Ignition suppression device

Abstract

This application relates to an ignition suppression device. The ignition suppression device (100) for shielding fasteners (106) includes a strip (102) and recesses (104) spaced apart from each other along the strip (102).

Description

Technical Field

[0001] This disclosure relates to an ignition suppression device for shielding fasteners in an aircraft fuel tank. Background Technology

[0002] Traditionally, metal fasteners in composite aircraft fuel tanks are isolated from the fuel volume by sealant and / or sealing caps. The sealant and / or sealing caps physically and / or electrically separate the metal fasteners from the fuel volume and are configured to contain any ignition hazard. Installing the sealant and / or sealing caps requires labor-intensive steps such as solvent cleaning, brush application, multiple manual application steps, curing, and inspection. The associated installation and inspection times increase the cost of the aircraft. Furthermore, many fasteners are positioned close enough to other fasteners that the sealing caps must be custom-trimmed to fit the corresponding fasteners without physically interfering with adjacent fasteners or sealing caps. Custom trimming further increases lead-up time and thus costs. Summary of the Invention

[0003] Therefore, devices and methods designed to solve at least the aforementioned problems are effective.

[0004] The following is a non-exhaustive list of examples of the topics discussed in this article.

[0005] This article discloses an ignition suppression device for shielding fasteners. The ignition suppression device includes a strip and recesses spaced apart from each other along the strip.

[0006] To this end, the ignition suppression device is configured to be mounted on a fastener within the aircraft fuel tank, wherein the fastener extends into a corresponding recess to suppress ignition events, such as those caused by lightning strikes on the aircraft. Having multiple recesses spaced apart along a band allows for easy distribution of the recess supply during the manufacture of the aircraft fuel tank, significantly reducing the time involved compared to installing individual rigid caps within the aircraft fuel tank.

[0007] This document also discloses an aircraft fuel tank. The aircraft fuel tank includes an ignition suppression device, a wall, and fasteners extending from the wall inside the aircraft fuel tank. Each fastener is received by a corresponding recess of the ignition suppression device.

[0008] This document also discloses a method for installing an ignition suppression device in an aircraft fuel tank. The method includes positioning each of a fastener extending from the wall of the aircraft fuel tank within the fuel tank in a corresponding recess of the ignition suppression device. The method further includes coupling the ignition suppression device to the wall. Attached Figure Description

[0009] Referring now to the accompanying drawings, which are not necessarily drawn to scale, and in which the same reference numerals denote the same or similar parts in several views. In the accompanying drawings:

[0010] Figure 1 This is a block diagram of an ignition suppression device and an aircraft fuel tank, based on one or more examples of the subject matter disclosed herein;

[0011] Figure 2 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic reverse side view of an ignition suppression device;

[0012] Figure 3 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic side view of an ignition suppression device;

[0013] Figure 4 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic cross-sectional side view of an ignition suppression device;

[0014] Figure 5 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic cross-sectional side view of an ignition suppression device;

[0015] Figure 6 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic cross-sectional side view of the aircraft's fuel tank;

[0016] Figure 7 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic cross-sectional side view of the aircraft's fuel tank;

[0017] Figure 8 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic cross-sectional side view of the aircraft's fuel tank;

[0018] Figure 9 This refers to one or more examples based on the subject matter disclosed in this article. Figure 1 A schematic isometric view of an ignition suppression device;

[0019] Figure 10 It is a block diagram of a method for installing an ignition suppression device in an aircraft fuel tank according to one or more examples of the subject matter disclosed herein;

[0020] Figure 11 It is a block diagram of aircraft production and maintenance methods; and

[0021] Figure 12 This is a schematic diagram of an aircraft. Detailed Implementation

