System for attaching heat-generating device to exterior of aircraft

Abstract

A mounting system and method for attaching a heat generating device to the exterior of an aircraft. The mounting system includes: a hot chamber made of a plurality of thermally conductive materials, the hot chamber having a recess open to an environment external to the aircraft; the heating device is fixed in the concave part; and an insulating layer between the hot cell and the aircraft, the insulating layer being positioned on a side of the hot cell opposite the opening of the recess.

Description

Technical Field

[0001] The present disclosure relates generally to aircraft, and more particularly to attaching a heat generating device to the exterior of an aircraft. Background Art

[0002] Antennas are present on aircraft for navigation or communication purposes. Aircraft also utilize many types of sensors to detect temperature, airflow, vibration, position, force, pressure, or any other desired characteristic. Adding antennas or sensors or utilizing new technologies for antennas and sensors may generate additional heat.

[0003] Therefore, there is a need for a method or apparatus that can take into account at least some of the above problems and other possible problems. Summary of the invention

[0004] Embodiments of the present disclosure provide a mounting system for attaching a heat generating device to the exterior of an aircraft. The mounting system includes a heat chamber, a heat generating device, and a thermal insulation layer. The heat chamber is made of a variety of heat conducting materials. The heat chamber has a recess that is open to the environment outside the aircraft. The heat generating device is fixed in the recess. The thermal insulation layer is located between the heat chamber and the aircraft. The thermal insulation layer is positioned on a side of the heat chamber opposite to the opening of the recess.

[0005] Another embodiment of the present disclosure provides a mounting system for attaching a heat generating device to the exterior of an aircraft. The mounting system includes a base plate having a recess surrounded by a flange, a heat generating device positioned in the recess, and a thermal insulation layer fixed to the back of the base plate. The base plate is made of a thermally conductive material.

[0006] Another embodiment of the present disclosure provides a method of attaching a heat generating device to the exterior of an aircraft. A thermal insulation layer is positioned between the heat generating device and the skin of the fuselage of the aircraft. A shield is secured over the thermal insulation layer to form a thermal chamber between the thermal insulation layer and the external environment.

[0007] The various features and the various functions may be implemented independently in various embodiments of the present disclosure, or may be combined in yet other embodiments, in which further details may be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0008] The novel features believed to characterize the various exemplary embodiments are set forth in the appended claims. However, these exemplary embodiments together with the preferred modes of use, and further objects and features thereof, will be best understood by reference to the following detailed description of exemplary embodiments of the present disclosure when read in conjunction with the accompanying drawings, in which:

[0009] Figure 1 is a diagram of an aircraft according to an exemplary embodiment;

[0010] Figure 2 is an illustration of a block diagram of an aircraft having a system installed according to an exemplary embodiment;

[0011] Figure 3 is an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0012] Figure 4 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0013] Figure 5 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0014] Figure 6 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0015] Figure 7 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0016] Figure 8 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0017] Fig. 9 is an illustration of a cross-sectional view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0018] Fig.10 is an illustration of a block diagram of an aircraft having a system installed according to an exemplary embodiment;

[0019] Fig.11 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0020] Fig.12 is an illustration of an isometric view of a portion of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0021] Fig.13 is an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0022] Fig.14 is an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment;

[0023] Fig.15is a flow chart of a method of attaching a heat generating device to the exterior of an aircraft according to an exemplary embodiment;

[0024] Fig.16 is a flow chart of a method of attaching a heat generating device to the exterior of an aircraft according to an exemplary embodiment;

[0025] Fig.17 is a flow chart of a method of retrofitting a radome for covering a heat generating device on an aircraft according to an exemplary embodiment;

[0026] Fig.18 is a schematic diagram showing, in block diagram form, an aircraft manufacturing and service method according to an exemplary embodiment; and

[0027] Fig.19 is a diagram showing, in block diagram form, an aircraft in which an illustrative embodiment may be implemented. DETAILED DESCRIPTION

[0028] Now turn to Figure 1 , depicts a diagram of an aircraft according to an exemplary embodiment. Aircraft 100 has wing 102 and wing 104 attached to body 106. Aircraft 100 includes engine 108 attached to wing 102 and engine 110 attached to wing 104.

[0029] The body 106 has a tail section 112. Attached to the tail section 112 of the body 106 are a horizontal stabilizer 114, a horizontal stabilizer 116, and a vertical stabilizer 118.

[0030] Aircraft 100 is one example of an aircraft that may have a heat generating device mounted to body 106 according to several illustrative examples. For example, mounting system 120 may be a physical implementation of a mounting system having a heat generating device. Several illustrative examples may be used to mount an electronic antenna or any other desired type of heat generating device to body 106 of aircraft 100.

[0031] Skin 122 of aircraft 100 has an upper temperature threshold. Depending on ambient temperature, environmental conditions, paint and other surface treatments on skin 122, and operating conditions of heat generating devices, undesirably high temperatures may be reached and the upper temperature threshold may be reached. Several illustrative examples provide a mounting system, i.e., mounting system 120, that reduces heat transferred from heat generating devices to skin 122 of aircraft 100. Mounting system 120 prevents skin 122 from reaching the upper temperature limit due to the heat generating devices.

[0032] Now turn to Figure 2 , depicts an illustration of a block diagram of an aircraft having an installed system according to an exemplary embodiment. Aircraft 100 may be Figure 2A physical implementation of the aircraft 200 in FIG.

[0033] The mounting system 202 is configured to attach the heat generating device 204 to the exterior 206 of the aircraft 200. The mounting system 202 includes a heat chamber 208, the heat generating device 204, and a thermal insulation layer 210. The heat chamber 208 is made of a plurality of heat conductive materials (heat conductive material 212 and heat conductive material 214). The heat chamber 208 has a recess 216 that is open to an environment 218 outside the aircraft 200. The heat generating device 204 is fixed in the recess 216. The thermal insulation layer 210 is located between the heat chamber 208 and the aircraft 200. The thermal insulation layer 210 is located on a side of the heat chamber 208 opposite to the opening of the recess 216.

[0034] Thermal insulation 210 is present to reduce heat transfer from heat generating device 204 to skin 246 of fuselage 256. In some illustrative examples, skin 246 is made of composite material 268. It is desirable to reduce the amount of heat transferred to composite material 268 during operation of aircraft 200 and heat generating device 204.

[0035] The skin 246 of the aircraft 200 has an upper temperature threshold. Depending on the ambient temperature, environmental conditions, paint and other surface treatments on the skin 246, and operating conditions for the heat generating device 204, undesirably high temperatures may be reached and the upper temperature threshold may be reached. The mounting system 202 reduces the amount of heat transferred from the heat generating device 204 to the skin 246 of the aircraft 200. The mounting system 202 prevents the skin 246 from reaching the upper temperature limit due to the heat generating device 204.

[0036] Thermal insulation 210 is provided to protect adapter plate 254 and underlying aircraft structure, such as skin 246 of fuselage 256, from heat generated by heat generating device 204 held by mounting system 202. Thermal insulation 210 may take any desired form. In some exemplary examples, thermal insulation 210 takes the form of thermal insulation pad 264. In some exemplary examples, thermal insulation pad 264 is the same material used in thermal propulsion insulation locations. In some exemplary examples, thermal insulation 210 has a temperature resistance of 450 degrees Fahrenheit.

