CLADDING OF VEHICLE COMPONENTS AND ASSOCIATED MOUNTING SYSTEM

Abstract

This document describes a system that can be attached to the outer skin of a vehicle, such as an aircraft. A disclosed version of the system comprises an antenna component, a support frame, brackets, and an aerodynamic fairing. The antenna component is connected to the support frame, which has a plurality of clevis mounting features. Each support fitting can be coupled between one of the clevis mounting features and the outer skin of the vehicle. The fairing consists of an upper and a lower part. The upper part has a defined opening. The lower part is configured and arranged to connect to the outer skin of the vehicle. The opening is shaped and dimensioned to accommodate at least a portion of the support frame that is connected to the upper part of the fairing.

Description

CROSS-REFERENCE TO A RELATED REGISTRATION

[0001] This application claims priority over US Provisional Application No. 63 / 638,188, which was filed on April 24, 2024. TECHNICAL AREA

[0002] The embodiments of the object described here generally relate to vehicle components. In particular, embodiments of the object relate to a fairing for an aircraft component, such as a communications antenna. BACKGROUND

[0003] Vehicles such as aircraft, automobiles, and watercraft often incorporate components attached to or integrated into exterior panels, features, or structures. For example, cameras, spoilers, antennas, sensors, and similar items may be mounted on the exterior of vehicles. Similarly, aircraft may use fuselage-mounted instruments, lighting fixtures, communication equipment, antennas, and other components. Mounting such components can be challenging and often requires balancing various factors, including weight, cost, structural integrity, aesthetics, and aerodynamic performance.

[0004] Accordingly, it is desirable to have a component fairing for a component that is mounted on or integrated into the exterior of a vehicle. Furthermore, it is desirable to have a component fairing and an associated mounting system that is robust, safe, and aerodynamic. Further desirable features and characteristics will become apparent from the following detailed description and the attached claims in conjunction with the attached drawings and the preceding technical field and background information. BRIEF SUMMARY

[0005] A system for attaching a component to the exterior bodywork of a vehicle is described herein. One disclosed embodiment of the system comprises: a support frame configured to receive and hold the component; a plurality of support fittings; and a panel. Each support fitting can be coupled between the support frame and the exterior bodywork of the vehicle, and the support fittings are configured to physically attach the support frame to the exterior bodywork of the vehicle. The panel has an upper section with an opening formed therein. The panel has a lower section configured and arranged for connection with the exterior bodywork of the vehicle. The opening in the panel is shaped and dimensioned to accommodate at least a portion of the support frame. The support frame is connected to the upper part of the panel.

[0006] A system configured for mounting on the outer body panel of a vehicle is also described herein. One disclosed embodiment of the system comprises: an antenna component; a support frame coupled to the antenna component; a plurality of brackets; and an aerodynamic fairing. The support frame has a plurality of clevis mounting features. Each support fitting can be coupled between one of the clevis mounting features and the outer body panel of the vehicle. The aerodynamic fairing has an upper section with an opening formed therein. The aerodynamic fairing also has a lower section configured and arranged for connection with the outer sheet metal of the vehicle. The opening in the fairing is shaped and dimensioned to accommodate at least a portion of the support frame. The support frame is connected to the upper part of the fairing.

[0007] Furthermore, a vehicle, e.g. an aircraft, is described here that contains an embodiment of the system described above.

[0008] This summary serves to present, in simplified form, a selection of concepts that are described in detail below. This summary is not intended to identify key features or essential characteristics of the claimed subject matter, nor is it intended to assist in determining the scope of the claimed subject matter. BRIEF DESCRIPTION OF THE DRAWINGS

[0009] A more complete understanding of the subject matter will result from the detailed description and claims when considered in conjunction with the following figures, where identical reference numerals refer to similar elements in the figures. Fig. 1 is a perspective top view of an aircraft with a component and an associated fairing, which are mounted on it according to certain embodiments of the invention; Fig. Figure 2 is a perspective view from above looking forward, showing a section of an aircraft fuselage with an antenna and associated fairing attached to it according to certain embodiments of the invention; Fig. 3 is a top view of the in Fig. 2 shown aircraft fuselage section; Fig. 4 is a perspective top view of the in Fig. 2 antennas shown; Fig. 5 is a perspective top view of a support frame configured in accordance with certain embodiments, wherein the support frame is connected to the Fig. The antenna shown in section 4 is compatible; Fig. Figure 6 is a perspective view from below of the in Fig. 5 supporting frames shown; Fig. Figure 7 is a perspective view of the area in Fig. 2. Shown paneling from top to front; Fig. 8 is a side view of the in Fig. 7 shown paneling (the opposite side view is symmetrically equivalent); Fig. 9 is a perspective view of the in Fig. 7 shown paneling from bottom to rear; Fig. Figure 10 is a perspective view showing an exemplary arrangement of components and features (for assembly, installation and structural support) located under the fuselage skin of an aircraft; Fig. 11 is a top view showing some of the Fig. The 10 components and features shown are included; Fig. 12 is a perspective view that includes some of the Fig. The 10 components and features shown are included; Fig. Figure 13 is a perspective side view of an embodiment of a support rib designed and configured to provide bird strike protection for the in Fig. The fairing shown in section 7 offers; Fig. Figure 14 is a perspective view showing the other side of the image. Fig. The supporting rib shown in section 13 is shown; Fig. Figure 15 is a perspective view from top to back of an embodiment of a support frame designed and configured to provide bird strike protection for the in Fig. The fairing shown in section 7 offers; Fig. 16 is a perspective view of the in Fig. 15 of the support frame shown, from top to front; Fig. Figure 17 is a perspective top view of an embodiment of a front support fitting used to attach the support frame to the aircraft fuselage; Fig. Figure 18 is a side view of the front support fitting; Fig. Figure 19 is a perspective exploded view showing the front support fitting, part of the support frame and parts forming a fastening pin arrangement for the front support fitting; Fig. Figure 20 is a schematic cross-sectional view showing the front support fitting, the support frame and a corresponding fastening pin arrangement connected to each other; Fig. Figure 21 is a perspective top view of an embodiment of a rear support fitting used to attach the support frame to the aircraft fuselage; Fig. Figure 22 is a side view of the rear support fitting; Fig. Figure 23 is a perspective exploded view showing the rear support fitting, part of the support frame and parts forming a fastening pin arrangement for the rear support fitting; Fig. Figure 24 is a schematic cross-sectional view showing the rear support fitting, the support frame and a corresponding fastening pin arrangement connected to each other; Fig. Figure 25 is a perspective view from below of an assembly comprising the antenna and the support frame, which are connected to each other; Fig. Figure 26 is a perspective view from above of an assembly comprising the antenna, the support frame and two front mounting devices; Fig. Figure 27 is a perspective view from the rear top of an assembly comprising the antenna, the support frame and two rear support fittings; Fig. Figure 28 is a perspective view from above, showing part of the aircraft fuselage with various components attached to it; Fig. 29 is a top view taken from Fig. 28 corresponds to; Fig. 30 is a side view, which is from Fig. 28 corresponds to; Fig. 31 is a front view, which Fig. 28 corresponds; and Fig. 32 is a view from behind, which Fig. 28 corresponds to. DETAILED DESCRIPTION

