the longitudinal and transverse stiffening elements of the fuselage.

[0029] The aircraft can be equipped with one or more of these electronic assemblies. It is advantageous that the electronic assembly can be located anywhere within the aircraft, for example, anywhere in the fuselage, such as on the top, bottom, or sides. The same applies to an assembly on or in other parts of the aircraft, such as a vertical stabilizer or a wing.

[0030] In a preferred embodiment of the aircraft, the structure has, in addition to the skin panels of the structural section, which can then also be referred to as first skin panels, a plurality of further skin panels, which can also be referred to as second skin panels, each of which is a section of the outer skin defined between two immediately adjacent longitudinal stiffening elements and two immediately adjacent transverse stiffening elements of the structure.For each of the first skin fields, the respective opening and the respective structural element are designed in such a way that the same opening can be formed in the same way in each of the second skin fields of the structure and can be closed by the structural element in such a way that the corresponding second skin field of the structure has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the extension direction of the outer skin in the second skin field or in the plane defined by the outer skin in the second skin field, as the same second skin field without the corresponding opening.This design advantageously ensures that the requirements for the structural elements regarding pressure sealing and the transmission of tensile, compressive, and shear forces are independent of whether the opening and structural element are located in the first or second skin panel. It is therefore possible to define one or more "standard openings," each with predetermined standard dimensions and shapes, and requirements for associated structural elements that depend solely on the specific "standard opening" and not on the skin panel in which it is formed. This allows for a particularly simple and cost-effective implementation of the electronics arrangement. Defining only one or a few such standard openings also offers several other advantages.Thus, it is possible to provide a corresponding structural element for each such standard opening, which does not contain any electronic components but serves only to close the respective opening; i.e., it is a cover or closure for the opening. Such covers or closures can be stocked easily and inexpensively, and therefore make it possible to equip aircraft with sealed standard openings from the outset in a cost-effective manner. These can then be modified by the airlines by replacing the covers with the structural elements according to the invention, which contain electronic components.Furthermore, it is possible to quickly replace structural elements according to the invention with the corresponding cover, for example, in the event of defects to quickly restore the aircraft to operational readiness or if it is desired to permanently reverse the modification of the aircraft with a standard opening and a structural element according to the invention. In addition, there is the advantage that it is simple and cost-effective to offer a catalog of various devices from which the operator of an aircraft can select for modifying the aircraft. Each such device has one or more electronic components that are provided as described in the manner as part of a structural element that fits the standard opening or openings.

[0031] According to the present invention, a method for providing an electronics arrangement according to one of the embodiments described above is further provided. In this method, a structural section of an aircraft structure, as described above, is provided. It thus comprises a stiffening arrangement of interconnected elongated longitudinal and transverse stiffening elements, an outer skin arranged on one side of the stiffening arrangement and attached to the longitudinal and transverse stiffening elements, wherein a surface of the outer skin facing away from these elements forms an outer surface of the structural section, and one or more skin panels, each of which is a section of the outer skin defined between two immediately adjacent longitudinal stiffening elements and two immediately adjacent transverse stiffening elements.Furthermore, one or more structural elements are provided, as described above, each comprising a frame and one or more electronic components attached to the respective frame. Additionally, an opening, also described in detail above, is formed in one, several, or all of the skin panels in the outer skin, completely within the skin panel.Finally, for each of the skin panels with one of the openings, a corresponding structural element is provided separately, for example by manufacturing it or selecting it from a group of prefabricated structural elements, and is detachably attached to the outer skin in the corresponding skin panel on the side of the outer skin opposite the outer surface in the manner already described above, such that it closes the corresponding opening in such a way that the skin panel has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the direction of extension of the outer skin in the skin panel or in the plane defined by the outer skin in the skin panel as the same skin panel without the corresponding opening.

