APPLIANCE TO LIMIT THE FLOW OF ELECTRIC CURRENT

专利摘要:
composite tubes for a fluid transport system. The present invention relates to a method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. in an illustrative embodiment, an apparatus comprises a transport member. the transport member is configured for use in the fluid transport system. the transport member is composed of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.
公开号:BR102013013977B1
申请号:R102013013977-7
申请日:2013-06-06
公开日:2021-06-29
发明作者:David William Minteer；James Patrick Irwin；Benjamin A. Johnson；John Thomas Axtell
申请人:The Boeing Company；
IPC主号:

专利说明:

Background Information
[0001] This application references, and claims priority benefit, the following US provisional patent applications: Provisional Patent Application Serial Number 61/657,248, filing date June 8, 2012, entitled "Conductive Coupling Assembly"; Provisional Patent Application Serial Number 61/669,299, filing date July 9, 2012, entitled "Composite Tubes for a Fluid Transport System"; and Provisional Patent Application Serial Number 61/712,930, filed October 12, 2012, entitled "Fluid Transport System for Preventing Electrical Discharge; as well as the following US Utility Patent Applications: "Conductive Coupling Assembly" , filed January 23, 2013, serial number 13/747732, attorney docket number 11-1056-US-NP; "Fluid Transport System for Preventing Electrical Discharge", filed January 23, 2013, serial number 13/747780, attorney docket number 12-0739-US-NP; and "Composite Tubes for a Fluid Transport System" filing date January 23, 2013, serial number 13/747761, attorney docket number 12 -0368-US-NP. 1. Field
[0002] The present description refers, in general, to a fluid transport system and, in particular, to a fluid transport system configured to have a desired electrical configuration. Even more particularly, the present description relates to a method and apparatus for limiting the flow of electrical current, induced by an event, such as lightning or electrical failure, along a fluid transport system and allowing for static dissipation. along the fluid transport system. 2. Background
[0003] Typically, a fluid transport system includes tubes connected together to move fluids through the tubes. Depending on the use in question, a "fluid" can comprise any number of liquids and/or gases. Fluid transport systems can be used to transport any number of fluids in vehicles such as, for example, an aircraft. A fluid transport system can include groups of tubes connected in series, in parallel, or in a combination of the two. In some cases, these tubes can be coupled together using, for example, but not limited to, coupling assemblies.
[0004] A fuel system is an example of a type of fluid transport system in an aircraft. Some currently available fuel systems comprise fuel tanks composed of metal and/or composite materials such as carbon fiber reinforced plastic (CFRP). When used in fuel tanks, fuel tubes composed of plastic and/or metallic materials can be prone to electrostatic charge buildup. Electrostatic charge buildup in a fuel pipe can be caused by a number of different factors including, but not limited to, the flow of fuel through and/or around the fuel pipe.
[0005] When an electrostatic charge accumulates on a surface of a fuel pipe, the fuel pipe may be prone to electrical discharge of this electrostatic charge. This electrical discharge can be referred to as "static discharge". Discharge static can take the form, for example, of an electrical arc coming from the fuel pipe to a nearby structure.
[0006] Furthermore, when used in a fuel tank composed of electrically resistant materials, such as, for example, carbon-reinforced plastic, fuel pipes composed of plastic and/or metallic materials can also be prone to induced voltages and currents by an electromagnetic event, such as lightning. In some situations, induced voltages can lead to electrical discharges in the form of sparking and/or electrical sparking from the tubes to one or more nearby structures. Additionally, in some situations, induced currents can lead to electrical discharges within connections between the tubes.
[0007] The voltage and currents induced by lightning can typically be small and be within selected tolerances in fuel tanks of an aircraft equipped with wings composed of metallic materials, such as, for example, aluminum. However, the voltages and currents induced by lightning within the fuel tanks of an aircraft with wings made of non-metallic materials, such as carbon fiber reinforced plastic, may be higher and outside selected tolerances. In particular, the higher electrical resistance of carbon fiber reinforced plastic compared to aluminum can cause higher voltages and currents to be induced relative to the pipes inside the fuel tanks.
[0008] Typically, with currently available aircraft, fuel transport systems use metal piping to transport fuel inside fuel tanks. In an aircraft composed of carbon fiber reinforced plastic, the metal tubing can be prone to induced voltages that can cause unwanted electrical discharges. Some methods currently available to reduce the level or intensity of an unwanted electrical discharge may include inserting high-resistance electrical insulators into metal piping. These insulators can be used to restrict the currents and voltages that can be induced by lightning, thus reducing the level of any unwanted electrical discharge that might occur.
[0009] However, the weight and expense required to install metal systems having these insulators may be greater than desired. Part of the cost and expense of installing such metal systems with insulators may be the need to protect the metal systems against sparking from the induced voltages remaining in the system after installing the insulators.
[00010] Additionally, an electrical discharge within a fuel system caused by the accumulation of electrostatic charge and/or induced voltages and currents in response to an electromagnetic event such as lightning can present safety issues. Therefore, it would be desirable to have a method and apparatus that take into account at least some of these issues discussed above, as well as other possible issues. summary
[00011] In an illustrative embodiment, an apparatus comprises a transport member. The transport member is configured for use in a fluid transport system. The transport member is composed of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member.
[00012] In another illustrative modality, a method is provided to reduce an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. A transport member in the fluid transport system in the aerospace vehicle is composed of a material having an electrical resistance within a selected range. Voltages and currents, induced in response to an electromagnetic event that occurs during operation of the aerospace vehicle, along the carrier member are reduced to within selected tolerances by the electrical resistance of the carrier member.
[00013] The features and functions can be obtained independently in various embodiments of the present description or can be combined in still other embodiments where additional details can be seen with reference to the description and drawings below. Brief Description of Drawings
[00014] The new features seen as characteristic of the illustrative modalities are presented in the attached claims. However, the illustrative embodiments, as well as a preferred mode of use, other purposes, and features thereof will be better understood with reference to the following detailed description of an illustrative embodiment of the present description when read in conjunction with the attached drawings, in what:
[00015] Figure 1 is an illustration of a fluid transport system in the form of a block diagram according to an illustrative embodiment;
[00016] Figure 2 is an illustration of a carrier member in the form of a block diagram according to an illustrative embodiment;
[00017] Figure 3 is an illustration of a connection in the form of a block diagram according to an illustrative embodiment;
[00018] Figure 4 is an illustration of tubes configured for use in a fluid transport system according to an illustrative embodiment;
[00019] Figure 5 is an illustration of components for a coupling assembly according to an illustrative embodiment;
[00020] Figure 6 is an illustration of a partially assembled coupling assembly according to an illustrative embodiment;
[00021] Figure 7 is an illustration of a fully assembled coupling assembly according to an illustrative embodiment;
[00022] Figure 8 is an illustration of a cross-sectional view of a coupling assembly according to an illustrative embodiment;
[00023] Figure 9 is an illustration of a cross-sectional view of a different configuration for a coupling assembly according to an illustrative embodiment;
[00024] Figure 10 is an illustration of a cross-sectional view of another configuration for a coupling assembly according to an illustrative embodiment;
[00025] Figure 11 is an illustration of a cross-sectional view of a different configuration for a coupling assembly according to an illustrative embodiment;
[00026] Figure 12 is an illustration of a process for reducing an intensity of an electrical discharge within a fluid transport system in the form of a flowchart according to an illustrative embodiment;
[00027] Figure 13 is an illustration of a process for reducing the energy that can be supplied to an electrical discharge within a fluid transport system in the form of a flowchart according to an illustrative embodiment;
[00028] Figure 14 is an illustration of a process to dissipate an electrostatic charge in the form of a flowchart according to an illustrative embodiment;
[00029] Figure 15 is an illustration of an aircraft manufacturing and service method in the form of a flowchart according to an illustrative modality; and
[00030] Figure 16 is an illustration of an aircraft in the form of a block diagram according to an illustrative modality. Detailed Description
[00031] The different illustrative modalities recognize and take into account different considerations. For example, the different illustrative modalities recognize and take into account that it may be desirable to have a fluid transport system configured to reduce the intensity of electrical discharge from components, such as, for example, tubes, within the fluid transport system. fluids.
[00032] The different illustrative modalities recognize and take into account that tubes composed of materials with high levels of electrical resistance can be used in a fluid transport system to reduce the intensity of electrical discharge caused by voltages and currents induced in response to an electromagnetic event, such as, for example, lightning. High levels of electrical resistance can include levels greater than, for example, about 100 kilohms per metric length of pipe.
[00033] Materials with high levels of electrical resistance include, but are not limited to, non-metallic fiber reinforced composite materials, carbon reinforced plastic materials, plastic materials, inhomogeneous metallic materials, and/or other types of materials. The illustrative modalities recognize and take into account that tubes composed of any of these types of materials can limit the levels of voltages and currents induced in response to the occurrence of an electromagnetic event, thus reducing the intensity of any electrical discharge caused by these induced voltages and/or currents.
[00034] For example, materials having high levels of electrical resistance can limit the current induced along a tube in response to an electromagnetic event such as lightning. With fuel pipes in a fuel system, limiting current flow along these fuel pipes can limit the voltages induced through connections between those fuel pipes when the electrical resistance of these connections is less than the electrical resistance across a fuel system. specific length of fuel pipe connected to the fitting. The specific length, for example, being 0.3 meters of pipe. In this way, electrical discharge in the form of sparking and/or electrical sparking can be reduced and/or avoided. Consequently, the illustrative modalities recognize and take into account that an upper limit for resistivity or, equivalently, a lower limit for conductivity, can be selected for the materials used in the connections between the fuel pipes to reduce an electrical discharge through these connections and along the fuel pipes.
[00035] However, the illustrative embodiments recognize and take into account that, in some cases, if a conductive material becomes displaced from a connection between the fuel tubes and forms a bridge between a metal fuel tube and a structure within of the fuel tank, the conductive material would short-circuit this bridge and allow, for example, lightning to induce a current flow or possibly a spark from the fuel pipe to the structure. As a result, the illustrative embodiments recognize and take into account that the resistivity of the conductive material may require a lower limit for resistivity, or, equivalently, an upper limit for conductivity.
[00036] However, the different illustrative modalities recognize and take into account that in other cases, the fuel tubes can be used in metallic fuel tanks where the voltages and/or currents induced by lightning may be within selected tolerances. Consequently, the materials used in the connections between the fuel tubes may only need to be selected to allow for the dissipation of electrostatic charge that has built up along these fuel tubes. Consequently, the illustrative modalities recognize and take into account that only an upper limit for resistivity or, equivalently, a lower limit for conductivity, may need to be selected for the materials used in the connections between the fuel pipes to reduce an electrical discharge through these connections.
[00037] In addition, the illustrative examples recognize and take into account that the possibility of a discharge static caused by the build-up of electrostatic charge can be reduced and/or avoided by grounding the fuel pipes to a structure having a resistance that is sufficient low to remove an electrostatic charge from the fuel pipes at a faster rate than the electrostatic charge can build up in the fuel pipes, such that a net charge on the fuel pipes within selected tolerances can be maintained. In particular, a net load on the fuel pipes can be reduced to within selected tolerances. The different illustrative modalities recognize and take into account that when the fuel pipes are connected in series, the electrostatic charge can be removed from the series of fuel pipes using conductive paths through the connections between the fuel pipes and then grounding up the series to the structure.
[00038] Therefore, the different illustrative modalities provide a system and a method to reduce an electrical discharge intensity within a fluid transport system. In an illustrative embodiment, the fluid transport system is located within a vehicle, such as an aerospace vehicle. Furthermore, the fluid transport system can be composed of selected materials such that the fluid transport system has a selected electrical configuration. This electrical configuration for the fluid transport system can be selected such that the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle can be reduced to within selected tolerances.
[00039] Referring now to the figures and in particular with reference to Figure 1, an illustration of a fluid transport system is described in the form of a block diagram according to an illustrative embodiment. Fluid transport system 100 is configured to transport materials within platform 104.
