System for attaching heat generating equipment to exterior of aircraft
Patent Information
- Application Number
- JP2024117524
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2023-07-25
- Filing Date
- 2024-07-23
- Publication Date
- 2025-02-19
Smart Images
Figure 2025023898000001_ABST
Abstract
Description
[Technical field]
[0001]
[0001] This disclosure relates generally to aircraft, and more particularly to mounting heat generating devices to the exterior of an aircraft. [Background technology]
[0002]
[0002] Antennas exist on aircraft for navigation and / or communication. Aircraft also utilize several types of sensors to detect temperature, airflow, vibration, position, force, pressure, or any other desired characteristic. Adding additional antennas or sensors or utilizing new technologies for antennas or sensors can generate additional heat.
[0003]
[0003] It would therefore be desirable to have a method and apparatus that takes into account at least some of the problems discussed above, as well as other possible problems. Summary of the Invention
[0004]
[0004] One embodiment of the present disclosure provides a mounting system for mounting a heat generating device to the exterior of an aircraft. The mounting system includes a heat chamber, a heat generating device, and an insulating layer. The heat chamber is formed by several conductive materials. The heat chamber has a recess that is open to an environment outside the aircraft. The heat generating device is secured within the recess. The insulating layer is between the heat chamber and the aircraft. The insulating layer is disposed on an opposite side of the heat chamber from the opening of the recess.
[0005]
[0005] Another embodiment of the present disclosure provides a mounting system for mounting a heat generating device to an exterior of an aircraft, the mounting system including a subplate having a recess surrounded by a flange, a heat generating device disposed within the recess, and a thermal insulation layer secured to a back side of the subplate, the subplate being formed of a conductive material.
[0006]
[0006] Yet another embodiment of the present disclosure provides a method for mounting a heat generating device to an exterior of an aircraft. An insulating layer is disposed between the heat generating device and a skin of a fuselage of the aircraft. A shroud is secured over the insulating layer to form a heat chamber between the insulating layer and an outside environment.
[0007] Another embodiment of the present disclosure provides a mounting system for mounting a heat generating device to an exterior of an aircraft, the mounting system including an adapter plate connected to a fuselage of the aircraft, a thermal insulation layer substantially covering a first side of the adapter plate, a subplate formed of a conductive material and connected to the adapter plate such that the thermal insulation layer is disposed between the subplate and the adapter plate, a heat generating device secured within the subplate, and a radome connected to the adapter plate and positioned to cover the heat generating device and the subplate.
[0008]
[0008] A further embodiment of the present disclosure provides a method for mounting a heat generating device to an exterior of an aircraft. A thermal insulation layer is disposed between the heat generating device and a skin of a fuselage of the aircraft. A radome is secured over the thermal insulation layer and the heat generating device.
[0009]
[0009] Another embodiment of the present disclosure provides a method of installing a radome for covering heat generating equipment on an aircraft. A heat transfer portal is cut into the radome. A heat transfer door is secured within the heat transfer portal. The heat transfer door includes a metal material and a plurality of perforations extending through the metal material.
[0010]
[0010] These features and functions may be realized individually in various embodiments of the present disclosure or may be combined in yet other embodiments, further details of which can be understood with reference to the following description and drawings.
[0011]
[0011] The novel features believed characteristic of the illustrative embodiments are set forth in the appended claims. However, the illustrative embodiments as well as the preferred modes of use, further objects and features thereof will be best understood by reading the following detailed description of the illustrative embodiments of the present disclosure in conjunction with the accompanying drawings. [Brief description of the drawings]
[0012] [Figure 1]
[0012] FIG. 1 is an illustration of an aircraft in accordance with an illustrative embodiment. [Diagram 2]
[0013] FIG. 1 is an illustration of a block diagram of an aircraft having a mounting system in accordance with an illustrative embodiment. [Diagram 3]
[0014] 1 is a cross-sectional view of a mounting system for mounting a heat-generating device according to an illustrative embodiment. [Figure 4]
[0015] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Diagram 5]
[0016] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 6]
[0017] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 7]
[0018] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 8]
[0019] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 9]
[0020] 1 is a cross-sectional view of a portion of a mounting system for mounting a heat-generating device according to an illustrative embodiment. [Figure 10]
[0021] FIG. 1 is an illustration of a block diagram of an aircraft having a mounting system in accordance with an illustrative embodiment. [Figure 11]
[0022] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 12]
[0023] FIG. 1 is an isometric view of a portion of a mounting system for mounting heat-generating equipment according to an illustrative embodiment. [Figure 13]
[0024] 1 is a cross-sectional view of a mounting system for mounting a heat-generating device according to an illustrative embodiment. [Figure 14]
[0025] 1 is a cross-sectional view of a mounting system for mounting a heat-generating device according to an illustrative embodiment. [Figure 15]
[0026] 1 is a flowchart of a method for mounting heat generating equipment to the exterior of an aircraft in accordance with an illustrative embodiment. [Figure 16]
[0027] 1 is a flowchart of a method for mounting heat generating equipment to the exterior of an aircraft in accordance with an illustrative embodiment. [Figure 17]
[0028] 1 is an illustration of a flowchart of a method for installing a radome to cover heat generating equipment on an aircraft in accordance with an illustrative embodiment. [Figure 18]
[0029] 1 is an illustration of an aircraft manufacturing and service method in the form of a block diagram in accordance with an illustrative embodiment; FIG. [Figure 19]
[0030] FIG. 1 is an illustration of an aircraft in the form of a block diagram in which an illustrative embodiment may be implemented; DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
[0013]
[0031] 1, an illustration of an aircraft is shown in accordance with an illustrative embodiment. Aircraft 100 has a wing 102 and a wing 104 attached to a fuselage 106. Aircraft 100 includes an engine 108 attached to wing 102 and an engine 110 attached to wing 104.
[0014]
[0032] The fuselage 106 has an empennage 112. A horizontal stabilizer 114, a horizontal stabilizer 116, and a vertical stabilizer 118 are attached to the empennage 112 of the fuselage 106.
[0015]
[0033] Aircraft 100 is one example of an aircraft that may have heat-generating equipment mounted to fuselage 106, according to example embodiments. For example, mounting system 120 may be one physical implementation of a mounting system having heat-generating equipment. Using the illustrated embodiments, electronic antennas or any other desired type of heat-generating equipment may be mounted to fuselage 106 of aircraft 100.
[0016]
[0034] The skin 122 of the aircraft 100 has an upper temperature threshold. Depending on the environmental temperature, environmental conditions, paint and other surface treatments on the skin 122, and operating conditions for the heat-generating equipment, the heat-generating equipment may reach undesirably high temperatures and may reach the upper temperature threshold. Example embodiments provide a mounting system. The mounting system 120 reduces heat transferred from the heat-generating equipment to the skin 122 of the aircraft 100. The mounting system 120 prevents the skin 122 from reaching the upper temperature limit due to the heat-generating equipment.
[0017]
[0035] With reference now to Figure 2, a block diagram of an aircraft having a mounting system is shown in accordance with an illustrative embodiment. Aircraft 100 may be one physical implementation of aircraft 200 in Figure 2.
[0018]
[0036] The mounting system 202 is configured to mount the heat generating device 204 to the exterior 206 of the aircraft 200. The mounting system 202 includes a heat chamber 208, a heat generating device 204, and an insulating layer 210. The heat chamber 208 is formed by several conductive materials, namely conductive material 212 and 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 within the recess 216. The insulating layer 210 is between the heat chamber 208 and the aircraft 200. The insulating layer 210 is disposed on a side of the heat chamber 208 opposite the opening of the recess 216.
[0019]
[0037] Insulation layer 210 is present to reduce the transfer of heat from heat-generating equipment 204 to skin 246 of fuselage 256. In some illustrative embodiments, skin 246 is formed of composite material 268. It is desirable to reduce the heat transferred to composite material 268 during operation of aircraft 200 and heat-generating equipment 204.