[0032] In a preferred embodiment of the method, forming the opening in at least one of the skin fields comprises that in each of the skin fields (i.e.(in each skin panel in which one of the openings is to be formed) the dimensions and shape of the opening to be formed are selected from a group consisting of one or more predetermined openings with predetermined dimensions and shapes, for each of which predetermined minimum requirements for a structural element are defined, which ensure that after forming an opening with the selected dimensions and shape and releasably attaching a structural element fulfilling the corresponding predetermined minimum requirements with its frame to the outer skin in the corresponding skin panel on the side of the outer skin opposite the outer surface, the corresponding opening is closed by the structural element in such a way that the skin panel has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces that occur in the extension direction of the outer skin in the skin panel orThe openings in the skin panel, defined by the outer skin, function in the same way as the same skin panel without the corresponding opening. As mentioned above, the openings in this embodiment are advantageously standardized, allowing the structural elements to be provided particularly easily and cost-effectively without compromising the tightness and mechanical properties of the outer skin. The structural element for each skin panel with one of the openings is then provided in such a way that the respective structural element meets the predetermined minimum requirements defined for the opening selected for the respective skin panel.

[0033] In this embodiment, it is further preferred if the electronics arrangement is provided on an aircraft according to the embodiment described above, which also has second skin panels. The aircraft can, for example, be an aircraft of a predetermined type or from a predetermined manufacturer. The group is defined such that when each of the openings of the group is formed in one of the first skin panels (then before the actual opening to be formed) or in one of the second skin panels, and the opening is closed with a structural element that meets the associated minimum requirements, the corresponding first skin panel or the corresponding second skin panel has the same pressure tightness and at least the same resistance to tensile, compressive, and shear forces as that in the extension direction of the outer skin in the respective skin panel.The openings function in the plane defined by the outer skin in the respective skin panel, just like the same skin panel without the corresponding opening. This design extends the standardization of the openings and the applicability of the associated structural elements to all skin panels of the aircraft defined between adjacent longitudinal and transverse stiffening elements.

[0034] The invention is explained in more detail below with reference to the figures, in which two exemplary embodiments are shown. Fig. Figure 1 shows a schematic perspective view of an aircraft with an electronic arrangement according to the invention, which is designed as an antenna arrangement. Fig. Figure 2 shows a schematic top view of a structural section of an aircraft structure, which has a skin panel in which an opening is formed, Fig. Figure 3a shows a schematic side view of an antenna arrangement according to a first embodiment of the present invention, Fig. 3b and Fig. Figure 3c shows the distance or assembly of a structural element of the antenna arrangement. Fig. 2a, Fig. Figure 4 shows a schematic side view of an antenna arrangement according to a second embodiment of the present invention, and Fig. Figure 5 shows a schematic side view of an antenna arrangement according to a third embodiment of the present invention.

[0035] The in Fig. The aircraft 1 shown in Figure 1 has a fuselage 2 and an electronics arrangement 3 according to the invention, which is designed as an antenna arrangement. For illustrative purposes, conventional sword antennas 4 are also shown alongside the antenna arrangement 3. These are attached to the outside of the fuselage 2 and project outwards from the fuselage 2. In contrast, the upper surface of the antenna arrangement 3 is flush or substantially flush with the surface of the fuselage 2, so that the air resistance of the fuselage 2 is not increased, or not significantly increased, by the antenna arrangement 3, and no or substantially no increased aerodynamic loads act on the antenna arrangement. It should be noted that – as will be explained below – the antenna arrangement 3 according to the invention can also be designed such that an antenna element, such as a sword antenna element, projects outwards from the fuselage 2. Fig. In Figure 1, the antenna assembly 3 is shown as an example on the upper surface of the fuselage 2. However, the antenna assembly can also be located at any other point on the fuselage 2, for example on a side or on the underside. The fuselage 2 has a conventional fuselage structure with a grid-like arrangement of interconnected longitudinal and transverse stiffening elements, on which an outer skin is arranged (for the aircraft in Figure 1). Fig. (1 not shown separately). As can be seen from the other figures, the antenna assembly 3 has a fuselage structural section or element 5, which is part of the fuselage structure of the fuselage 2 and can be formed integrally with the fuselage structure of the fuselage 2 or integrated into it as a separate component. It should be noted that the antenna assembly 3 can also be provided at locations other than the fuselage 2, such as the vertical stabilizer or a wing. The figures show the arrangement on the fuselage 2 only as an example. In the case of an arrangement at another location, a structural section of the corresponding substructure of the aircraft is provided instead of the fuselage structural section 5, such as a vertical stabilizer structural section or a wing structural section.