[00040] Materials transported may include any number of liquid materials, gaseous materials, and/or solid materials. As an illustrative example, fluid transport system 100 can be used to transport fluid 102 within platform 104. Fluid 102 can comprise any number of liquids and/or gases.
[00041] In an illustrative example, the platform 104 takes the form of an aerospace vehicle 106. In this illustrative example, the fluid transport system 100 may take the form of a fuel system 105 configured to transport the fluid 102 in the form of fuel 108 within aerospace vehicle 106. Aerospace vehicle 106 may be selected from an aircraft, a helicopter, an unmanned aerial vehicle (UAV), a space shuttle, or some other suitable type of vehicle configured to travel in the air. and/or in space. Of course, in other illustrative examples, platform 104 may take the form of a land vehicle, a watercraft, or some other suitable type of vehicle.
[00042] As described, the fluid transport system 100 comprises a plurality of transport members 110 and a series of connections 112. As the usage in question, a "plurality of" items means two or more items. Furthermore, a "series of" items means one or more items. For example, a plurality of transport members 110 means two or more transport members, while a series of connections 112 means one or more connections.
[00043] As the usage in question, a "carrying member," such as a plurality of carrying members 110, can be any structural member having a channel through which materials can be moved. Depending on the implementation, a transport member in a plurality of transport members 110 may take the form of, for example, a tube, a duct, a cylinder, a pipe, a pipe, a duct, or some other type of structure having a channel through which materials can flow. As an illustrative example, a plurality of transport members 110 may take the form of a plurality of tubes 111.
[00044] Furthermore, depending on the usage in question, a "connection", such as one among a series of connections 112, may be any type of permanent or removable physical connection between two or more transport members in a plurality of transport members 110. Depending on the implementation, a connection in a series of connections 112 may comprise any number of components, such as, for example, without limitation, fastening elements, joining elements, screws, ferrules, rings, seals, adhesive connections, and /or other types of components.
[00045] As an illustrative example, a series of fittings 112 may take the form of a series of coupling assemblies 113. Each coupling assembly in a series of coupling assemblies 113 may be configured to engage a carrying member in a plurality of transport members 110 with another transport member on a plurality of transport members 110. In this way, when the plurality of transport members 110 take the form of a plurality of tubes 111, a series of coupling assemblies 113 can be used. to couple the tubes in a plurality of tubes 111 to each other.
[00046] According to the usage in question, a first component, such as a tube, "coupled" to a second component, such as another tube, means that the first component is connected or fixed to the second component. This connection can be a direct connection or an indirect connection. For example, one end of one tube can be coupled to the end of another tube using a mating assembly. With a direct connection, the end of the tube can contact the end of the other tube when these two ends are mated. With an indirect connection, the end of the tube and the end of the other tube may not contact each other when these two ends are mated.
[00047] Of course, in other illustrative examples, a series of connections 112 can take other forms. For example, the transport members can be secured together using other methods, such as applying adhesives to permanently connect the transport members or performing thermoplastic welding operations.
[00048] In these illustrative examples, the fluid transport system 100 is configured such that the fluid transport system 100 has a selected electrical configuration 114. The selected electrical configuration 114 can be composed of a set of electrical properties 116, each having a value within a selected range. According to the usage in question, a "set of" items means one or more items.
[00049] The set of electrical properties 116 may include, for example, resistance, resistivity, conductivity, and/or other types of electrical properties. Furthermore, in some cases, any component that makes up the fluid transport system 100 can be configured such that the component also has a set of electrical properties with values within selected ranges.
[00050] Selected electrical configuration 114 can be selected such that an intensity of electrical discharge that occurs within fluid transport system 100 during operation of aerospace vehicle 106 can be reduced to within selected tolerances. In particular, selected electrical configuration 114 can be selected such that voltages and currents induced within fluid transport system 100 in response to an electromagnetic event, such as lightning, can be constrained within selected tolerances. In addition, selected electrical configuration 114 may be selected to allow a dissipation of electrostatic charge that accumulates along the plurality of transport members 110 during operation of aerospace vehicle 106.
[00051] Turning now to Figure 2, an illustration of a carrier member in a plurality of carrier members 110 is described from Figure 1 in the form of a block diagram according to an illustrative embodiment. Carrier member 200 in Figure 2 is an example of an implementation for a carrier member in a plurality of carrier members 110 in Figure 1. In an illustrative example, carrier member 200 takes the form of a tube 201. tube 201 may be an example of an implementation for a tube in the plurality of tubes 111 in Figure 1.
[00052] As described, the carrying member 200 has a first end 202 and a second end 204. Furthermore, the carrying member 200 has an outer surface 203 and an inner surface 205. The inner surface 205 can form a channel 206 that extends along axis 215 through carrying member 200 from first end 202 of carrying member 200 to second end 204 of carrying member 200. Axle 215 may be a central axis extending through a member of transport 200 from the first end 202 of the transport member 200 to the second end 204 of the transport member 200. The fluid 102 of Figure 1 can be transported within the channel 206.
[00053] In these illustrative examples, connection 218 can be an example of a connection in a series of connections 112 that can be used to connect transport member 200 to another transport member in a plurality of transport members 110 in Figure 1 As described, connection 218 may be used at a first end 202 of transport member 200 or at a second end 204 of transport member 200 to connect transport member 200 to another transport member.
[00054] In an illustrative example, the connection 218 takes the form of a coupling assembly 220. The coupling assembly 220 can comprise any number of components, such as, for example, without limitation, fastening elements, joining elements, screws, ferrules, rings, seals, and/or other types of components.
[00055] In these illustrative examples, the carrying member 200 can be composed of a material 207. The material 207 can be selected such that the carrying member 200 has a 210 electrical configuration. The electrical configuration 210 may comprise a set of electrical properties 212, each having a value within a selected range. In an illustrative example, electrical property set 212 includes a resistor 214. Resistance 214 may be an electrical resistor in these examples.
[00056] As the usage in question, the "resistance" of an item, such as the carrying member 200, is the opposition of the item to the flow of electric current through the item. In this way, the resistance 214 of the transport member 200 can be the opposition of the transport member 200 to the flow of electric current through the transport member 200.
[00057] Material 207 can be selected such that resistance 214 is within selected range 216. Selected range 216 for resistance 214 can be selected such that resistance 214 is high enough to limit the stresses and strains. currents, induced along the transport member 200 in response to an electromagnetic event, within selected tolerances. The electromagnetic event can be, for example, a lightning collision, a short circuit, an overloaded circuit, an electric field, or some other type of electromagnetic event.
[00058] In particular, the material 207 can be selected in such a way that the induced voltages and currents can be limited to levels at or below the level at which an unwanted electrical discharge can be formed. The unwanted electrical discharge can be, for example, an arc between the transport member 200 and a structure and/or a spark in connection 218 having at least one property outside selected tolerances.
[00059] In an illustrative example, when the carrying member 200 is installed within a particular specific electromagnetic environment, the selected range 216 for the resistance 214 of the carrying member 200 can be selected such that the resistance per unit length 214 of the transport member 200 is at or above about 100 kilohms per meter (kQ/m). For example, when the transport member 200 is installed in an aircraft fuel tank composed of carbon fiber reinforced plastic, the specific electromagnetic environment may be a specific lightning environment.
[00060] In addition, when the transport member 200 is configured to allow static dissipation and reduce and/or prevent electrostatic charge build-up, the selected range 216 for resistance 214 of the transport member 200 can be selected such that the resistance per unit length 214 of the carrying member 200 is at or below about 100 megohms per meter (MQ/m).
[00061] Material 207 can take a number of different forms. Material 207 may comprise, for example, without limitation, non-metallic fiber reinforced composite materials, plastic materials, and/or other suitable types of non-homogeneous metallic materials. In an illustrative example, material 207 takes the form of a composite material 208 composed of any number of non-metallic materials. When composed of a composite material 208, the carrier member 200 may be referred to as a composite carrier member. In this way, tube 201 can be referred to as a composite tube.
[00062] In this way, the selected range 216 can include resistance levels 214 low enough to provide static dissipation. Furthermore, the selected range 216 may include resistance levels 214 high enough to limit voltages and currents induced along the transport member 200 in response to an electromagnetic event.
[00063] Furthermore, in these illustrative examples, strength 214 of carrier member 200 may vary along axis 215. However, composite material 208 may be selected such that strength 214 does not vary outside selected tolerances. For example, the transport member 200 can be formed using a composite material 208 selected such that the strength 214 of the transport member 200 can vary only by less than a selected percentage with respect to the length of the transport member and the time relative to axis 215. This selected percentage can be between about 20 percent and about 40 percent in an illustrative example.
[00064] In an illustrative example, each transport member in a plurality of transport members 110 in Figure 1 can be implemented similarly to the transport member 200. The resistance within the selected range 216 can be distributed evenly in individual intervals of length of piping installed in the fluid transport system 100 in Figure 1.
[00065] When the fluid transport system 100 takes the form of a fuel system 105 in Figure 1 located in a fuel tank, the high electrical resistance distributed can prevent the electromagnetic fields within the fuel tank induced by lightning from being concentrates, thus reducing the voltages and currents induced along the pipeline. The resistance per unit length relative to the particular lengths of tubing in fuel system 105 may be different between the different length ranges, but evenly distributed within these length ranges.
[00066] With reference to Figure 3, an illustration of a connection in a series of connections 112 from Figure 1 is described in the form of a block diagram according to an illustrative embodiment. Connection 300 is an example of an implementation for a connection in a series of connections 112 in Figure 1. Connection 300 can take the form of a coupling assembly 301. Coupling assembly 301 can be an example of an implementation for a coupling assembly in a series of coupling assemblies 113 in Figure 1.
[00067] In some cases, connection 300 can be used to implement a connection 218 in Figure 2. For example, coupling assembly 301 can be used to implement a coupling assembly 220 in Figure 2.
[00068] As described, the connection 300 is used to couple the first transport member 302 to the second transport member 304. In particular, the first end 306 of the first transport member 302 is coupled to the second end 308 of the second transport member 304 using connection 300. The first transport member 302 has a first surface 310 and a first channel 312. The second transport member 304 has a second surface 314 and a second channel 316.
[00069] The first channel 312 and the second channel 316 can be configured to allow different types of materials to flow through the first transport member 302 and the second transport member 304, respectively. These materials can include any number of liquid materials, gaseous materials, and/or solid materials. In an illustrative example, the first transport member 302 and the second transport member 304 may be a first fuel transport member and a second fuel transport member, respectively, through which the fuel 108 of Figure 1 is allowed to flow. .
[00070] When the first end 306 of the first transport member 302 is coupled to the second end 308 of the second transport member 304, material can flow between the first channel 312 within the first transport member 302 and the second channel 316 within the second transport member 304. In this way, the first channel 312 and the second channel 316 can form a channel that extends through both the first transport member 302 and the second transport member 304 when the first transport member 302 and the second transport member 304 are coupled together.
[00071] In these illustrative examples, the connection 300 can be configured such that the electrical resistance across the connection 300 is less than the electrical resistance across a specific length of the first transport member 302 and across a specific length of the second member of transport 304. This specific length may be, for example, without limitation, about one foot (ft) or about one third of a meter (m) when connection 300 is implemented inside a fuel tank in a aircraft composed of carbon fiber reinforced plastic. In particular, this specific length may apply when the first transport member 302, the second transport member 304, and the connection 300 are composed of highly electrically resistive non-metallic materials.
[00072] In this way, each of the individual components that constitute a connection 300 can be configured in such a way that the electrical resistance across the connection 300 is less than the electrical resistance across the specific length of the first transport member 302 and across the length specific to the second transport member 304. The components that make up the connection 300 can be composed of any number of materials including, but not limited to, metal, plastic, a composite material, and/or other types of materials.