[0020]
[0038] The skin 246 of the aircraft 200 has an upper temperature threshold. Depending on the environmental temperature, environmental conditions, paint and other surface treatments on the skin 246, and the operating conditions for the heat-generating equipment 204, the heat-generating equipment 204 may reach an undesirably high temperature and may reach the upper temperature threshold. The mounting system 202 reduces heat transferred from the heat-generating equipment 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 equipment 204.
[0021]
[0039] Insulation layer 210 is provided to shield underlying aircraft structure, such as adapter plate 254 and skin 246 of fuselage 256, from heat generated by heat generating equipment 204 held by mounting system 202. Insulation layer 210 may take any desired form. In some illustrative embodiments, insulation layer 210 takes the form of insulation blanket 264. In some illustrative embodiments, insulation blanket 264 is the same material used in high temperature propulsion insulation points. In some illustrative embodiments, insulation layer 210 has an operating temperature of 450 degrees Fahrenheit.
[0022]
[0040] Heat generating device 204 may take any desired form of heat generating device that is preferably secured to exterior 206 of aircraft 200. In some illustrative examples, heat generating device 204 includes a number of electronic antennas 219. In some illustrative examples, heat generating device 204 includes a number of sensors 220.
[0023]
[0041] In some illustrative embodiments, heat chamber 208 is formed by two or more components joined together. In some illustrative embodiments, heat chamber 208 is formed by a shroud 222 and a sub-plate 224. Shroud 222 is configured to cover insulation layer 210. Shroud 222 is the portion of mounting system 202 that is exposed to environment 218 outside aircraft 200. Shroud 222 may also be referred to as a shell or a cover. Shroud 222 is configured to provide an aerodynamic design 274.
[0024]
[0042] The shroud 222 is formed from the conductive material 214. By being formed from the conductive material 214, the shroud 222 provides lightning strike protection. By being formed from the conductive material 214, the shroud 222 provides a path for radiant heat 226 to exit the mounting system 202. In some illustrative examples, the shroud 222 is referred to as a "radiator." Radiant heat 226 is heat generated by the heat-producing equipment 204 that is substantially isolated within the heat chamber 208 by the insulation layer 210.
[0025]
[0043] In some illustrative embodiments, conductive material 214 includes a metal 228. In some illustrative embodiments, metal 228 is aluminum 230. Conductive material 214 is selected based on at least one of weight, machinability, wearability, and other material properties.
[0026]
[0044] The shroud 222 has any desired design configured to cover portions of the mounting system 202 while leaving the heat producing equipment 204 exposed to the environment 218. In some exemplary embodiments, the shroud 222 includes multiple portions secured together. In some exemplary embodiments, the shroud 222 includes a skin 232 and an access panel 234. The skin 232 and the access panel 234 are connected in any desired manner.
[0027]
[0045] In some illustrative embodiments, the skin 232 and the access panel 234 are connected by an upper ring 236. In some illustrative embodiments, the upper ring 236 connects the skin 232 to the sub-plate 224. In some illustrative embodiments, the upper ring 236 is directly connected to a flange 238 of the sub-plate 224 and the skin 232. In some illustrative embodiments, the upper ring 236 may be referred to as an upper bracket or a connecting bracket. The flange 238 of the sub-plate 224 is fixed to the shroud 222.
[0028]
[0046] As shown, shroud 222 further includes a lower ring 240. In some exemplary embodiments, skin 232 is connected to adapter plate 254 by lower ring 240. In some exemplary embodiments, lower ring 240 may be referred to as a lower bracket or a connecting bracket.
[0029]
[0047] As shown, the mounting system 202 further includes a skirt seal 242 connected to the lower ring 240 of the shroud 222. The skirt seal 242 seals the mounting system 202 against liquids.
[0030]
[0048] In some illustrative embodiments, a number of thermal isolators, namely thermal isolators 244, are disposed between shroud 222 and skin 246 of aircraft 200. As shown, attachment system further includes thermal isolators 244 disposed between lower ring 240 and skin 246 of the aircraft. Thermal isolators 244 are provided to prevent the conduction of heat from shroud 222 to skin 246 of aircraft 200.
[0031]
[0049] The sub-plate 224 is configured to support the heat-producing equipment 204 and forms a lower portion of the heat chamber 208. The shroud 224 is formed of a conductive material 212. The sub-plate 224 conducts heat from the heat-producing equipment 204 to the shroud 222 for dissipation to the environment 218 as radiant heat 226.
[0032]
[0050] In some exemplary embodiments, the conductive material 212 includes a metal 248. In some exemplary embodiments, the metal 248 is aluminum 250. In some exemplary embodiments, the sub-plate 224 is of unitary 252 construction. In some exemplary embodiments, the sub-plate 224 is of unitary 252 metal 248 construction.
[0033]
[0051] In some exemplary embodiments, the sub-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 a variety of different designs of electronic antennas. In some exemplary embodiments, the recess 216 holds several sensors 220. Because the recess 216 is designed to hold any desired heat generating device 204, the sub-plate 224 may be referred to as a universal component.
[0034]
[0052] Subplate 224 is secured to adapter plate 254. Adapter plate 254 is configured to connect the component to skin 246 of aircraft 200. Adapter plate 254 is configured to be attached directly to fuselage 256 of aircraft 200. Adapter plate 254 is connected to fuselage 256 by fasteners 266. Fasteners 266 may take the form of any desired type of fastener. In some illustrative embodiments, adapter plate 254 is a common component for several different aircraft designs. In some illustrative embodiments, adapter plate 254 has a common design for mounting different types of components to mounting system 202.
[0035]
[0053] In some illustrative examples, aircraft 200 is already in service 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. As a result of being used for multiple functions, being retrofittable, and being used across multiple aircraft designs, adapter plate 254 may also be referred to as a universal adapter.
[0036]
[0054] Fittings 258 connect the sub-plate 224 to the adapter plate 254. The fittings 258 penetrate the thermal insulation layer 210. In some exemplary embodiments, a number of thermal isolators 260 are disposed between the sub-plate 224 and the adapter plate 254. In some exemplary embodiments, a number of thermal isolators 260 are associated with the fittings 258 to reduce the conduction of heat from the sub-plate 224 to the adapter plate 254.
[0037]
[0055] In some illustrative embodiments, a number of thermal isolators, namely thermal isolators 244, are disposed between heat chamber 208 and aircraft 200. Thermal isolators 244 reduce or prevent the transfer of heat from heat chamber 208 to aircraft 200.
[0038]
[0056] In some illustrative embodiments, a mounting system 202 for mounting a heat generating device 204 to an exterior 206 of an aircraft 200 includes a sub-plate 224, a heat generating device 204, and a thermal insulation layer 210. The sub-plate 224 has a recess 216 surrounded by a flange 238. The sub-plate 224 is formed of a conductive material 212. The heat generating device 204 is disposed within the recess 216. The thermal insulation layer 210 is secured to a back side 262 of the sub-plate. In some illustrative embodiments, the heat generating device 204 includes a number of electronic antennas 219.
[0039]
[0057] In some illustrative embodiments, the shroud 222 includes multiple sections secured together. The shroud 222 is formed from conductive material 214 and is configured to provide an aerodynamic design.
[0040]
[0058] In some illustrative embodiments, the portions 272 of the shroud 222 include a skin 232 and an access panel 234. The skin 246 is secured to an adapter plate 254 configured to connect components to the skin 246 of the aircraft 200. The access panel 234 is designed to accommodate the cross-sectional shape of the heat-producing equipment 204.
[0041]
[0059] The illustration of aircraft 200 in Figure 2 is not meant to imply physical or architectural limitations to the manner in which an illustrative embodiment may be implemented. Other components in addition to or instead of the ones illustrated may be used. Some components may be unnecessary. Also, blocks are presented to illustrate some functional components. When implemented in an illustrative embodiment, one or more of these blocks may be combined, divided, or combined and divided into different blocks.
[0042]
[0060] For example, although not shown, insulation is provided between heat chamber 208 and adapter plate 254. For example, insulation is disposed between shroud 222 and adapter plate 254. Although several thermal isolators disposed between shroud 222 and skin 246 of aircraft 200 are shown as thermal isolators 244, some thermal isolators may include two or more thermal isolators.