[0037] Heat generating device 204 takes any desired form of heat generating device that is desirably secured to exterior 206 of aircraft 200 . In some illustrative examples, heat generating device 204 includes number of electronic antennas 219 . In some illustrative examples, heat generating device 204 includes number of sensors 220 .

[0038] In some illustrative examples, heat chamber 208 is formed of two or more parts that are joined together. In some illustrative examples, heat chamber 208 is formed of shroud 222 and base plate 224. Shield 222 is configured to cover insulation layer 210. Shield 222 is the portion of mounting system 202 that is exposed to environment 218 outside aircraft 200. Shield 222 may also be referred to as a shell or cover. Shield 222 is configured to have aerodynamic design 274.

[0039] Shield 222 is made of thermally conductive material 214. By being made of thermally conductive material 214, shield 222 provides protection against lightning strikes. By being made of thermally conductive material 214, shield 222 provides a path for radiant heat 226 to escape from mounting system 202. In some illustrative examples, shield 222 is referred to as a "heat sink." Radiant heat 226 is heat generated by heat generating device 204 and is substantially isolated in thermal chamber 208 by insulation layer 210.

[0040] In some exemplary examples, thermally conductive material 214 includes metal 228. In some exemplary examples, metal 228 is aluminum 230. Thermally conductive material 214 is selected taking into account at least one of weight, machinability, wearability, thermal conductivity, and other material properties.

[0041] Shield 222 has any desired design configured to cover portions of mounting system 202 while exposing heat generating device 204 to environment 218. In some exemplary examples, shield 222 includes multiple portions secured together. In some exemplary examples, shield 222 includes skin 232 and access panel 234. Skin 232 and access panel 234 are connected in any desired manner.

[0042] In some exemplary examples, skin 232 and access panel 234 are connected by upper ring 236. In some exemplary examples, upper ring 236 connects skin 232 to base plate 224. In some exemplary examples, upper ring 236 is directly connected to flange 238 of base plate 224 and skin 232. In some exemplary examples, upper ring 236 may be referred to as an upper bracket or a connecting bracket. Flange 238 of base plate 224 is fixed to shroud 222.

[0043] As shown, shroud 222 also includes a lower ring 240. In some illustrative examples, skin 232 is connected to adapter plate 254 via lower ring 240. In some illustrative examples, lower ring 240 may be referred to as a lower bracket or a connecting bracket.

[0044] As depicted, the mounting system 202 also includes a skirt seal 242 coupled to the lower ring 240 of the shroud 222. The skirt seal 242 seals the mounting system 202 to prevent fluid leakage.

[0045] In some illustrative examples, a plurality of thermal insulators (thermal insulators 244) are positioned between shield 222 and skin 246 of aircraft 200. As described, mounting system also includes thermal insulators 244 positioned between lower ring 240 and skin 246 of aircraft. Thermal insulators 244 are provided to prevent heat from being conducted from shield 222 to skin 246 of aircraft 200.

[0046] The bottom plate 224 is configured to support the heat generating device 204 and form a bottom portion of the thermal chamber 208. The bottom plate 224 is made of a thermally conductive material 212. The bottom plate 224 conducts heat from the heat generating device 204 into the shield 222 for dissipation of the heat as radiant heat 226 to the environment 218.

[0047] In some illustrative examples, thermally conductive material 212 includes metal 248. In some illustrative examples, metal 248 is aluminum 250. In some illustrative examples, base plate 224 is a unitary 252 structure. In some illustrative examples, base plate 224 is a unitary 252 metal 248 structure.

[0048] In some exemplary examples, the bottom plate 224 includes a recess 216 and a flange 238 surrounding the recess 216. The recess 216 can hold any desired type or design of heat generating device. The recess 216 can hold electronic antennas of a variety of different designs. In some exemplary examples, the recess 216 holds a plurality of sensors 220. Because the recess 216 is designed to hold any desired heat generating device 204, the bottom plate 224 can be referred to as a universal component.

[0049] The bottom plate 224 is secured to an adapter plate 254. The adapter plate 254 is configured to connect a plurality of components to the skin 246 of the aircraft 200. The adapter plate 254 is configured to be mounted directly to a fuselage 256 of the aircraft 200. The adapter plate 254 is connected to the fuselage 256 by fasteners 266. The fasteners 266 take the form of any desired type of fastener. In some illustrative examples, the adapter plate 254 is a common component of multiple aircrafts of different designs. In some illustrative examples, the adapter plate 254 has a design common to different types of components for mounting in addition to the mounting system 202.

[0050] In some illustrative examples, aircraft 200 is already in operation, and adapter plate 254 is an existing structure of aircraft 200. In some of these illustrative examples, adapter plate 254 is already present on aircraft 200, and the remaining components of mounting system 202 are retrofitted to adapter plate 254. Because adapter plate 254 serves multiple functions, can be retrofitted, and used on multiple aircraft designs, it may be referred to as a universal adapter.

[0051] Fitting 258 connects base plate 224 to adapter plate 254. Fitting 258 pierces insulation layer 210. In some exemplary examples, a plurality of thermal insulators 260 are positioned between base plate 224 and adapter plate 254. In some exemplary examples, a plurality of thermal insulators 260 and fitting 258 are used together to reduce heat conduction from base plate 224 to adapter plate 254.

[0052] A plurality of thermal insulators (thermal insulators 244 ) are positioned between thermal chamber 208 and aircraft 200 . Thermal insulators 244 reduce or prevent heat transfer from thermal chamber 208 to aircraft 200 .

[0053] In some illustrative examples, mounting system 202 for attaching heat generating device 204 to exterior 206 of aircraft 200 includes base plate 224, heat generating device 204, and thermal insulation 210. Base plate 224 has recess 216 surrounded by flange 238. Base plate 224 is made of thermally conductive material 212. Heat generating device 204 is positioned within recess 216. Thermal insulation 210 is secured to back side 262 of base plate. In some illustrative examples, heat generating device 204 includes a plurality of electronic antennas 219.

[0054] In some illustrative examples, shroud 222 includes multiple parts that are secured together. Shield 222 is made of thermally conductive material 214 and is configured to have an aerodynamic design.

[0055] In some illustrative examples, portions 272 of shroud 222 include skin 232 and access panels 234. Skin 246 is secured to adapter plate 254 that is configured to connect components to skin 246 of aircraft 200. Access panels 234 are designed to accommodate the cross-sectional shape of heat generating device 204.

[0056] Figure 2 The illustration of aircraft 200 in FIG. 1 is not meant to imply physical or structural limitations to the methods in which the exemplary embodiments may be implemented. Other components in addition to or in place of the components shown may be used. Some components may not be required. In addition, the blocks are presented to illustrate some functional components. When implemented in the exemplary embodiments, one or more of these blocks may be combined, split, or combined and split into different multiple blocks.