[00073] If components having an electrical resistance outside the selected range are used in forming the connection 300, the size and/or placement of these parts in relation to the first transport member 302 and the second transport member 304 may be restrictions. As an illustrative example, if a metal part having an electrical resistance outside the selected range is used, the part may need to have electrical ground paths through the first transport member 302, the second transport member 304, and/or other transport members. This type of grounding can allow static dissipation from pipe to pipe through the metal part and from the metal part to the ground through one of the pipes.
[00074] In an illustrative example, the connection 300 may include a first fit 318, a second fit 320, a seal 322, and a cover 324. The first fit 318 and the second fit 320 are associated with the first end 306 of the first member of carrying member 302 and to the second end 308 of the second carrying member 304, respectively. In particular, the first fit 318 is associated with the first surface 310 of the first transport member 302 at the first end 306 of the first transport member 302. Furthermore, the second fit 320 is associated with the second surface 314 of the second transport member 304 at the second end 308 of second transport member 304.
[00075] When a component is "associated" with another component, depending on the usage in question, this association is a physical association. For example, a first component, such as the first fit 318, can be considered to be associated with a second component, such as the first transport member 302, being secured to the second component, joined to the second component, mounted to the second component, welded to the second component, secured to the second component, and/or connected to the second component in some other suitable way. The first component can also be connected to the second component using a third component. Additionally, the first component can also be considered to be associated with the second component being formed as part and/or an extension of the second component.
[00076] In an illustrative example, the first fit 318 takes the form of a first ferrule 326, and the second fit 320 takes the form of a second ferrule 328. As the usage in question, a "ferro" such as the first ferrule 326 and the second ferrule 328, is a ring-like object for fastening, joining and/or strengthening. A ferrule can take the form of a ring, bracelet, sleeve, circular armband, stake, band, or some other suitable type of object.
[00077] The first ferrule 326 is placed around the first surface 310 of the first transport member 302 at the first end 306 of the first transport member 302. The second ferrule 328 is placed around the second surface 314 of the second transport member 304 at the second end 308 of the second transport member 304.
[00078] In these illustrative examples, the seal 322 is configured for placement around the first fit 318 and the second fit 320 when the first end 306 of the first transport member 302 is positioned relative to the second end 308 of the second transport member 304 For example, seal 322 can be placed around first end 306 and second end 308 when first end 306 is positioned against second end 308.
[00079] The seal 322 is configured to seal the interface 330 formed between the first end 306 of the first transport member 302 and the second end 308 of the second transport member 304 when the first end 306 of the first transport member 302 is the second end 308 of the second transport member 304 are positioned relative to one another. Sealing interface 330 means reducing the possibility of material flowing in and/or out of the channel formed by the first channel 312 within the first transport member 302 and by the second channel 316 within the second transport member 304 at the interface 330 when the first member carrier 302 is coupled to the second carrier member 304.
[00080] In some illustrative examples, the seal 322 can be configured such that the connection 300 has an electrical configuration 329. The electrical configuration 329 comprises a set of electrical properties 333, each having a value within a selected range. The electrical configuration 329 for a connection 300 can be selected such that the connection 300 forms a conductive path 331 between the first transport member 302 and the second transport member 304.
[00081] The conductive path 331 may be a path that allows an electric current to flow between the first transport member 302 and the second transport member 304.
[00082] In other words, the conductive path 331 allows an electric current to be conducted between the first transport member 302 and the second transport member 304. For example, the electric currents flowing through the first surface 310 of the first transport member conveyors 302 can be conducted to the second surface 314 of the second conveyor member 304 when the conductive path 331 is present. In this way, the electrostatic charge can be dissipated using a conductive path 331 formed by connection 300.
[00083] In an illustrative example, at least a portion of seal 322 comprises a viscoelastic material 332. The viscoelastic material 332 is a material comprising both viscous properties and elastic properties. A viscous material is a material that is resistant to deformation by shear forces. An elastic material is a material that can return to its original shape after a stress that caused the deformation is no longer applied.
[00084] In these illustrative examples, the viscoelastic material 332 is a non-metallic material. Furthermore, the viscoelastic material 332 can be selected such that the viscoelastic material 332 has a conductivity level 335 within the selected range 334 in these examples.
[00085] The selected strip 334 can be selected such that the conductive path 331 is formed between the first transport member 302 and the second transport member 304 when the first transport member 302 is coupled to the second transport member 304 using connection 300 is provided. In this illustrative example, selected strip 334 may include sufficiently high conductivity levels to allow an electrostatic charge that builds up on the first transport member 302 and/or the second transport member 304 to be dissipated through the seal. 322.
[00086] However, in some cases, the selected range 334 may also include conductivity levels low enough to reduce voltages and currents, induced in response to an electromagnetic event, such as, for example, lightning, along the first carrying member 302 and/or the second carrying member 304.
[00087] For example, the selected range 334 may be between about 1 x 10-4Siemens/centimeter (S/cm) and about 1 x 10-9 Siemens/centimeter (S/cm). Of course, in other illustrative examples, the selected range 334 can be a particular level of conductivity between about 1 x 10-4Siemens/centimeter and about 1 x 10-9 Siemens/centimeter. Of course, in other illustrative examples, the upper limit and/or the lower limit for selected range 334 may be different depending on the particular implementation for the seal 322.
[00088] Selected range 334 of conductivity 335 may also be the selected range for conductivity of other components within connection 300, first transport member 302, and/or second transport member 304. carrier 302, second carrier member 304, first fit 318, second fit 320, seal 322, and cover 324 may together have a level of conductivity that is within the selected range 334.
[00089] Conductivity is related to resistivity. The resistivity of an item is the ability of that item to prevent an electrical current from being conducted through the item. In particular, conductivity is reciprocal to resistivity. As an item's conductivity increases, the item's resistivity decreases. Similarly, as an item's conductivity decreases, the item's resistivity increases. The selected range 334 for conductivity 335 corresponds to a range for resistivity between about 1 x 104 ohm-centimeters (Q-cm) and about 1 x 109 ohm-centimeters (Q-cm).
[00090] The viscoelastic material 332 can be selected from any number of materials configured to provide a level of conductivity 335 within the selected range 334. For example, the viscoelastic material 332 can comprise at least one of a conductive elastomer, a rubber conductive, a conductive silicone material, and other suitable types of materials. An elastomer is a polymer that is viscoelastic.
[00091] As per the usage in question, the phrase "at least one of", when used with a list of items, means that different combinations of one or more of the listed items can be used and only one of each item in the list can be required. For example, "at least one of item A, item B, and item C" may include, without limitation, item A or item A and item B. This example may also include item A, item B, and item C, or item B and item C. In other examples, "at least one of" may be, for example, without limitation, two from item A, one from item B, and 30 from item C; four from item B and seven from item C; or some other suitable combination.
[00092] In these illustrative examples, the seal 322 comprises a first seal 336, a second seal 338, and a sleeve 340. As the use in question, a "seal", such as the first seal 336 and the second seal 338, is a mechanical seal. In an illustrative example, the first seal 336 takes the form of a first O-ring 342, and the second seal 338 takes the form of a second O-ring 344. As the usage in question, an "O-ring," such like the first O-ring 342 and the second O-ring 344, it is a mechanical seal in the shape of a torus. Furthermore, an O-ring has a loop-like shape.
[00093] Of course, in other illustrative examples, the first seal 336 and the second seal 338 may take some other suitable shape. For example, in some cases, the first seal 336 and the second seal 338 can be configured such that a cross-section of these seals has a triangular shape, a square shape, a rectangular shape, an oval shape, or some other type of Format.
[00094] The first O-ring 342 and the second O-ring 344 are configured to be received by the first setting 318 and the second setting 320, respectively. As an illustrative example, the first O-ring 342 might fit in a groove around the first fit 318, and the second O-ring 344 might fit in a groove around the second fit 320.
[00095] Sleeve 340 is then placed around the first O-ring 342 and the second O-ring 344 to apply pressure to the first O-ring 342 and the second O-ring 344. This pressure compresses the first O-ring 344. The 342 is the second O-ring 344 and causes these O-rings to seal the interface 330 between the first end 306 of the first carrier member 302 and the second end 308 of the second carrier member 304.
[00096] Additionally, in some illustrative examples, cover 324 may be placed over seal 322, at least a portion of first fit 318, and at least a portion of second fit 320. Cover 324 may be used to cover seal 322 and hold the seal 322 in position. In an illustrative example, the cover 324 takes the form of a capsule device 346.
[00097] When the interface 330 has been sealed using the seal 322, the conductive path 331 is formed between the first transport member 302 and the second transport member 304. As an illustrative example, the first O-ring 342 and the second O-ring 344 may be composed of a viscoelastic material 332 having a conductivity level within the selected range 334. Furthermore, each of the first fit 318, the second fit 320, and the sleeve 340 may be composed of a material non-metallic having a conductivity level within the selected range 334.
[00098] In this illustrative example, the conductive path 331 can be formed through the first carrier member 302, through the first adjustment 318, through the first O-ring 342, through the sleeve 340, through the second O-ring 344, through of the second adjustment 320, and through the second transport member 304. When the conductive path 331 is formed, an electric current can flow in a first direction and in a second direction.
[00099] The first direction can be from the first carrier member 302, through the first adjustment 318, through the first O-ring 342, through the sleeve 340, through the second O-ring 344, through the second adjustment 320, and to the second transport member 304. The second direction can be from the second transport member 304, through the second fit 320, through the second O-ring 344, through the sleeve 340, through the first O-ring 342, through the first adjustment 318, and up to the first transport member 302.
[000100] In this way, the electrical currents induced by the electrostatic charge that accumulates on the first surface 310 of the first transport member 302 and/or the second surface 314 of the second transport member 304 can be dissipated using the conductive path 331 In particular, with a connection 300 coupling the first transport member 302 and the second transport member 304, the first transport member 302 and the second transport member 304 can be considered grounded to each other.
[000101] In other words, an electrical current flowing in the first transport member 302 can flow in the second transport member 304 through the coupling assembly 301 without interruption and without the level of electrical current changing outside selected tolerances. Similarly, an electrical current flowing in the second transport member 304 can flow in the first transport member 302 through the coupling assembly 301 without interruption and without the level of electrical current changing outside selected tolerances.
[000102] In some cases, the electrical current traveling along the conductive path 331 may be an electrical current induced in response to an electromagnetic event, such as a lightning collision. The selected range 334 of conductivity 335 can be selected such that the voltage drop across the first O-ring 342 and the voltage drop across the second O-ring 344 when this type of electrical current travels through the first o-ring at O 342 and the second O ring 344, respectively, are reduced to within the selected tolerances.
[000103] In these illustrative examples, the first transport member 302 and the second transport member 304 may be fuel pipes, for example, in the fuel system 105 in the aerospace vehicle 106 in Figure 1. In some cases, the fuel system 105 can be configured such that fuel system 105 has an overall level of conductivity within the selected range 334. Different parts of fuel system 105 can have different levels of conductivity and different ranges that apply to different portions of the fuel system. fuel. It may not be necessary for some parts of the system to be within the specified conductivity range. One or more conductivity levels within selected range 334 may be less than conductivity levels for other parts of aerospace vehicle 106. For example, fuel system 105 may have a conductivity level between about 1 x 10-4Siemens/ centimeters and about 1 x 10-9Siemens/centimeters. However, one or more parts of aerospace vehicle 106 can have a conductivity level above about 1 x 10-4Siemens/centimeter.
[000104] In this way, the fluid transport system 100 in Figure 1 having a plurality of transport members 110, each implemented similarly to the transport member 200 in Figure 2, and the number of connections 112, each implemented similarly to connection 300 in Figure 3, they can be configured to reduce electrical discharge within fluid transport system 100. The plurality of transport members 110 interconnected within fluid transport system 100 can have high levels of electrical resistance. substantially and evenly distributed throughout this interconnected piping system.