[0022] The above-mentioned Figure 1 In this document, solid lines (if any) connecting various elements and / or components may represent mechanical, electrical, fluid, optical, electromagnetic, and other connections and / or combinations thereof. As used herein, "connection" means direct and indirect association. For example, component A may be directly associated with component B, or indirectly associated with it, for example, via another component C. It should be understood that not all relationships between the disclosed elements are necessarily represented. Therefore, connections other than those depicted in the block diagrams may also exist. Dashed lines (if any) connecting various elements and / or components indicate connections similar in function and purpose to those represented by solid lines; however, connections represented by dashed lines may optionally provide or may relate to alternative examples of the subject matter disclosed herein. Similarly, elements and / or components (if any) represented by dashed lines indicate alternative examples of the subject matter disclosed herein. One or more elements shown in solid and / or dashed lines may be omitted from certain examples without departing from the scope of the subject matter disclosed herein. Environmental elements (if any) are represented by dashed lines. Virtual (imaginary) elements may also be shown for clarity. Those skilled in the art will understand that... Figure 1 Some of the features shown can be combined in various ways without needing to be included. Figure 1 Other features described in the accompanying drawings and / or disclosures, even if such combinations are not explicitly shown herein. Similarly, additional features, not limited to the examples presented, may be combined with some or all of the features shown and described herein.

[0023] exist Figure 10 In this text, as mentioned above, boxes may represent operations and / or parts thereof, and the lines connecting the various boxes do not imply any particular order or dependency of the operations or their parts. Boxes represented by dashed lines indicate alternative operations and / or parts thereof. Dashed lines connecting the various boxes (if any) indicate alternative dependencies of operations or their parts. It will be understood that not all dependencies among the various disclosed operations must be represented. Figure 10 The appended disclosures describing the operations of the methods expounded herein should not be construed as requiring a predetermined order of operations. Rather, while an illustrative order is indicated, it should be understood that the order of operations can be modified as appropriate. Therefore, some operations may be performed in a different order or simultaneously. Furthermore, those skilled in the art will understand that not all of the described operations need to be performed.

[0024] In the following description, numerous specific details are set forth to provide a thorough understanding of the disclosed concepts, which can be practiced without some or all of these details. In other instances, details of known apparatuses and / or processes have been omitted to avoid unnecessarily obscuring this disclosure. While some concepts will be described in conjunction with specific examples, it should be understood that these examples are not intended to be limiting.

[0025] Unless otherwise stated, the terms “first,” “second,” etc., are used merely as labels in this document and are not intended to impose any order, position, or hierarchy requirements on the items referred to by these terms. Furthermore, references to items such as “second” do not require or exclude the existence of items such as “first” or lower-numbered items and / or items such as “third” or higher-numbered items.

[0026] The reference to "one or more examples" in this document means that one or more features, structures, or characteristics described in connection with that example are included in at least one implementation. The phrase "one or more examples" appearing throughout the specification may or may not refer to the same example.

[0027] As used herein, a system, apparatus, structure, article, element, component, or hardware "configured to" perform a specified function is actually capable of performing the specified function without any changes, rather than merely having the potential to perform the specified function after further modification. In other words, a system, apparatus, structure, article, element, component, or hardware "configured to" perform a specified function is specifically selected, created, implemented, utilized, programmed, and / or designed for the purpose of performing the specified function. As used herein, "configured to" indicates existing characteristics of the system, apparatus, structure, article, element, component, or hardware that enable the system, apparatus, structure, article, element, component, or hardware to perform the specified function without further modification. For the purposes of this disclosure, a system, apparatus, structure, article, element, component, or hardware described as "configured to" perform a particular function may additionally or alternatively be described as "suitable" and / or "operably" to perform that function.

[0028] The following provides illustrative, non-exhaustive examples of the topics disclosed in this article.

[0029] General reference Figure 1 And specifically refer to, for example Figures 2 to 9 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 1 of the subject matter disclosed herein. According to Example 1, an ignition suppression device 100 for shielding fastener 106 includes a strip 102 and recesses 104 spaced apart from each other along the strip 102.

[0030] Therefore, the ignition suppression device 100 is configured to be mounted on a fastener 106 within the aircraft fuel tank 108, wherein the fastener 106 extends into a corresponding recess 104 to suppress ignition events, such as those caused by lightning strikes on the aircraft. Having a plurality of recesses 104 spaced apart along the band 102 allows for easy distribution of the recesses 104 during the manufacture of the aircraft fuel tank 108, thereby significantly reducing the time involved compared to installing individual rigid caps within the aircraft fuel tank.

[0031] In one or more examples, the ignition suppression device 100 is configured to have a specific spacing of sockets 104 corresponding to a specific spacing of fasteners 106 within the aircraft fuel tank 108. Therefore, in such examples, the ignition suppression device 100 can be distributed and installed without requiring alterations, further reducing the time involved compared to installing a separate rigid cover.