[0057] For example, although not depicted, thermal isolation may be provided between the thermal chamber 208 and the adapter plate 254. For example, the thermal isolation portion is positioned between the shroud 222 and the adapter plate 254. Although the thermal isolation positioned between the shroud 222 and the skin 246 of the aircraft 200 is described as the thermal isolation 244, the number of thermal isolations may include more than one thermal isolation.

[0058] Now turn to Figure 3, depicts an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment. View 300 of mounting system 301 is a cross-sectional view of mounting system 301 mounted to skin 302 of aircraft 303 .

[0059] The installation system 301 is Figure 2 In view 300, adapter plate 304 is connected to aircraft 303. Insulation layer 306 is positioned between base plate 308 and adapter plate 304. Insulation layer 306 reduces or prevents heat from heat generating device 310 from being conducted to adapter plate 304 and skin 302 of aircraft 303.

[0060] The shield 312 is connected to the adapter plate 304 and the base plate 308. The shield 312 provides a housing for the mounting system 301. The shield 312 has lightning protection, heat dissipation and aerodynamic properties.

[0061] Bottom plate 308 and shroud 312 form heat chamber 314. Heat chamber 314 has heat from heat generating device 310. Heat chamber 314 is thermally isolated from adapter plate 304 and skin 302 of aircraft 303 by thermal insulation layer 306. In some exemplary examples, additional thermal insulation is positioned at the connection point of shroud 312 to adapter plate 304. In some exemplary examples, additional thermal insulation is positioned at the connection point of bottom plate 308 to adapter plate 304.

[0062] The heat leaves the thermal chamber 314 in the form of radiant heat 316. The radiant heat 316 leaves a recess 318 in the base plate 308. The radiant heat 316 also radiates from the thermally conductive material of the shroud 312.

[0063] Now turn to Figure 4 , depicts an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. The mounting system 400 includes an adapter plate 402 and a thermal insulation layer 404. The adapter plate 402 is Figure 2 The physical implementation of the adapter plate 254 in FIG. The thermal insulation layer 404 is Figure 2 The physical implementation of the thermal insulation layer 210 in FIG.

[0064] Adapter plate 402 is configured to be mounted directly to the fuselage of an aircraft. If the other components of mounting system 400 are retrofits, adapter plate 402 may already be present on the aircraft. In some illustrative examples, adapter plate 402 has a design that is common to aircraft of multiple designs. Because adapter plate 402 serves multiple functions, can be retrofitted, and is used on multiple aircraft designs, the adapter plate may be referred to as a universal adapter.

[0065] Insulation layer 404 is provided to protect adapter plate 402 and the underlying aircraft structure from heat generated by the heat generating device held by mounting system 400. In some exemplary embodiments, insulation layer 404 takes the form of an insulating pad. Although insulation layer 404 is shown as being applied to adapter plate 402 as a first step, in other exemplary embodiments, insulation layer 404 may first be attached to an additional component such as a heat generating device. Figure 2 In some exemplary embodiments, the thermal insulation layer 404 is Figure 2 A portion of the antenna assembly 270 manufactured in FIG. 4 is connected as a part to the adapter board 402 .

[0066] Now turn to Figure 5 , depicts an illustration of an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. In view 500 of mounting system 400, base plate 502 is also depicted. Base plate 502 is connected to adapter plate 402 by fitting 504. Fitting 504 extends through insulation layer 404. A sealant (not shown) is applied to seal insulation layer 404 at the location where fitting 504 extends through insulation layer 404. The sealant prevents liquid from entering insulation layer 404. In some exemplary instances, the sealant is also insulating so that heat does not extend through insulation layer 404 at the location of fitting 504.

[0067] The bottom plate 502 is configured to support a heat generating device such as a sensor or an antenna. The bottom plate 502 includes a recess 506. When assembled, the heat generating device is positioned within the recess 506. A flange 508 extends around the recess 506. The flange 508 is configured to secure the bottom plate 502 to a shield such as a Figure 7 Shield portion 702 is shown.

[0068] As depicted, base plate 502 is a unitary structure. Base plate 502 is made from a single piece of thermally conductive material. Base plate 502 is configured to form a portion of a thermal chamber of mounting system 400.

[0069] The base plate 502 is configured to support any desired type of heat generating device.The base plate 502 can be described as a general purpose component.

[0070] Now turn to Figure 6 , depicts an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. View 600 is a view of mounting system 400 with heat generating device 601 positioned within recess 506 of base plate 502. In this exemplary example, heat generating device 601 includes electronic antenna 602 and electronic antenna 604. In view 600, electronic antenna 602 and electronic antenna 604 are positioned within recess 506 of base plate 502.

[0071] In some exemplary embodiments, thermal insulation layer 404, base plate 502, and heat generating device 601 are assembled into a prefabricated antenna assembly before base plate 502 is connected to adapter plate 402. By securing heat generating device 601 in base plate 502 before securing base plate 502 to adapter plate 402, assembly time on the final assembly line can be reduced. Connecting heat generating device 601 offline can reduce manufacturing time.

[0072] Now turn to Figure 7 , depicts an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. In view 700 of mounting system 400, shield portion 702 is attached to Figure 4 The bottom plate 502 and the adapter plate 402 in the embodiment of the present invention are shown in FIG. 7 . Although the shield portion 702 appears to be one component, the shield portion 702 can be formed by multiple components connected together. In some exemplary embodiments, the shield portion 702 includes a skin.

[0073] Now turn to Figure 8 , depicts an illustration of an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. View 800 of mounting system 400 is a fully assembled system.

[0074] In view 800, shield 802 includes shield portion 702 and access panel 803. Access panel 803 is configured based on the design and location of heat generating device 601. By having access panel 803, shield portion 702 can be used for any type or design of heat generating device that may be present in recess 506 of base plate 502. Access panel 803 includes access panel 804, access panel 806, access panel 808, and access panel 810. Each of shield portion 702 and access panel 803 is connected to base plate 502.

[0075] The skirt seal 812 is coupled to the shroud portion 702 . The skirt seal 812 is configured to seal to the fuselage of the aircraft to reduce the intrusion of fluids into the mounting system 400 .

[0076] Now turn to Fig. 9 , depicts a cross-sectional view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. View 900 is a cross-sectional view of mounting system 901. Mounting system 901 is Figure 2 The physical implementation of the installation system 202 in FIG. Figure 3 The installation system 901 can be the same as the installation system 301 in FIG. Figures 4 to 8 The same as the mounting system 400 in.

[0077] In view 900 of mounting system 901, heat generating device 904 takes the form of a plurality of electronic antennas 902. The plurality of electronic antennas 902 are located in base plate 906. The plurality of electronic antennas 902 are exposed to the environment outside mounting system 901.

[0078] The bottom plate 906 is connected to a shroud 910. The shroud 910 includes an upper ring 912, a skin 914, and a lower ring 916. The shroud 910 is connected to an adapter plate 918.

[0079] Although not shown in view 900, base plate 906 is connected in a plurality of discrete locations to adapter plate 918. Although not depicted in view 900, adapter plate 918 is mounted to the fuselage of the aircraft.