[0036] The Fig. Figure 2 shows a schematic top view of a structural section 5 of the aircraft 1, which—as described above—can, for example, be a fuselage structural section. The structural section 5 has two longitudinal stiffening elements 6 and two transverse stiffening elements 7, which are connected to each other and together form a stiffening assembly 8 of longitudinal and transverse stiffening elements 6, 7. When installed in the fuselage 2, the longitudinal stiffening elements 6 extend longitudinally along the fuselage 2, and the transverse stiffening elements 7 extend circumferentially around the fuselage 2, perpendicular to the longitudinal stiffening elements 6. Furthermore, the structural section 5 has an outer skin 9, which is located on and attached to one side of the stiffening assembly 8. As shown, among other things, in Fig. Figure 3a, which shows a schematic side view of a first embodiment of an antenna arrangement 3 according to the invention, shows that the outer skin 9 is attached to the longitudinal stiffening elements 6 and directly to the transverse stiffening elements 7 via clips 10. When installed in the fuselage 2, an outer surface 11 of the outer skin 9 forms part of the outer surface or the outside of the fuselage 2. The stiffening arrangement 8 is located on the side of the outer skin 9 opposite the outer surface 11.

[0037] The outer skin 9 is not only provided in the area of ​​structural section 5, but extends beyond it. In Fig. However, as can be seen in Figure 2, a rectangular section of the outer skin 9 is defined between the longitudinal stiffening elements 6 and the transverse stiffening elements 7; this section is referred to as the skin field 12. Normally, the outer skin 9 is closed in this skin field 12. However, to form an antenna arrangement 3 according to the invention, an opening 13 is provided in the outer skin 9 within the skin field 12, as shown in Figure 2. Fig. Figure 2 shows this opening 13 being completely located within the skin field 12 and surrounded by a plurality of spaced-apart bores 14.

[0038] The Fig. Figures 3a to 3c show a first embodiment of the antenna arrangement 3. The antenna arrangement 3 has the structural element 5, the structure of which is shown in Fig. Figure 2 shows that the opening 13 is closed by a structural element 15, which is arranged on the side of the outer skin 9 opposite the outer surface 11 and is attached to the outer skin 9. The structural element 15 has a rigid frame 16 with a base plate 17 and a circumferential raised rim 29, a sealing ring 18 arranged on a sealing surface 19 formed by the surface of the rim 29, and several electronic components 20a, 20b, 20c attached to the frame 16. A plurality of bores 21 are provided in the rim 29 of the frame 16, which correspond in number, arrangement, and orientation to the bores 14 in the outer skin 9, so that the frame 16, and thus the structural element 15, is sealed in the Fig. The outer skin 9 can be attached to the opening 13 in the position shown in Figure 3a by means of a plurality of screws (or other detachable fasteners) 22 using a plurality of screws (or other detachable fasteners). It is preferred if one head of each screw or fastener 22 is countersunk in the outer skin and is flush or substantially flush with the outer surface of the outer skin. The electronic components comprise an antenna element 20a, antenna electronics 20b connected to the antenna element 20a, and a connector 20c provided on the antenna electronics 20b. Due to the design of the frame 16 with the base plate 17 and the raised edge 29, the frame 16 is shaped like a trough with a receiving chamber 23 in which the antenna element 20a is arranged such that its surface is flush or substantially flush with the outer surface 11 of the outer skin 9.The antenna electronics 20b are located on the underside of the antenna element 20a and extend through a through-opening 24 formed in the base plate 17. This advantageously allows the antenna electronics 20b to be actively cooled from inside the aircraft 1 with conditioned cabin air, e.g., when the antenna electronics 20b are operating at high thermal power or when outside temperatures are high, especially when the antenna element 20a is exposed to direct sunlight. This advantage also applies to any other embodiment in which one of the electronic components is wholly or partially accessible from inside the aircraft 1. Even if this is not the case, cooling of the electronic components can be achieved by actively cooling the structural element from inside the aircraft with conditioned cabin air, and the structural element then transferring the cooling effect to the electronic component(s).To seal the through-opening 24 in the illustrated embodiment, for example an epoxy resin seal can be provided between the antenna element 20a and the frame 16 (not shown).