[0010] The following detailed description is purely illustrative and is not intended to limit the embodiments of the subject matter or the application and use of such embodiments. As used herein, the word "exemplary" means "to serve as an example, instance, or illustration." Any implementation described herein as exemplary is not necessarily to be understood as preferred or advantageous over other implementations. Furthermore, there is no intention to be bound by any express or implied theories presented in the preceding technical field, background, brief summary, or the following detailed description.

[0011] The following description can refer to elements, nodes, or features that are "connected" or "coupled" to one another. Unless explicitly stated otherwise, "coupled" means that an element / node / feature is directly or indirectly connected to (or communicates with) another element / node / feature, not necessarily mechanically. Likewise, unless explicitly stated otherwise, "connected" means that an element / node / component is directly connected to (or communicates with) another element / node / component, not necessarily mechanically.

[0012] Furthermore, certain terms in the following description may be used for reference purposes only and should therefore not be considered restrictive. For example, terms such as "top" and "bottom" refer to directions in the referenced drawings. Terms such as "front," "back," "side," "outside," and "inside" describe the orientation and / or location of parts of the component within a uniform but arbitrary frame of reference, which becomes clear by referring to the text and the associated drawings in which the component in question is described. This terminology may include the terms explicitly mentioned above, their derivatives, and terms of similar meaning. Similarly, the terms "first," "second," and other numerical terms relating to structures do not imply any order unless clearly evident from the context.

[0013] A fairing for a vehicle component and the associated installation and assembly system are disclosed herein. According to certain non-limiting embodiments, the vehicle component and the fairing are used on board an aircraft, such as an airplane. However, it should be noted that embodiments of the disclosed subject matter can be used for other vehicle applications, including, but not limited to: trains, helicopters, automobiles, watercraft, submarines, monorails, amusement park rides, transportation systems, spacecraft, and the like. Although the exemplary application described herein relates to the mounting of an antenna component, the disclosed subject matter can also be used in conjunction with other types of vehicle-mounted components, e.g.,Cameras, instruments, sensors, lighting fixtures, solar panels, aerodynamic features, structural elements, windows or similar items.

[0014] Certain embodiments of the disclosed subject matter relate to a system for attaching a component to the outer wall of a vehicle. The disclosed system comprises an aerodynamic fairing and associated assemblies for attaching an antenna component to the upper fuselage of an aircraft. In accordance with certain embodiments, the disclosed subject matter provides a solution for installing a flat satellite communications antenna and fairing on the fuselage skin of an aircraft. A flat panel antenna is attached and held in an adapter resembling a picture frame, and the adapter is supported by four integrated clevises (e.g., using screws, nuts, washers, bushings, ball bearings, or connecting pins), thereby creating pin connections to tab fittings mounted on the upper fuselage.These bolted connections form a system that mitigates the distribution of loads normally acting on the fuselage. The adapter is surrounded by a low-profile aerodynamic fairing made of composite material(s) and / or other suitable materials. The fairing incorporates structural features and is designed to be resistant to lightning strikes and bird strikes. According to the described design, the upper fuselage panel to which the fairing is attached is reinforced by a system of Dopplers, frames, intermediate ribs, and clips to respond to loads from the antenna and fairing and to safely distribute these loads across the aircraft structure.

[0015] Fig. Figure 1 is a perspective view of an aircraft 100 from above, showing an exemplary embodiment of a component mounting system 102 attached to an outer panel (e.g., a fuselage skin 104 or a section thereof) of the aircraft 100. The system 102 comprises an antenna and an associated fairing attached to the fuselage skin 104. Fig. Figure 2 is a perspective view from above, showing a section of the aircraft fuselage 106 with an antenna 108 and an associated aerodynamic fairing 110, and Fig. 3 is a top view of the in Fig. 2 shown section of the hull 106. The exposed outer surface of the hull 106 corresponds to the hull skin 104.

[0016] Fig. Figure 4 is a perspective view from above of an exemplary embodiment of the antenna 108. Fig. Figure 5 is a perspective view from above of a support frame 116 configured in accordance with certain embodiments, and Fig. Figure 6 is a perspective view from below of the support frame 116. Fig. Figure 7 is a perspective view of the cladding 110 from above, Fig. Figure 8 is a side view of the fairing 110, and Fig. Figure 9 is a perspective view of the fairing 110 from below looking back.