[0080] The shield 910, the bottom plate 906 and the insulation layer 908 form a hot chamber. The insulation layer 908 reduces the amount of heat that travels from the hot chamber to the aircraft structure below the insulation layer 908. The insulation layer 908 reduces the amount of heat that is transferred from the heat generating device 904 to the adapter plate 918 and the aircraft skin (not shown) below the adapter plate 918. In addition, the distance between the bottom plate 906 and the adapter plate 918 reduces the amount of heat that reaches the adapter plate 918. The distance between the bottom plate 906 and the adapter plate 918 provides passive control of the amount of heat that the adapter plate 918 is subjected to. The skirt seals and the thermal insulation 920 reduces the amount of heat that is transferred from the shield 910 to the fuselage.

[0081] The heat generated by the heat generating device 904 is radiated to the environment outside the mounting system 901. The heat generating device 904 directly radiates the heat to the environment. In addition, the heat is radiated from the shield 910.

[0082] Now turn to Fig.10 , depicts an illustration of a block diagram of an aircraft having an installed system according to an exemplary embodiment. Aircraft 100 may be Fig.10 A physical implementation of aircraft 1000 in FIG.

[0083] Mounting system 1002 is configured to attach heat generating device 1016 to exterior 1074 of aircraft 1000. Mounting system 1002 includes adapter plate 1004, thermal insulation layer 1008, base plate 1012, heat generating device 1016, and radome 1018. Adapter plate 1004 is coupled to fuselage 1006 of aircraft 1000. Thermal insulation layer 1008 substantially covers first side 1010 of adapter plate 1004. Base plate 1012 is made of thermally conductive material 1014 and coupled to adapter plate 1004 such that thermal insulation layer 1008 is positioned between base plate 1012 and adapter plate 1004. In some illustrative examples, thermal insulation layer 1008 is in contact with back side 1060 of base plate 1012. Heat generating device 1016 is secured within base plate 1012. The radome 1018 is connected to the adapter plate 1004 and is positioned to cover the heat generating device 1016 and the base plate 1012 .

[0084] Thermal insulation 1008 is present to reduce the amount of heat transferred from heat generating devices 1016 to skin 1070 of fuselage 1006. In some illustrative examples, skin 1070 is made of composite material 1072. It is desirable to reduce the amount of heat transferred to composite material 1072 during operation of aircraft 1000 and heat generating devices 1016.

[0085] The skin 1070 of the aircraft 1000 has an upper temperature threshold. Depending on the ambient temperature, environmental conditions, paint and other surface treatments on the skin 1070, and operating conditions for the heat generating device 1016, undesirably high temperatures may be reached and the upper temperature threshold may be reached. The mounting system 1002 reduces the amount of heat transferred from the heat generating device 1016 to the skin 1070 of the aircraft 1000. The mounting system 1002 prevents the skin 1070 from reaching the upper temperature limit due to the heat generating device 1016.

[0086] Thermal insulation 1008 is provided to protect adapter plate 1004 and underlying aircraft structure, such as skin 1070 of fuselage 1006, from heat generated by heat generating device 1016 held by mounting system 1002. Thermal insulation 1008 may take any desired form. In some exemplary examples, thermal insulation 1008 takes the form of thermal insulation pad 1064. In some exemplary examples, thermal insulation pad 1064 is the same material used in thermal propulsion insulation locations. In some exemplary examples, thermal insulation 1008 has a temperature resistance of 450 degrees Fahrenheit.

[0087] The radome 1018 is connected to the adapter plate 1004 so that the heat generating device 1016 is positioned within the interior 1019 of the radome 1018. The radome 1018 is connected to the adapter plate 1004 by thermal insulation 1078 to reduce or prevent heat transfer from the radome 1018 to the adapter plate 1004, the skin 1070, and the fuselage 1006. The skirt seal 1076 seals the radome 1018 to the skin 1070 to reduce the ingress of liquids into the interior 1019 of the radome 1018.

[0088] In some exemplary examples, radome 1018 is made of thermally conductive material 1020. Thermally conductive material 1020 may take the form of metal 1022. When radome 1018 is made of thermally conductive material 1020, heat from heat generating device 1016 may escape radome 1018 and enter environment 1028 outside radome 1018 in the form of radiated heat 1026. In some exemplary examples, when radome 1018 is made of thermally conductive material 1020, radome 1018 may have a conventional design. In some exemplary examples, when radome 1018 is made of thermally conductive material 1020, radome 1018 does not have any additional heat dissipation design or features.

[0089] In some exemplary examples, radome 1018 is made of composite material 1024. In some exemplary examples, heat transfer vents 1030 extend through radome 1018. Heat transfer vents 1030 are openings in radome 1018. When present, heat transfer vents 1030 provide a path for heat to escape from interior 1019 of radome 1018.

[0090] In some exemplary examples, radome 1018 is an off-the-shelf component. When radome 1018 is an off-the-shelf component, heat transfer vents 1030 are cut into radome 1018. In some exemplary examples, radome 1018 is designed and manufactured for mounting system 1002. In some exemplary examples, when radome 1018 is manufactured for mounting system 1002, heat transfer vents 1030 may be formed in radome 1018 during manufacturing. For example, when radome 1018 is made of composite material 1024, heat transfer vents 1030 may be formed during the process of laying up composite material 1024.

[0091] Radome 1018 is configured to have an aerodynamic design 1080 . In some illustrative examples, heat transfer vents 1030 are present in the rear portion of radome 1018 . Having heat transfer vents 1030 in the rear portion of radome 1018 may reduce drag in aerodynamic design 1080 .

[0092] In some illustrative examples, heat transfer element 1032 is present in mounting system 1002. In some illustrative examples, heat transfer element 1032 is positioned within heat transfer port 1030. Heat transfer element 1032 is configured to transfer heat from interior 1019 of radome 1018 to environment 1028 external to mounting system 1002.

[0093] In some illustrative examples, heat transfer element 1032 includes metal material 1034 having plurality of perforations 1036 therein. Perforations 1036 are configured to allow heat to escape from interior 1019 via plurality of perforations 1036.

[0094] In some illustrative examples, some of plurality of perforations 1036 take the form of one of a matrix of holes 1038 , plurality of slots 1040 , or plurality of overlapping louvers 1042 .

[0095] Hole matrix 1038 includes any desired layout of holes. In some exemplary examples, hole matrix 1038 can include holes in columns and rows. In some exemplary examples, hole matrix 1038 can include holes in staggered rows. The holes of hole matrix 1038 can have any desired shape. In some exemplary examples, the holes of hole matrix 1038 can be at least one of a circle, a square, an oval, a triangle, or any other desired hole shape. Multiple slots 1040 can have any desired layout and any desired size.

[0096] In some exemplary examples, heat transfer element 1032 includes louvers 1042. In these exemplary examples, louvers 1042 can radiate heat to environment 1028. When louvers 1042 are present, the louvers increase the surface area of ​​metal material 1034 to radiate heat from heat transfer element 1032 to environment 1028. In some exemplary examples, louvers 1042 are fixed. When louvers 1042 are fixed, the angle of louvers 1042 is fixed. In some exemplary examples, louvers 1042 are movable. When louvers 1042 are movable, the angle of louvers 1042 is adjustable.

