Cryogenic tank support system
The cryogenic tank support system addresses integration challenges by structurally isolating tanks from the aircraft fuselage, supporting loads, and allowing for thermal insulation, thus ensuring safe and efficient hydrogen fuel storage.
Patent Information
- Application Number
- JP2025095307
- Authority / Receiving Office
- JP · JP
- Patent Type
- Applications
- Current Assignee / Owner
- Priority Date
- 2024-06-19
- Filing Date
- 2025-06-09
- Publication Date
- 2026-01-14
AI Technical Summary
Integrating large cryogenic liquid hydrogen tanks into aircraft poses challenges in terms of storage, thermal management, packaging, and ensuring that the added weight does not affect flight dynamics or compromise structural integrity.
A cryogenic tank support system comprising support collars and saddle brackets that structurally isolate the tanks from the aircraft fuselage, supporting radial and axial loads while allowing for axial expansion and contraction, and are integrated with a fairing for aerodynamic purposes.
The system effectively supports cryogenic tanks without affecting the aircraft's structural stiffness or flight dynamics, maintaining thermal insulation and ensuring safe, efficient integration of hydrogen fuel.
Smart Images
Figure 2026004233000001_ABST
Abstract
Description
[Technical Field]
[0001] CROSS-REFERENCE TO RELATED APPLICATIONS
[0001] This application claims the benefit of U.S. Provisional Patent Application No. 63 / 659,039, filed June 12, 2024, entitled "Cryogenic Tank Support System," which is incorporated herein by reference in its entirety.
[0002] This application is related to the following United States patent application: U.S. Patent Application No. 18 / 747,546, Attorney Docket No. 23-2040-US-NP, entitled "Top-Fuselage Mounted Cryogenic Tank," having the same filing date as this application, which is incorporated herein by reference in its entirety.
[0003]
[0003] This disclosure relates generally to aircraft. In particular, this disclosure relates to aircraft that use propulsion systems powered using cleaner emitting fuel alternatives, such as hydrogen, stored in fuel tanks installed on the aircraft. [Background technology]
[0004]
[0004] As the price of conventional jet fuel or carbon taxes increase, combined with climate change, the incentive to use alternative fuels to power large commercial aircraft will grow over time.
[0005]
[0005] One such alternative fuel is hydrogen. Hydrogen is an essentially inexhaustible resource because the most common source of hydrogen is water. As a fuel source, hydrogen is stored in a liquid state. Liquid hydrogen fuel must be stored at cryogenic temperatures. Large on-board cryogenic tanks are required for each aircraft to provide enough fuel for normal aircraft function.
[0006]
[0006] Fuel tank packaging, the addition of a dedicated hydrogen system to an aircraft, and the impact of various safety considerations on the aircraft provide unique challenges when incorporating the use of alternative fuels stored in cryogenic fuel tanks.
[0007]
[0007] These challenges include the storage of cryogenic liquid hydrogen and methods and locations for mounting cryogenic tanks on aircraft without upsetting the aircraft's flight dynamics and without compromising the aircraft's structural integrity.
[0008]
[0008] 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
[0009]
[0009] One embodiment of the present disclosure provides a cryogenic tank support. The cryogenic tank support includes a cryogenic tank, a first support collar, a second support collar, a first saddle bracket, and a second saddle bracket. The first support collar is connected to the cryogenic tank. The first support collar is also connected to the first saddle bracket. The second support collar is connected to the cryogenic tank. The second support collar is also connected to the second saddle bracket. The first support collar supports a radial load on the cryogenic tank and an axial load on the cryogenic tank. However, the second support collar only supports the radial load on the cryogenic tank and allows axial expansion and contraction of the cryogenic tank.
[0010] Another exemplary embodiment of the present disclosure provides a system for mounting a cryogenic tank to an aircraft. The system includes an inner ring of a support collar connected to an inner wall of the cryogenic tank. The system also includes an outer ring of the support collar connected to an outer wall of the cryogenic tank. The system also includes a saddle of a saddle bracket connected to the outer ring of the support collar. The system also includes a mounting surface of the saddle bracket connected to a crown region of a fuselage of the aircraft.
[0011] Another exemplary embodiment of the present disclosure provides a method for installing a cryogenic tank on an aircraft. An inner ring of a support collar is connected to an inner wall of the cryogenic tank. An outer ring of the support collar is connected to an outer wall of the cryogenic tank. The support collar is connected to a saddle bracket. The saddle bracket is connected to a fuselage of the aircraft.
[0012]
[0012] These features and functions may be realized individually in various embodiments of the present disclosure or may be combined in further embodiments, further details of which can be understood by reference to the following description and drawings.