[0043]
[0061] 3, an illustration of a cross-sectional view of a mounting system for mounting heat generating equipment is shown in accordance with an illustrative embodiment. View 300 of mounting system 301 is a cross-sectional view of mounting system 301 mounted to skin 302 of aircraft 303.
[0044]
[0062] Mounting system 301 is one physical implementation of mounting system 202 of Figure 2. In figure 300, an adapter plate 304 is connected to an aircraft 303. An insulating layer 306 is disposed between a sub-plate 308 and the adapter plate 304. The insulating layer 306 reduces or prevents the transfer of heat from heat generating equipment 310 to the adapter plate 304 and the skin 302 of the aircraft 303.
[0045]
[0063] The shroud 312 connects to the adapter plate 304 and the subplate 308. The shroud 312 provides an outer shell for the mounting system 301. The shroud 312 provides lightning protection, heat dissipation, and aerodynamic properties.
[0046]
[0064] The sub-plate 308 and the shroud 312 form a heat chamber 314. The heat chamber 314 receives heat from the heat generating equipment 310. The heat chamber 314 is thermally isolated from the adapter plate 304 and the skin 302 of the aircraft 303 by the insulation layer 306. In some illustrative embodiments, an additional thermal isolator is disposed at the connection point of the shroud 312 to the adapter plate 304. In some illustrative embodiments, an additional thermal isolator is disposed at the connection point of the sub-plate 308 to the adapter plate 304.
[0047]
[0065] Heat exits the heat chamber 314 as radiant heat 316. The radiant heat 316 exits a recess 318 in the subplate 308. The radiant heat 316 also radiates from the conductive material of the shroud 312.
[0048]
[0066] 4, an isometric view of a portion of a mounting system for mounting heat producing equipment is shown according to an exemplary embodiment. Mounting system 400 includes an adapter plate 402 and an insulating layer 404. Adapter plate 402 is one physical implementation of adapter plate 254 of FIG. 2. Insulating layer 404 is one physical implementation of insulating layer 210 of FIG. 2.
[0049]
[0067] The adapter plate 402 is configured to be mounted directly to a fuselage of an aircraft. The adapter plate 402 may already be present on the aircraft if other components of the mounting system 400 are retrofitted. In some illustrative examples, the adapter plate 402 is a common component across multiple designs of aircraft. As a result of being used for multiple functions, being retrofittable, and being used across multiple aircraft designs, the adapter plate 402 may be referred to as a universal adapter.
[0050]
[0068] The insulation layer 404 is provided to shield the adapter plate 402 and the underlying aircraft structure from heat generated by heat generating equipment carried by the mounting system 400. In some illustrative embodiments, the insulation layer 404 takes the form of a thermal insulation blanket. Although the insulation layer 404 is shown as being added to the adapter plate 402 as a first step, in other illustrative embodiments, the insulation layer 404 may first be connected to an additional component, such as the sub-plate 224 of FIG. 2. In some illustrative embodiments, the insulation layer 404 is part of the assembled antenna assembly 270 of FIG. 2 that is connected to the adapter plate 402 as one section.
[0051]
[0069] 5, an isometric view of a portion of a mounting system for mounting heat generating equipment is shown, according to one exemplary embodiment. Also shown in the view 500 of the mounting system 400 is a subplate 502. The subplate 502 is connected to the adapter plate 402 by a connecting piece 504. The connecting piece 504 extends through the insulation layer 404. A sealant (not shown) is applied to seal the insulation layer 404 where the connecting piece 504 extends through the insulation layer 404. The sealant prevents the ingress of liquid into the insulation layer 404. In some exemplary embodiments, the sealant is also insulating to prevent heat from spreading through the insulation layer 404 at the connecting piece 504.
[0052]
[0070] Subplate 502 is configured to support a heat generating device, such as a sensor or antenna. Subplate 502 includes a recess 506. When assembled, the heat generating device is disposed within recess 506. A flange 508 extends around recess 506. Flange 508 is configured to secure subplate 502 to a shroud, such as shroud portion 702 shown in FIG.
[0053]
[0071] As shown, the subplate 502 is of unitary construction. The subplate 502 is formed from a single piece of conductive material. The subplate 502 is configured to form a portion of the heat chamber of the mounting system 400.
[0054]
[0072] The subplate 502 is configured to support any desired type of heat generating device and may be described as a universal component.
[0055]
[0073] 6, an isometric view of a portion of a mounting system for mounting a heat generating device is shown according to an exemplary embodiment. View 600 is a diagram of mounting system 400 with heat generating device 601 in recess 506 of subplate 502. In this exemplary embodiment, heat generating device 601 includes electronic antenna 602 and electronic antenna 604. In view 600, electronic antenna 602 and electronic antenna 604 are positioned in recess 506 of subplate 502.
[0056]
[0074] In some demonstrative embodiments, the insulation layer 404, the sub-plate 502, and the heat generating equipment 601 are assembled into a prefabricated antenna assembly prior to connecting the sub-plate 502 to the adapter plate 402. By fastening the heat generating equipment 601 within the sub-plate 502 prior to fastening the sub-plate 502 to the adapter plate 402, assembly time may be reduced on the final assembly line. By connecting the heat generating equipment 601 offline, manufacturing time may be reduced.
[0057]
[0075] 7, an isometric view of a portion of a mounting system for mounting heat generating equipment is shown, according to an exemplary embodiment. In view 700 of mounting system 400, a shroud portion 702 is connected to subplate 502 and adapter plate 402 of FIG. 4. Although shroud portion 702 appears to be one component, shroud portion 702 may be formed of multiple components connected together. In some exemplary embodiments, shroud portion 702 includes an outer panel.
[0058]
[0076] 8, an isometric view of a portion of a mounting system for mounting heat generating equipment is shown according to one illustrative embodiment. View 800 of mounting system 400 is a fully assembled system.
[0059]
[0077] In diagram 800, shroud 802 includes shroud portion 702 and access panel 803. Access panel 803 is configured based on the design and location of heat generating equipment 601. By having access panel 803, shroud portion 702 can be used for any type or design of heat generating equipment that may reside within recess 506 of subplate 502. Access panel 803 includes access panel 804, access panel 806, access panel 808, and access panel 810. Each of shroud portion 702 and access panel 803 is connected to subplate 502.
[0060]
[0078] A skirt seal 812 is connected to the shroud portion 702. The skirt seal 812 is configured to seal against the aircraft fuselage to reduce fluid ingress into the mounting system 400.
[0061]
[0079] Referring now to Figure 9, a cross-sectional view of a portion of a mounting system for mounting a heat generating device is shown, according to an example embodiment. Figure 900 is a cross-sectional view of mounting system 901. Mounting system 901 is one physical implementation of mounting system 202 of Figure 2. Mounting system 901 may be the same as mounting system 301 of Figure 3. Mounting system 901 may be the same as mounting system 400 of Figures 4-8.
[0062]
[0080] In the diagram 900 of the mounting system 901, the heat generating devices 904 take the form of several electronic antennas 902. The several electronic antennas 902 are disposed within a sub-plate 906. The several electronic antennas 902 are exposed to the environment outside the mounting system 901.
[0063]
[0081] The subplate 906 is connected to a shroud 910. The shroud 910 includes an upper ring 912, an outer plate 914, and a lower ring 916. The shroud 910 is connected to an adapter plate 918.
[0064]
[0082] Although not shown in view 900, subplate 906 is connected at discrete points to an adapter plate 918. Although not shown in view 900, adapter plate 918 is attached to the fuselage of the aircraft.
[0065]
[0083] The shroud 910, sub-plate 906, and insulation layer 908 form a heat chamber. The insulation layer 908 reduces heat transferred from the heat chamber to the aircraft structure below the insulation layer 908. The insulation layer 908 reduces heat transferred from the heat generating equipment 904 to the adapter plate 918 and to the skin of the aircraft (not shown) below the adapter plate 918. Additionally, the distance between the sub-plate 906 and the adapter plate 918 reduces the heat that reaches the adapter plate 918. The distance between the sub-plate 906 and the adapter plate 918 passively controls the heat received by the adapter plate 918. The skirt seal and thermal isolators 920 reduce heat transferred from the shroud 910 to the fuselage.