[0032] In one or more examples, the strip 102 and / or the ignition suppression device 100 are described as a strip.

[0033] In one or more examples, such as Figure 9 As shown, the ignition suppression device 100 can be wound up for easy storage and subsequently dispensed during installation in the aircraft fuel tank 108.

[0034] In one or more examples, the recess 104 and the band 102 are made of any material used to perform their functions as discussed herein, including materials compatible with aircraft fuel.

[0035] General reference Figure 1 And specifically refer to Figures 2 to 9 For example, for illustrative purposes and not for limiting purposes, the following section of this paragraph describes Example 2 of the subject matter disclosed herein. According to Example 2, which includes Example 1 above, the band 102 and the recess 104 are constructed as an integral structure of the material.

[0036] The ignition suppression device 100 can be easily manufactured by using the same material as the overall structure.

[0037] As used herein, “integral structure” simply means that the band 102 and the recess 104 are essentially one piece and are not constructed separately and subsequently joined together. For example, “integral structure” does not exclude materials having multiple layers or fibers woven together.

[0038] General reference Figure 1The following section of this paragraph describes Example 3 of the subject matter disclosed herein. According to Example 3, which includes Example 1 or 2 above, the recess 104 is permeable to gas, permeable to gas and permeable to aircraft fuel, or permeable to gas but impermeable to aircraft fuel.

[0039] Following an electrical event, a permeable gas causes combustion gases within the recess 104 to leak into the fuel tank. The recess 104 also allows combustion gases to leak from the recess into the fuel tank. With both permeable gas and permeable aircraft fuel, the recess will suppress any combustion of fuel vapors or liquid fuel even if they are present in the recess during an electrical event. With impermeable aircraft fuel, the recess 104 not only contains jets of hot particles and / or gases that may be generated by lightning strikes or other electrical events, but also retains aircraft fuel that, under certain conditions, will evaporate and flammably flow out of the recess 104.

[0040] In one or more examples, materials that are permeable to gases but impermeable to liquids include woven and nonwoven polymer fabrics, including stretched polytetrafluoroethylene (PTFE), such as in Gore-TEX. TM Sold under the brand.

[0041] In one or more examples, the recess 104 and / or the band 102 are composed of multiple layers of material. In one or more such examples, a wadding such as nylon felt may be positioned between two outer layers of material such as PTFE fabric.

[0042] General reference Figure 1 And specifically refer to, for example Figure 2 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 4 of the subject matter disclosed herein. According to Example 4, which includes any one of Examples 1 to 3 above, the ignition suppression device 100 further includes a front side 101, a back side 103, and a side 118 located between the front side 101 and the back side 103. The ignition suppression device 100 further includes an adhesive region 110.

[0043] The bonding area 110 connects the ignition suppression device 100 to the aircraft fuel tank 108.

[0044] In one or more examples, at least a subset of the adhesive region 110 is positioned to adhere the ignition suppression device 100 to the wall 114 of the aircraft fuel tank 108. In one or more additional examples, as discussed herein, at least another subset of the adhesive region 110 is positioned to adhere the ignition suppression device 100 to a fastener 106 extending from the wall 114 of the aircraft fuel tank 108.

[0045] In one or more examples, the adhesive region 110 includes any suitable adhesive that is compatible with the materials of the ignition suppression device 100, the walls 114 of the aircraft fuel tank 108 and / or the fasteners 106, and the aircraft fuel.

[0046] General reference Figure 1 And specifically refer to, for example Figure 2 For illustrative purposes only and not by way of limitation, the following portion of this paragraph depicts Example 5 of the subject matter disclosed herein. According to Example 5, which includes Example 4 above, the adhesive region 110 includes an adhesive edge region 120 located on the back surface 103 and extending along and adjacent to the side surface 118.

[0047] The adhesive edge region 120 connects the ignition suppression device 100 to the wall 114 of the aircraft fuel tank 108 and seals the recess 104 relative to the fuel in the aircraft fuel tank 108.