[0017] As previously mentioned, the described version of the Antenna 108 is a flat satellite communication antenna with a low-profile configuration. The Antenna 108's design incorporates various mounting holes, cutouts, and a specific shape. As shown in Fig. As shown in Figure 4, the antenna 108 has a main surface 120 and a circumferential edge 122, which corresponds to a side wall of the antenna 108. As explained in more detail below, the support frame 116 is shaped, dimensioned, and configured to surround the circumferential edge 122 of the antenna 108. The support frame 116 is coupled to the antenna 108 and holds the antenna 108 such that the main surface 120 is exposed when the system 102 is installed on the aircraft 100. The system 102 can be positioned at a desirable location on the fuselage skin 104, which improves the electromagnetic performance of the antenna 108. In certain embodiments, the fairing 110 and the support frame 116 are designed, configured, and manufactured to be compatible with the specific shape, size, dimensions, and layout of the antenna 108.

[0018] The in Fig. The embodiment of the antenna 108 shown in Figure 4 comprises a plurality of mounting points 126 distributed around the outer circumference of the antenna 108. In this particular embodiment, the antenna 108 has twelve mounting points 126 – three on each side. Each mounting point 126 includes or interacts with a projection containing a mounting hole. Furthermore, each mounting point 126 can be defined by a cutout or recess such that an upper main surface of each mounting point 126 lies below an uppermost circumferential surface of the antenna 108. In this context, Figure 4 shows that the antenna 108 has twelve mounting points 126 – three on each side. Each mounting point 126 includes a projection with a mounting hole formed therein or interacts with one. Fig. Four twelve recesses around the outer circumference of the antenna 108, with the projections and mounting holes arranged together with the projections. These structural features of the antenna 108 interact with the corresponding structural features of the support frame 116, as described below.

[0019] As in Fig. 5 and Fig. As shown in Figure 6, the support frame 116 is suitably configured to be compatible with the specific shape, size, and dimensions of the antenna 108 and to accommodate and hold the antenna 108 in accordance with the desired installation scheme. The support frame 116 is made of a strong and durable material such as steel, aluminum, a composite material, plastic, or the like. The illustrated embodiment of the support frame 116 is designed to be placed over at least a portion of the antenna 108 and then attached to the antenna 108 by means of bolts, screws, fasteners, clips, or the like. More specifically, the support frame 116 has at least one connecting structure that overlaps an outer edge region of the antenna 108 to facilitate coupling with the antenna 108.When the support frame 116 is connected to the antenna 108, it surrounds or encloses the circumferential edge 122 of the antenna 108 (see, for example, the . Fig. 25-29).

[0020] According to the illustrated embodiment, the support frame 116 comprises a plurality of mounting tabs 130 corresponding to the mounting points 126 of the antenna 108. The support frame 116 has twelve mounting tabs 130 arranged in a 1:1 relationship to the twelve mounting points 126. Each mounting tab 130 has a mounting hole (which may be a threaded hole or a through hole) that connects to a corresponding mounting hole in the antenna 108. When the support frame 116 is installed on the antenna 108, the mounting tabs 130 are located in the recesses defined by the mounting points 126. When the support frame 116 is attached to the antenna 108, the upper surfaces of the mounting tabs 130 are flush (or nearly flush) with the adjacent upper surface of the antenna 108.A flush mounting in this way is desirable to improve aerodynamic performance and achieve a clean / smooth appearance.

[0021] As in Fig. As shown in Figure 6, the support frame 116 contains a plurality of cutouts 134, which correspond to the mounting points 126 of the antenna 108. Each cutout 134 is located at the same position as one of the mounting tabs 130. Accordingly, the support frame 116 has twelve cutouts 134, which are arranged in a 1:1 ratio to the twelve mounting tabs 130 and in a 1:1 ratio to the twelve mounting points 126 of the antenna 108 (in Figure 6). Fig. (Figure 6 shows three of the cutouts 134 not visible). The cutouts 134 are shaped, dimensioned, and otherwise configured to fit the projections of the mounting points 126. In this respect, the mounting tabs 130, the cutouts 134, and the mounting points 126 work together to ensure that the antenna 108 is installed in the correct orientation and arrangement relative to the support frame 116.

[0022] The top of the support frame 116 (see Fig. 5) includes structures and features that facilitate the mounting of the aerodynamic fairing 110 onto the support frame 116. In this respect, the support frame 116 has an outer edge 138 that forms a mounting surface 140 for the fairing 110. The outer edge 138 has a plurality of mounting holes 142 arranged to correspond to the pattern of mounting holes of the fairing 110 (as shown below with reference to the Fig. 7-9). In the illustrated, non-restrictive embodiment, nineteen mounting holes 142 are used. The top of the support frame 116 also includes a plurality of projections 146, which correspond to a corresponding number of cutouts 216 in the cladding 110 (as described below with reference to Fig. (described in more detail in 7-9). As in Fig. As shown in Figure 5, the embodiment comprises nine projections 146, each associated with one of the mounting tabs 130. Three projections 146 are located on the front 150 of the support frame 116, three projections 146 are located on the left side 152 of the support frame 116, and three projections 146 are located on the right side 154 of the support frame. The rear side 156 of the support frame 116 does not contain any of the projections 146; instead, a straight side wall 160 is used on the rear side 156. The straight side wall 160 serves as an alignment reference to ensure the correct orientation of the antenna 108 during installation. In accordance with the embodiment shown here, the straight side wall 160 accommodates an electrical connection located on the rear side of the antenna 108 (see Figure 5). Fig. 25).

[0023] The underside of the support frame 116 (see Fig. 6) includes or interacts with structures and features that facilitate the installation of the support frame 116 on the aircraft fuselage 106, e.g., mounting bracket features. In accordance with certain embodiments, the support frame 116 includes a plurality of clevis mounting features 166, 168, 170, 172 that are integrally formed therein or attached to it. Clevis mounting feature 166 is located at the front 150 of the support frame 116 near the right side 154; clevis mounting feature 168 is located at the front 150 of the support frame 116 near the left side 152; clevis mounting feature 170 is located at the rear 156 of the support frame 116 near the right side 154; and the clevis head fastening feature 172 is located on the rear 156 of the support frame 116 near the left side 152.As explained in more detail below, the clevis head fastening features 166, 168, 170, 172 correspond to a variety of support fittings used to couple the support frame 116 to the fuselage 106.