[0013]
[0013] The novel features believed characteristic of the illustrative embodiments are set forth in the appended claims. However, the illustrative embodiments, as well as their preferred modes of use, further objects and features thereof, will best be understood by reading the following detailed description of illustrative embodiments of the present disclosure when read in conjunction with the accompanying drawings. [Brief explanation of the drawings]
[0014] [Figure 1]
[0014] FIG. 1 is a block diagram of a platform according to an exemplary embodiment. [Figure 2]
[0015] 1 is an illustration of an aircraft having a cryogenic tank in accordance with an illustrative embodiment; [Figure 3]
[0016] FIG. 1 is an illustration of a cryogenic tank and a cryogenic tank support system in accordance with an illustrative embodiment. [Figure 4]
[0017] FIG. 1 is an illustration of a cryogenic tank support system in accordance with an illustrative embodiment. [Figure 5]
[0018] FIG. 1 is an illustration of a support collar for a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 6]
[0019] FIG. 1 is an illustration of a support collar for a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 7]
[0020] FIG. 1 is a cross-sectional view of a support collar of a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 8]
[0021] FIG. 1 is a cross-sectional view of a support collar of a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 9]
[0022] FIG. 1 is an illustration of a saddle bracket of a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 10]
[0023] FIG. 1 is an illustration of a saddle bracket of a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 11]
[0024] FIG. 1 is an illustration of a cross-sectional view of a tank support system connected to a cryogenic tank in accordance with an illustrative embodiment. [Figure 12]
[0025] FIG. 1 is an illustration of a strut of a cryogenic tank support system in accordance with an illustrative embodiment; [Figure 13]
[0026] 1 is an illustration of a flowchart of a process for installing a cryogenic tank on an aircraft in accordance with an illustrative embodiment; [Figure 14]
[0027] FIG. 1 is an illustration of an aircraft manufacturing and service method in accordance with an illustrative embodiment. [Figure 15]
[0028] FIG. 1 is a block diagram of an aircraft in which an illustrative embodiment may be implemented; DETAILED DESCRIPTION OF THE INVENTION
[0015]
[0029] The illustrative embodiments recognize and take into account several different challenges associated with aircraft operating using alternative fuel sources, such as liquid hydrogen fuel. The challenges recognized by various illustrative embodiments are described herein.
[0016]
[0030] The illustrative embodiments recognize and take into account that integrating a liquid hydrogen (LH2) system into a passenger aircraft, such as a large commercial airliner, can be challenging. For example, there are design challenges in determining where to safely place a large hydrogen tank and how to package the thermal management and fuel tank stack systems, both of which have large volume requirements.
[0017]
[0031] These illustrative examples describe the placement of fuel tanks on or along the sides of the fuselage and how they are attached to the fuselage. This type of configuration can integrate the tanks in a safe manner so that the added weight does not affect the flight dynamics of the aircraft and while structurally isolating the tanks from the aircraft structure. In one illustrative example, four cryogenic tanks are used to add redundancy and minimize slosh. In one illustrative example, a fairing encases the tanks and tank support system for aerodynamic purposes.
[0018]
[0032] Referring now to the figures, and in particular to Figure 1, a block diagram of a platform is depicted in accordance with an illustrative embodiment. In this illustrative embodiment, platform 100 includes aircraft 102.
[0019]
[0033] 1 is not meant to suggest physical or architectural limitations to the manner in which an illustrative embodiment may be implemented. For example, aircraft 102 may be a civilian aircraft, but aircraft 102 may also be a military aircraft, a rotorcraft, a helicopter, an unmanned aerial vehicle, or any other suitable aircraft.
[0020]
[0034] Although exemplary embodiments are described with respect to an aircraft, an exemplary embodiment may also be applied to other types of platforms. The platform may be, for example, a mobile platform, a fixed platform, a land structure, an underwater structure, or a space structure. More specifically, the platform may be an aircraft, a surface ship, a tank, a personnel carrier, a train, a spacecraft, a space station, a satellite, a submarine, an automobile, a power plant, a bridge, a dam, a house, a manufacturing facility, a building, a tool, a mechanical structure, or some other suitable platform or structure for which a cryogenic tank support system is desired.
[0021]
[0035] In this illustrative example, platform 100 takes the form of aircraft 102. In this illustrative example, when platform 100 takes the form of aircraft 102, aircraft 102 includes fairing 104, fuselage 106, tank support system 108, and cryogenic tank 110.
[0022]
[0036] The tank support system 108 connects the cryogenic tank 110 to the fuselage 106 of the aircraft 102. When the tank support system 108 is used to connect the cryogenic tank 110 to the fuselage 106 of the aircraft 102, the cryogenic tank 110 is structurally isolated 112 from the aircraft 102. In other words, the connection of the cryogenic tank 110 to the aircraft 102 does not structurally affect the fuselage 106. The tank support system 108 supports radial and axial loads on the cryogenic tank 110 at one end of the cryogenic tank 110, while at the opposite end of the cryogenic tank 110, it supports only radial loads on the cryogenic tank 110 and allows for axial expansion / contraction of the cryogenic tank 110 relative to the aircraft 102. As a result, adding the tank support system 108 to connect the cryogenic tank 110 to the aircraft 102 does not affect the structural stiffness and flexure of the aircraft 102. Any forces acting on the aircraft resulting from the aircraft's intended use are isolated from the cryogenic tank, and any forces acting on the cryogenic tank are isolated from the aircraft. A fairing 104 is connected to the fuselage 106. The fairing 104 encases the tank support system 108 and the cryogenic tank 110 for aerodynamic purposes.