[0048] General reference Figure 1 And specifically refer to, for example Figure 2 and Figures 6 to 8 For illustrative purposes only and not by way of limitation, the following portion of this paragraph depicts Example 6 of the subject matter disclosed herein. According to Example 6, which includes Example 5 above, the adhesive region 110 also includes an adhesive lateral region 122 located on the back surface 103, which extends laterally between the sides 118 to the adhesive edge region 120 and is spaced apart from each other between the recesses 104 along the ignition suppression device 100.

[0049] The adhesive lateral region 122 and the adhesive edge region 120 form a closed space around each recess 104. Therefore, in the event of an electrical event associated with a recess, adjacent recesses will not necessarily be impacted. That is, hot particles and / or combustion gases will not travel from one recess to another.

[0050] General reference Figure 1 And specifically refer to, for example Figure 2 and Figures 6 to 8 For illustrative purposes only and not by way of limitation, the following section of this paragraph depicts Example 7 of the subject matter disclosed herein. According to Example 7, which includes Example 6 above, the adhesive region 110 also includes adhesive center regions 130 located on the back surface 103 and spaced apart from each other along the tape 102. Each of the adhesive center regions 130 is positioned between adhesive edge regions 120.

[0051] The bonding center area 130 helps to properly position the ignition suppression device 100 on the wall 114 of the aircraft fuel tank 108 during installation.

[0052] In addition, such as Figure 7 and Figure 8 As shown, in one or more examples, the adhesive center region 130 helps to join adjacent regions of the back surface 103 together to reduce the spacing between adjacent recesses 104 so as to properly align with adjacent fasteners of similar spacing in the fasteners 106.

[0053] General reference Figure 1 The following section of this paragraph describes Example 8 of the subject matter disclosed herein. According to Example 8, which includes Example 7 above, the adhesive center region 130 has a faster curing rate than the adhesive edge region 120 and the adhesive transverse region 122.

[0054] Because the bonding center region 130 cures faster than the bonding edge region 120 and the bonding transverse region 122, the ignition suppression device 100 can be easily and properly positioned on the wall 114 during installation, so that after the initial placement of the ignition suppression device 100, a long-term, stronger and / or more chemically resistant bond can be subsequently established with the bonding edge region 120 and the bonding transverse region 122.

[0055] General reference Figure 1 And specifically refer to, for example Figure 2 and Figures 6 to 8 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 9 of the subject matter disclosed herein. According to Example 9, which includes any of Examples 5 through 8 above, the adhesive region 110 further includes adhesive fastener regions 124 located on the back surface 103 and spaced apart from each other along the ignition suppression device 100. Each of the adhesive fastener regions 124 is positioned within a corresponding recess 104.

[0056] Therefore, the adhesive fastener area 124 is positioned to ensure that the recess 104 remains in place during and after the installation of the ignition suppression device 100, once operably positioned on the fastener 106.

[0057] General reference Figure 1 And specifically refer to, for example Figure 2 and Figures 6 to 8 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 10 of the subject matter disclosed herein. According to Example 10, which includes Example 9 above, each adhesive fastener region 124 includes a first adhesive portion 126 and a second adhesive portion 128. The first adhesive portion 126 has a faster curing rate than the second adhesive portion 128.

[0058] The faster curing portion allows the recess 104 to be operatively positioned and held on the fastener 106 during installation of the ignition suppression device 100, while the slower curing portion allows for a long-term bond between the recess 104 and the fastener 106 after the initial positioning of the recess 104 on the fastener 106.

[0059] Examples of slower-curing adhesives used as the second adhesive portion 128 for bonding the edge region 120, the lateral region 122, and the fastener region 124 include polysulfide sealants such as polyurethane, polysulfide, manganese dioxide-cured polysulfides, dichromate-cured polysulfides, epoxy-cured polysulfides, and combinations thereof. Examples of faster-curing adhesives used as the first adhesive portion 126 for bonding the center region 130 and the fastener region 124 include structural acrylics, epoxy resins, and the like.

[0060] General reference Figure 1 And specifically refer to, for example Figure 6 For illustrative purposes only and not in a limiting manner, the following section of this paragraph depicts Example 11 of the subject matter disclosed herein. According to Example 11, which includes Example 10 above, the first adhesive portion 126 and the second adhesive portion 128 are adjacent to each other.