[000105] In particular, the voltages and currents induced by lightning can be reduced and/or limited in such a way that the energy given to the electrical discharge can be reduced. In this way, unwanted effects of electrical discharge within fluid transport system 100 can be reduced and/or avoided. In particular, the overall energy supplied to the electrical discharge can be restricted within selected tolerances.
[000106] In some cases, when implementing the fluid transport system 100 comprising an interconnected network of transport members with high electrical resistance, such as the plurality of transport members 110, it may be necessary that the network of transport members be grounded to the structure at one or more points for the purposes of removing electrostatic charge buildup and restricting lightning induced voltages to the carrying members. It may also be necessary for the transport members to be grounded at the penetrations of an enclosure that covers an electrically shielded volume where the fluid transport system 100 is installed, such as a fuel tank, in order to reduce the possibility of a from an external electromagnetic environment, such as lightning, or an electrical fault, entering the volume.
[000107] Grounds made to the structure for the purpose of removing an electrical charge to prevent an electrostatic charge from building up along the transport members may be located at one or more locations in a fluid transport system 100 as a means to ensuring that an electrical path exists although the fluid transport system 100 from any point in the fluid transport system 100 to the structure or ground with a sufficiently low resistance dissipates the electrostatic charge at a rate fast enough to prevent a build-up of static charge at the point. In an electrostatic charging environment, such as a fuel tank in an aircraft, an acceptable electrical resistance to provide the ability to dissipate an electrostatic charge from a point in a pipe although a trajectory to the structure or ground may be a value. at or below 100 megohms (MQ).
[000108] In this case, grounds made for this purpose need only ensure that this overall ground path resistance is met. As such, a static ground resistance can be a value of about 100 megohms (MQ) in the borderline case, but in the usual case a value of up to about 10 MQ.
[000109] Grounds made to the structure for the purpose of restraining lightning induced voltages in the network of transport members in fluid transport system 100 may be located at one or more locations in fluid transport system 100 as a means to ensure that the voltage induced from transport member to transport member and from the transport member to the structure at any point in the fluid transport system 100 is less than a selected threshold. Grounds made to the structure at the perimeter of a fuel tank for the purpose of shielding the fuel tank may be located at one or more locations on the perimeter to prevent unwanted voltages and currents from entering the fuel tank through conductive members to which said voltages and currents are induced by an external environment, such as lightning outside the tank.
[000110] The illustrations of the fluid transport system 100 in Figure 1, the transport member 200 in Figure 2, and the connection 300 in Figure 3 are not intended to imply physical or architectural limitations to the manner in which an illustrative embodiment can be implemented. Other components can be used in addition to or instead of those illustrated. Some components may be optional. Likewise, blocks are presented to illustrate some functional components. One or more of these blocks can be combined, split, or combined and split into different blocks when implemented in an illustrative modality.
[000111] In some illustrative examples, the transport member 200 may have additional features not described in Figure 2. For example, without limitation, one or more structural features may extend into channel 206 from the inner surface 205 of the transport member 200. These structural features may need to be taken into account when measuring resistance 214 for the carrying member 200.
[000112] In other illustrative examples, the seal 322 may comprise only a seal 352. The seal 352 is configured to be placed around the first fit 318 and the second fit 320. The seal 352 may have a shape configured for placement on the around the first fit 318 and the second fit 320. For example, the seal 352 may have a first end that fits in a groove around the first fit 318 and a second end that fits in a groove around the second fit 320 when first end 306 of first transport member 302 is positioned relative to second end 308 of second transport member 304. In addition, seal 352 may comprise a viscoelastic material 332 having a level of conductivity within selected range 334.
[000113] With this type of configuration for the seal 322 in connection 300, the cover 324 is used to compress the seal 352 to seal the interface 330 between the first end 306 of the first transport member 302 and the second end 308 of the second member of transport 304, rather than sleeve 340. Furthermore, with this configuration for seal 322, conductive path 331 is formed through first transport member 302, through first fit 318, through seal 352, through second fit 320 , and through the second transport member 304.
[000114] In still other illustrative examples, seal 322 may include one or more seals in addition to first seal 336 and second seal 338. For example, seal 322 may also include a third O-ring configured for placement around the first fit 318 and a fourth O-ring configured for placement around the second fit 320.
[000115] These additional O-rings can be positioned such that cap 324 compresses the third O-ring and fourth O-ring instead of sleeve 340. In addition, the third O-ring and fourth O-ring provide an additional conductive path. This additional conductive path occurs through the first transport member 302, through the first fit 318, through the third O-ring, through the cover 324, through the fourth O-ring, through the second fit 320, and through the second O-ring member. transport 304.
[000116] In some illustrative examples, first fit 318 and/or second fit 320 may not be considered part of connection 300. For example, when first fit 318 and second fit 320 are part of first transport member 302 and of the second transport member 304, respectively, these sockets may be considered separate from connection 300. In other illustrative examples, cover 324 may not be considered part of connection 300. For example, in some cases, connection 300 may only include the seal 322.
[000117] Referring now to Figure 4, an illustration of tubes configured for use in a fluid transport system is described according to an illustrative embodiment. In Figure 4, tube 402, tube 404, and tube 406 can be configured for use in a fluid transport system, such as, for example, fluid transport system 100 in Figure 1. In particular, the tube 402, tube 404, and tube 406 are examples of implementations of tubes in the plurality of tubes 111 in Figure 1. Furthermore, each tube 402, tube 404, and tube 406 can be implemented similarly to tube 201 in Figure 2 .
[000118] In this illustrative example, tube 402, tube 404, and tube 406 are composed of non-metallic composite materials and configured to have a resistance within a selected range. This selected range can be between about 100 kilohms per meter to about 100 megohms per meter along axis 405 through tube 402, tube 404, and tube 406. With each tube 402, tube 404, and tube 406 having a resistance within the selected range with respect to axis 405, the flow of an electrical current, induced in response to an electromagnetic event around these tubes, although these tubes may be limited within selected tolerances. Shaft 405 is a center shaft for tube 402, tube 404, and tube 406.
[000119] The illustration of tube 402, tube 404, and tube 406 in Figure 4 is not meant to imply physical or architectural limitations to the way in which an illustrative modality can be implemented. For example, in some cases these tubes can be connected using other types of coupling assemblies in addition to the 408 coupling assembly and the 410 coupling assembly.
[000120] Referring now to Figures 5 to 11, the illustrations of different configurations for a coupling assembly are described according to different illustrative embodiments. The components described in Figures 5 to 11 can be illustrative examples of how the components shown in block form in Figure 3 can be implemented as physical structures. The different components shown in Figures 5 to 11 can be combined with the components in Figure 3, used with components in Figure 3, or a combination of the two.
[000121] Turning now to Figure 5, an illustration of components for a coupling assembly is described according to an illustrative embodiment. In this illustrative example, components for a coupling assembly, such as a coupling assembly 301 in Figure 3, are described. These components can be assembled to form a coupling assembly configured to couple the first tube 500 to the second tube 502. The first tube 500 and the second tube 502 are examples of implementations for the first transport member 302 and the second transport member 304 , respectively, in Figure 3.
[000122] As described, the first tube 500 has a first end 504, and the second tube 502 has a second end 506. Furthermore, the first tube 500 has a first surface 508 and a first channel 510. The second tube 502 has a second surface 512 and second channel 514.
[000123] The first ferrule 516, the second ferrule 518, the first O-ring 520, the second O-ring 522, the sleeve 524, and the cap device 526 are components that can be assembled to form a coupling assembly 528 The first ferrule 516 and the second ferrule 518 are examples of implementations for the first ferrule 326 and the second ferrule 328, respectively, in Figure 3. Furthermore, the sleeve 524 and the capsule device 526 are examples of implementations for the sleeve 340 and the capsule device 346, respectively, in Figure 3.
[000124] The first ferrule 516, the second ferrule 518, the sleeve 524, and the capsule device 526 may be composed of non-metallic materials having a conductivity level within a selected range. This range can be, for example, without limitation, between about 1 x 10-4 Siemens/cm and about 1 x 10-9 Siemens/centimeter. For example, the first ferrule 516, the second ferrule 518, the sleeve 524, and the cap device 526 can be composed of composite materials. In particular, these components can be composed of composite materials selected in such a way that these components have a level of conductivity within the selected range.
[000125] The first O ring 520 and the second O ring 522 are examples of implementations for the first O ring 342 and the second O ring 344, respectively, in Figure 3. In this illustrative example, each first O ring 520 and second O-ring 522 is composed of a viscoelastic material, such as viscoelastic material 332 in Figure 3. This viscoelastic material has a level of conductivity, for example, without limitation, within the selected range 334 for conductivity 335 in Figure 3.
[000126] As described, the coupling assembly 528 has been partially assembled. In particular, the first ferrule 516 was placed around the first surface 508 of the first tube 500 at the first end 504 of the first tube 500. The second ferrule 518 was placed around the second surface 512 of the second tube 502 at the second end 506 of the second tube 502. In addition, the first O-ring 520 was placed around the first O-ring 516, and the second O-ring 522 was placed around the second O-ring 518. In this illustrative example, the first O-ring 520 fits into a groove in first ferrule 516. Second O-ring 522 fits into a groove in second ferrule 518.
[000127] Turning now to Figure 6, an illustration of a partially assembled coupling assembly is described according to an illustrative embodiment. In Figure 6, sleeve 524 has been placed around the first O-ring 520 and the second O-ring 522 (not shown in this view) of the coupling assembly 528 of Figure 5.
[000128] When sleeve 524 is placed around these two O-rings, these O-rings are compressed by sleeve 524. Sleeve 524, the first O-ring 520, and the second O-ring 522 form the seal 600 when the first O-ring 520 and the second O-ring 522 are compressed by sleeve 524. Seal 600 is an example of an implementation for Seal 322 in Figure 3.
[000129] The seal 600 seals the interface (not shown) between the first end 504 (not shown) of the first tube 500 and the second end 506 (not shown) of the second tube 502. Furthermore, the seal 600 forms a conductive path between first tube 500 and second tube 502. As described, coupling assembly 528 remains partially assembled without cap device 526.
[000130] Turning now to Figure 7, an illustration of a fully assembled coupling assembly is described according to an illustrative embodiment. In Figure 7, the coupling assembly 528 has been completely assembled. In particular, the cap device 526 has been placed around the seal 600 and at least a portion of the first ferrule 516 and at least a portion of the second ferrule 518 to form the fully assembled coupling assembly 528.
[000131] With reference to Figure 8, an illustration of a cross-sectional view of a coupling assembly is described according to an illustrative embodiment. In this illustrative example, a cross-sectional view of the coupling assembly 528 in Figure 7 taken along lines 8-8 is depicted.
[000132] As described, the seal 600 forms a conductive path 800 between the first tube 500 and the second tube 502. In particular, the conductive path 800 is formed at the interface 802 between the first tube 500 and the second tube 502. 802 is between the first end 504 of the first tube 500 and the second end 506 of the second tube 502. The first O-ring 520 fits into the groove 806 of the first ferrule 516. The second O-ring 522 fits into the groove 808 of the second ferrule 518.
[000133] In this illustrative example, the conductive path 800 is formed through the first surface 508 of the first tube 500, the first ferrule 516, the first O-ring 520, the sleeve 524, the second O-ring 522, the second ferrule 518 , and the second surface 512 of the second tube 502. The conductive path 800 allows the first tube 500, the second tube 502, and the coupling assembly 528 to function as a ground between the two tubes. At least one of the first tube 500, the second tube 502, and the coupling assembly 528 can be connected for ground such that the conductive path 800 can be considered as a ground for these two tubes.
[000134] Referring to Figure 9, an illustration of a cross-sectional view of a different configuration for a coupling assembly is described according to an illustrative embodiment. In Figure 9, the coupling assembly 528 has a different configuration than the configuration for the coupling assembly 528 in Figure 8.
[000135] As depicted in Figure 9, coupling assembly 528 includes a third 900 o-ring and a fourth 902 o-ring in addition to the first o-ring 520 and the second o-ring 522 in seal 600. The 900 fits within groove 906 of the first ferrule 516. The fourth O-ring 902 fits within the groove 908 of the second ferrule 518. The third O-ring 900 and fourth O-ring 902 could also be elastic or viscoelastic features which are not seals, but could be attached to the capsule device 526 to provide a conductive path as described below.
[000136] In this illustrative example, the third O-ring 900 and the fourth O-ring 902 allow the seal 600 to form an additional conductive path 904 between the first tube 500 and the second tube 502. In particular, the additional conductive path 904 is formed through the first surface 508 of the first tube 500, the first ferrule 516, the third O-ring 900, the cap device 526, the fourth O-ring 902, the second ferrule 518, and the second surface 512 of the second tube. 502.