[0023]
[0037] As used herein, a first component being "connected" or "coupled" or "associated" with a second component means that the first component can be directly or indirectly connected to the second component. A connection is a physical association. In other words, there may be additional components between the first component and the second component. When there are one or more additional components between the two components, the first component is considered to be indirectly connected to the second component. When a first component is directly connected to a second component, there are no additional components between the two components.
[0024]
[0038] For example, a first component may be considered to be physically connected to a second component by at least one of being fixed to the second component, glued to the second component, attached to the second component, welded to the second component, fastened to the second component, or connected to the second component in some other suitable manner. The first component may also be connected to the second component using a third component. The first component may also be physically connected to the second component by being formed as part of the second component, as an extension of the second component, or both.
[0025]
[0039] The size and capacity of the cryogenic tank 110 may be designed for the intended purpose of the aircraft 102. The cryogenic tank 110 may be more than one cryogenic tank, for example, a set of cryogenic tanks may be required. The tank support system 108 may be configured to accommodate any number of cryogenic tanks and is not limited to a single cryogenic tank.
[0026]
[0040] As used herein, the term "set" when used in reference to a plurality of items means one or more items. For example, a "set of cryogenic tanks" is one or more cryogenic tanks.
[0027]
[0041] 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. In other words, "at least one of" means that any combination of items and any number of items from the list may be used, and not all of the enumerated items may be required. An item may be a specific object, article, or category.
[0028]
[0042] 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 some illustrative examples, "at least one of" may be, by way of example and not limitation, "two items A, one item B, and ten items C," "four items B, and seven items C," or other suitable combinations.
[0029]
[0043] Fuselage 106 includes frame 114. In this illustrative example, frame 114 represents structural members that form fuselage 106. Frame 114 of fuselage 106 includes crown region 116 disposed at a top of fuselage 106 and side regions 118 disposed at one or both sides of fuselage 106.
[0030]
[0044] The tank support system 108 is connected to a frame 114 of the fuselage 106 at either a crown region 116 or a side region 118. The tank support system 108 is connected to a cryogenic tank 110.
[0031]
[0045] The tank support system 108 includes at least a first support collar 120 and a second support collar 122. The total number of support collars depends on the number of cryogenic tanks to be supported. Each cryogenic tank requires at least two support collars.
[0032]
[0046] First support collar 120 has shape 130. Second support collar 122 has shape 131. Shapes 130 and 131 are sized and shaped to fit cryogenic tank 110. Generally, cryogenic tank 110 is cylindrical in shape due to efficiency of fuel storage. As a result, first support collar 120 and second support collar 122 are ring-shaped with circumferences and dimensions that fit the cylindrical shape of cryogenic tank 110. The shapes of cryogenic tank 110 and support collars are not limited to a cylinder and a ring, respectively. First support collar 120 and second support collar 122 are shaped to fit cryogenic tank 110, regardless of the shape of cryogenic tank 110.
[0033]
[0047] The first support collar 120 includes an inner ring 132 connected to an outer ring 136 by a web 134. The web 134 extends completely around the first support collar 120 between the inner ring 132 and the outer ring 136. The inner ring 132 is wider than the outer ring 136 to allow access to the welding area. Ribs 138 connect the inner ring 132 and the outer ring 136 between the inner ring 132 and the outer ring 136. The ribs 138 extend at an angle from the web 134. The ribs 138 may be perpendicular to the web 134. The ribs 138 may be a set of ribs evenly spaced around the circumference of the first support collar 120. A flange 140 extends radially outward from the outer ring 136. A gusset 142 connects the outer ring 136 to the flange 140. The gussets 142 may be a set of gussets evenly spaced around the circumference of the first support collar 120. Each rib 138 is linearly aligned with at least one gusset 142.
[0034]
[0048] The second support collar 122 includes an inner ring 133 connected to an outer ring 137 by a web 135. The web 135 extends around the entire circumference of the second support collar 122 between the inner ring 133 and the outer ring 137. The inner ring 133 is wider than the outer ring 137 to allow access to the welding area. A flange 141 extends radially outward from the outer ring 137.
[0035]
[0049] The first support collar 120 is able to support the cryogenic tank radial load 162 and the cryogenic tank axial load 164 because of the presence of the ribs 138 and gussets 142. The second support collar 122 does not include the ribs or gussets found on the first support collar 120. As a result, the second support collar 122 is able to support only the cryogenic tank radial load 162 while allowing for axial expansion / contraction of the cryogenic tank.
[0036]
[0050] The tank support system 108 includes at least a first saddle bracket 124 and a second saddle bracket 126. The total number of saddle brackets depends on the number of cryogenic tanks to be supported. Each cryogenic tank requires at least two saddle brackets. In that case, each saddle bracket is paired with at least one support collar. More than two support collars may be paired with each saddle bracket.