[0061] The manufacture of the ignition suppression device 100 is facilitated by the first adhesive portion 126 and the second adhesive portion 128 of the adhesive fastener region 124 being adjacent to each other on the back surface 103 of the ignition suppression device 100, for example by using two adjacent nozzles of adhesive to dispense the respective adhesive onto the back surface 103 of the ignition suppression device 100.

[0062] Figure 6 The adhesive fastener area shown on the right is an example of the first adhesive portion 126 and the second adhesive portion 128 being adjacent to each other.

[0063] General reference Figure 1 And specifically refer to, for example Figure 2 and Figures 6 to 8 For illustrative purposes only and not in a limiting manner, the following section of this paragraph depicts Example 12 of the subject matter disclosed herein. According to Example 12, which includes Example 10 or 11 above, the first adhesive portion 126 and the second adhesive portion 128 are concentric with each other.

[0064] The manufacture of the ignition suppression device 100 is facilitated by the first adhesive portion 126 and the second adhesive portion 128 of the adhesive fastener region 124 being concentric with each other on the back surface 103 of the ignition suppression device 100, for example by utilizing a nozzle having a concentric outlet for dispensing the corresponding adhesive onto the back surface 103 of the ignition suppression device 100.

[0065] Figure 6 The adhesive fastener area shown on the left and Figure 7 and Figure 8 The adhesive fastener region 124 is an example of the first adhesive portion 126 and the second adhesive portion 128 being concentric with each other.

[0066] General reference Figure 1 And specifically refer to, for example Figure 2 , Figure 8 and Figure 9 For illustrative purposes only and not by way of limitation, the following portion of this paragraph describes Example 13 of the subject matter disclosed herein. According to Example 13, which includes any one of Examples 5 to 12 above, the adhesive region 110 also includes adhesive holding regions 131 located on the front side 101 and spaced apart from each other in recesses 104 along the ignition suppression device 100.

[0067] like Figure 8 As shown, the ignition suppression device 100 includes an adhesive holding region 131 on its front surface 101, allowing multiple regions of the belt 102 to be placed together and folded onto adjacent regions of the belt 102. Therefore, the spacing between two adjacent recesses 104 is reduced to correspond to the spacing between two adjacent fasteners 106, and the flaps created by placing the multiple regions of the belt 102 together are secured to adjacent regions of the belt 102 via the adhesive holding region, thereby preventing the flaps from extending into the fuel volume within the aircraft fuel tank 108, for example, as... Figure 7 As shown.

[0068] General reference Figure 1 And specifically refer to, for example Figure 9 For illustrative purposes only and not by way of limitation, the following portion of this paragraph describes Example 14 of the subject matter disclosed herein. According to Example 14, which includes any one of Examples 4 to 13 above, the ignition suppression device 100 also includes a back release tab 132 releasably coupled to the back surface 103 of the ignition suppression device 100.

[0069] The back release sheet 132 restricts premature curing of the adhesive area 110 on the back side 103 and allows for handling and storage of the ignition suppression device 100.

[0070] In one or more examples, the back-side release sheet 132 is an aluminum strip. In one or more examples, the back-side release sheet 132 is a polymer film.

[0071] General reference Figure 1 And specifically refer to, for example Figure 9For illustrative purposes only and not by way of limitation, the following portion of this paragraph describes Example 15 of the subject matter disclosed herein. According to Example 15, which includes any of Examples 4 to 14 above, the ignition suppression device 100 also includes a front release tab 133 releasably coupled to the front side 101 of the ignition suppression device 100.

[0072] The front release sheet 133 restricts premature curing of the adhesive area 110 on the front side 101 and allows for handling and storage of the ignition suppression device 100.

[0073] In one or more examples, the front release sheet 133 is an aluminum strip. In one or more examples, the front release sheet 133 is a polymer film.

[0074] General reference Figure 1 And specifically refer to, for example Figure 9 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 16 of the subject matter disclosed herein. According to Example 16, which includes Example 15 above, the front release tab 133 includes an opening 135 extending around the recess 104.

[0075] In one or more examples, the opening 135 allows the front release tab 133 to accommodate the recess 104 extending away from the band 102.

[0076] In one or more examples, the front release tab 133 alternatively includes a plurality of spaced portions that are individually releasably coupled to the band 102 on the front side 101 of the ignition suppression device 100.