[0066]
[0084] Heat generated by the heat generating devices 904 is radiated to the environment outside the mounting system 901. The heat generating devices 904 radiate heat directly to the environment. Additionally, heat is radiated from the shroud 910.
[0067]
[0085] With reference now to Figure 10, a block diagram of an aircraft having a mounting system is shown in accordance with an illustrative embodiment. Aircraft 100 may be one physical implementation of aircraft 1000 in Figure 10.
[0068]
[0086] The mounting system 1002 is configured to mount the heat generating device 1016 to an exterior 1074 of the aircraft 1000. The mounting system 1002 includes an adapter plate 1004, a thermal insulation layer 1008, a sub-plate 1012, the heat generating device 1016, and a radome 1018. The adapter plate 1004 is connected to a fuselage 1006 of the aircraft 1000. The thermal insulation layer 1008 substantially covers a first side 1010 of the adapter plate 1004. The sub-plate 1012 is formed of a conductive material 1014 and is connected to the adapter plate 1004 such that the thermal insulation layer 1008 is disposed between the sub-plate 1012 and the adapter plate 1004. In some illustrative embodiments, the thermal insulation layer 1008 is in contact with a back side 1060 of the sub-plate 1012. The heat generating device 1016 is secured within the sub-plate 1012. The radome 1018 is connected to the adapter plate 1004 and is positioned to cover the heat generating device 1016 and the sub-plate 1012 .
[0069]
[0087] The insulation layer 1008 is present to reduce the transfer of heat from the heat producing equipment 1016 to the skin 1070 of the fuselage 1006. In some illustrative embodiments, the skin 1070 is formed of a composite material 1072. It is desirable to reduce the heat transferred to the composite material 1072 during operation of the aircraft 1000 and the heat producing equipment 1016.
[0070]
[0088] The skin 1070 of the aircraft 1000 has an upper temperature threshold. Depending on the environmental temperature, environmental conditions, paint and other surface treatments on the skin 1070, and the operating conditions for the heat-generating equipment 1016, the heat-generating equipment 1016 may reach an undesirably high temperature and may even reach the upper temperature threshold. The mounting system 1002 reduces heat transferred from the heat-generating equipment 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 equipment 1016.
[0071]
[0089] The insulation layer 1008 is provided to shield the adapter plate 1004 and underlying aircraft structure, such as the skin 1070 of the fuselage 1006, from heat generated by heat generating equipment 1016 carried by the mounting system 1002. The insulation layer 1008 may take any desired form. In some illustrative examples, the insulation layer 1008 takes the form of an insulation blanket 1064. In some illustrative examples, the insulation blanket 1064 is the same material used in high temperature propulsion insulation points. In some illustrative examples, the insulation layer 1008 has an operating temperature of 450 degrees Fahrenheit.
[0072]
[0090] The radome 1018 is connected to the adapter plate 1004 such that the heat generating equipment 1016 is located in an interior 1019 of the radome 1018. The radome 1018 is connected to the adapter plate 1004 using a thermal isolator 1078 to reduce or prevent heat transfer from the radome 1018 to the adapter plate 1004, the skin 1070, and the fuselage 1006. A skirt seal 1076 seals the radome 1018 to the skin 1070 to reduce the ingress of liquid into the interior 1019 of the radome 1018.
[0073]
[0091] In some illustrative embodiments, the radome 1018 is formed of a conductive material 1020. The conductive material 1020 may take the form of a metal 1022. When the radome 1018 is formed of a conductive material 1020, heat from the heat generating device 1016 may escape from the radome 1018 as radiated heat 1026 to the environment 1028 outside the radome 1018. In some illustrative embodiments, when the radome 1018 is formed of a conductive material 1020, the radome 1018 may have a conventional design. In some illustrative embodiments, when the radome 1018 is formed of a conductive material 1020, the radome 1018 does not have any additional heat dissipation designs or features.
[0074]
[0092] In some demonstrative embodiments, the radome 1018 is formed of a composite material 1024. In some demonstrative embodiments, a heat transfer portal 1030 extends through the radome 1018. The heat transfer portal 1030 is an opening in the radome 1018. When present, the heat transfer portal 1030 provides a path for heat to exit the interior 1019 of the radome 1018.
[0075]
[0093] In some illustrative embodiments, the radome 1018 is prefabricated. When the radome 1018 is prefabricated, the heat transfer portals 1030 are cut into the radome 1018. In some illustrative embodiments, the radome 1018 is designed and manufactured for the mounting system 1002. In some illustrative embodiments, when the radome 1018 is manufactured for the mounting system 1002, the heat transfer portals 1030 may be formed in the radome 1018 during manufacturing. For example, when the radome 1018 is formed of a composite material 1024, the heat transfer portals 1030 may be formed during layup of the composite material 1024.
[0076]
[0094] The radome 1018 is configured with an aerodynamic design 1080. In some illustrative embodiments, heat transfer portals 1030 are present in the aft section of the radome 1018. By having the heat transfer portals 1030 in the aft section of the radome 1018, drag in the aerodynamic design 1080 can be reduced.
[0077]
[0095] In some demonstrative embodiments, a heat transfer door 1032 is present in the mounting system 1002. In some demonstrative embodiments, the heat transfer door 1032 is disposed in the heat transfer portal 1030. The heat transfer door 1032 is configured to transfer heat from the interior 1019 of the radome 1018 to an environment 1028 outside the mounting system 1002.
[0078]
[0096] In some demonstrative embodiments, the heat transfer door 1032 includes a metal material 1034 having a number of perforations 1036 within the metal material 1034. The number of perforations 1036 is configured to allow heat to escape from the interior 1019 via the number of perforations 1036.
[0079]
[0097] In some illustrative embodiments, the perforations in the plurality of perforations 1036 take the form of one of a matrix of holes 1038 , a plurality of slots 1040 , or a plurality of overlapping louvers 1042 .
[0080]
[0098] The matrix of holes 1038 may include holes of any desired layout. In some exemplary embodiments, the matrix of holes 1038 may include columns and rows of holes. In some exemplary embodiments, the matrix of holes 1038 may include alternating rows of holes. The matrix of holes 1038 may have any desired shape. In some exemplary embodiments, the holes of the matrix of holes 1038 may be at least one of circular, square, oval, triangular, or any other desired shape. The plurality of slots 1040 may have any desired layout and any desired dimensions.
[0081]
[0099] In some illustrative embodiments, the heat transfer door 1032 includes heat exhaust vents 1042. In these illustrative embodiments, the heat exhaust vents 1042 may radiate heat to the environment 1028. When present, the heat exhaust vents 1042 increase the surface area of the metal material 1034 to radiate heat from the heat transfer door 1032 to the environment 1028. In some illustrative embodiments, the heat exhaust vents 1042 are stationary. When the heat exhaust vents 1042 are stationary, the angle of the heat exhaust vents 1042 is fixed. In some illustrative embodiments, the heat exhaust vents 1042 are movable. When the heat exhaust vents 1042 are movable, the angle of the heat exhaust vents 1042 is adjustable.
[0082]
[0100] In some illustrative embodiments, the heat transfer door 1032 includes an actuator connected to the heat exhaust vent 1042. In some illustrative embodiments, the heat transfer door 1032 includes a shape memory alloy actuator 1044.
[0083]
[0101] In some illustrative embodiments, heat travels within the interior 1019 of the radome 1018 to exit through the heat transfer door 1032. In some illustrative embodiments, the mounting system 1002 includes a metal connection 1046 disposed between the heat transfer door 1032 and the subplate 1012. In some illustrative embodiments, the metal connection 1046 is configured to conduct heat between the subplate 1012 and the heat transfer door 1032.