[0097] In some illustrative examples, heat transfer element 1032 includes an actuator connected to shutter 1042. In some illustrative examples, heat transfer element 1032 includes shape memory alloy actuator 1044.

[0098] In some illustrative examples, heat travels within interior 1019 of radome 1018 to exit through heat transfer pad 1032. In some illustrative examples, mounting system 1002 includes metal connector 1046 positioned between heat transfer pad 1032 and base plate 1012. In some illustrative examples, metal connector 1046 is configured to conduct heat between base plate 1012 and heat transfer pad 1032.

[0099] Heat generating device 1016 takes any desired form of heat generating device that is desirably secured to exterior 1074 of aircraft 1000. In some illustrative examples, heat generating device 1016 includes a plurality of electronic antennas 1048. In some illustrative examples, heat generating device 1016 includes a plurality of sensors 1050. Heat generating device 1016 is positioned within recess 1052 in floor 1012.

[0100] Bottom plate 1012 is connected to adapter plate 1004. In some exemplary examples, bottom plate 1012 is made of thermally conductive material 1014. In some exemplary examples, thermally conductive material 1014 takes the form of metal 1056, such as aluminum 1058. In some exemplary examples, bottom plate 1012 is a unitary 1054 metal 1056 structure.

[0101] The bottom plate 1012 is secured to the adapter plate 1004. The adapter plate 1004 is configured to connect a plurality of components to the skin 1070 of the aircraft 1000. The adapter plate 1004 is configured to be mounted directly to the fuselage 1006 of the aircraft 1000. The adapter plate 1004 is connected to the fuselage 1006 by fasteners 1068. The fasteners 1068 take the form of any desired type of fastener. In some illustrative examples, the adapter plate 1004 is a common component of multiple aircrafts of different designs. In some illustrative examples, the adapter plate 1004 has a design common to different types of components for mounting in addition to the mounting system 1002.

[0102] Bottom plate 1012 is connected to adapter plate 1004 via fittings 1062 that extend through insulation 1008. In some illustrative examples, thermal insulators 1066 reduce the transfer of heat from bottom plate 1012 through fittings 1062 to adapter plate 1004.

[0103] Fig.10 The illustration of aircraft 1000 in FIG. 1 is not meant to imply physical or structural limitations to the methods in which the exemplary embodiments may be implemented. Other components in addition to or in place of the components shown may be used. Some components may not be required. In addition, blocks are presented to illustrate some functional components. When implemented in the exemplary embodiments, one or more of these blocks may be combined, split, or combined and split into different blocks.

[0104] For example, although only one heat transfer element is depicted, other examples not depicted may include more than one heat transfer element.As another example, although fasteners for the radome 1018 are not depicted, fasteners connect the radome 1018 to the adapter plate 1004.

[0105] Now turn to Fig.11 , depicts an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. The mounting system 1100 is Fig.10 The mounting system 1002 in the embodiment of the present invention is a physical implementation of the mounting system 1002 in the embodiment of the present invention. The mounting system 1100 can be used to mount the heat generating device on the Figure 1 On the plane 100.

[0106] The mounting system 1100 includes an adapter plate 1102 and a thermal insulation layer 1104. The adapter plate 1102 is configured to mount a plurality of components to an aircraft such as a Fig.10 Adapter plate 1102 may be used to mount any desired component to the exterior of an aircraft. Insulation layer 1104 is positioned to cover a first side of adapter plate 1102. Insulation layer 1104 reduces or prevents heat from traveling to adapter plate 1102.

[0107] Now turn to Fig.12 , depicts an isometric view of portions of a mounting system for attaching a heat generating device according to an exemplary embodiment. In view 1200, a base plate 1202 resides on an insulating layer 1104. The base plate 1202 is connected to an adapter plate 1102. The insulating layer 1104 extends between the base plate 1202 and the adapter plate 1102.

[0108] Heat generating device 1204 is shown in exploded form above base plate 1202. In this illustrative example, heat generating device 1204 takes the form of a plurality of electronic antennas 1206. A plurality of electronic antennas 1206 are connected to base plate 1202.

[0109] Now turn to Fig.13 , depicts an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment. In view 1300, a radome 1302 has been attached to an adapter plate 1102 in the mounting system 1100. The radome 1302 is Fig.10 The radome 1018 in FIG. 1302 is connected to the adapter plate 1102 and is positioned to cover the heat generating device 1204 and the base plate 1202 .

[0110] The thermal insulation layer 1104 is positioned on the first side 1308 of the adapter plate 1102. A plurality of electronic antennas 1206 are connected in the base plate 1202.

[0111] In this exemplary example, heat transfer port 1304 is present in radome 1302. Heat transfer port 1304 is an opening formed in radome 1302. Heat transfer port 1304 can be formed by at least one of machining, molding, or material laying. In this exemplary example, heat transfer door 1306 is present in heat transfer port 1304. Heat transfer door 1306 is configured to radiate heat from radome 1302. Heat transfer door 1306 is made of a metal material to radiate heat to the environment outside radome 1302. Heat transfer door 1306 includes a plurality of perforations (not shown) to allow heat to escape from radome 1302. The plurality of perforations include perforations of any desired number, positioning, size, and shape. In other examples not shown, heat transfer door 1306 may include a plurality of shutters.

[0112] Now turn to Fig.14 , depicts an illustration of a cross-sectional view of a mounting system for attaching a heat generating device according to an exemplary embodiment. In view 1400, a radome 1402 has been connected to an adapter plate 1102 in the mounting system 1100. The radome 1402 is Fig.10 The radome 1018 in FIG. 1402 is connected to the adapter plate 1102 and is positioned to cover the heat generating device 1204 and the base plate 1202 .

[0113] The heat insulating layer 1104 is positioned on the first surface 1410 of the adapter plate 1102. The heat generating device 1204 is connected in the bottom plate 1202.

[0114] In this exemplary example, heat transfer port 1404 is present in radome 1402. Heat transfer port 1404 is an opening formed in radome 1402. Heat transfer port 1404 can be formed by at least one of machining, molding, or material laying. In this exemplary example, heat transfer door 1406 is present in heat transfer port 1404. Heat transfer door 1406 is configured to radiate heat from radome 1402. Heat transfer door 1406 is made of a metal material to radiate heat to the environment outside radome 1402. Heat transfer door 1406 includes a plurality of perforations to allow heat to escape from radome 1402. The plurality of perforations include perforations of any desired number, positioning, size, and shape. In other examples not shown, heat transfer door 1406 may include a plurality of shutters.

[0115] In view 1400, metal connector 1408 is present in mounting system 1100. Metal connector 1408 is made of any desired metal configured to provide thermal conduction. Metal connector 1408 contacts base plate 1202. Metal connector 1408 contacts thermal conduction point 1406. Metal connector 1408 conducts heat from base plate 1202 to thermal conduction point 1406 to remove heat from under radome 1402.

[0116] Now turn to Fig.15 , depicts a flow chart of a method for attaching a heat generating device to the exterior of an aircraft according to an exemplary embodiment. The method 1500 may be performed to attach the mounting system 120 to Figure 1 The method 1500 may be performed to attach the mounting system 202 to the aircraft 100. Figure 2 Aircraft in 200. Can be used Figure 3 The method 1500 can be performed using the installation system 301 in Figures 4 to 8 The method 1500 can be performed using the installation system 401 in Fig. 9 The installation system 901 in is used to execute method 1500.