[0037]
[0051] The first saddle bracket 124 includes a saddle 144 disposed opposite a mounting surface 146. The mounting surface 146 is the edge of the first saddle bracket 124 that connects to the fuselage 106. The saddle 144 has a contour 150. The contour 150 has a profile that matches the shape 130 of the first support collar 120. The saddle 144 includes a saddle flange 148. The saddle flange 148 is connected to the flange 140 of the first support collar 120 using shear bolts 166. A strut 152 extends from the first saddle bracket 124. In combination with the first support collar 120, the first saddle bracket 124 can support a radial load 162 of the cryogenic tank. In combination with the first support collar 120, the first saddle bracket 124 can support an axial load 164 of the cryogenic tank because of the presence of the strut 152.
[0038]
[0052] The second saddle bracket 126 includes a saddle 145 disposed opposite a mounting surface 147. The mounting surface 147 is the edge of the second saddle bracket 126 that connects to the fuselage 106. The saddle 145 has a contour 151. The contour 151 has a profile that matches the shape 131 of the second support collar 122. The saddle 145 includes a saddle flange 149. The saddle flange 149 is connected to the flange 141 of the second support collar 122 using shear bolts 166. The second saddle bracket 126 does not include a strut like that found in the first saddle bracket 124. As a result, the second saddle bracket 126, in combination with the second support collar 122, can support only the radial load 162 of the cryogenic tank while allowing for axial expansion / contraction of the cryogenic tank.
[0039]
[0053] Cryogenic tank 110 is a double-walled, insulated tank for cryogenically storing liquid hydrogen. Cryogenic tank 110 may be a set of cryogenic tanks. Cryogenic tank 110 includes an inner wall 156 separated from an outer wall 160 by a vacuum insulation layer 158. Cryogenic tank 110 is generally cylindrical and has a shape 154. Shape 154 matches shape 130 of first support collar 120, shape 131 of second support collar 122, contour 150 of saddle 144, and contour 151 of saddle 145.
[0040]
[0054] The tank support system 108 supports the cryogenic tank 110 and connects the cryogenic tank 110 to the fuselage 106 of the aircraft 102. The tank support system 108 structurally isolates the cryogenic tank 110 from the fuselage 106 of the aircraft 102. At one end of the cryogenic tank 110, the tank support system 108 supports a radial load 162 and an axial load 164 on the cryogenic tank 110, while at the other opposite end of the cryogenic tank 110, the tank support system 108 supports only the radial load 162 on the cryogenic tank 110 and allows for axial expansion / contraction of the cryogenic tank 110 relative to the aircraft 102. Because the tank support system 108 allows for axial expansion / contraction of the cryogenic tank relative to the fuselage, forces acting on the aircraft are isolated from the cryogenic tank, and forces acting on the cryogenic tank are isolated from the aircraft.
[0041]
[0055] The inner ring of the support collar is connected to the inner wall of the cryogenic tank. The inner ring is either welded to or directly co-bonded with the inner wall of the cryogenic tank, since mechanical fasteners would likely penetrate the inner wall if used. The outer ring of the support collar is connected to the outer wall of the cryogenic tank. As a result, rather than the tank support system 108 alone connecting the cryogenic tank 110 to the fuselage 106 of the aircraft 102, the first support collar 120 and the second support collar 122 support the inner wall 156 within the outer wall 160 of the cryogenic tank 110. In other words, the support collars keep the outer wall of the cryogenic tank spaced apart from the inner wall of the cryogenic tank. As a result, the vacuum insulation layer 158 between the inner wall 156 and the outer wall 160 remains intact, providing cryogenic insulation around the entire exterior surface of the inner wall 156.
[0042]
[0056] Referring now to Figure 2, a diagram of an aircraft having a cryogenic tank connected thereto using a tank support system is shown, according to an exemplary embodiment. In this and the following exemplary embodiments, the same reference numbers may be used in multiple figures. Such repeated reference numbers in different figures represent the same elements in such different figures. The components shown in Figure 2 are examples of physical implementations of the aircraft 102, fairing 104, fuselage 106, tank support system 108, and cryogenic tank 110 shown in block form in Figure 1.
[0043]
[0057] As shown, aircraft 200 includes a fuselage 202. Aircraft 200 has wings 204 and 206 connected to fuselage 202. Aircraft 200 includes engines 208 connected to wings 204. Another engine (not shown) is connected to wings 206. Fuselage 202 has a tail section 210. Horizontal stabilizer 212, horizontal stabilizer 214, and vertical stabilizer 216 are connected to tail section 210 of fuselage 202. Each tank of set of cryogenic tanks 220 is connected to crown region 222 of fuselage 202 using tank support system 224. Tank support system 224 structurally isolates set of cryogenic tanks 220 from fuselage 202 of aircraft 200. Fairing 226 is connected to fuselage 202. Fairing 226 encases tank support system 224 and set of cryogenic tanks 220 to improve aerodynamics.
[0044]
[0058] 3-4, diagrams of cryogenic tanks connected to tank support systems are shown, according to an illustrative embodiment. The components shown in Figures 3-4 are examples of physical implementations of tank support system 108 and cryogenic tank 110, shown in block form in Figure 1. Tank support system 302 connects cryogenic tank 304 and cryogenic tank 306 to aircraft 308. Tank support system 312 connects cryogenic tank 314 and cryogenic tank 316 to aircraft 308.