[0084]
[0102] The heat generating device 1016 may take any desired form of heat generating device that is desirably secured to the exterior 1074 of the aircraft 1000. In some illustrative examples, the heat generating device 1016 includes a number of electronic antennas 1048. In some illustrative examples, the heat generating device 1016 includes a number of sensors 1050. The heat generating device 1016 is disposed within a recess 1052 in the subplate 1012.
[0085]
[0103] The subplate 1012 is connected to the adapter plate 1004. In some exemplary embodiments, the subplate 1012 is formed of a conductive material 1014. In some exemplary embodiments, the conductive material 1014 takes the form of a metal 1056, such as aluminum 1058. In some exemplary embodiments, the subplate 1012 is a unitary 1054 metal 1056 structure.
[0086]
[0104] The subplate 1012 is secured to an adapter plate 1004. The adapter plate 1004 is configured to connect a component to an exterior skin 1070 of the aircraft 1000. The adapter plate 1004 is configured to be attached directly to a fuselage 1006 of the aircraft 1000. The adapter plate 1004 is connected to the fuselage 1006 by fasteners 1068. The fasteners 1068 may take the form of any desired type of fastener. In some illustrative examples, the adapter plate 1004 is a common component for several different designs of aircraft. In some illustrative examples, the adapter plate 1004 has a common design for mounting different types of components to the mounting system 1002.
[0087]
[0105] The subplate 1012 is connected to the adapter plate 1004 by connecting pieces 1062 that extend through the thermal insulation layer 1008. In some demonstrative embodiments, a thermal isolator 1066 reduces heat transferred from the subplate 1012 through the connecting pieces 1062 to the adapter plate 1004.
[0088]
[0106] The illustration of aircraft 1000 in Figure 10 is not meant to imply physical or architectural limitations to the manner in which an illustrative embodiment may be implemented. Other components in addition to or instead of the ones illustrated may be used. Some components may be unnecessary. Also, blocks are presented to illustrate some functional components. When implemented in an illustrative embodiment, one or more of these blocks may be combined, divided, or combined and divided into different blocks.
[0089]
[0107] For example, only one heat transfer door is shown, although other unillustrated embodiments may include two or more heat transfer doors. As another example, fasteners for the radome 1018 are not shown, although fasteners may connect the radome 1018 to the adapter plate 1004.
[0090]
[0108] 11, an isometric view of a portion of a mounting system for mounting heat-generating equipment is shown in accordance with an illustrative embodiment. Mounting system 1100 is one physical implementation of mounting system 1002 of FIG. 10. Mounting system 1100 may be used to mount heat-generating equipment on aircraft 100 of FIG.
[0091]
[0109] The mounting system 1100 includes an adapter plate 1102 and a thermal insulation layer 1104. The adapter plate 1102 is configured to mount a component to the exterior of an aircraft, such as the aircraft 1000 of FIG. 10. The adapter plate 1102 can be used to mount any desired component to the exterior of the aircraft. The thermal insulation layer 1104 is disposed to cover a first side of the adapter plate 1102. The thermal insulation layer 1104 reduces or prevents heat from being transferred to the adapter plate 1102.
[0092]
[0110] 12, an isometric view of a portion of a mounting system for mounting heat producing equipment is shown according to an exemplary embodiment. In FIG. 1200, a subplate 1202 resides on top of an insulating layer 1104. The subplate 1202 is connected to an adapter plate 1102. The insulating layer 1104 extends between the subplate 1202 and the adapter plate 1102.
[0093]
[0111] The heat generating device 1204 is shown exploded on the subplate 1202. In this illustrative embodiment, the heat generating device 1204 takes the form of several electronic antennas 1206. The several electronic antennas 1206 are connected to the subplate 1202.
[0094]
[0112] 13, a cross-sectional view of a mounting system for mounting heat generating equipment is shown according to an exemplary embodiment. In FIG. 1300, a radome 1302 is connected to the adapter plate 1102 in the mounting system 1100. The radome 1302 is one physical implementation of the radome 1018 of FIG. 10. The radome 1302 is connected to the adapter plate 1102 and positioned to cover the heat generating equipment 1204 and the sub-plate 1202.
[0095]
[0113] A thermal insulation layer 1104 is disposed on a first surface 1308 of the adapter plate 1102. Several electronic antennas 1206 are connected within the subplate 1202.
[0096]
[0114] In this illustrative example, a heat transfer portal 1304 is present in the radome 1302. The heat transfer portal 1304 is an opening formed in the radome 1302. The heat transfer portal 1304 may be formed via at least one of machining, molding, or material layup. In some illustrative examples, a heat transfer door 1306 is present in the heat transfer portal 1304. The heat transfer door 1306 is configured to radiate heat away from the radome 1302. The heat transfer door 1306 is formed of a metallic material to radiate heat to an environment outside the radome 1302. The heat transfer door 1306 includes a plurality of perforations (not shown) to allow heat to escape from the radome 1302. The plurality of perforations may include perforations of any desired quantity, location, size, and shape. In other not shown examples, the heat transfer door 1306 may include a plurality of heat exhaust holes.
[0097]
[0115] 14, a cross-sectional view of a mounting system for mounting heat generating equipment is shown according to an exemplary embodiment. In FIG. 1400, a radome 1402 is connected to the adapter plate 1102 in the mounting system 1100. The radome 1402 is one physical implementation of the radome 1018 of FIG. 10. The radome 1402 is connected to the adapter plate 1102 and positioned to cover the heat generating equipment 1204 and the sub-plate 1202.
[0098]
[0116] The thermal insulation layer 1104 is disposed on the first surface 1410 of the adapter plate 1102. The heat generating device 1204 is connected within the subplate 1202.
[0099]
[0117] In this illustrative example, a heat transfer portal 1404 is present in the radome 1402. The heat transfer portal 1404 is an opening formed in the radome 1402. The heat transfer portal 1404 may be formed via at least one of machining, molding, or material layup. In some illustrative examples, a heat transfer door 1406 is present in the heat transfer portal 1404. The heat transfer door 1406 is configured to radiate heat from the radome 1402. The heat transfer door 1406 is formed of a metallic material to radiate heat to an environment outside the radome 1402. The heat transfer door 1406 includes a plurality of perforations to allow heat to escape from the radome 1402. The plurality of perforations may include perforations of any desired quantity, location, size, and shape. In other non-illustrated examples, the heat transfer door 1406 may include a plurality of heat exhaust holes.
[0100]
[0118] In FIG. 1400, a metal connection 1408 is present in the mounting system 1100. The metal connection 1408 is formed of any desired metal configured to provide thermal conduction. The metal connection 1408 contacts the subplate 1202. The metal connection 1408 contacts the heat transfer door 1406. The metal connection 1408 conducts heat from the subplate 1202 to the heat transfer door 1406 for removal of heat from below the radome 1402.
[0101]
[0119] Referring now to FIG. 15, a flow chart of a method for mounting heat generating equipment to the exterior of an aircraft is shown in accordance with an illustrative embodiment. Method 1500 may be performed to mount mounting system 120 to aircraft 100 of FIG. 1. Method 1500 may be performed to mount mounting system 202 to aircraft 200 of FIG. 2. Method 1500 may be performed using mounting system 301 of FIG. 3. Method 1500 may be performed using mounting system 401 of FIG. 4-8. Method 1500 may be performed using mounting system 901 of FIG. 9.
[0102]
[0120] The method 1500 places an insulation layer between the heat generating equipment and the skin of the aircraft fuselage (step 1502). The method 1500 secures a shroud over the insulation layer to form a heat chamber between the insulation layer and the outside environment (step 1504). The method 1500 then ends.
[0103]
[0121] In some illustrative examples, placing the insulation layer includes connecting the assembled antenna assembly, including the insulation layer, the subplate, and the number of electronic antennas, to the fuselage (step 1506). In these illustrative examples, the assembled antenna assembly is assembled offline. Assembling the assembled antenna assembly offline can reduce time and resources used during assembly on the aircraft. In some illustrative examples, connecting the assembled antenna assembly to the fuselage includes connecting the assembled antenna assembly to an adapter plate secured to the fuselage (step 1508). In some illustrative examples, the adapter plate is already secured to the fuselage of an aircraft in service. In these illustrative examples, the assembled antenna assembly may be connected to the adapter plate as a retrofit. In other illustrative examples, the assembled antenna assembly may be connected to the adapter plate during manufacture of the aircraft.