[0039] Since the opening 13 lies entirely within the skin panel 12 and requires no modification of the longitudinal and transverse stiffening elements 6, 7, and since the structural element 15 closes the opening 13 and is designed to fully restore the pressure tightness and strength of the outer skin 9 within the skin panel 12 against tensile, compressive, and shear forces acting in the direction of extension of the outer skin 9 within the skin panel 12 or in the plane defined by the outer skin 9 within the skin panel 12, the antenna arrangement 3 can be implemented particularly easily and can also be retrofitted to the aircraft 1 without affecting other skin panels or the stiffening arrangement of the aircraft 1. Furthermore, the structural element 15 can be easily detached and removed from the outer skin 9 as a single unit by a worker located outside the aircraft. As shown in the Fig. 3b and Fig. As shown in 3c, it is only necessary to loosen the screws or other detachable connecting elements 22, tilt the structural element 15 inwards on one side and, if necessary, disconnect a plug connection 25 to external units (see Fig. 3b) and then tilt the structural element 15 at an angle and pull it out of the opening 13 (see Fig. 3c). The installation of structural element 15 is just as easy by reversing the order of these steps.

[0040] The Fig. Figure 4 shows a second embodiment of the antenna arrangement 3. This differs from the one shown in the Fig. The embodiment shown in 3a to 3c differs essentially only in that the frame 16 is not trough-shaped and does not have a receiving space, and that instead of the antenna element 20a, a leaf antenna element 26 is provided that projects outwards from the outer surface 11 of the outer skin 9.

[0041] The Fig. Figure 5 shows a third embodiment of the antenna arrangement 3. In this embodiment, the structural section 5 has three longitudinal stiffening elements 7 and two adjacent skin panels 12, each of which has an opening 13 and a structural element 15. One of these skin panels 12 (in the Fig. 5 left) Structural element 15 has essentially the same structure as structural element 15 of the Fig. 3a. However, instead of antenna element 20a, an antenna element 27 is provided, so that this structural element 15 connects with the other (in the Fig. 5 right) structural element 15 divides and is attached to each of the frames 16 of the two structural elements 15. This antenna element 27 therefore extends over both skin panels 12 and can thus be larger than the antenna element 20a. In order to remove the structural elements 15, the antenna element 27 must first be removed from the frames 16. For this purpose, among other things, screws or other detachable connecting elements 28 must be loosened from inside the aircraft 1, with which a sealing device 29 for sealing the through-opening in the frame 16 of the left structural element 15 is attached (cf. the through-opening the Fig.3a) Subsequently, the antenna element 27 and then the structural element 15 can be removed from the outside. Since the structural elements 15 in each of the skin panels 12 separately ensure the complete restoration of the pressure tightness and strength of the outer skin 9 in the skin panels 12 against tensile, compressive and shear forces acting in the direction of extension of the outer skin 9 in the skin panels 12 or in the plane defined by the outer skin 9 in the skin panels 12, which is destroyed by the openings 13, it is very easy to provide such antenna elements extending over several skin panels 12.

[0042] In each of the embodiments, the openings 13 do not have arbitrary dimensions and shapes, but are selected from a predetermined group of standard openings, each with predetermined dimensions and shapes. Each of these standard openings is assigned specific minimum requirements for a structural element 15 for closing the respective opening. These minimum requirements are defined such that, after the associated opening is closed, the pressure tightness and shear strength are fully restored in each skin panel.