[000137] Turning now to Figure 10, an illustration of a cross-sectional view of another configuration for a coupling assembly is described according to an illustrative embodiment. In this illustrative example, seal 600 on coupling assembly 528 comprises only one O-ring instead of two O-rings. As described, seal 600 uses a 1000 O-ring in place of both the first 520 and second O-rings. O-ring 522 in Figure 8.
[000138] With this configuration for the seal 600, the conductive path 1002 is formed between the first tube 500 and the second tube 502. The conductive path 1002 is formed through the first surface 508 of the first tube 500, the first ferrule 516, of the O-ring 1000, second ferrule 518, and second surface 512 of second tube 502. As described, electrical currents may also flow from first ferrule 516 in sleeve 524, and second ferrule 518.
[000139] Turning now to Figure 11, an illustration of a cross-sectional view of a different configuration for a coupling assembly is described according to an illustrative embodiment. In this illustrative example, seal 600 on coupling assembly 528 comprises a seal 1100. Furthermore, seal 600 does not include a sleeve 524 in this example.
[000140] As described, the seal 1100 has a shape 1102. The shape 1102 is configured such that the first end 1104 of the seal 1100 fits the groove 806 in the first ferrule 516. Furthermore, the shape 1102 is configured in such a way that the second end 1106 of the seal 1100 fits the groove 808 in the second ferrule 518. The cap device 526 can be used to compress the seal 1100 such that the seal 1100 forms a seal 600 to seal the interface 802 when the device of capsule 526 is placed around the seal 600.
[000141] In this illustrative example, the seal 1100 forms a conductive path 1108 between the first tube 500 and the second tube 502. The conductive path 1108 is formed through the first surface 508 of the first tube 500, the first ferrule 516, the seal 1100 , the second ferrule 518, and the second surface 512 of the second tube 502.
[000142] The illustrations of the different configurations for the coupling assembly 528 in Figures 5-11 are not intended to imply physical or architectural limitations to the way in which an illustrative modality can be implemented. Other components can be used in addition to or instead of those illustrated. Some components may be optional.
[000143] Referring to Figure 12, an illustration of a process for reducing an intensity of an electrical discharge within a fluid transport system in the form of a flowchart is described according to an illustrative embodiment. The process illustrated in Figure 12 can be implemented using the fluid transport system 100 in Figure 1. In this illustrative example, the fluid transport system 100 can be configured for use in an aerospace vehicle 106 in Figure 1.
[000144] The process begins by operating the aerospace vehicle in which the fluid transport system has an electrical configuration comprising a set of electrical properties where each electrical property in the electrical property set has a value within a selected range (operation 1200). The process can then reduce an intensity of an electrical discharge within the fluid transport system during aerospace vehicle operation to within tolerances selected by the electrical configuration of the fluid transport system (operation 1202), with the process ending the follow.
[000145] Referring to Figure 13, an illustration of a process for reducing the energy that can be supplied to an electrical discharge within a fluid transport system in the form of a flowchart is described according to an illustrative embodiment. The process illustrated in Figure 13 can be implemented using the fluid transport system 100 in Figure 1. In particular, this process can be implemented using tube 201 in Figure 2. Tube 201 can be configured for use in the aerospace vehicle 106 in Figure 1.
[000146] The process begins by operating the aerospace vehicle in which a transport member in the fluid transport system in the aerospace vehicle is composed of a material selected such that the transport member has a resistance within a selected range ( operation 1300). This selected range can only include electrical resistance levels above about 100 kilohms. Furthermore, in some cases, this selected range may also only include electrical resistance levels below about 100 megohms.
[000147] The process can then reduce the voltages and currents induced in response to an electromagnetic event that occurs during the operation of the aerospace vehicle along the carrying member into tolerances selected by the resistance of the carrying member ( operation 1302), with the process ending next. Reducing these voltages and currents can reduce the energy that can be supplied to an electrical discharge within the fluid transport system. In this way, this reduction in induced voltages and currents can reduce the intensity of an electrical discharge that can occur within the fluid transport system.
[000148] Referring to Figure 14, an illustration of a process to dissipate electrostatic charge in the form of a flowchart is described according to an illustrative embodiment. The process illustrated in Figure 14 can be implemented using a coupling assembly, such as, for example, a 301 coupling assembly in Figure 3.
[000149] The process begins by operating the aerospace vehicle in such a way that an electrostatic charge accumulates on a surface of at least one of a first transport member and a second transport member in the fluid transport system in the aerospace vehicle ( operation 1400). In an illustrative example, a first end of the first carrying member may be coupled to a second end of the second carrying member using a connection in the form of a coupling assembly comprising a first fit, a second fit, and a seal. The first fit can be associated with the first end of the first transport member. The second fit can be associated with the second end of the second carrying member.
[000150] The seal is placed around the first fit and the second fit with the first end of the first transport member positioned close to the second end of the second transport member. The seal is configured to seal an interface between the first end of the first carrying member and the second end of the second carrying member when the first end and the second end are positioned close together.
[000151] In an illustrative example, the seal includes a first seal, a second seal, and a sleeve. The first seal is placed around the first fit, and the second seal is placed around the second fit. The sleeve is then positioned around the first seal and the second seal. The sleeve compresses the first seal and the second seal to seal the interface between the first end of the first transport member and the second end of the second transport member. The coupling assembly between the first transport member and the second transport member can be configured to form a conductive path between the first transport member and the second transport member.
[000152] The process dissipates the electrostatic charge that accumulates on the surface of at least one of the first transport member and the second transport member during the operation of the aerospace vehicle, using the conductive path between the first transport member and the second transport member (operation 1402), with the process ending next. In this way, the coupling assembly allows the first transport member and the second transport member to be grounded from one transport member to the other. A series of electrical currents can flow from one transport member to another transport member without interruption and without the level of the electrical currents changing outside selected tolerances.
[000153] The flowchart and block diagrams in the different described modalities illustrate the architecture, functionality, and operation of some possible implementations of devices and methods in an illustrative modality. In this aspect, each block in flowcharts or block diagrams can represent a module, a segment, a function, and/or a portion of an operation or step.
[000154] In some alternative implementations of an illustrative modality, the function or functions noted in the blocks may occur outside the one noted in the figures. For example, in some cases, two blocks shown in succession can be performed at substantially the same time, or the blocks may sometimes be performed in reverse order, depending on the functionality involved. Likewise, other blocks can be added in addition to the blocks illustrated in a flowchart or block diagram.
[000155] The illustrative modalities of the description can be described in the context of the 1500 aircraft manufacturing and service method as shown in Figure 15 and the 1600 aircraft as shown in Figure 16. Turning first to Figure 15, an illustration of a method of aircraft manufacturing and service is described according to an illustrative modality. During pre-production, the 1500 aircraft fabrication and service method may include a 1502 specification and design of the 1600 aircraft in Figure 16 and a 1504 materials purchase.
[000156] During production, 1506 component and sub-assembly fabrication and 1508 system integration of the 1600 aircraft take place. Thereafter, the 1600 aircraft may undergo a 1510 certification and distribution for the purpose of being placed in 1512 service. While in 1512 service by a consumer, the 1600 aircraft is scheduled for routine 1514 maintenance and service, which may include modifications, reconfigurations , renovation, and other maintenance or services.
[000157] Each of the 1500 aircraft manufacturing and service method processes may be performed or performed by a system integrator, a third party, and/or an operator. In these examples, the operator can be a consumer. For purposes of this description, a system integrator may include, without limitation, any number of aircraft manufacturers and main system sub-suppliers; a third party may include, without limitation, any number of vendors, sub-suppliers, and suppliers; and an operator can be an airline, a leasing company, a military entity, a service organization, and so on.
[000158] Referring to Figure 16, an illustration of an aircraft in which an illustrative modality can be implemented is described. In this example, aircraft 1600 is produced by aircraft manufacturing and service method 1500 in Figure 15 and may include a 1602 aircraft structure with 1604 systems and a 1606 interior. Examples of 1604 systems include one or more of a 1608 propulsion system , an electrical system 1610, hydraulic system 1612, an environmental system 1614, and a fuel system 1616. Fuel system 1616 and hydraulic system 1612 can be implemented using, for example, a fluid transport system 100 in the Figure 1.
[000159] Any number of other systems can be included in 1604 systems, depending on implementation. Although an aerospace example is shown, different illustrative modalities can be applied to other industries, such as the automotive industry.
[000160] The apparatus and methods incorporated herein may be employed during at least one of the stages of the aircraft manufacturing and service method 1500 in Figure 15. For example, tubes, such as a plurality of tubes 111 in Figure 1, may be manufactured, installed, and/or processed 1600 during at least one component fabrication and subassembly 1506, system integration 1508, and maintenance and service 1514.
[000161] In an illustrative example, components or subassemblies produced in a 1506 component and subassembly fabrication in Figure 15 can be fabricated or manufactured in a similar manner to the components or subassemblies produced while the 1600 aircraft is in service 1512 in Figure 15. How In yet another example, one or more apparatus modalities, method modalities, or a combination thereof may be used during the production stages, such as component fabrication and subassembly 1506 and system integration 1508 in Figure 15. One or more apparatus modalities, method modalities, or a combination of these may be used while the aircraft 1600 is in service 1512 and/or during maintenance and service 1514 in Figure 15. The use of a number of different illustrative modalities can substantially promote assembly and/or reduce the costs of the 1600 aircraft.
[000162] Therefore, the different illustrative modalities provide a method and an apparatus to reduce an intensity of an electrical discharge that can occur within a fluid transport system. In an illustrative embodiment, a fluid transport system comprises a plurality of transport members and a series of connections connecting transport members in the plurality of transport members to each other. The plurality of transport members and the number of connections can be composed of selected materials such that the intensity of an electrical discharge occurring within the fluid transport system can be reduced to within selected tolerances.
[000163] According to an aspect of the present description, there is provided an apparatus comprising a transport member (200) configured for use in a fluid transport system, wherein the transport member (200) comprises a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the transport member (200). Advantageously, the transport member is a tube. Advantageously, the transport member is a fuel transport member located within a fuel tank in the fluid transport system. Advantageously, the apparatus further comprises a coupling assembly configured to couple the first transport member to the second transport member in the fluid transport system. Advantageously, the transport member is one of a plurality of transport members configured for use in the fluid transport system. Advantageously, the fluid transport system is a fuel system and the transport member is a tube having a channel through which fuel is moved. Advantageously, the fluid transport system is configured for use on a platform selected from one of an aerospace vehicle, a land vehicle, and a water vehicle.
[000164] According to one aspect of the present description, a method is provided for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle, the method comprising operating the aerospace vehicle, wherein a transport member (200) in the fluid transport system in the aerospace vehicle is composed of a material having an electrical resistance within a selected range; and reducing voltages and currents, induced in response to an electromagnetic event that occurs during operation of the aerospace vehicle, along the carrier member (200) to within tolerances selected by the electrical resistance of the carrier member (200). Advantageously, the transport member is one of a plurality of transport members configured for use in the fluid transport system.
[000165] The description of the different illustrative modalities has been presented for purposes of illustration and description and is not intended to be exhaustive or limited to the modalities in the disclosed form. Many modifications and variations will become apparent to individuals with common knowledge in the art. Furthermore, different illustrative modalities can provide different features compared to other desirable modalities. The selected modality or modalities are chosen and described in order to better explain the modality principles, practical application, and allow other individuals with common knowledge in the art to understand the description for various modalities with various modifications as they are adapted for use particular contemplated.