[0117] Method 1500 positions a thermal insulation layer between a heat generating device and a skin of an aircraft fuselage (operation 1502 ). Method 1500 secures a shield over the thermal insulation layer to form a thermal chamber between the thermal insulation layer and an external environment (operation 1504 ). Thereafter, method 1500 terminates.

[0118] In some exemplary examples, the step of positioning the thermal insulation layer includes connecting a manufactured antenna assembly to the fuselage (operation 1506), the antenna assembly including the thermal insulation layer, the base plate, and a plurality of electronic antennas. In these exemplary examples, the manufactured antenna assembly can be assembled offline. Assembling the manufactured antenna assembly offline can reduce the time and resources used during assembly on the aircraft. In some exemplary examples, the step of connecting the manufactured antenna assembly to the fuselage includes connecting the manufactured antenna assembly to an adapter plate fixed to the fuselage (operation 1508). In some exemplary examples, the adapter plate is already fixed to the fuselage of the aircraft in use. In these exemplary examples, the manufactured antenna assembly can be connected to the adapter plate as a retrofitted part. In other exemplary examples, the manufactured antenna assembly can be connected to the adapter plate during the manufacturing process of the aircraft.

[0119] In some exemplary examples, securing the shield includes connecting a skin of the shield to an adapter plate secured to the fuselage (operation 1510). In some exemplary examples, securing the shield also includes connecting an access panel of the shield to a base plate holding a heat generating device (operation 1512), wherein the base plate and the shield form a heat chamber. In these exemplary examples, the shield includes a plurality of individual pieces. In some exemplary examples, securing the shield includes assembling a plurality of portions of the shield and securing the plurality of portions to an adapter plate secured to the fuselage and to the base plate holding the heat generating device (operation 1514).

[0120] Now turn to Fig.16 , depicts a flow chart of a method for attaching a heat generating device to the exterior of an aircraft according to an exemplary embodiment. The method 1600 may be performed to attach the mounting system 120 to the exterior of an aircraft. Figure 1The method 1600 may be performed to attach the mounting system 1002 to the aircraft 100. Fig.10 Aircraft in 1000. Can be used Figure 11 to Figure 12 The method 1600 can be performed using the installation system 1100 in Fig.13 Method 1600 may be performed using the components of mounting system 1100 depicted in view 1300 of FIG. Fig.14 Method 1600 is performed using the installation system 1100 depicted in view 1400 in FIG.

[0121] Process 1600 positions a thermal insulation layer between a heat generating device and a skin of a fuselage of an aircraft (operation 1602 ). Process 1600 secures a radome over the thermal insulation layer and the heat generating device (operation 1604 ).

[0122] In some illustrative examples, positioning the thermal insulation layer includes laying the thermal insulation layer on an adapter panel coupled to the fuselage (operation 1606). The thermal insulation layer is configured to cover a first side of the adapter panel to reduce or eliminate heat transferred to the adapter panel.

[0123] In some exemplary examples, method 1600 mounts a base plate to an adapter plate such that the insulation layer is between the base plate and the adapter plate, wherein the base plate is configured to support a heat generating device (operation 1608). In some exemplary examples, the base plate is a universal base plate configured to receive multiple different types of heat generating devices. In some exemplary examples, the base plate is a single metal structure.

[0124] In some exemplary examples, securing the radome over the insulation and the heat generating device includes attaching the radome to an adapter plate (operation 1610). In some exemplary examples, the adapter plate is present on an aircraft already in service. In these exemplary examples, the radome may be secured as part of a retrofit. In some exemplary examples, the adapter plate is attached to the aircraft as part of an initial manufacture of the aircraft to receive the radome.

[0125] In some illustrative examples, method 1600 places a metal connector connecting the base plate and the heat transfer heat source in the radome (operation 1612 ), wherein the metal connector is configured to conduct heat between the base plate and the heat transfer heat source.

[0126] Now turn to Fig.17 , depicts a flow chart of a method for modifying a radome for covering a heat generating device on an aircraft according to an exemplary embodiment. The method 1700 may be performed to modify Fig.10 The method 1700 can be used to modify the radome to connect to Figure 11 to Figure 12 The method 1700 can be used to modify Fig.13The method 1700 can be used to modify the radome 1302. Fig.14 The antenna cover 1402 in.

[0127] Method 1700 cuts a heat transfer opening in a radome (operation 1702). Method 1700 fixes a heat transfer heat within the heat transfer opening (operation 1704), wherein the heat transfer heat comprises a metal material and a plurality of perforations through the metal material. Thereafter, method 1700 terminates.

[0128] In some illustrative examples, method 1700 connects a radome having a heat transfer port to an adapter plate connected to a fuselage of the aircraft such that the radome covers the heat generating device (operation 1706). In some illustrative examples, method 1700 brings the heat transfer element into contact with a metal connector of a base plate supporting the heat generating device such that heat is conducted between the base plate and the heat transfer element via the metal connector (operation 1708).

[0129] In some illustrative examples, method 1700 covers a first side of the adapter plate with an insulating layer (operation 1710). In some illustrative examples, method 1700 connects a base plate to the adapter plate such that the base plate is in contact with the insulating layer (operation 1712).

[0130] As used herein, when used with a series of items, the phrase "at least one of..." means that different combinations of one or more of the multiple items listed may be used, and only one of each item in the list may be required. For example, "at least one of item A, item B, or item C" may include, but is not limited to, item A, item A and item B, or item B. This example may also include item A, item B, and item C or item B and item C. Of course, any combination of these items may exist. In other examples, "at least one of..." may be, for example, but not limited to: two of item A; one of item B; and ten of item C; four of item B and seven of item C; or other suitable combinations. Items may be specific objects, things, or categories. In other words, at least one means that any combination of items and multiple items in the list may be used, but not all items in the list are required.

[0131] As used herein, "plurality" when used with respect to items means one or more items.

[0132] The flowcharts and block diagrams in the different described embodiments illustrate the architecture, functions and operations of some possible implementations of the apparatus and methods in the exemplary embodiments. In this regard, each box in the flowchart or block diagram may represent at least one of a module, a fragment, a function or a part of an operation or a step.

[0133] In some alternative implementations of the exemplary embodiments, one or more functions indicated in the frame may not occur in the order indicated in the figure. For example, in some cases, two frames shown in succession may be performed substantially simultaneously, or the frames may sometimes be performed in reverse order, depending on the functions involved. In addition, in addition to the frames shown in the flow chart or block diagram, other frames may be added. Some frames may be optional. For example, operations 1506 to 1514 may be optional. As another example, operations 1606 to 1612 may be optional. As another example, operations 1706 to 1712 may be optional.

[0134] You can Fig.18 Aircraft manufacturing and service method 1800 and the like are shown Fig.19 Exemplary embodiments of the present disclosure are described in the context of aircraft 1900 as shown. Fig.18 , a schematic diagram of an aircraft manufacturing and service method is depicted in the form of a block diagram according to an exemplary embodiment. During pre-production, aircraft manufacturing and service method 1800 may include Fig.19 Specification and design 1802 of aircraft 1900, and including material procurement 1804.