[0045]
[0059] The tank support system 302 includes a first support collar 322 and a first support collar 323. The first support collar 322 and the first support collar 323 are each connected to a first saddle bracket 324. A strut 318 is connected to the first saddle bracket 324 and to the aircraft 308. The tank support system 302 includes a second support collar 326 and a second support collar 327. The second support collar 326 and the second support collar 327 are each connected to a second saddle bracket 328.
[0046]
[0060] Tank support system 302 supports radial load 330 and axial load 332 of cryogenic tank 304 and cryogenic tank 306 at end 350 of tank support system 302. Tank support system 302 supports only radial load 330 of cryogenic tank 304 and cryogenic tank 306 at end 352 of tank support system 302, while allowing axial expansion / contraction 334 of cryogenic tank 304 and cryogenic tank 306 relative to aircraft 308 at end 352 of tank support system 302. Because tank support system 302 allows axial expansion / contraction of the cryogenic tanks relative to the fuselage, forces acting on the aircraft are decoupled from the cryogenic tanks, and forces acting on the cryogenic tanks are decoupled from the aircraft.
[0047]
[0061] Tank support system 312 has the exact same setup as tank support system 302, but in a mirror image orientation. As a result, further description of tank support system 312 will not be provided.
[0048]
[0062] Each of the cryogenic tanks 304, 306, 314, and 316 is a double-walled, vacuum-insulated cryogenic tank. Each tank is comprised of an outer wall spaced apart from an inner wall by a vacuum insulation layer. Each cryogenic tank is comprised of three sections; for example, cryogenic tank 304 includes an end dome 340 connected to a cylindrical body 342 connected to a nose dome 344. End dome 340 is connected to cylindrical body 342, for example, by a first support collar 322. Cylindrical body 342 is connected to nose dome 344, for example, by a second support collar 326.
[0049]
[0063] The inner ring of the support collar is connected to the inner wall of the cryogenic tank ( FIG. 11 ). The inner ring is either welded to or directly co-bonded to the inner wall of the cryogenic tank, as conventional mechanical fasteners would be prone to penetration of the inner wall. The outer ring of the support collar is connected to the outer wall of the cryogenic tank. As a result, rather than the tank support system alone connecting the cryogenic tank to the aircraft fuselage, in this embodiment, first support collar 322 and second support collar 326 support the inner wall of the cryogenic tank 304 within the outer wall of the cryogenic tank 304. In other words, the support collars keep the outer wall of the cryogenic tank spaced apart from the inner wall of the cryogenic tank. As a result, the vacuum insulation layer between the inner and outer walls remains intact, providing cryogenic insulation.
[0050]
[0064] FIG. 4 shows a view 400 from FIG. 3 . The shape 402 of the second support collar 326 and the second support collar 327 is generally circular. The shape 402 matches the shape 404 of the cryogenic tank 304 and the cryogenic tank 306. Generally, the cryogenic tank 304 and the cryogenic tank 306 are cylindrical. The second saddle bracket 328 includes saddles 410 and 411 disposed on opposite sides of a mounting surface 412. The mounting surface 412 is the edge of the second saddle bracket 328 that connects to or abuts the fuselage of the aircraft 308. The saddle 410 has a contour 414. The saddle 411 has a contour 415. The contours 414 and 415 each have a profile that matches the shape 402 of the second support collar 326 and the second support collar 327. The second saddle bracket 328 (and indeed all of the saddle brackets) may be connected to the aircraft fuselage along their respective mounting surfaces, or each saddle bracket may include mounting points 418. If mounting points 418 are utilized, the respective mounting surfaces may not include mounting hardware. Alternatively, each saddle bracket may be connected to the aircraft both along its respective mounting surface and at mounting points 418.
[0051]
[0065] 5 and 7, diagrams of a first support collar are shown according to an exemplary embodiment. The components shown in FIGS. 5 and 7 are examples of physical implementations of the first support collar 120 shown in block form in FIG. 1. FIG. 7 is a cross-sectional view of the first support collar 500 taken along line 7-7 in FIG. 5. The first support collar 500 includes an inner ring 502 connected to an outer ring 504 by a web 506. The web 506 extends between the inner ring 502 and the outer ring 504 around the entire circumference of the first support collar 500. The inner ring 502 has a width 508, while the outer ring 504 has a width 510. The width 508 is greater than the width 510. Thus, the inner ring 502 is wider than the outer ring 504 to allow access to the welding area (FIG. 11). Ribs 512 connect the inner and outer rings 502, 504 between the inner and outer rings 502, 504. The ribs 512 extend at an angle from the webs 506. The ribs 512 may be perpendicular to the webs 506. The ribs 512 may be a set of ribs evenly spaced around the circumference of the first support collar 500. Flanges 514 extend radially outward from the outer ring 504. Gussets 516 connect the outer ring 504 and the flanges 514. The gussets 516 may be a set of gussets evenly spaced around the circumference of the first support collar 500. Each rib 512 is linearly aligned with at least one gusset 516.