[0104]
[0122] In some illustrative embodiments, securing the shroud includes connecting an outer panel of the shroud to an adapter plate secured to the fuselage (Step 1510). In some illustrative embodiments, securing the shroud further includes connecting an access panel of the shroud to a subplate that holds the heat generating equipment, the subplate forming a heat chamber with the shroud (Step 1512). In these illustrative embodiments, the shroud includes multiple pieces. In some illustrative embodiments, securing the shroud includes assembling multiple portions of the shroud and securing the multiple portions to an adapter plate secured to the fuselage and to the subplate that holds the heat generating equipment (Step 1514).
[0105]
[0123] Referring now to FIG. 16 , a flow chart of a method for mounting heat generating equipment to the exterior of an aircraft is shown in accordance with an illustrative embodiment. Method 1600 may be performed to mount mounting system 120 to aircraft 100 of FIG. 1 . Method 1600 may be performed to mount mounting system 1002 to aircraft 1000 of FIG. 10 . Method 1600 may be performed using mounting system 1100 of FIGS. 11-12 . Method 1600 may be performed using mounting system 1100 shown in view 1300 of FIG. 13 . Method 1600 may be performed using mounting system 1100 shown in view 1400 of FIG. 14 .
[0106]
[0124] The method 1600 includes disposing an insulation layer between the heat-generating equipment and the skin of the aircraft fuselage (step 1602). The method 1600 includes securing a radome over the insulation layer and the heat-generating equipment (step 1604).
[0107]
[0125] In some demonstrative embodiments, disposing the insulation layer includes laminating an insulation layer over the adapter plate connected to the fuselage (operation 1606). The insulation layer is configured to cover a first side of the adapter plate to reduce or eliminate heat transfer to the adapter plate.
[0108]
[0126] In some demonstrative embodiments, the method 1600 attaches a subplate to the adapter plate such that a thermal barrier is between the subplate and the adapter plate, the subplate being configured to support the heat generating device (step 1608). In some demonstrative embodiments, the subplate is a universal subplate configured to accept a number of different types of heat generating devices. In some demonstrative embodiments, the subplate is a unitary metal structure.
[0109]
[0127] In some illustrative examples, securing the radome over the insulation layer and the heat generating equipment includes connecting the radome to an adapter plate (step 1610). In some illustrative examples, the adapter plate is present on an aircraft already in service. In these illustrative examples, the radome may be secured as a retrofit part. In some illustrative examples, the adapter plate is connected to the aircraft to accept the radome as part of the initial manufacture of the aircraft.
[0110]
[0128] In some demonstrative embodiments, the method 1600 positions a metal connection between the subplate and the heat transfer door within the radome, the metal connection being configured to conduct heat between the subplate and the heat transfer door (step 1612).
[0111]
[0129] Referring now to Figure 17, a flow chart of a method for installing a radome to cover heat generating equipment on an aircraft is shown according to an exemplary embodiment. Method 1700 may be performed to install radome 1018 of Figure 10. Method 1700 may be used to install a radome to adapter plate 1102 of Figures 11-12. Method 1700 may be used to install radome 1302 of Figure 13. Method 1700 may be used to install radome 1402 of Figure 14.
[0112]
[0130] The method 1700 cuts a heat transfer portal into the radome (step 1702). The method 1700 secures a heat transfer door within the heat transfer portal, the heat transfer door including a metal material and a plurality of perforations extending through the metal material (step 1704). The method 1700 then ends.
[0113]
[0131] In some demonstrative embodiments, the method 1700 connects the radome having the heat transfer portals to an adapter plate connected to a fuselage of the aircraft such that the radome covers the heat generating equipment (step 1706). In some demonstrative embodiments, the method 1700 places the heat transfer door in contact with the metal connection of the subplate supporting the heat generating equipment such that heat is conducted between the subplate and the heat transfer door through the metal connection of the subplate (step 1708).
[0114]
[0132] In some demonstrative embodiments, the method 1700 covers a first side of the adapter plate with an insulating layer (step 1710). In some demonstrative embodiments, the method 1700 connects a subplate to the adapter plate such that the subplate contacts the insulating layer (step 1712).
[0115]
[0133] As used herein, the phrase "at least one of" used in conjunction with enumerated items means that various combinations of one or more of the enumerated items may be used and that only one of each enumerated item may be required. For example, without limitation, "at least one of item A, item B, and item C" may include 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 be present. In other examples, "at least one of" may be, for example, without limitation, "2 items A, 1 item B, and 10 items C," "4 items B and 7 items C," or other suitable combinations. An item may be a particular object, thing, or category. In other words, "at least one of" means that any combination of items, and some items, may be used from among the enumeration, but not all of the enumerated items are required.
[0116]
[0134] As used herein, the term "a number of" when used in connection with items means one or more items.
[0117]
[0135] The flowcharts and block diagrams in the various illustrated embodiments illustrate the structure, functionality, and operation of some possible implementations of the apparatus and methods in an example embodiment. In this regard, each block in the flowchart or block diagram may represent at least one of a module, a segment, a function, or a portion of an operation or step.
[0118]
[0136] In some alternative implementations of an exemplary embodiment, one or more functions described in a block may occur out of the order described in the figures. For example, in some cases, two blocks shown in succession may be executed substantially simultaneously, or the blocks may sometimes be executed in reverse order, depending on the functionality involved. Also, other blocks may be added in addition to the blocks shown in the flowchart or block diagram. Some blocks may be optional. For example, steps 1506 to 1514 may be optional. As another example, steps 1606 to 1612 may be optional. As another example, steps 1706 to 1712 may be optional.
[0119]
[0137] An example embodiment of the disclosure may be described in the context of an aircraft maintenance and service method 1800 shown in Figure 18 and an aircraft 1900 shown in Figure 19. Referring initially to Figure 18, an aircraft manufacturing and maintenance method is illustrated in the form of a block diagram in accordance with an example embodiment. During the pre-production stage, aircraft manufacturing and service method 1800 may include specification and design 1802 and material sourcing 1804 of the aircraft 1900 of Figure 19.
[0120]
[0138] During production, component and subassembly manufacturing 1806 and system integration 1808 of the aircraft 1900 takes place. The aircraft 1900 may then proceed through certification and delivery 1810 and be placed into service 1812. While in customer service 1812, the aircraft 1900 is scheduled for routine maintenance and service 1814, which may include modification, reconfiguration, refurbishment, or other maintenance and service.
[0121]
[0139] Each process of aircraft manufacturing and service method 1800 may be performed or implemented by a system integrator, a third party, and / or an operator. In some examples, the operator may be a customer. As used herein, 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 entity may be an airline, a leasing company, a military entity, a service organization, etc.
[0122]
[0140] Referring now to Figure 19, an aircraft is shown in the form of a block diagram in which an illustrative embodiment may be implemented. In this example, aircraft 1900 is manufactured by aircraft manufacturing and service method 1800 in Figure 18 and may include an airframe 1902 having a number of systems 1904 and an interior 1906. Example systems 1904 include one or more of a propulsion system 1908, an electrical system 1910, a hydraulic system 1912, and an environmental system 1914. Any number of other systems may also be included.
[0123]
[0141] Apparatus and methods embodied herein may be used during at least one stage of aircraft manufacturing and service method 1800. One or more illustrative embodiments may be manufactured or used during at least one of component and subassembly manufacturing 1806, system integration 1808, operation 1812, or maintenance and service 1814 in FIG.
[0124]
[0142] The illustrative embodiments provide the ability to manufacture and retrofit new antenna technologies into existing airplane structures. The illustrative embodiments also enable thermal management of new electronic antenna technologies that may get hotter than the fuselage skin can tolerate if the antenna is installed directly on the skin.