[0135] During production, component and subassembly manufacturing 1806 and system integration 1808 of the aircraft 1900 occurs. Thereafter, the aircraft 1900 may undergo certification and delivery 1810 for entry into service 1812. While in service 1812 by a customer, the aircraft 1900 is scheduled for routine maintenance and service 1814, which may include modification, reconfiguration, refitting, or other maintenance and service.

[0136] Each process of aircraft manufacturing and service method 1800 may be performed or executed by a system integrator, a third party, and / or an operator. In these examples, the operator may be a customer. For the purposes of this specification, a system integrator may include, but is not limited to, any number of aircraft manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, a leasing company, a military entity, a service organization, etc.

[0137] Reference now Fig.19 , depicts an illustration of an aircraft in block diagram form in which an exemplary embodiment may be implemented. In this example, aircraft 1900 is composed of Fig.18 Aircraft manufacturing and service method 1800 is produced and may include aircraft frame 1902 and plurality of systems 1904 and interior 1906. Examples of plurality of systems 1904 include one or more of propulsion system 1908, electrical system 1910, hydraulic system 1912, and environmental system 1914. Any number of other systems may be included.

[0138] Apparatus and methods embodied herein may be employed during at least one of the multiple stages of aircraft manufacturing and service method 1800. One or more exemplary embodiments may be employed in Fig.18 The components and subassemblies are manufactured or used during at least one of manufacturing 1806 , system integration 1808 , in use 1812 , or maintenance and service 1814 .

[0139] These exemplary embodiments enable the installation of new antenna technology into existing aircraft structures in production and retrofit. These exemplary embodiments also enable the management of heat for new electronic antenna technology. If the antenna is mounted directly on top of the skin, the new electronic antenna technology may become hotter than the fuselage skin can accept.

[0140] These exemplary embodiments provide a mounting system that has less protrusion than conventional radomes. These exemplary embodiments provide a mounting system that is shorter than conventional radomes.

[0141] These exemplary embodiments provide protection against overheating of the aircraft skin. These exemplary embodiments provide thermal protection without triggering hardware thermal shutdown protection.

[0142] Electronically steered antennas are expected to generate excess heat, which directly ensures that the temperature of the aircraft skin may be increased to undesirably high levels. These exemplary examples establish a new method to direct excess heat from the base of a very hot electronically steered antenna (ESA) upward and outward to the atmosphere through a base plate and shroud heat sink. A thermal shield below the ESA protects the aircraft fuselage skin.

[0143] The shield is low profile and is an aerodynamically advantageous design. Due to the aerodynamics, the shield causes a lower level of aerodynamic drag compared to conventional radomes. These exemplary embodiments provide protection from bird strike impacts. Due to the large and continuous grounding path, the shield provides lightning strike protection. The integrated nature of the base plate and its attached accessories will allow the antenna, associated line repair unit (LRU), wiring harness, ground strap to be installed off-site into a single assembly for delivery to the final assembly line. Less manpower is used to bolt together the integrated base plate and ESA assembly compared to full assembly on the assembly line. Decentralized manufacturing using off-site installation will save a lot of time and cost compared to the very long installation time required for current mechanically manipulated antennas.

[0144] The description of different multiple exemplary embodiments has been presented for the purpose of illustration and description, and is not intended to be exhaustive or limited to multiple embodiments in the disclosed form. Many modifications and variations will be apparent to those of ordinary skill in the art. In addition, different exemplary embodiments may provide different features compared to other exemplary embodiments. One or more selected embodiments are selected and described to best explain the principles and practical applications of these embodiments, and to enable others of ordinary skill in the art to understand that the present disclosure of multiple embodiments with multiple modifications is suitable for the specific purposes contemplated.

[0145] Also provided herein are the implementations specified in the following referenced clauses:

[0146] 1. A mounting system 1002 for attaching a heat generating device 1016 to the exterior of an aircraft 1000, the system 1002 comprising:

[0147] an adapter plate 1004 connected to a fuselage 1006 of the aircraft 1000;

[0148] a heat-insulating layer 1008 , substantially covering a first surface 1010 of the adapter plate 1004 ;

[0149] a bottom plate 1012 made of a thermally conductive material 1014 and connected to the adapter plate 1004 such that the thermal insulation layer 1008 is positioned between the bottom plate 1012 and the adapter plate 1004;

[0150] A heating device 1016 is fixed in the bottom plate 1012; and

[0151] The radome 1018 is connected to the adapter plate 1004 and is positioned to cover the heat generating device 1016 and the base plate 1012 .

[0152] 2. The mounting system 1002 of clause 1, wherein the radome 1018 is made of a thermally conductive material 1020.

[0153] 3. The mounting system 1002 of clause 1, wherein the base plate 1012 is a unitary 1054 metal 1056 structure.

[0154] 4. The mounting system 1002 of clause 1, wherein the heat generating device 1016 comprises a plurality of electronic antennas 1048.

[0155] 5. The mounting system 1002 of clause 1, wherein the radome 1018 is made of a composite material 1024.

[0156] 6. The installation system 1002 according to clause 1, further comprising:

[0157] Heat transfer openings 1030 are cut in the radome 1018 .

[0158] 7. The installation system 1002 according to clause 6, further comprising:

[0159] Heat transfer opening 1030 is positioned within heat transfer opening 1032 .

[0160] 8. The mounting system 1002 of clause 7, wherein the heat transfer element 1032 comprises a metal material 1034 having a plurality of perforations 1036 therein.

[0161] 9. The mounting system 1002 of clause 8, wherein the perforations 1036 are in the form of one of a hole matrix 1038 , a plurality of slots 1040 , or a plurality of overlapping louvers 1042 .

[0162] 10. The mounting system 1002 of clause 8, wherein the heat transfer element 1032 comprises a shape memory alloy actuator 1044.

[0163] 11. The installation system 1002 according to clause 7, further comprising:

[0164] The metal connector 1046 is positioned between the heat transfer element 1032 and the bottom plate 1012 , wherein the metal connector 1046 is configured to conduct heat between the bottom plate 1012 and the heat transfer element 1032 .

[0165] 12. A method 1600 of attaching a heat generating device 1016 to an exterior 1074 of an aircraft 1000, the method comprising:

[0166] Positioning step 1602 , positioning thermal insulation layer 1008 between heat generating device 1016 and skin 1070 of fuselage 1006 of aircraft 1000 ; and

[0167] In a fixing step 1604 , the radome 1018 is fixed on the thermal insulation layer 1008 and the heating device 1016 .

[0168] 13. The method 1600 of clause 12, wherein the step of positioning the thermal insulation layer 1008 comprises the step 1606 of laying the thermal insulation layer 1008 on an adapter plate 1004 connected to the fuselage 1006.

[0169] 14. The method 1600 of clause 13, further comprising:

[0170] In an installation step 1608 , the bottom plate 1012 is installed to the adapter plate 1004 , such that the thermal insulation layer 1008 is located between the bottom plate 1012 and the adapter plate 1004 , wherein the bottom plate 1012 is configured to support the heat generating device 1016 .