[0052]
[0066] Referring now to FIGS. 6 and 8, diagrams of a second support collar are shown according to an exemplary embodiment. The components shown in FIGS. 6 and 8 are examples of physical implementations of the second support collar 122 shown in block form in FIG. 1. FIG. 8 is a cross-sectional view of the second support collar 600 taken along line 8-8 in FIG. 6. The second support collar 600 includes an inner ring 602 connected to an outer ring 604 by a web 606. The web 606 extends between the inner ring 602 and the outer ring 604 around the entire circumference of the second support collar 600. The inner ring 602 has a width 608, while the outer ring 604 has a width 610. The width 608 is greater than the width 610. Thus, the inner ring 602 is wider than the outer ring 604 to allow access to the welding area (FIG. 11). A flange 612 extends radially outward from the outer ring 604.
[0053]
[0067] First support collar 500 is able to support both the radial load of the cryogenic tank and the axial load of the cryogenic tank because of the presence of ribs 512 and gussets 516. Second support collar 600 does not include the ribs or gussets found on first support collar 500. As a result, second support collar 600 is able to support only the radial load of the cryogenic tank while allowing for axial expansion / contraction of the cryogenic tank.
[0054]
[0068] 9-10, a saddle bracket is shown according to an exemplary embodiment. The components shown in Figures 9-10 are examples of physical implementations of first saddle bracket 124 and second saddle bracket 126, shown in block form in Figure 1.
[0055]
[0069] First saddle bracket 900 (shown in FIG. 9 ) includes saddle 902 and saddle 904 positioned on opposite sides of mounting surface 906. Mounting surface 906 is the edge of first saddle bracket 900 that abuts or connects to the aircraft fuselage. Saddle 902 has contour 910. Saddle 904 has contour 911. Contours 910 and 911 each have a profile that matches the shape of a respective support collar. As shown, contours 910 and 911 are arc shapes that match the exterior size and dimensions of a cylindrical cryogenic tank. Saddle 902 includes saddle flange 914. Saddle flange 914 is connected to a flange of the support collar using shear bolts. Saddle 904 includes saddle flange 916. Saddle flange 916 is connected to a flange of the support collar using shear bolts. A strut can be attached to first saddle bracket 900 at brace 918. The first saddle bracket 900 may include two or more braces 918 for connection to two or more struts. The first saddle bracket 900, in combination with the first support collar 500, can support the radial load of the cryogenic tank. The first saddle bracket 900 including struts, in combination with the first support collar 500, can support the axial load of the cryogenic tank, for example, because there is a strut or two or more struts connected to the first saddle bracket 900 at the braces 918.
[0056]
[0070] The second saddle bracket 1000 (shown in FIG. 10) includes a saddle 1002 and a saddle 1004 positioned on opposite sides of a mounting surface 1006. The mounting surface 1006 is the edge of the second saddle bracket 1000 that abuts or connects to the aircraft fuselage. The saddle 1002 has a contour 1010. The saddle 1004 has a contour 1011. The contours 1010 and 1011 each have a profile that matches the shape of a respective support collar. The saddle 1002 includes a saddle flange 1014. The saddle flange 1014 connects to a flange of the support collar. The second saddle bracket 1000 does not include a brace 918 for connecting to a strut as found on the first saddle bracket 900. As a result, the second saddle bracket 1000, in combination with the second support collar 600, can support only the radial load of the cryogenic tank while allowing for axial expansion / contraction of the cryogenic tank.
[0057]
[0071] Referring now to Figure 11, a cross-sectional view of a tank support system connected to a cryogenic tank is shown, according to an exemplary embodiment. Figure 11 illustrates the connection between the support collars and two sections of the cryogenic tank. As previously described, the support collars connect the end dome of the cryogenic tank to the cylinder of the cryogenic tank. An additional support collar connects the cylinder of the cryogenic tank to the nose dome of the cryogenic tank.
[0058]
[0072] In this illustrative example, a support collar 1102 connects a cryogenic tank cylinder 1104 to a cryogenic tank nose dome 1106. The inner walls 1110 of both the cylinder 1104 and the nose dome 1106 are connected to an inner ring 1120 of the support collar 1102 at weld spots 1130 and 1131. The outer walls 1112 of both the cylinder 1104 and the nose dome 1106 are connected to an outer ring 1122 of the support collar 1102 at weld spots 1134 and 1135. A web 1124 extends between the inner ring 1120 and the outer ring 1122. A flange 1126 extends radially outward from the outer ring 1122. A saddle flange 1142 of a saddle bracket 1140 is connected to the flange 1126 using shear bolts at axles 1148. In another alternative connection, tension bolts (not shown) may be used to attach the outer ring 1122 to the saddle bracket 1140. The axis of the tension bolt in this alternative arrangement may be perpendicular to the axis 1148.
[0059]
[0073] Referring now to Figure 12, a diagram of a strut of a cryogenic tank support system is shown, according to an illustrative embodiment. The components shown in Figure 12 are examples of physical implementations of strut 152 shown in block form in Figure 1. Strut 1200 is connected at end 1202 to the aircraft fuselage. Strut 1200 is connected at end 1204 to a saddle bracket, for example, first saddle bracket 900. First saddle bracket 900, including struts 1200, can support the axial load of the cryogenic tank.