[0024] The aerodynamic fairing 110 is now being developed with reference to Fig. The fairing 110 is described in Figures 7-9. It can be designed as a single, one-piece component made of any suitable material or material composition with the desired physical, mechanical, and aerodynamic properties. For example, one embodiment of the fairing 110 may be made of a composite material, a metal such as aluminum, a plastic, or the like. The fairing 110 is shaped, dimensioned, and contoured to accommodate the antenna 108, which is configured for attachment to the aircraft fuselage 106 via the support frame 116. The fairing 110 is also shaped, dimensioned, and contoured to be aerodynamic (low drag) and to reduce or minimize noise generated during flight. To this end, the fairing 110 is relatively flat and has a low profile with a curved contour that is optimized both aerodynamically and acoustically.The fairing 110 generally and without limitation comprises: an upper section 202; a main opening 204 defined in the upper section 202; a lower section 206; a front section 208; and a rear section 210.

[0025] The main opening 204 of the cover 110 is shaped, dimensioned, and positioned to accommodate at least a portion of the support frame 116, which can be connected to the upper section 202 of the cover 110. When attached to the support frame 116, the portion of the upper section 202 defining the main opening 204 overlaps the mounting surface 140 of the support frame 116. Consequently, the mounting tabs 130 and the projections 146 of the support frame 116 are located within the main opening 204 and are exposed after installation. The main opening 204 also allows the main surface 120 of the antenna 108 to be substantially or completely exposed after installation (see Fig. 2 and Fig. 3).

[0026] The area of ​​the upper section 202 surrounding the main opening 204 has suitably configured and arranged fastening and / or interface features and structures to facilitate the positioning and assembly of the support frame 116 in the correct orientation. For example, a series of fastening holes 214 arranged around the main opening 204 accommodates fasteners (e.g., screws, rivets, or bolts) that connect the cladding 110 to the support frame 116. In the illustrated embodiment, the arrangement of the fastening holes 214 corresponds to the arrangement of the mounting holes 142 located in the support frame 116. The main opening 204 also includes or defines a plurality of cutouts 216 that are shaped, dimensioned, and arranged to correspond to the arrangement of the projections 146 on the support frame 116.Accordingly, the upper section 202 of the cladding 110 has nine cutouts 216, corresponding to the nine projections 146: three cutouts 216 are located at the front of the main opening 204; three cutouts 216 are located on the left side of the main opening 204; and three cutouts are located on the right side of the main opening 204. The main opening 204 also has a straight trailing edge 218, corresponding to the straight side wall 160 of the support frame 116.

[0027] The lower section 206 of the fairing 110 is configured and arranged to connect to an outer panel (e.g., the fuselage skin 104) of the aircraft 100. For example, the lower section 206 of the fairing 110 includes a plurality of mounting holes 224 located near the outermost perimeter of the fairing 110. These mounting holes 224 are designed to accommodate fasteners (e.g., screws, rivets, or bolts) that connect the bottom of the fairing 110 to the aircraft fuselage 106. As explained in more detail below, these fasteners interact with the mounting structure located beneath the fuselage skin 104.

[0028] The front section 208 of the fairing 110 also has a plurality of mounting holes 228 formed within it. These mounting holes 228 are for receiving fasteners (e.g., screws, rivets, or bolts) that connect the fairing 110 to underlying components and / or a reinforcing substructure, providing additional support and protection against objects striking the front section 208 of the fairing 110 (e.g., bird strikes). Fig. The mounting holes 228 form a pattern resembling an inverted "U" shape. The underlying substructure and its associated components are described in more detail below.

[0029] The component mounting system 102 comprises a variety of support fittings that can be installed between the support frame 116 and the outer skin of the aircraft 100 (e.g., a section of the fuselage 106). The support fittings are configured to physically fasten the support frame 116 to the outer skin of the aircraft 100. When the system 102 is fully installed on board the aircraft 100, the support fittings secure the antenna 108 to the fuselage 106, as the antenna 108 is held by the support frame 116. In addition, the support fittings indirectly couple the aerodynamic fairing 110 to the fuselage 106 via the support frame 116. The support fittings and their operation are described below with reference to the Fig. 17-27 described in more detail.

[0030] Fig. Figure 10 is a perspective view showing an exemplary installation arrangement of support and fastening elements, components and features located under the fuselage skin 104 of the aircraft 100. Fig. Figure 10 shows only a small section of the fuselage 106, along with various components, features, and structures used for the installation of the antenna 108, the support frame 116, and the fairing 110 (which are shown in Fig. 10 are not visible, as they are located on the outside of the fuselage skin 104). The support and fastening features are configured, positioned, and installed to allow the fairing 110 to be attached to the fuselage 106. The support and fastening features are further configured, positioned, and arranged to provide structural support for the fairing 110 when it is installed on the aircraft 100. Fig. 11 and Fig. Figure 12 shows some of the components and features of the Installation Arrangement 300 used for assembly, installation and structural support.

[0031] Fig. 10 corresponds to a view from inside the hull 106 looking upwards at the concave inner surface 176 of the hull skin 104 (the opposite outer surface of the hull skin 104 is in Fig. 10 not visible). Fig. Figure 10 shows a series of upwardly curved frames 302 that are part of the hull 106. Frame 302-1 is located at or near the aft end of the installation assembly 300, and frame 302-2 is located at or near the forward end of the installation assembly 300. The installation assembly 300 is designed, configured, and implemented to accommodate the existing structure and components of the hull 106, such as frames, stringers, skin, intermediate ribs, supports, and conduits. In this respect, the installation assembly 300 represents a complementary or reinforcing arrangement of components that can be connected to existing elements of the hull 106 to provide additional structural integrity and robustness. As shown in Figure 10, the installation assembly 300 is designed, configured, and implemented to accommodate the existing structure and components of the hull 106, such as frames, stringers, skin, intermediate ribs, supports, and conduits. Fig. As shown in Figure 10, the installation assembly 300 can be connected to the inner surface 176 of the fuselage skin 104. The various elements of the installation assembly 300 are positioned so that they correspond exactly to the respective features of the system 102 above them (e.g., mounting devices, support structures, mounting holes of the aerodynamic fairing 110, electrical connections, or cables associated with the antenna 108).