[0171] 15. The method 1600 of clause 14, wherein the step of securing the radome 1018 over the thermal insulation layer 1008 and the heat generating device 1016 comprises the step 1610 of connecting the radome 1018 to the adapter plate 1004 .

[0172] 16. The method 1600 of clause 15, further comprising:

[0173] In a placement step 1612 , the metal connector 1046 is placed between the base plate 1012 and the heat transfer element 1032 in the radome 1018 , wherein the metal connector 1046 is configured to conduct heat between the base plate 1012 and the heat transfer element 1032 .

[0174] 17. A method 1700 of retrofitting a radome 1018 for covering a heat generating device 1016 on an aircraft 1000, the method comprising:

[0175] Cutting step 1702, cutting heat transfer openings 1030 in the radome 1018; and

[0176] In a fixing step 1704 , the heat transfer element 1032 is fixed in the heat transfer port 1030 , wherein the heat transfer element 1032 includes a metal material 1034 and a plurality of through holes 1036 passing through the metal material 1034 .

[0177] 18. The method 1700 of clause 17, further comprising:

[0178] In a connecting step 1706 , the radome 1018 having the heat transfer opening 1030 is connected to the adapter plate 1004 connected to the fuselage 1006 of the aircraft 1000 , so that the radome 1018 covers the heat generating device 1016 .

[0179] 19. The method 1700 of clause 18, further comprising:

[0180] In a placement step 1708 , the heat transfer element 1032 is placed in contact with the metal connector 1046 of the bottom plate 1012 supporting the heat generating device 1016 , so that heat is conducted between the bottom plate 1012 and the heat transfer element 1032 via the metal connector 1046 .

[0181] 20. The method 1700 of clause 19, further comprising:

[0182] A covering step 1710 of covering the first surface 1010 of the adapter plate 1004 with the heat insulating layer 1008; and

[0183] In a connecting step 1712 , the bottom plate 1012 is connected to the adapter plate 1004 , so that the bottom plate 1012 is in contact with the insulation layer 1008 .

Claims

1. A mounting system (202) for attaching a heat generating device (204) to an exterior (206) of an aircraft (200), the mounting system (202) comprising: a heat chamber (208) made of a plurality of heat conductive materials (212, 214), wherein the heat chamber (208) has a recess (216) open to an environment (1028) outside the aircraft (200); A heating device (204) is fixed in the recess (216); and A thermal insulation layer (210) is located between the heat chamber (208) and the aircraft (200), wherein the thermal insulation layer (210) is positioned on a side of the heat chamber (208) opposite to an opening of the recess (216).

2. The mounting system (202) of claim 1, wherein: The heating device (204) comprises a plurality of electronic antennas (219).

3. The mounting system (202) of claim 1, wherein: The heat chamber (208) is formed by a shield (222) and a bottom plate (224).

4. The mounting system (202) of claim 3, wherein: The shield (222) includes a plurality of sections (272) secured together.

5. The mounting system (202) according to claim 4, further comprising: a skirt seal (242) connected to the lower ring (240) of the shroud (222); as well as A thermal insulation member (244) is located between the lower ring (240) and the skin (246) of the aircraft (200).

6. The mounting system (202) of claim 3, wherein: The base plate (224) is a unitary (252) metal (248) structure.

7. The mounting system (202) of claim 3, wherein: The bottom plate (224) includes the recess (216) and a flange (238) surrounding the recess (216).

8. The mounting system (202) of claim 7, wherein: The flange (238) of the base plate (224) is fixed to the shield (222).

9. The mounting system (202) of claim 3, further comprising: A plurality of thermal insulation members (260) are located between the thermal chamber (208) and the aircraft (200).

10. A mounting system (202) for attaching a heat generating device (204) to an exterior (206) of an aircraft (200), the mounting system (202) comprising: A bottom plate (224) having a recess (216) surrounded by a flange (238), wherein the bottom plate (224) is made of a thermally conductive material (212); A heating device (204) is located in the recess (216); and The heat insulating layer (210) is fixed to the back side (262) of the bottom plate (224).

11. The mounting system (202) of claim 10, wherein: The heating device (204) comprises a plurality of electronic antennas (219).

12. The mounting system (202) of claim 10, further comprising: an adapter plate (254) configured to connect a plurality of components to a skin (246) of the aircraft (200); as well as A plurality of fittings (258) connect the base plate (224) to the adapter plate (254).

13. The mounting system (202) of claim 12, wherein: A plurality of thermal insulation members (260) are positioned between the base plate (224) and the adapter plate (254).

14. The mounting system (202) of claim 10, further comprising: A shield (222) includes a plurality of sections (272) secured together, wherein the shield (222) is made of a thermally conductive material (214) and is configured to have an aerodynamic design (274).

15. The mounting system (202) of claim 14, wherein: The plurality of portions (272) of the shield (222) include a skin (232) and a plurality of access panels (234), wherein the skin (232) is secured to an adapter plate (254) configured to connect a plurality of components to a skin (246) of the aircraft (200), and wherein the access panels (234) are designed to accommodate a cross-sectional shape of the heat generating device (204).

16. The mounting system (202) of claim 14, wherein: A plurality of thermal insulation (244) are positioned between the shroud (222) and a skin (246) of the aircraft (200).

17. A method (1500) of attaching a heat generating device (204) to an exterior (206) of an aircraft (200), the method (1500) comprising: a positioning step (1502), positioning a thermal insulation layer (210) between the heat generating device (204) and a skin (246) of a fuselage (256) of the aircraft (200); and A fixing step (1504) fixes the shield (222) onto the thermal insulation layer (210) to form a thermal chamber (208) between the thermal insulation layer (210) and the external environment (1028).

18. The method (1500) of claim 17, wherein: The positioning step of positioning the thermal insulation layer (210) includes the step (1506) of attaching a manufactured antenna assembly (270) having the thermal insulation layer (210), a base plate (224), and a plurality of electronic antennas (219) to the fuselage (256).

19. The method (1500) of claim 18, wherein: The step of connecting the manufactured antenna assembly (270) to the fuselage (256) includes the step (1508) of connecting the manufactured antenna assembly (270) to an adapter plate (254) secured to the fuselage (256).

20. The method (1500) of claim 17, wherein: The securing step of securing the shield (222) includes the step (1510) of connecting a skin (232) of the shield (222) to an adapter plate (254) secured to the fuselage (256).

21. The method (1500) of claim 20, wherein: The securing step of securing the shield (222) further includes a step (1512) of connecting a plurality of access panels of the shield (222) to a base plate (224) holding the heat generating device (204), wherein the base plate (224) and the shield (222) form the heat chamber (208).

22. The method (1500) of claim 17, wherein: The step of fixing the shield (222) includes the following steps (1514): Assembling the plurality of portions (272) of the shield (222); and The plurality of parts (272) are fixed to an adapter plate (254) and a bottom plate (224), wherein the adapter plate is fixed to the fuselage (256), and the bottom plate (224) holds the heat generating device (204).

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