[0060]
[0074] Referring now to Figure 13, a flow chart of a process 800 for installing a cryogenic tank on an aircraft is shown. The method illustrated in Figure 13 may be used in conjunction with the tank support system illustrated in Figures 1-12.
[0061]
[0075] The process begins by connecting the inner ring of the support collar to the inner wall of the cryogenic tank (operation 1302). The system continues by connecting the outer ring of the support collar to the outer wall of the cryogenic tank (operation 1304). In operation 1306, the process connects the support collar to the saddle bracket. In operation 1308, the process connects the saddle bracket to the aircraft fuselage. In operation 1310, the process connects the strut to the saddle bracket. In operation 1312, as a result of the connections, the process structurally isolates the cryogenic tank from the aircraft. The structure uses at least one support collar to support the cryogenic tank radial load and the cryogenic tank axial load, and at least one other support collar to support the cryogenic tank radial load while allowing for cryogenic tank axial expansion / contraction.
[0062]
[0076] In some alternative implementations of an exemplary embodiment, one or more functions noted in a block may not be required or may occur out of the order noted in the figures. For example, in some cases, two blocks shown in succession may be executed substantially concurrently, 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 a flowchart or block diagram.
[0063]
[0077] Illustrative embodiments of the present disclosure may be further described in conjunction with aircraft manufacturing and service method 1400 shown in Figure 14 and aircraft 1500 shown in Figure 15. Referring initially to Figure 14, a block diagram of an aircraft manufacturing and service method is shown in accordance with an illustrative embodiment. During pre-production, aircraft manufacturing and service method 1400 may include specification and design 1402 of aircraft 1500 in Figure 15 and material procurement 1404.
[0064]
[0078] During production, component and subassembly manufacturing 1406 and system integration 1408 of the aircraft 1500 of Figure 15 occurs. The aircraft 1500 of Figure 15 then undergoes certification and delivery 1410 before being placed into service 1412. While in customer service 1412, the aircraft 1500 of Figure 15 is scheduled for routine maintenance and service 1414, which may include modification, reconfiguration, refurbishment, and other maintenance, upkeep, or inspection.
[0065]
[0079] Apparatus of the present disclosure may be installed on an aircraft during component and subassembly manufacturing 1406. Additionally, apparatus of the present disclosure may also be retrofitted onto aircraft 1500 of FIG. 15 during routine maintenance and service 1414 as part of a modification, reconfiguration, or refurbishment of aircraft 1500 of FIG. 15 .
[0066]
[0080] Each process of aircraft manufacturing and service method 1400 may be performed or carried out by a system integrator, a third party, an entity, or some combination thereof. In these examples, the operator may be the 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.
[0067]
[0081] Referring now to Figure 15, a block diagram of an aircraft is shown in which an illustrative embodiment may be implemented. In this example, aircraft 1500 is manufactured via aircraft manufacturing and service method 1400 in Figure 14 and may include airframe 1502 having a number of systems 1504 and interior 1506. Example systems 1504 include one or more of propulsion system 1508, electrical system 1510, hydraulic system 1512, and environmental system 1514. Any number of other systems may be included. While an aerospace example is shown, various illustrative embodiments may be applied to other industries, such as the automotive industry.
[0068]
[0082] Apparatus and methods embodied herein may be utilized during at least one of the stages of aircraft manufacturing and service method 1400 in Figure 14. In one illustrative example, the components or subassemblies produced in component and subassembly manufacturing 1406 in Figure 14 are fabricated or manufactured in a similar manner as the components or subassemblies produced while aircraft 1500 is in service 1412 in Figure 14. In yet another example, one or more apparatus embodiments, method embodiments, or a combination thereof may be utilized during a production stage, such as component and subassembly manufacturing 1406 and system integration 1408 in Figure 14. One or more apparatus embodiments, method embodiments, or a combination thereof may be utilized while aircraft 1500 is in service 1412 in Figure 14, during maintenance and service 1414 (including inspection), or both. Utilization of some various illustrative embodiments may significantly increase the efficiency of assembly of aircraft 1500, reduce the cost of aircraft 1500, or both significantly increase the efficiency of assembly of aircraft 1500 and reduce the cost of aircraft 1500.
[0069]
[0083] The description of various exemplary embodiments has been presented for purposes of illustration and description and is not intended to be exhaustive or to limit the embodiments to the precise form disclosed. Many modifications and variations will be apparent to those skilled in the art. Furthermore, different exemplary embodiments may offer different features as compared to other preferred embodiments. The selected embodiment or embodiments have been chosen and described in order to best explain the principles and practical applications of the embodiments and to enable others skilled in the art to understand the disclosure of the various embodiments, including various modifications suitable for the particular use contemplated.