[0032] In Fig. 11 and Fig. Figure 12 shows certain components of the installation arrangement 300 excluding the fuselage 106, the fuselage skin 104, and components located above the fuselage skin 104. At least some of the components shown are also in Fig. Figure 10 is shown (for simplicity and better illustration, the individual components are shown in Fig. 10 not provided with reference numbers). One embodiment of the installation arrangement 300 may include the following components for attaching the support frame 116 and the fairing 110 to the aircraft fuselage 106: interrib supports 308, 310, 312, 314; cross frames 320, 322, 324, 326; Doppler 332; mounting plates 336; and clamps 342. In Fig. 11 and Fig. Only four of the eight interrib supports are numbered, only two Doppler 332 are marked, only two mounting plates 336 are marked, and only one bracket 342 is marked. Any number of Doppler 332 can be used to provide structural support in specific areas under the fuselage skin 104 (which are shown in Fig. 11 or Fig. (12 not shown). Any number of mounting plates 336 can be used to accommodate mounting features for components located outside the fuselage 106. Any number of brackets 342 (which can be realized in various shapes, sizes, and configurations) can be used to connect adjacent structural components. For example, brackets 342 can be used to connect an inter-rib support to a transverse frame.

[0033] As above with reference to Fig. As mentioned in section 7, the component assembly system 102 can include a suitably configured reinforcing substructure that is installed between the outer sheet (fuselage skin 104) of the aircraft 100 and the forward section 208 of the fairing 110. The reinforcing substructure is configured, arranged, and installed to provide structural support below the forward section 208 for protection against object impacts, such as bird strikes during flight. With reference to Fig. Figures 13-16 show the embodiment of the reinforcing substructure with at least one support rib 402 and at least one support frame 406. The illustrated embodiment of the system 102 comprises two longitudinal support ribs 402 and one transverse support frame 406 (see Figures 13-16). Fig. 28-31). Fig. 13 and Fig. Figure 14 shows a support rib 402 that can be used for one side of the reinforcing substructure (e.g., the left side). A mirror-image version of the support rib 402 can be used for the other side of the reinforcing substructure.

[0034] Fig. Figure 13 shows the support rib 402 with five mounting plates 410 attached to it, and Fig. Figure 14 shows the other side of the support rib 402 with the attached mounting plates 410. The mounting plates 410 accommodate threaded screws for attaching the overlying fairing 110 to the upper surface 414 of the support rib 402. Mounting holes 415 are machined into the base of the support rib 402. These mounting holes 415, which can be threaded holes or through holes, accommodate fasteners (e.g., screws, bolts, rivets) used to attach the support rib 402 to the aircraft fuselage 106.

[0035] Fig. Figure 15 is a perspective view of the support frame 406 from top to back, and Fig. Figure 16 is a perspective view of the support frame 406 from above looking forward. Although in Fig. 15 or Fig. Figure 16 (not shown) shows that the support frame 406 houses nine mounting plates (similar to the mounting plates 410) which accommodate threaded connections for attaching the overlying fairing 110 to the upper surface 416 of the support frame 406. Mounting holes 420 are machined into the base of the support frame 406. These mounting holes 420, which can be threaded holes or through holes, accommodate fasteners (e.g., screws, bolts, rivets) used to attach the support frame 406 to the aircraft fuselage 106.

[0036] As above with reference to Fig. 5 and Fig. As explained in section 6, the support frame 116 can be attached to the fuselage 106 using a series of support fittings. In the exemplary application described here, four support fittings are used, which are attached to or near the corners of the support frame 116. In this context, the Fig. 17-20 a front support fitting 502 configured to connect the support frame 116 to the aircraft fuselage 106, and the Fig. Figures 21-24 show a rear support fitting 504 configured to connect the support frame 116 to the aircraft fuselage 106. In practice, two versions of the front support fitting 502 (which may be mirror images of each other) and two versions of the rear support fitting 504 (which may be mirror images of each other) are used to attach the support frame 116 to the fuselage 106.

[0037] The forward support fitting 502 comprises, without limitation: a base 508; mounting holes 510 formed in the base 508; a support column 512 extending from the base 508; and a bearing component 514 (such as a ball bearing) that can be held in a hole formed in the support column 512. The base 508 and its mounting holes 510 are configured and arranged to allow the forward support fitting 502 to be mounted on the hull 106. In this respect, the arrangement of the mounting holes 510 corresponds to an arrangement of mounting plates that form part of the underlying installation arrangement 300. Threaded fasteners can be installed and tightened in the mounting holes 510 to secure the forward support fitting 502 to the hull 106.The support column 512 extends over the base 508 to a specific height to hold the support frame 116 above the fuselage 106 by the desired amount. The bearing component 514 is shaped, dimensioned, and sized to accommodate hardware components connected by a suitable fastening pin arrangement (see ). Fig. 19 and Fig. 20). As described in more detail below, the upper section of the support column 512 is shaped and dimensioned to be compatible with the front clevis attachment features 166, 168 of the support frame 116.

[0038] Fig. Figure 19 shows the front support fitting 502, a section of the support frame 116, and a series of parts that form a fastening pin assembly used to connect the front support fitting 502 to the support frame 116. More precisely, the fastening pin assembly couples the front support fitting 502 to its corresponding clevis fastening feature 168. According to the Fig. In the embodiment shown in Figure 19, the fastening pin arrangement comprises, without limitation: a bolt, a threaded fastener or a pin 520; a crown nut 522 compatible with the pin 520; a cotter pin 524 compatible with the crown nut 522 and the pin 520; a first flange sleeve 526; a first washer 528; a sleeve 530; a second washer 532; a second flange sleeve 534; and a third flange sleeve 536. Fig. Figure 20 shows the arrangement of these parts in the installed state and in conjunction with the front support fitting 502 and the clevis head fastening feature 168.