权利要求:
Claims (5)
[0001]
1. Apparatus comprising: a first composite transport member (200) configured for use in a fluid transport system (100), wherein the first composite transport member (200) comprises a composite material (208) configured to reduce voltages and currents, induced in response to an electromagnetic event, along the first composite transport member (200); a second composite transport member (200) configured for use in the fluid transport system (100), wherein the second composite transport member (200) comprises the composite material (208) configured to reduce stresses and currents, induced in response to the electromagnetic event, along the second composite transport member (200); and a coupling assembly (220) configured to couple the first composite transport member (200) to the second composite transport member (200) in the fluid transport system (100), characterized in that the fluid transport system (100) is a fuel system and each of the first composite transport member (200) and the second composite transport member (200) is a tube (111) having a channel through which fuel is moved; and the electrical resistance of the coupling assembly (220) is less than the electrical resistance across a specified length of the first composite transport member (200) and the second composite transport member (200), wherein the specified length is 0.3m; and the electrical resistance of the first composite transport member (200) varies with respect to a central axis (215) across the composite transport member (200).
[0002]
2. Apparatus according to claim 1, characterized in that the composite material is selected so that the first composite transport member (200) and the second composite transport member (200) are configured to allow static dissipation and prevent an electrostatic charge buildup.
[0003]
3. Apparatus according to claim 1 or 2, characterized in that the electrical resistance of the first composite transport member (200) varies less than a selected percentage over time.
[0004]
4. Apparatus according to claim 3, characterized in that the selected percentage is between 20 percent and 40 percent.
[0005]
5. Apparatus according to any one of claims 1 to 4, characterized in that the first composite transport member (200) is a fuel transport member located within a fuel tank in the fluid transport system ( 100).