[0125]
[0143] Exemplary embodiments provide a radome with a smaller protrusion in the mounting system than conventional radomes. Exemplary embodiments provide a mounting system that is shorter than conventional radomes.
[0126]
[0144] The exemplary embodiments provide protection against overheating of the skin of an aircraft. The exemplary embodiments provide thermal protection even if a hardware thermal shutdown is not triggered.
[0127]
[0145] Electronically steered antennas are expected to generate excessive amounts of heat, which, if directly mounted, can raise the temperature of the aircraft skin to undesirably high levels. The illustrative embodiments define a new method for conducting excess heat from the very hot base of the Electronically Steered Antenna (ESA) through a subplate and shroud heat sink to the surrounding atmosphere. Thermal insulation below the ESA protects the skin of the aircraft fuselage.
[0128]
[0146] The shroud is a low profile, aerodynamically advantageous design. Aerodynamically, the shroud has a low level of aerodynamic drag compared to conventional radomes. Exemplary embodiments provide protection from bird strike effects. The shroud provides lightning strike protection due to a large, continuous ground path. Because the subplate and its mounting connections are integrated, the antenna, associated line repair unit (LRU), wire harness, and ground straps can be installed off-site in a single assembly and transported to the final assembly line. Bolting the integrated subplate to the ESA assembly is less labor intensive than fully assembling it on an assembly line. Manufacturing with distributed off-site installation provides significant time and cost savings compared to the lengthy installation times required for today's mechanically steered antennas.
[0129]
[0147] Furthermore, the present disclosure includes embodiments according to the following clauses:
[0130] Article 1. A mounting system (202) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising: a heat chamber (208) formed by a number of conductive materials (212, 214), the heat chamber (208) having a recess (216) open to an environment (1028) outside the aircraft (200); the heat generating device (204) fixed in the recess (216); and A mounting system (202) including an insulating layer (210) between the heat chamber (208) and the aircraft (200), the insulating layer (210) being positioned opposite an opening of the recess (216) of the heat chamber (208).
[0131] Article 2. 2. The mounting system (202) of claim 1, wherein the heat generating device (204) includes a number of electronic antennas (219).
[0132] Article 3. 2. The mounting system (202) of claim 1, wherein the heat chamber (208) is formed by a shroud (222) and a subplate (224).
[0133] Article 4. 4. The mounting system (202) of claim 3, wherein the shroud (222) includes a plurality of portions (272) secured together.
[0134] Article 5. a skirt seal (242) connected to a lower ring (240) of the shroud (222); and 5. The mounting system (202) of claim 4, further comprising a thermal isolator (244) disposed between the lower ring (240) and a skin (246) of the aircraft (200).
[0135] Article 6. 4. The mounting system (202) of claim 3, wherein the subplate (224) is of unitary (252) metal (248) construction.
[0136] Article 7. 4. The mounting system (202) of claim 3, wherein the subplate (224) includes the recess (216) and a flange (238) surrounding the recess (216).
[0137] Article 8. 8. The mounting system (202) of claim 7, wherein the flange (238) of the subplate (224) is fixed to the shroud (222).
[0138] Article 9. The mounting system (202) as recited in clause 3, further comprising a number of thermal isolators (260) disposed between the heat chamber (208) and the aircraft (200).
[0139] Article 10. A mounting system (202) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising: a subplate (224) having a recess (216) surrounded by a flange (238), the subplate (224) being formed of a conductive material (212); the heat generating device (204) disposed within the recess (216); and The mounting system (202) includes an insulating layer (210) secured to a back side (262) of the subplate (224).
[0140] Article 11. 11. The mounting system (202) of claim 10, wherein the heat generating device (204) includes a number of electronic antennas (219).
[0141] Article 12. an adapter plate (254) configured to connect a component to the skin (246) of the aircraft (200); and 11. The mounting system (202) of claim 10, further comprising a connection piece (258) connecting said subplate (224) to said adapter plate (254).
[0142] Article 13. 13. The mounting system (202) according to claim 12, wherein a number of thermal isolators (260) are disposed between said subplate (224) and said adapter plate (254).
[0143] Article 14. 11. The mounting system (202) of claim 10, further comprising a shroud (222) including a plurality of portions (272) secured together, the shroud (222) being formed from a conductive material (214) and configured to provide an aerodynamic design (274).
[0144] Article 15. The mounting system (202) described in clause 14, wherein the multiple portions (272) of the shroud (222) include an outer panel (232) and an access panel (234), the outer panel (232) secured to an adapter panel (254) configured to connect components to the outer panel (246) of the aircraft (200), and the access panel (234) is designed to fit the cross-sectional shape of the heat-generating equipment (204).
[0145] Article 16. 15. The mounting system (202) as recited in claim 14, wherein a number of thermal isolators (244) are disposed between the shroud (222) and a skin (246) of the aircraft (200).
[0146] Article 17. A method (1500) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising: disposing (1502) a thermal barrier (210) between the heat generating equipment (204) and a skin (246) of a fuselage (256) of the aircraft (200); and A method (1500) comprising securing (1504) a shroud (222) over the insulation layer (210) to form a heat chamber (208) between the insulation layer (210) and an outside environment (1028).
[0147] Article 18. The method (1500) of claim 17, wherein disposing the insulation layer (210) includes connecting (1506) an assembled antenna assembly (270), including the insulation layer (210), a subplate (224), and a number of electronic antennas (219), to the fuselage (256).
[0148] Article 19. The method (1500) of clause 18, wherein connecting the assembled antenna assembly (270) to the fuselage (256) includes connecting (1508) the assembled antenna assembly (270) to an adapter plate (254) secured to the fuselage (256).
[0149] Article 20. Clause 17. The method (1500) of clause 17, wherein securing the shroud (222) includes connecting (1510) an outer panel (232) of the shroud (222) to an adapter plate (254) secured to the fuselage (256).
[0150] Article 21. The method (1500) of clause 20, wherein fixing the shroud (222) further includes connecting an access panel of the shroud (222) to a subplate (224) that holds the heat-generating equipment (204), the subplate (224) forming (1512) with the shroud (222) the heat chamber (208).
[0151] Article 22. Fixing the shroud (222) assembling a plurality of portions (272) of said shroud (222); and The method (1500) according to clause 17, further comprising fastening (1514) the plurality of portions (272) to an adapter plate (254) secured to the body (256) and to a subplate (224) that holds the heat generating device (204).
[0152] Article 23. A mounting system (1002) for mounting a heat generating device (1016) to the exterior of an aircraft (1000), comprising: an adapter plate (1004) connected to a fuselage (1006) of the aircraft (1000); a thermal barrier layer (1008) substantially covering a first surface (1010) of the adapter plate (1004); a subplate (1012) formed of a conductive material (1014), the subplate (1012) being connected to the adapter plate (1004) such that the thermal insulation layer (1008) is disposed between the subplate (1012) and the adapter plate (1004); a heat generating device (1016) fixed within the subplate (1012); and A mounting system (1002) including a radome (1018) connected to the adapter plate (1004), the radome (1018) being positioned to cover the heat-generating equipment (1016) and the subplate (1012).
[0153] Article 24. 24. The mounting system (1002) of claim 23, wherein the radome (1018) is formed of a conductive material (1020).
[0154] Article 25. 24. The mounting system (1002) of claim 23, wherein the subplate (1012) is of unitary (1054) metal (1056) construction.
[0155] Article 26. 24. The mounting system (1002) of claim 23, wherein the heat generating device (1016) includes a number of electronic antennas (1048).
[0156] Article 27. 24. The mounting system (1002) of claim 23, wherein the radome (1018) is formed of a composite material (1024).
[0157] Article 28. 24. The mounting system (1002) as recited in claim 23, further comprising a heat transfer portal (1030) cut into said radome (1018).
[0158] Article 29. 29. The mounting system (1002) of claim 28, further comprising a heat transfer door (1032) disposed within the heat transfer portal (1030).
[0159] Article 30. 30. The mounting system (1002) of claim 29, wherein the heat transfer door (1032) comprises a metal material (1034) having a plurality of perforations (1036) therein.