Claims

[1] Electronic arrangement for an aircraft (1) - a structural section (5) of a structure of an aircraft (1), which - a stiffening arrangement (8) of interconnected elongated longitudinal and transverse stiffening elements (6, 7), - an outer skin (9) arranged on one side of the stiffening arrangement (8) and attached to the longitudinal and transverse stiffening elements (6, 7), wherein a surface of the outer skin (9) facing away from these forms an outer surface (11) of the structural section (5), and - has one or more skin fields (12), each of which is a section of the outer skin (9) defined between two immediately adjacent longitudinal stiffening elements (6) and two immediately adjacent transverse stiffening elements (7), and - comprising one or more structural elements (15), each of which has a frame (16) and one or more electronic components (20a-c, 26, 27) attached to the frame (16), wherein in at least one of the skin panels (12) in the outer skin (9) an opening (13) is formed that is completely arranged in the skin panel (12) and for each of the skin panels (12) with one of the openings (13) a separate associated structural element (15) is provided, which is designed and detachably attached with its frame (16) to the outer skin (9) in the corresponding skin panel (12) on the side of the outer skin (9) opposite the outer surface (11) in such a way that it closes the corresponding opening (13) in such a way that the skin panel (12) has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the direction of extension of the outer skin (9) in the skin panel (12) as the same skin panel (12) without the corresponding opening (13), wherein the frame (16) of at least one of the structural elements (15) has a through-opening (24) which connects a side of the frame (16) located on the side of the outer surface (11) with an opposite side of the frame (16) and through which at least one of the electronic components (20a-c, 26, 27) of the respective structural element (15) passes at least partially, wherein each of these structural elements (15) has at least one second sealing device which is designed and arranged in such a way as to prevent air from passing through the through-opening (24) of the frame (16). [2] Electronic arrangement according to claim 1, wherein the structural elements (15) each have a first sealing device (18) and the frame (16) of the structural elements (15) each has an annularly closed sealing surface (19), wherein the frame (16) of each of the structural elements (15) is attached to the outer skin (9) in the corresponding skin field (12) in such a way that the sealing surface (19) is arranged on the side of the outer skin (9) opposite the outer surface (11), opposite an annularly closed section of the outer skin (9) surrounding the respective opening (13) in the respective skin field (12) and the first sealing device (18) is arranged between the section of the outer skin (9) and the sealing surface (19). [3] Electronic arrangement according to claim 1 or claim 2, wherein the structural elements (15) each have a plurality of fastening elements and the frames (16) of the structural elements (15) each have a corresponding plurality of bores adapted to accommodate the fastening elements for fastening the respective frame (16) to the outer skin (9). [4] Electronic arrangement according to claim 1, wherein the second sealing device is arranged between each of the electronic components (20a-c, 26, 27) and the frame (16) of the respective structural element (15). [5] Electronic arrangement according to one of the preceding claims, wherein the frame (16) of at least one of the structural elements (15) has a section (29) which surrounds a receiving space (23) in an annular manner in which at least one of the electronic components (20a-c, 26, 27) of the respective structural element (15) is wholly or partially arranged. [6] Electronic arrangement according to one of the preceding claims, wherein at least one of the structural elements (15) is designed such that it can be removed as a unit from the outer skin (9) in the respective skin field (12) and attached to it. [7] Electronic arrangement according to one of the preceding claims, comprising at least two of the skin fields (12) and at least two of the structural elements (15), wherein at least two of the skin fields (12) are arranged adjacent to each other and the structural elements (15) associated with these skin fields (12) are designed such that at least one of their electronic components (27) is common to the structural elements (15) and is attached to the frame (16) of each of the structural elements (15). [8] Electronic arrangement according to one of the preceding claims, in which in each of the skin fields (12) the respective opening (13) and the associated structural element (15) are designed and dimensioned in such a way that the attachment of the frame (16) of the structural element (15) to the outer skin (9) can be released and made from the side of the outer surface (11) and the structural element (15) can be removed from the side of the outer surface (11) after releasing the attachment by tilting the frame (16) and moving it outwards from the opening (13), or the structural element (15) can be arranged in the attachment position from the side of the outer surface (11) before making the attachment by tilting the frame (16) and inserting it into the opening (13). [9] Electronic arrangement according to one of the preceding claims, wherein the electronic arrangement (3) is an antenna arrangement, wherein at least one of the electronic components of at least one of the structural elements (15) is an antenna element (20a, 26, 27). [10] Aircraft with a structure and an electronics arrangement (3) according to one of the preceding claims, wherein the