[0039] As in Fig. As shown in Figure 20, the flange sleeves 534 and 536 are inserted into the through holes of the clevis head mounting feature 168. The second flange sleeve 534 receives the first flange sleeve 526, and the third flange sleeve 536 receives the sleeve 530. The bolt 520 and the washers 528 and 532 can then be installed such that the bolt 520 sits in the through holes defined in the first flange sleeve 526, the first washer 528, the bearing part 514, the sleeve 530, and the second washer 532. The nut 522 is then screwed onto the end of the bolt 520, tightened, and secured with the cotter pin 524. Fig. 19 and Fig. The fastening pin arrangement shown in 20 is configured and installed such that a displacement of the support frame 116 relative to the front support fitting 502 is prevented in the dimension corresponding to the main longitudinal axis of the pin 520 (i.e. the horizontal dimension of Fig. 20). This configuration can be used to attach a support fitting to its respective clevis head mounting feature in a fixed and stationary position. In contrast, the configuration described in Fig. 23 and Fig. The fastening pin arrangement shown in Figure 24 results in a certain displacement of the support frame 116 relative to the support fitting. These aspects of the fastening pin arrangements are described in more detail below.

[0040] The rear support fitting 504 comprises, without limitation: a base 548; mounting holes 550 formed in the base 548; a support column 552 extending from the base 548; and a bearing component 554 (such as a ball bearing) that can be held in a hole formed in the support column 552. The base 548 and its mounting holes 550 are configured and arranged to allow the rear support fitting 504 to be mounted on the hull 106. In this respect, the arrangement of the mounting holes 550 corresponds to an arrangement of mounting plates that form part of the underlying installation arrangement 300. Threaded fasteners can be installed and tightened in the mounting holes 550 to secure the rear support fitting 504 to the hull 106.The support column 552 extends over the base 548 to a specific height to hold the support frame 116 above the fuselage 106 by the desired amount. The bearing component 554 is shaped, measured, and dimensioned to accommodate hardware components connected by a suitable fastening pin arrangement (see ). Fig. 23 and Fig. 24). As described in more detail below, the upper section of the support column 552 is shaped and dimensioned to be compatible with the rear clevis mounting features 170, 172 of the support frame 116.

[0041] Fig. Figure 23 shows the rear support fitting 504, a section of the support frame 116, and a series of parts forming a fastening pin assembly used to connect the rear support fitting 504 to the support frame 116. More precisely, the fastening pin assembly couples the rear support fitting 504 to its corresponding clevis fastening feature 170, 172. According to the Fig. In the embodiment shown in Figure 23, the fastening pin arrangement comprises, without limitation: a bolt, a threaded fastening element or a pin 560; a castle nut 562 compatible with the pin 560; a cotter pin 564 compatible with the castle nut 562 and the pin 560; a first washer 566; a first sleeve 568; a second sleeve 570; a second washer 572; a first flange sleeve 576; and a second flange sleeve 578. Fig. Figure 24 shows the arrangement of these parts as they are installed and connected to the rear support fitting 504 and the clevis head fastening feature 172.

[0042] As in Fig. As shown in Figure 24, the flange sleeves 576 and 578 are inserted into the through holes of the clevis head mounting feature 172. The first flange sleeve 576 receives the first sleeve 568, and the second flange sleeve 578 receives the second sleeve 570. The bolt 560 and the washers 566 and 572 can then be installed such that the bolt 560 sits in the through holes defined in the first washer 566, the first sleeve 568, the bearing part 554, the second sleeve 570, and the second washer 572. The nut 562 is then screwed onto the end of the bolt 560, tightened, and secured with the cotter pin 564. Fig. 23 and Fig. The fastening pin arrangement shown in Figure 24 is configured and installed to allow a displacement of the support frame 116 relative to the rear support fitting 504 in the dimension corresponding to the main longitudinal axis of the bolt 560 (i.e., the horizontal dimension of Fig. 24). More precisely, the clevis head 172 can move laterally freely (by an amount limited by its physical dimensions) relative to the fixed position of the fastening pin assembly and the rear support fitting 504. This configuration can be used to couple a support fitting with its respective clevis head fastening feature in such a way that a certain displacement of the support frame 116 relative to the support fitting is possible.

[0043] Fig. Figure 25 is a view from below, showing the antenna 108 connected to the support frame 116. Fig. Figure 26 is a front top view showing the antenna 108 coupled to the support frame 116 together with two front support fittings 502. Fig. Figure 27 is a rear top view showing the antenna 108 coupled to the support frame 116, along with two rear support fittings 504. Each of the support fittings 502, 504 is connected to one of the corresponding clevis-head fastening features 166, 168, 170, 172 (using a corresponding fastening pin arrangement). In this respect, the support fittings 502 and their respective fastening pin arrangements are used to connect the forward section of the support frame 116 to the fuselage skin 104 (or other outer sheet metal) of the aircraft 100, and the support fittings 504 and their respective fastening pin arrangements are used to connect the rear section of the support frame 116 to the fuselage skin 104 (or other outer sheet metal) of the aircraft 100.

[0044] In the Fig. Figures 25-27 show a three-axis reference coordinate system comprising an x-axis corresponding to the principal longitudinal dimension of the aircraft 100, a y-axis corresponding to the lateral dimension of the aircraft, and a z-axis corresponding to a vertical dimension of the aircraft 100. Referring to Fig. 26 The clevis head mounting feature 166, the front support fitting 502-R, and the respective mounting pin assembly are suitably configured, arranged, and installed to allow a degree of rotation about the longitudinal axis of the associated pin 520 (which is an axis parallel to the y-axis). Likewise, the clevis head mounting feature 168, the front support fitting 502-L, and the respective mounting pin assembly are suitably configured, arranged, and installed to allow rotation about the longitudinal axis of the associated pin 520 (which is an axis parallel to the y-axis). As in Fig. As shown in Figure 27, the clevis head fastening feature 170, the rear support fitting 504-R, and the respective fastening pin assemblies are suitably configured, arranged, and installed to allow rotation about the longitudinal axis of the associated bolt 520 (which is an axis parallel to the X-axis). Likewise, the clevis head fastening feature 172, the rear support fitting 504-L, and the respective fastening pin assemblies are suitably configured, arranged, and installed to allow rotation about the longitudinal axis of the associated pin 520 (which is an axis parallel to the X-axis).

