Fluid transport system for preventing electrical discharge
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
H05F-003/00
B64D-045/02
F16L-025/02
F17D-001/00
F16L-009/14
H05F-001/00
F16L-021/06
F16L-025/01
출원번호
US-0747780
(2013-01-23)
등록번호
US-9162774
(2015-10-20)
발명자
/ 주소
Minteer, David William
Irwin, James Patrick
Johnson, Benjamin A.
Axtell, John Thomas
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
0인용 특허 :
19
초록▼
A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport sys
A method and apparatus for reducing an intensity of an electrical discharge that occurs within a fluid transport system in an aerospace vehicle. The aerospace vehicle is operated. The fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration. The intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle is reduced to within selected tolerances by the electrical configuration of the fluid transport system.
대표청구항▼
1. A fluid transport system comprising: a plurality of transport members; anda number of connections connecting transport members in the plurality of transport members to each other, wherein the plurality of transport members and the number of connections are comprised of materials selected such tha
1. A fluid transport system comprising: a plurality of transport members; anda number of connections connecting transport members in the plurality of transport members to each other, wherein the plurality of transport members and the number of connections are comprised of materials selected such that an intensity of an electrical discharge that occurs within the fluid transport system is reduced to within selected tolerances and wherein a connection in the number of connections is configured to connect a first transport member in the plurality of transport members and a second transport member in the plurality of transport members and wherein the connection is configured such that an electrical resistance across the connection is less than the electrical resistance through a specified length of at least one of the first transport member and the second transport member. 2. The fluid transport system of claim 1, wherein the plurality of transport members is a plurality of tubes and wherein each tube in the plurality of tubes is comprised of a material configured to reduce voltages and currents, induced in response to an electromagnetic event, along the tube. 3. The fluid transport system of claim 2, wherein the material for the tube is selected such that the tube has an electrical resistance within a selected range in which the selected range includes per unit length electrical resistance levels at least one of above about 100 kilohms per meter and below about 100 megohms per meter. 4. The fluid transport system of claim 2, wherein the material is a non-metallic composite material. 5. The fluid transport system of claim 1, wherein the connection is a coupling assembly comprising: a first fitting associated with a first end of the first transport member;a second fitting associated with a second end of the second transport member; anda seal configured for placement around the first fitting and the second fitting when the first end of the first transport member is positioned relative to the second end of the second transport member, wherein the seal is configured to seal an interface between the first end of the first transport member and the second end of the second transport member. 6. The fluid transport system of claim 5, wherein the seal is comprised of a material configured such that the seal has a level of conductivity within a selected range and such that the connection forms a conductive pathway between the first transport member and the second transport member. 7. The fluid transport system of claim 6, wherein the conductive pathway allows electrostatic charge that builds up on at least one of the first transport member and the second transport member to be dissipated. 8. The fluid transport system of claim 1, wherein a first transport member of the plurality of transport members, a second transport member of the plurality of transport members, and a connection of the number of connections form a conductive pathway grounding the first transport member and the second transport member without directly grounding the connection to a structure. 9. The fluid transport system of claim 1, wherein resistance within a selected range is distributed evenly over individual intervals of a length of the plurality of the transport members. 10. The fluid transport system of claim 1, wherein each transport member in the plurality of transport members has a respective resistance within a selected range, wherein each respective resistance is distributed evenly over a respective length of each respective transport member. 11. A fluid transport system having an electrical configuration configured to reduce an intensity of an electrical discharge that occurs within the fluid transport system, the fluid transport system comprising: a plurality of tubes, wherein a tube in the plurality of tubes is comprised of a composite material selected such that the tube has a resistance within a selected range configured to reduce voltages and currents, induced in response to an electromagnetic event, along the tube to within selected tolerances; anda number of coupling assemblies configured to couple tubes in the plurality of tubes to each other, wherein a coupling assembly in the number of coupling assemblies comprises:a first fitting associated with a first end of a first tube in the plurality of tubes;a second fitting associated with a second end of a second tube in the plurality of tubes; anda seal configured for placement around the first fitting and the second fitting when the first end of the first tube is positioned relative to the second end of the second tube, wherein the seal is configured to seal an interface between the first end of the first tube and the second end of the second tube and provide a conductive pathway between the first tube and the second tube to allow electrostatic charge that builds up on at least one of the first tube and the second tube to be dissipated, and wherein the first tube, the second tube, and the coupling assembly form the conductive pathway grounding the first tube and the second tube without directly grounding the coupling assembly to a structure. 12. The fluid transport system of claim 11, wherein reducing the voltages and currents, induced in response to the electromagnetic event, along the tube reduces energy available to the electrical discharge. 13. The fluid transport system of claim 11, wherein dissipating the electrostatic charge that builds up on the at least one of the first tube and the second tube reduces energy available to the electrical discharge. 14. A method 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 the fluid transport system in the aerospace vehicle is comprised of materials selected such that the fluid transport system has an electrical configuration, wherein the fluid transport system comprises a plurality of transport members and a plurality of connections connecting transport members in the plurality of transport members to each other, wherein the plurality of transport members and the plurality of connections are comprised of materials selected such that an intensity of the electrical discharge that occurs within the fluid transport system is reduced to within selected tolerances, and wherein a connection in the plurality of connections is configured to connect a first transport member in the plurality of transport members and a second transport member in the plurality of transport members and wherein the connection is configured such that an electrical resistance across the connection is less than the electrical resistance through a specified length of at least one of the first transport member and the second transport member; andreducing the intensity of the electrical discharge that occurs within the fluid transport system during operation of the aerospace vehicle to within selected tolerances by the electrical configuration of the fluid transport system. 15. The method of claim 14, wherein the step of operating the aerospace vehicle comprises: operating the aerospace vehicle, wherein the electrical configuration of the fluid transport system comprises a set of electrical properties in which each electrical property in the set of electrical properties has a value within a selected range. 16. The method of claim 15, wherein the step of operating the aerospace vehicle comprises: operating the aerospace vehicle such that an electrostatic charge builds up around a surface of at least one of the first transport member and the second transport member in the fluid transport system in the aerospace vehicle. 17. The method of claim 16, wherein the step of reducing the intensity of the electrical discharge that occurs within the fluid transport system during the operation of the aerospace vehicle to within selected tolerances comprises: dissipating the electrostatic charge using the connection in the fluid transport system between the first transport member and the second transport member. 18. The method of claim 17, wherein dissipating the electrostatic charge using the connection in the fluid transport system between the first transport member and the second transport member includes the first transport member, the second transport member, and the connection forming a conductive pathway grounding the first transport member and the second transport member without directly grounding the connection to a structure. 19. The method of claim 14, wherein the step of operating the aerospace vehicle comprises: operating the aerospace vehicle, wherein each transport member of the plurality of transport members in the fluid transport system in the aerospace vehicle is comprised of a material selected such that each transport member of the plurality of transport members has an electrical resistance that is above about 100 kilohms and below about 100 megohms per meter. 20. The method of claim 19, wherein the step of reducing the intensity of the electrical discharge that occurs within the fluid transport system during the operation of the aerospace vehicle to within selected tolerances comprises: limiting current, induced in response to an electromagnetic event that occurs during operation of the aerospace vehicle, along each transport member of the plurality of transport members to within selected tolerances by the electrical resistance of each transport member of the plurality of transport members, wherein limiting the current along each transport member of the plurality of transport members limits the current that can be supplied to the electrical discharge.
Winter, Karl-Heinz; Gerth, Klaus, Glass elements with a conductive coating, the use thereof, as well as devices, installations and pipe conducts produced therefrom.
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