[0077] General reference Figure 1 And specifically refer to, for example Figure 4 and Figure 5 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 17 of the subject matter disclosed herein. According to Example 17, which includes any one of Examples 4 to 16 above, each of the recesses 104 includes a back surface 154 located on the back surface 103 of the ignition suppression device 100. Each of the recesses 104 is configured to extend away from the band 102 in response to a predetermined pressure applied to the entire back surface 154 of said recess and / or in response to a predetermined force applied to a portion of the back surface 154 of said recess.

[0078] Therefore, during a lightning strike or other electrical event, where hot gas forms within the recess or hot particles are ejected from or near the fastener, the recess will expand due to the increased pressure within it. Consequently, the forces associated with the electrical event will be suppressed, and the integrity of the recess will be maintained, enabling it to operate operably during subsequent electrical events.

[0079] Additionally, in one or more examples, such as Figure 9 As shown, the ignition suppression device 100 can be easily wound, wherein the recess 104 is generally flattened into a collapsed configuration and selectively unfolded into an unfolded configuration when positioned on the fastener 106 during installation. That is, the fastener 106 will engage a portion of the back surface 154 and force the corresponding recess to extend away from the adjacent portion of the band 102 to form a volume within the corresponding recess into which the fastener extends.

[0080] General reference Figure 1 And specifically refer to, for example Figure 2 , Figure 3 and Figures 6 to 8 For illustrative purposes and not by way of limitation, the following portion of this paragraph describes Example 18 of the subject matter disclosed herein. According to Example 18, which includes Example 17 above, each of the recesses 104 includes at least one circular corrugation 146 that is capable of extending away from the band 102 in response to an increase in pressure within the recess 104.

[0081] When an electrical event occurs, the circular corrugations allow for a greater increase in volume within the recess 104. The circular corrugations also allow the recess 104 to accommodate various sizes and / or shapes of the fastener 106.

[0082] In one or more examples, circular ripples are described or formed as follows.

[0083] General reference Figure 1 And specifically refer to, for example Figure 2 and Figure 9 For illustrative purposes only and not by way of limitation, the following portion of this paragraph describes Example 19 of the subject matter disclosed herein. According to Example 19, which includes any one of Examples 1 to 18 above, the band 102 includes at least one weakened region 134 that extends laterally across the band 102 between adjacent recesses in the recess 104.

[0084] In the case where there is at least one weakening region 134 between adjacent recesses in recess 104, individual recesses or subsets in recess 104 may be separated from the rest of the ignition suppression device 100 during its installation, for example after installation on the fasteners 106 of the linear row and / or when the spacing between recesses 104 is not aligned with the spacing of the fasteners 106 on which the recesses 104 are positioned.

[0085] In one or more examples, multiple weakened regions extend laterally across band 102 between adjacent dimples in dimple 104.

[0086] By including multiple weakening regions (such as at least one weakening region 134) between adjacent recesses in recess 104, different lengths of the strip 102 can be selectively removed during installation of the ignition suppression device 100 to correspond to various intervals of the fastener 106.

[0087] In one or more examples, in addition to or instead of multiple weakened regions, markings representing cutting lines are provided to facilitate technicians in separating adjacent regions of the ignition suppression device 100 along the weakened regions or cutting the ignition suppression device 100 along the cutting lines.

[0088] General reference Figure 1 And specifically refer to, for example Figure 2 and Figure 9 For illustrative purposes only and not in a limiting manner, the following portion of this paragraph depicts Example 20 of the subject matter disclosed herein. According to Example 20, which includes Example 19 above, at least one weakened region 134 includes a perforation 148.

[0089] The perforation 148 facilitates the separation of adjacent portions of the ignition suppression device 100 without the need for tools such as scissors or other cutters.

[0090] General reference Figure 1 The following section of this paragraph describes Example 21 of the subject matter disclosed herein. According to Example 21, which includes Examples 19 or 20 above, at least one weakened region 134 includes one or more serration lines 150.

[0091] The scoring lines facilitate the separation of adjacent portions of the ignition suppression device 100 without the need for tools such as scissors or other cutters.