[0045] The clevis mounting features, support fittings, mounting pin assemblies, and associated hardware components are configured and assembled to accommodate expansion, contraction, or movement of materials (e.g., caused by flight operations, temperature changes, or environmental variations). According to the exemplary embodiment described herein, both rear mounting assemblies prevent displacement about the y- and z-axes but allow some displacement about the x-axis (where the x-axis corresponds to the aircraft's main longitudinal axis, the y-axis to the aircraft's horizontal left-right axis, and the z-axis to the vertical dimension).In contrast, one of the two front mounting arrangements inhibits or prevents displacement about the x-axis, y-axis and z-axis, while the other front mounting arrangement inhibits or prevents displacement about the x-axis and z-axis, but allows displacement about the y-axis.

[0046] More precisely, the right front support bracket 502-R, its clevis mounting feature 166, and its corresponding mounting pin arrangement are collectively configured to prevent displacement along the x-axis, prevent displacement along the z-axis, and allow some displacement along the y-axis. In contrast, the left front support bracket 502-L, its clevis mounting feature 168, and its corresponding mounting pin arrangement are collectively configured to prevent displacement in all three axes. In other words, the front left section of the support frame 116 is effectively connected (fixed) to the front support bracket 502-L. As shown in Fig. As shown in Figure 27, the rear right support fitting 504-R, its clevis mounting feature 170, and its corresponding mounting pin arrangement are configured to prevent displacement along the y-axis, prevent displacement along the z-axis, and allow some displacement along the x-axis. Similarly, the left rear support fitting 504-L, its clevis mounting feature 172, and its corresponding mounting pin arrangement are collectively configured to prevent displacement along the y-axis, prevent displacement along the z-axis, and allow some displacement along the x-axis.

[0047] Fig. Figure 28 is a perspective view from above of the front, showing part of the aircraft fuselage 106 with various components attached to it (the aerodynamic fairing 110 is not shown). Fig. 29 is a top view, which Fig. 28 corresponds to Fig. 30 is a side view that Fig. 28 corresponds to Fig. 31 is a front view, which Fig. 28 corresponds to Fig. 32 is a rear view, which Fig. 28 corresponds to most of the in Fig. The components shown in sections 28-32 are not visible and are covered by the cover 110 (see Fig. 1-3). These figures show an exemplary installation of the antenna 108, the support frame 116, the support ribs 402, the support frame 406 and the support fittings 502, 504, which lie above the fuselage skin 104. Fig. 28 and Fig. Figure 29 also shows a fairing seal 608 (e.g., at least one seal, a layer of sealing material, or the like) arranged and configured to seal the fairing 110 against the fuselage skin 104. A support seal 610 (e.g., at least one seal, a layer of sealing material, or the like) is arranged and configured to seal the fairing 110 against the support frame 116 (and / or against the antenna 108). Seals and / or sealing material can also be used to seal the upper surfaces of the support ribs 402 and the support frame 406 against the fairing 110. The support frame 116 serves as an adapter and interface that allows the antenna 108 to be mounted on an edge region of the fairing 110 adjacent to the main opening 204 of the fairing 110. As shown in Fig. As shown in Figure 11, the underlying inner components are used to control the outer components above (in the Fig. to attach (shown on 28-32) to the fuselage 106.

[0048] In accordance with certain exemplary implementations, the following procedure can be carried out to install the antenna 108 and the associated antenna fairing 110 on a vehicle, such as the aircraft 100. As a first step, the support frame 116 and the four support fittings 502, 504 are assembled to form a support subassembly. The support fittings 502, 504 are provided with mounting holes, and the bases 508, 548 of the support fittings 502, 504 serve as mounting feet for the support subassembly. A template containing the desired hole pattern (e.g., a printed Mylar film) is applied to the outer surface of the fuselage skin 104 and positioned and secured to identify the desired mounting locations for the support fittings 502, 504.The template serves as a guide for drilling a series of holes for the temporary installation of the support fittings 502 and 504 at the designated locations, which in turn facilitates the correct positioning, alignment, and installation of other structures and components (e.g., components to be installed inside the hull 106). For reasons that will be explained later, temporary fasteners are used at this point.

[0049] In this example, the mounting holes of each support fitting 502, 504 correspond to reference positions on the respective inter-rib support structure (e.g., the mounting assembly 300 described above) that is installed under the fuselage skin 104. In this way, the guide holes can serve as a reference for locating the mounting positions of inter-rib support structures, Doppler components, support frames, and the like. The Mylar template contains markings corresponding to all the necessary mounting holes that penetrate the fuselage skin 104 (for fasteners, bolts, rivets, etc.). This allows technicians to attach the various parts to the inside and outside of the fuselage skin 104. For this purpose, various coordinate holes can be marked for the components to be installed, such as the support fittings 502, 504, the support ribs 402, the support frame 406, etc.

[0050] The coordinated holes serve to temporarily fix structures to the fuselage skin 104, which in turn facilitates the correct positioning and installation of the internal components. Once all the coordinated holes have been formed, a technician inside the fuselage 106 can install the Dopplers, interrib braces, support frames, and the like. The reference holes and reference positions can then be used as a guide for drilling or creating the remaining holes required for installing the various components. After drilling or otherwise creating the required holes in the fuselage, the temporarily installed components are removed to facilitate cleaning, deburring, etc.