类似技术:

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BR102013013977B1|2021-06-29|APPLIANCE TO LIMIT THE FLOW OF ELECTRIC CURRENT

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AU2013205236B2|2017-02-09|Fluid transport system for preventing electrical discharge

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EP2672157A1|2013-12-11|

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JP2018115766A|2018-07-26|

引用文献:

---

公开号 | 申请日 | 公开日 | 申请人 | 专利标题

---

---

US2589876A|1947-08-07|1952-03-18|William A Sesher|Pipe and gasket joint|

---

US2883211A|1955-05-31|1959-04-21|Rubber Teck Inc|Connector for flexibly connecting tubing|

---

US2966539A|1957-10-07|1960-12-27|American Cast Iron Pipe Co|Electrically conductive pipe joint and gasket|

---

US3244797A|1961-04-22|1966-04-05|Cedric H Watson|Pipe joint structure incorporating electrical conductivity means|

---

US3838205A|1969-10-09|1974-09-24|Dresser Ind|Electrically conductive pipe coupling gasket|

---

US3783178A|1972-08-03|1974-01-01|Gen Signal Corp|Expansion joint for connecting rigid conduit with grounding continuity|

---

US4120325A|1974-03-04|1978-10-17|Wavin B.V.|Electrically conducting plastic pipe system|

---

DE7308162U|1973-03-03|1973-08-23|Bode D & Co|Electrically conductive and flame-retardant plastic pipe|

---

US3891290A|1973-10-15|1975-06-24|Mc Donnell Douglas Corp|Washer for electrically connecting the tubes of a fluid line|

---

US3891291A|1974-02-05|1975-06-24|Wiggins Inc E B|Tubing coupling incorporating bridging conductor|

---

US3992568A|1974-06-12|1976-11-16|Dresser Industries, Inc.|Electrically conductive pipe coupling|

---

US4008937A|1974-09-20|1977-02-22|Stanley Aviation Corporation|Coupling assembly|

---

US3999825A|1975-12-17|1976-12-28|De Laval Turbine Inc.|Tubing coupling with electrical bonding|