Claims
1. 1. A cryogenic tank support apparatus comprising: a first support collar (120) connected to the cryogenic tank (110), the first support collar (120) connected to a first saddle bracket (124); and a second support collar (122) connected to the cryogenic tank (110), the second support collar (122) connected to a second saddle bracket (126); the first support collar (120) supports a radial load (162) of the cryogenic tank (110) and supports an axial load (164) of the cryogenic tank, and the second support collar (122) supports only the radial load (162) of the cryogenic tank (110) and allows axial expansion and contraction of the cryogenic tank (110).
2. Each of the first support collar (120) and the second support collar (122) comprises: Inner circle (132), a web (134) connected to the inner ring (132); an outer ring (136) connected to said web (134); and The apparatus of claim 1 , further comprising a flange (140) extending radially outward from the outer ring (136).
3. 3. The apparatus of claim 2, wherein the inner ring (132) is connected to an inner wall (156) of the cryogenic tank (110) and the outer ring (136) is connected to an outer wall (160) of the cryogenic tank (110).
4. 3. The apparatus of claim 2, wherein the first support collar further comprises a rib connected to the inner ring and the outer ring between the inner ring and the outer ring, the rib extending from the web.
5. The apparatus of claim 2, wherein the inner ring (132) is wider than the outer ring (136).
6. The apparatus of claim 1 , wherein each of the first support collar (120) and the second support collar (122) is welded or bonded to the cryogenic tank (110).
7. Each of the first saddle bracket (124) and the second saddle bracket (126) comprises: a saddle (144) having a contour (150) that matches the shape (130) of each support collar (120) and the cryogenic tank (110); a saddle flange (148) extending from said saddle (144); and The apparatus of claim 1, further comprising a shear bolt (166) for connecting the saddle flange (148) to a flange (140) extending from the respective support collar (120).
8. 8. The apparatus of claim 7, wherein the first saddle bracket supports the radial load of the cryogenic tank, the first saddle bracket further comprising a strut that supports the axial load of the cryogenic tank, and the second saddle bracket supports only the radial load of the cryogenic tank and allows axial expansion and contraction of the cryogenic tank.
9. 8. The apparatus of claim 7, wherein the first saddle bracket and the second saddle bracket each further comprise a mounting surface disposed on an opposite side of the saddle, the mounting surface being for connection to a fuselage of the aircraft.
10. 2. The apparatus of claim 1, wherein each of the first saddle bracket and the second saddle bracket is connected to a frame of the aircraft within a crown region of the aircraft.
11. 2. The apparatus of claim 1, wherein each of the first saddle bracket and the second saddle bracket is connected to a frame of the aircraft within a side region of the aircraft.
12. The cryogenic tank comprises: an inner wall (156); and The apparatus of claim 1, further comprising an outer wall (160) surrounding the inner wall (156) and separated from the inner wall (156) by a vacuum insulation layer (158).
13. 1. A system for mounting a cryogenic tank on an aircraft, comprising: an inner ring (132) of a support collar (120) connected to the inner wall (156) of the cryogenic tank (110); an outer ring (136) of the support collar (120) connected to the outer wall (160) of the cryogenic tank (110); a saddle (144) of a saddle bracket (124) connected to the outer ring (136) of the support collar (120); and A system comprising: a mounting surface (146) of the saddle bracket (124) connected to a crown region (116) of a fuselage (106) of the aircraft (102).
14. The system of claim 13 , wherein the system provides structural isolation between the cryogenic tank and the fuselage of the aircraft.
15. The system of claim 13, wherein the inner ring (132) is wider than the outer ring (136).
16. a web (134) connected to the inner ring (132) and the outer ring (136); and The system of claim 13, further comprising a flange (140) extending radially outward from the outer ring (136) for connection to the saddle bracket (124).
17. The support collars include a first support collar (120) and a second support collar (122), each of the first support collar (120) and the second support collar (122) being connected to the cryogenic tank (110); The saddle brackets include a first saddle bracket (124) connected to the first support collar (120) and a second saddle bracket (126) connected to the second support collar (122); a strut (152) connecting to said first saddle bracket (124); 14. The system of claim 13, wherein the first support collar, the first saddle bracket, and the strut support a radial load on the cryogenic tank and an axial load on the cryogenic tank, and the second support collar and the second saddle bracket support only the radial load on the cryogenic tank and allow for axial expansion and contraction of the cryogenic tank.
18. 1. A method for installing a cryogenic tank on an aircraft, comprising: connecting (1302) an inner ring (132) of a support collar (120) to an inner wall (156) of the cryogenic tank (110); connecting (1304) the outer ring (136) of the support collar (120) to the outer wall (160) of the cryogenic tank (110); connecting (1306) said support collar (120) to a saddle bracket (124); and connecting (1308) the saddle bracket (124) to a fuselage (106) of the aircraft (102).
19. The method of claim 18, further comprising connecting (1310) a strut (152) to the saddle bracket (124).
20. 20. The method of claim 18, further comprising structurally isolating the cryogenic tank from the aircraft by using at least one support collar to support a radial load on the cryogenic tank and an axial load on the cryogenic tank, and using at least one other support collar to support the radial load on the cryogenic tank while allowing axial expansion and contraction of the cryogenic tank.