[0051] The Doppler 332 (some of which may be fitted with mounting plates) are connected to the inner surface of the fuselage skin 104, e.g., by rivets. Subsequently, the internal support structures can be attached: the inter-rib supports, the transverse bulkheads, the connecting brackets, and the like. Outside the fuselage 106, the supporting ribs 402 and the support frame 406 (for protection against object impacts), as well as the support assembly, are attached to the fuselage skin 104 at the designated locations. Seals, gaskets, and / or other treatments are applied to seal the fuselage as required, resulting in the [missing information - likely a specific type of seal or component]. Fig. The condition shown in Figures 28-32 is achieved. Next, the aerodynamic fairing 110 is inserted and attached to the support frame 116, the fuselage skin 104, the support ribs 402, and the support frame 406, so that the [condition] shown in the Fig. The state shown in 1-3 is reached.

[0052] Although at least one exemplary embodiment has been presented in the preceding detailed description, it should be understood that a multitude of variations exist. It should also be noted that the exemplary embodiment(s) described here are in no way intended to limit the scope, applicability, or configuration of the claimed subject matter. Rather, the preceding detailed description is intended to provide the person skilled in the art with a practical guide for implementing the described embodiment(s). It is understood that various modifications to the function and arrangement of the elements can be made without departing from the scope defined by the claims, which includes known equivalents foreseeable at the time of filing this patent application. QUOTES INCLUDED IN THE DESCRIPTION

[0000] This list of documents cited by the applicant was automatically generated and is included solely for the reader's convenience. The list is not part of the German patent or utility model application. The DPMA accepts no liability for any errors or omissions. Cited patent literature

[0000] US 63 / 638,188

[0001]

Claims

[1] A system for attaching a component to an outer wall of a vehicle, wherein the system comprises: a support frame configured to accommodate and hold the component; a variety of support fittings, each of which can be coupled between the support frame and the outer panel of the vehicle, the support fittings being configured to physically attach the support frame to the outer panel of the vehicle; and a fairing comprising an upper section with an opening defined therein and a lower section configured and arranged for connection with the outer sheet metal of the vehicle, wherein the opening is shaped and dimensioned to accommodate at least a part of the support frame, and wherein the support frame is connected to the upper section of the fairing. [2] The system according to claim 1, wherein the support frame is configured to surround a circumferential edge of the component; and the support frame holds the component such that a main surface of the component is exposed. [3] The system according to claim 1, wherein the support frame has a plurality of clevis attachment features corresponding to the plurality of support fittings; and wherein each support fitting of the plurality of support fittings is connected to a corresponding clevis attachment feature using a fastening pin arrangement. [4] The system according to claim 3, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and wherein a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to interact such that they prevent displacement along the x-axis, prevent displacement along the z-axis, and allow displacement along the y-axis. [5] System according to claim 4, wherein the provided fork head fastening feature, the corresponding support fitting and the corresponding fastening pin arrangement are used to connect a front section of the support frame to the outer wall of the vehicle. [6] The system according to claim 3, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and wherein a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to interact such that they prevent displacement along the y-axis, prevent displacement along the z-axis, and allow displacement along the x-axis. [7] System according to claim 6, wherein the provided fork head fastening feature, the corresponding support fitting and the corresponding fastening pin arrangement are used to connect a rear section of the support frame to the outer wall of the vehicle. [8] The system according to claim 3, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and wherein a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to interact such that they prevent displacement along the x-axis, displacement along the z-axis, and displacement along the y-axis. [9] The system according to claim 1, further comprising a reinforcing substructure coupled between the outer sheet metal of the vehicle and a front section of the fairing, wherein the reinforcing substructure is configured and arranged to provide structural support below the front section of the fairing for protection against objects striking the front section of the fairing. [10] The system according to claim 1, wherein the outer plate has an outside and an opposite inside; the system further comprises an arrangement of support and fastening features connected to the inside of the outer plate; and The arrangement of the support and fastening features is designed to enable the cladding to be attached to the outer panel, and is further designed to provide structural support to the cladding when the cladding is attached to the outer panel. [11] A system configured to be attached to the exterior paneling of a vehicle, the system comprising: an antenna component; a support frame coupled to the antenna component, wherein the support frame has a plurality of fork-head mounting features; a variety of support fittings, each of which can be coupled between one of the fork-head mounting features and the outer wall of the vehicle; and an aerodynamic fairing comprising an upper section with an opening defined therein and a lower section configured and arranged to couple with the outer sheet metal of the vehicle, wherein the opening is shaped and dimensioned to accommodate at least a part of the support frame, and wherein the support frame is coupled to the upper section of the fairing. [12] System according to claim 11, wherein the antenna component is a flat panel satellite communication antenna. [13] The system according to claim 11, wherein each support fitting of the plurality of support fittings is connected to a corresponding clevis head fastening feature using a fastening pin arrangement. [14] The system according to claim 13, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to interact such that they prevent displacement along the x-axis, prevent displacement along the z-axis, and allow displacement along the y-axis. [15] The system according to claim 13, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to interact such that they prevent displacement along the y-axis, prevent displacement along the z-axis, and allow displacement along the x-axis. [16] The system according to claim 13, wherein a three-axis reference coordinate system has an x-axis corresponding to a longitudinal dimension of the vehicle, a y-axis corresponding to a lateral dimension of the vehicle, and a z-axis corresponding to a vertical dimension of the vehicle; and a specific clevis head fastening feature from the plurality of clevis head fastening features, a corresponding support fitting, and a corresponding fastening pin arrangement are configured to act together such that they prevent displacement along the x-axis, displacement along the z-axis, and displacement along the y-axis. [17] The system according to claim 11, further comprising a reinforcing substructure coupled between the outer sheet metal of the vehicle and a front section of the fairing, wherein the reinforcing substructure is configured and arranged to provide structural support below the front section of the fairing for protection against objects striking the front section of the fairing. [18] The system according to claim 11, wherein the outer plate has an outside and an opposite inside; the system further comprises an arrangement of support and fastening features connected to the inside of the outer plate; and the arrangement of support and fastening features is configured to allow the cladding to be attached to the outer panel, and is further configured to provide structural support to the cladding when the cladding is attached to the outer panel. [19] A vehicle with the system according to claim 11. [20] The vehicle according to claim 19, wherein the vehicle is an aircraft; the outer plate of an aircraft fuselage skin; and The antenna component is a flat panel satellite communication antenna.

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