structure has a plurality of longitudinal and transverse stiffening elements (6, 7) and an outer skin (9) and wherein the structural section (5) is a part of the structure. [11] Aircraft according to claim 10, wherein the structure, in addition to the skin panels (12) of the structural section (5), has a plurality of further skin panels (12), each of which is a section of the outer skin (9) defined between two immediately adjacent longitudinal stiffening elements (6) of the longitudinal stiffening elements (6) and two immediately adjacent transverse stiffening elements (7) of the transverse stiffening elements (7) of the structure, wherein for each of the skin panels (12) of the structural section (5) the opening (13) and the structural element (15) are configured such that the same opening (13) can be configured in the same way in each of the further skin panels (12) of the structure and can be closed by the structural element (15) in such a way that the corresponding further skin panel (12) of the structure has at least the same pressure tightness and at least the same shear strength as the same skin panel (12) without the corresponding opening (13). [12] Method for providing an electronic arrangement (3) according to any one of claims 1 to 9, wherein - a structural section (5) of a structure of an aircraft (1) is provided which - a stiffening arrangement (8) of interconnected elongated longitudinal and transverse stiffening elements (6, 7), - an outer skin (9) arranged on one side of the stiffening arrangement (8) and attached to the longitudinal and transverse stiffening elements (6, 7), wherein a surface of the outer skin (9) facing away from these forms an outer surface (11) of the structural section (5), and - has one or more skin fields (12), each of which is a section of the outer skin (9) defined between two immediately adjacent longitudinal stiffening elements (6) and two immediately adjacent transverse stiffening elements (7), - one or more structural elements (15) are provided, each of which has a frame (16) and one or more electronic components (20a-c, 26, 27) attached to the frame (16), - in at least one of the skin fields (12) in the outer skin (9) an opening (13) is formed that is completely located in the skin field (12) and - for each of the skin panels (12) with one of the openings (13), a corresponding structural element (15) is provided separately and is detachably attached to the outer skin (9) in the corresponding skin panel (12) on the side of the outer skin (9) opposite the outer surface (11) with its frame (16) in such a way that it closes the corresponding opening (13) so that the skin panel (12) has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the direction of extension of the outer skin (9) in the skin panel (12) as the same skin panel (12) without the corresponding opening (13), - the frame (16) of at least one of the structural elements (15) has a through-opening (24) which connects a side of the frame (16) located on the side of the outer surface (11) with an opposite side of the frame (16) and through which at least one of the electronic components (20a-c, 26, 27) of the respective structural element (15) passes at least partially, wherein each of these structural elements (15) has at least one second sealing device which is designed and arranged in such a way as to prevent air from passing through the through-opening (24) of the frame (16). [13] The method of claim 12, wherein - the formation of the opening (13) in at least one of the skin panels (12), in each of the at least one skin panel (12) the dimensions and shape of the opening (13) to be formed are to be selected from a group consisting of one or more predetermined openings (13) with predetermined dimensions and shapes, for which predetermined minimum requirements for a structural element (15) are defined, which ensure that after the formation of an opening (13) with the selected dimensions and shape and the releasable attachment of a structural element (15) that meets the corresponding predetermined minimum requirements with its frame (16) to the outer skin (9) in the corresponding skin panel (12) on the side of the outer skin (9) opposite the outer surface (11), the corresponding opening (13) is closed by the structural element (15) in such a way thatthat the skin panel (12) has at least the same pressure tightness and at least the same resistance to tensile, compressive and shear forces acting in the extension direction of the outer skin (9) in the skin panel (12) as the same skin panel (12) without the corresponding opening (13), and, - the provision of the structural element (15) for each of the skin fields (12) with one of the openings (13) is carried out in such a way that the respective structural element (15) meets the predetermined minimum requirements defined for the opening (13) selected for the respective skin field (12). [14] Method according to claim 13, wherein the electronic arrangement (3) is provided on an aircraft (1) according to claim 11, the group being defined such that when each of the openings (13) of the group is formed in one of the skin panels (12) of the structural section (5) or in one of the further skin panels (12) of the structure and the opening (13) is closed with a structural element (15) that meets the associated minimum requirements, the corresponding skin panel (12) of the structural section (5) or of the corresponding further skin panel (12) of the structure has at least the same pressure tightness and at least the same strength against tensile, compressive and shear forces acting in the extension direction of the outer skin (9) in the respective skin panel (12) as the same skin panel (12) without the corresponding opening (13).

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