[0160] Article 31. The mounting system (1002) of claim 30, wherein the plurality of perforations (1036) take the form of one of a matrix of holes (1038), a plurality of slots (1040), or a plurality of overlapping heat exhaust holes (1042).
[0161] Article 32. 31. The mounting system (1002) of claim 30, wherein the heat transfer door (1032) comprises a shape memory alloy (1044).
[0162] Article 33. The mounting system (1002) of clause 29 further comprises a metal connection (1046) disposed between the heat transfer door (1032) and the subplate (1012), the metal connection (1046) being configured to conduct heat between the subplate (1012) and the heat transfer door (1032).
[0163] Article 34. A method (1600) for attaching a heat generating device (1016) to an exterior (1074) of an aircraft (1000), comprising: disposing (1602) a thermal barrier (1008) between the heat generating equipment (1016) and a skin (1070) of a fuselage (1006) of the aircraft (1000); and The method (1600) includes securing (1604) a radome (1018) over the thermal insulation layer (1008) and the heat-generating equipment (1016).
[0164] Article 35. The method (1600) of claim 34, wherein positioning the insulation layer (1008) includes laminating (1606) the insulation layer (1008) onto an adapter plate (1004) connected to the fuselage (1006).
[0165] Article 36. The method (1600) according to clause 35, further comprising attaching the subplate (1012) to the adapter plate (1004) such that the insulating layer (1008) is between the subplate (1012) and the adapter plate (1004), the subplate (1012) being configured (1608) to support the heat-generating device (1016).
[0166] Article 37. The method (1600) of claim 36, wherein fixing the radome (1018) over the insulating layer (1008) and the heat-generating equipment (1016) includes connecting (1610) the radome (1018) to the adapter plate (1004).
[0167] Article 38. The method (1600) of clause 37 further includes disposing a metal connection (1046) between the subplate (1012) and a heat transfer door (1032) in the radome (1018), the metal connection (1046) being configured (1612) to conduct heat between the subplate (1012) and the heat transfer door (1032).
[0168] Article 39. 1. A method (1700) for installing a radome (1018) for covering heat generating equipment (1016) on an aircraft (1000), comprising: cutting (1702) a heat transfer portal (1030) into said radome (1018); and A method (1700) comprising fixing (1704) a heat transfer door (1032) within the heat transfer portal (1030), the heat transfer door (1032) comprising a metal material (1034) and a plurality of perforations (1036) extending through the metal material (1034).
[0169] Article 40. The method (1700) of clause 39 further includes connecting (1706) the radome (1018) having the heat transfer portals (1030) to an adapter plate (1004) connected to a fuselage (1006) of the aircraft (1000) so that the radome (1018) covers the heat-generating equipment (1016).
[0170] Article 41. The method (1700) of clause 40 further includes positioning (1708) the heat transfer door (1032) in contact with the metal connection (1046) of the subplate (1012) supporting the heat generating equipment (1016) so that heat is conducted between the subplate (1012) and the heat transfer door (1032) via the metal connection (1046).
[0171] Article 42. covering (1710) a first surface (1010) of the adapter plate (1004) with a thermal barrier (1008); and 42. The method (1700) of clause 41, further comprising connecting (1712) the subplate (1012) to the adapter plate (1012) such that the subplate (1012) is in contact with the insulating layer (1008).
[0172]
[0148] The description of the various exemplary embodiments is presented for the purpose of illustration and explanation, and is not intended to be exhaustive or to limit the embodiments to the disclosed forms. Many modifications and variations will be apparent to those skilled in the art. Furthermore, various exemplary embodiments may provide different features compared to other exemplary embodiments. The selected one or more embodiments have been selected and described in order to best explain the principles and practical applications of the embodiments, and to facilitate understanding by others skilled in the art of the disclosure of the various embodiments and various modifications suitable for the particular application under consideration.
Claims
1. A mounting system (202) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising: a heat chamber (208) formed by a number of conductive materials (212, 214), the heat chamber (208) having a recess (216) open to an environment (1028) outside the aircraft (200); The heat generating device (204) fixed in the recess (216), and 1. A mounting system comprising: an insulating layer between the heat chamber and the aircraft, the insulating layer being disposed on an opposite side of an opening of the recess in the heat chamber.
2. The mounting system (202) of claim 1, wherein the heat generating device (204) comprises a number of electronic antennas (219).
3. The mounting system (202) of claim 1, wherein the heat chamber (208) is defined by a shroud (222) and a subplate (224).
4. The mounting system (202) of claim 3, wherein the shroud (222) comprises a plurality of portions (272) secured together.
5. a skirt seal (242) connected to a lower ring (240) of said shroud (222); and The mounting system (202) of claim 4, further comprising a thermal isolator (244) disposed between the lower ring (240) and a skin (246) of the aircraft (200).
6. The mounting system (202) of claim 3, wherein the subplate (224) is a unitary (252) metal (248) construction.
7. The mounting system (202) of claim 3, wherein the subplate (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 subplate (224) is fixed to the shroud (222).
9. The mounting system (202) of claim 3, further comprising a number of thermal isolators (260) disposed between the heat chamber (208) and the aircraft (200).
10. A mounting system (202) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising: a subplate (224) having a recess (216) surrounded by a flange (238), the subplate (224) being formed of a conductive material (212); The heat generating device (204) disposed within the recess (216); and A mounting system (202) including a thermal insulation layer (210) secured to a back side (262) of the subplate (224).
11. The mounting system (202) of claim 10, wherein the heat generating device (204) comprises a number of electronic antennas (219).
12. an adapter plate (254) configured to connect a component to a skin (246) of the aircraft (200); and The mounting system (202) of claim 10, further comprising a connection piece (258) connecting said subplate (224) to said adapter plate (254).
13. The mounting system (202) of claim 12, wherein a number of thermal isolators (260) are disposed between the subplate (224) and the adapter plate (254).
14. 11. The mounting system (202) of claim 10, further comprising a shroud (222) including a plurality of portions (272) secured together, the shroud (222) formed from a conductive material (214) and configured to provide an aerodynamic design (274).
15. 15. The mounting system of claim 14, wherein the plurality of portions of the shroud include a skin and an access panel, the skin secured to an adapter panel configured to connect a component to a skin of the aircraft, the access panel designed to accommodate a cross-sectional shape of the heat producing equipment.
16. The mounting system (202) of claim 14, wherein a number of thermal isolators (244) are disposed between the shroud (222) and a skin (246) of the aircraft (200).
17. A method (1500) for mounting a heat generating device (204) to an exterior (206) of an aircraft (200), comprising the steps of: disposing (1502) a thermal insulation layer (210) between the heat generating equipment (204) and a skin (246) of a fuselage (256) of the aircraft (200); and The method (1500) includes securing (1504) a shroud (222) over the insulation layer (210) to form a heat chamber (208) between the insulation layer (210) and an outside environment (1028).
18. 20. The method (1500) of claim 17, wherein disposing the insulation layer (210) includes connecting (1506) an assembled antenna assembly (270) including the insulation layer (210), a subplate (224), and a number of electronic antennas (219) to the fuselage (256).
19. 20. The method (1500) of claim 18, wherein connecting the assembled antenna assembly (270) to the fuselage (256) includes connecting (1508) the assembled antenna assembly (270) to an adapter plate (254) secured to the fuselage (256).
20. 20. The method (1500) of claim 17, wherein securing the shroud (222) includes connecting (1510) a skin (232) of the shroud (222) to an adapter plate (254) secured to the fuselage (256).
21. 21. The method (1500) of claim 20, wherein fixing the shroud (222) further comprises connecting an access panel of the shroud (222) to a subplate (224) that holds the heat generating equipment (204), the subplate (224) forming (1512) with the shroud (222) the heat chamber (208).
22. Securing the shroud (222) assembling a plurality of portions (272) of said shroud (222); and 20. The method (1500) of claim 17, further comprising: fastening (1514) the plurality of sections (272) to an adapter plate (254) secured to the fuselage (256) and to a subplate (224) that holds the heat generating equipment (204).