[0092] General reference Figure 1 And specifically refer to, for example Figure 4 and Figure 5 For illustrative purposes only and not by way of limitation, the following portion of this paragraph describes example 22 of the subject matter disclosed herein. According to example 22, which includes any one of examples 1 to 21 above, each of the recesses 104 includes a substrate portion 152 and a concentric ring 136 connected to the substrate portion 152.

[0093] The concentric ring 136 provides a structure that holds the recess 104 in a generally circular configuration around the fastener 106 when the ignition suppression device 100 is installed. Furthermore, in one or more examples, the concentric ring 136 facilitates the collapse of the recess 104 into a collapsed configuration, such as... Figure 4 and Figure 9 As shown, and selectively expanded to expanded structures, such as Figure 5 As shown.

[0094] General reference Figure 1 And specifically refer to, for example Figure 4 and Figure 5 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes example 23 of the subject matter disclosed herein. According to example 23, which incorporates example 22 above, the concentric ring 136 is more rigid than the substrate portion 152.

[0095] By being more rigid than the substrate portion 152, the concentric ring 136 provides a structure that holds the recess 104 in a generally circular configuration around the fastener 106 when the ignition suppression device 100 is mounted.

[0096] General reference Figure 1 And specifically refer to, for example Figure 4 and Figure 5 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 24 of the subject matter disclosed herein. According to Example 24, which includes Examples 22 or 23 above, one of the concentric rings 136 is different in diameter from at least one other concentric ring in the concentric rings 136.

[0097] By having different diameters, the concentric rings 136 not only facilitate the collapse and expansion of the recesses 104, but also allow the recesses to gradually taper toward the end of the fastener 106.

[0098] General reference Figure 1 And specifically refer to, for example, for illustrative purposes and not for limitation, Figures 6 to 8 The following section of this paragraph describes Example 25 of the subject matter disclosed herein. According to Example 25, which includes any one of Examples 1 to 24 above, the aircraft fuel tank 108 includes an ignition suppression device 100, a wall 114, and fasteners 106 extending from the wall 114 within the aircraft fuel tank 108. Each of the fasteners 106 is received by a corresponding recess 104 of the ignition suppression device 100.

[0099] General reference Figure 10 And specifically refer to, for example Figures 1 to 9 For illustrative purposes only and not by way of limitation, the following section of this paragraph describes Example 26 of the subject matter disclosed herein. According to Example 26, which includes Example 25 above, a method 200 for installing an ignition suppression device 100 in an aircraft fuel tank 108 includes (box 202) positioning each of fasteners 106 extending from a wall 114 within the aircraft fuel tank 108 into a corresponding socket 104 of the ignition suppression device 100. Method 200 also includes (box 204) coupling the ignition suppression device 100 to the wall 114.

[0100] Examples of the topics disclosed in this article can be found in, for example... Figure 11 The aircraft manufacturing and maintenance methods 1100 and as shown are... Figure 12 The description is made in the context of the aircraft 1102 shown. During pre-production, illustrative method 1100 may include the specification and design of aircraft 1102 (box 1104) and material procurement (box 1106). During production, the manufacturing of components and sub-assemblies of aircraft 1102 (box 1108) and system integration (box 1110) may occur. Subsequently, aircraft 1102 may undergo certification and delivery (box 1112) to enter service (box 1114). In service, aircraft 1102 may be scheduled for routine maintenance and repair (box 1116). Routine maintenance and repair may include modification, reconfiguration, refurbishment, etc., of one or more systems of aircraft 1102.

[0101] Each process of illustrative method 1100 may be performed or executed by a systems integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this specification, a systems integrator may include, but is not limited to, any number of aircraft manufacturers and main system subcontractors; a third party may include, but is not limited to, any number of suppliers, subcontractors, and vendors; and an operator may be an airline, leasing company, military entity, service organization, etc.

[0102] like Figure 12 As shown, an aircraft 1102 produced by illustrative method 1100 may include a fuselage 1118 having multiple advanced systems 1120 and an interior 1122. Examples of advanced systems 1120 include one or more of a propulsion system 1124, an electrical system 1126, a hydraulic system 1128, and an environmental system 1130. Any number of other systems may be included. Although an aerospace example is shown, the principles disclosed herein can be applied to other industries, such as the automotive industry. Therefore, in addition to aircraft 1102, the principles disclosed herein can also be applied to other vehicles, such as land vehicles, sea vehicles, space vehicles, etc.