---

US4107452A|1976-10-14|1978-08-15|Razvi Masood H|Electrically conductive pipe fitting|

---

US4249786A|1978-11-03|1981-02-10|Hydraflow Supply, Inc.|Flexible coupling|

---

SU1186013A1|1983-08-09|1994-06-15|В.Ф. Ряхин|Protective material for thin-film resistive elements|

---

JPS6049189A|1983-08-25|1985-03-18|Taimei Kinzoku Kogyo Kk|Corrosion preventive device for underground buried piping|

---

US4633363A|1985-08-05|1986-12-30|Ameron, Inc.|Conductive flanged fitting|

---

US4635162A|1985-11-08|1987-01-06|Ameron, Inc.|Conductive flanges for pipe fittings|

---

FR2617568B1|1987-07-02|1989-10-20|Aerospatiale|TUBE FOR THE CIRCULATION OF A FLAMMABLE FLUID, AND PIPING MADE FROM SUCH TUBES|

---

US4881760A|1988-11-07|1989-11-21|Stanley Aviation Corporation|Conduit coupling device with redundancy features|

---

US5466890A|1994-03-22|1995-11-14|Cooper Industries, Inc.|Expansion joint for an electrical conduit which is electrically grounded through the expansion joint|

---

US5620210A|1995-10-24|1997-04-15|Stanley Aviation Corporation|Fluid conduit coupling|

---

US5871239A|1996-10-31|1999-02-16|Stanley Aviation Corporation|Positive lock coupling|

---

US6655218B1|1999-05-28|2003-12-02|Fuji Jukogyo Kabushiki Kaisha|Composite material and method of controlling damage thereto and damage sensor|

---

DE10024738A1|2000-05-19|2001-11-29|Qvf Engineering Gmbh|Glass components with a conductive coating, their use and the apparatus, systems and pipelines made from them|

---

RU2192991C2|2000-12-18|2002-11-20|Открытое Акционерное Общество "Московский Вертолетный Завод Им. М.Л. Миля"|Method of protection of helicopter fuel tanks against thermal effect of lightning current|

---

JP4293777B2|2002-10-29|2009-07-08|株式会社クラレ|Fuel pipe joint with excellent fuel permeation resistance|

---

US6880859B2|2003-07-31|2005-04-19|Stanley Aviation Corporation|Conduit coupling assembly|

---

US20060099843A1|2004-11-01|2006-05-11|Fullner Todd C|Dielectric fittings|

---

US7222889B2|2005-08-23|2007-05-29|Stanley Aviation Corporation|Self-locking self-bonding rigid coupling|

---

CN101346281B|2005-12-23|2011-03-16|空客西班牙公司|Current insulation apparatus used for fuel system|

---

MX2008010924A|2006-02-27|2008-11-10|Textron Innovations Inc|Fluid conduit with self-healing protective sleeve.|

---

WO2008000854A1|2006-06-22|2008-01-03|Airbus España, S.L.|Current-insulating system for fluid systems|

---

US7690692B2|2006-08-21|2010-04-06|Continental Automotive Systems Us, Inc.|Electrostatic discharge solution for angled fuel port of a fuel pump|

---

US9360144B2|2007-10-22|2016-06-07|The Boeing Company|Conduit with joint covered by a boot|

---

US8075024B2|2008-06-30|2011-12-13|Eaton Corporation|Coupling assembly|

---

US8003014B2|2008-07-02|2011-08-23|Eaton Corporation|Dielectric isolators|

---

US8956556B2|2008-07-02|2015-02-17|Eaton Corporation|Dielectric isolators|

---

GB0815203D0|2008-08-20|2008-09-24|Airbus Uk Ltd|A connector for a pipe and bonding means for use therein|

---

FR2938624B1|2008-11-20|2010-12-24|Espa|DEVICE FOR CARRYING OUT A FLUID, IN PARTICULAR FOR FUEL|

---

JP5155833B2|2008-12-01|2013-03-06|三菱重工業株式会社|Aircraft fuel tank|

---

US8305727B2|2009-03-09|2012-11-06|Airbus Operations Limited|Aircraft joint and bonding lead|

---

GB0908786D0|2009-05-21|2009-07-01|Airbus Uk Ltd|A connector for a pipe|

---

FR2948254B1|2009-07-16|2011-12-30|Airbus Operations Sas|DEVICE FOR PROTECTING PIPES AGAINST LIGHTNING|

---

US8360477B2|2009-12-18|2013-01-29|Eaton Corporation|Compliant conduit connector|

---

RU2013114825A|2010-09-03|2014-10-10|Аэразюр С.А.|SYSTEMS AND METHODS FOR CREATING ELECTRICAL CONDUCTIVITY AROUND PIPES AND OTHER PIPELINES|

---

EP2614283A2|2010-09-10|2013-07-17|Aerazur S.A.|Anti-static and lightning compatible transport element|

---

CN202226063U|2011-08-15|2012-05-23|中国航空工业集团公司西安飞机设计研究所|Injection device for inerting gas distributing pipeline of onboard fuel tank|

---

US9233758B2|2011-12-16|2016-01-12|The Boeing Corporation|Electrostatic discharge protected ferrule|US9145993B1|2012-10-22|2015-09-29|The Boeing Company|Non-metallic fluid coupling assemblies|

---

JP2014188239A|2013-03-28|2014-10-06|Seiko Epson Corp|Fluid injection device and medical equipment|

---

GB2519957A|2013-11-01|2015-05-13|Stratec Biomedical Ag|Hybrid connection device|

---

US9408283B2|2014-06-23|2016-08-02|Key Technology, Inc.|Electrical grounding arm|

---

EP3317572B1|2015-06-30|2021-08-25|Exotic Metals Forming Company LLC|Hybrid waste tube assembly|

---

US20170198855A1|2016-01-13|2017-07-13|Philpott Rubber LLC|Intrinsically conduct joint for metallic pipe and method of using the same|

---

GB2548559A|2016-03-17|2017-09-27|Eaton Ltd|Aircraft fluid line coupling assembly for releasably interconnecting fluid conveying members|

---

US10717529B2|2016-10-28|2020-07-21|Whole Life Living LLC|Unmanned aerial vehicle liquid transport, method and system using same|

---

CN109937178A|2016-11-11|2019-06-25|庞巴迪公司|Signal for compound aircraft returns to network|

---

CN106771856B|2016-11-30|2020-01-03|国网河南省电力公司滑县供电公司|Electric power transmission line lightning stroke point determination method based on unmanned aerial vehicle technology|

---

US9599262B1|2016-12-06|2017-03-21|Robin C. Moore|Sleeve tool and method of use|

---

DE102017128251A1|2017-11-29|2019-05-29|Airbus Operations Gmbh|Exhaust pipe for a battery in an aircraft|

---

US20190178425A1|2017-12-13|2019-06-13|Eaton Intelligent Power Limited|Coupler with non-metallic conductive gasket|

---

CN112368502A|2018-05-28|2021-02-12|绝对天才有限公司|Mounting device|

---

US11098828B2|2018-12-07|2021-08-24|The Boeing Company|Apparatus and methods for connecting a first electrically conductive tube and a second electrically conductive tube|

---

US10651572B1|2019-06-10|2020-05-12|Meter Technology Werks, LLC|Bonding jumper system|

---

US11140890B2|2019-08-21|2021-10-12|Cnh Industrial America Llc|Agricultural vehicle having an improved application boom with a composite tube|

---

US20210071788A1|2019-09-09|2021-03-11|Entegris, Inc.|Electrostatic discharge mitigation device|

---

CN110953420A|2019-12-19|2020-04-03|宜宾三江机械有限责任公司|Threaded conduit flexible joint|

---

CN111578037B|2020-05-29|2021-08-13|山西冶金工程技术有限公司|Gas delivery system for metallurgical machinery|

---

CN112503274B|2020-11-26|2022-02-01|中国商用飞机有限责任公司|Pipeline for aircraft fuel system and pipeline system|

法律状态:
2015-06-23| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|

---

2018-12-04| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|

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2019-12-17| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|

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2021-01-05| B07A| Application suspended after technical examination (opinion) [chapter 7.1 patent gazette]|

---

2021-05-11| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|

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2021-06-29| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 06/06/2013, OBSERVADAS AS CONDICOES LEGAIS. |

优先权:

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申请号 | 申请日 | 专利标题

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US201261657248P| true| 2012-06-08|2012-06-08|

---

US61/657,248|2012-06-08|

---

US201261669299P| true| 2012-07-09|2012-07-09|

---

US61/669,299|2012-07-09|

---

US201261712930P| true| 2012-10-12|2012-10-12|

---

US61/712,930|2012-10-12|

---

US13/747,761|2013-01-23|

---

US13/747,761|US9688419B2|2012-06-08|2013-01-23|Composite tubes for a fluid transport system|

---

US13/747,780|US9162774B2|2012-06-08|2013-01-23|Fluid transport system for preventing electrical discharge|

---

US13/747,732|2013-01-23|

---

US13/747,732|US9169029B2|2012-06-08|2013-01-23|Conductive coupling assembly|

---