[0103] The apparatuses and methods shown or described herein may be employed during any one or more stages of manufacturing and maintenance method 1100. For example, a component or sub-assembly corresponding to the manufacture of parts and sub-assemblies (box 1108) may be manufactured or produced in a manner similar to that of a component or sub-assembly produced while aircraft 1102 is in service (box 1114). Furthermore, one or more examples of apparatuses, methods, or combinations thereof may be utilized during production stages 1108 and 1110, for example, by significantly accelerating the assembly of aircraft 1102 or reducing the cost of aircraft 1102. Similarly, one or more examples of apparatuses or methods, or combinations thereof, may be utilized, for example, but not limited to, during service of aircraft 1102 (box 1114) and / or during maintenance and repair (box 1116).

[0104] The various examples of apparatuses and methods disclosed herein include a wide range of components, features, and functions. It should be understood that the various examples of apparatuses and methods disclosed herein may include any component, feature, and function of any other example of apparatuses and methods disclosed herein in any combination.

[0105] With the help of the teachings presented in the foregoing description and the associated figures, those skilled in the art will conceive of many modifications to the examples set forth herein.

[0106] Therefore, it should be understood that the subject matter disclosed herein is not limited to the specific examples shown, and modifications and other examples are intended to be included within the scope of the appended claims. Furthermore, although the foregoing description and associated drawings illustrate examples of the subject matter disclosed herein in the context of certain illustrative combinations of elements and / or functions, it should be understood that different combinations of elements and / or functions may be provided by alternative embodiments without departing from the scope of the appended claims. Therefore, the reference numerals in parentheses in the appended claims are for illustrative purposes only and are not intended to limit the scope of the claimed subject matter to the specific examples provided herein.

Claims

1. An ignition suppression device (100) for shielding a fastener (106) within an aircraft fuel tank (108), the aircraft fuel tank (108) having a wall (114), the ignition suppression device (100) being configured to be mounted on the fastener (106) within the aircraft fuel tank (108) and connected to the wall (114), the ignition suppression device (100) comprising: (102); as well as Multiple recesses (104) are spaced apart from each other along the band (102). The fastener (106) extends from the wall (114) into a corresponding recess (104) of the plurality of recesses on the inner side of the aircraft fuel tank (108) to suppress ignition events. The ignition suppression device (100) also includes a front (101), a back (103), and a side (118) between the front (101) and the back (103), as well as an adhesive area (110). The adhesive area (110) includes an adhesive edge area (120) located on the back surface (103) and extending along and adjacent to the side surface (118). The adhesive area (110) further includes an adhesive transverse area (122) located on the back side (103), which extends transversely to the adhesive edge area (120) between the sides (118) and is spaced apart from each other between the recesses (104) along the ignition suppression device (100).

2. The ignition suppression device (100) according to claim 1, wherein: The recess (104) is permeable to gas; or The recess (104) is permeable to gas and permeable to aircraft fuel; or The recess (104) is permeable to gas but impermeable to aircraft fuel.

3. The ignition suppression device (100) according to claim 1, wherein: The adhesive area (110) further includes adhesive center areas (130) located on the back side (103) and spaced apart from each other along the strip (102); and Each of the adhesive center regions (130) is positioned between the adhesive edge regions (120).

4. The ignition suppression device (100) according to claim 3, wherein The bonding center region (130) has a faster curing rate than the bonding edge region (120) and the bonding transverse region (122).

5. The ignition suppression device (100) according to claim 1, wherein: The adhesive area (110) further includes adhesive fastener areas (124) located on the back side (103) and spaced apart from each other along the ignition suppression device (100); and Each of the adhesive fastener regions (124) is positioned within a corresponding recess (104).

6. The ignition suppression device (100) according to claim 5, wherein: Each of the adhesive fastener regions (124) includes a first adhesive portion (126) and a second adhesive portion (128); and The first adhesive portion (126) has a faster curing rate than the second adhesive portion (128).

7. The ignition suppression device (100) according to claim 6, wherein The first adhesive portion (126) and the second adhesive portion (128) are adjacent to each other.

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