Common bulkhead for composite propellant tanks
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64G-001/00
B64C-001/10
B32B-003/30
B64G-001/10
B64G-001/40
출원번호
US-0027429
(2011-02-15)
등록번호
US-8939407
(2015-01-27)
발명자
/ 주소
Robinson, Michael James
Hand, Michael Leslie
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
1인용 특허 :
31
초록▼
An apparatus comprising a first structure, a second structure, a first layer, and a second layer. The first structure has a first plurality of channels extending towards a number of edges of the first structure. The second structure has a second plurality of channels extending towards a number of ed
An apparatus comprising a first structure, a second structure, a first layer, and a second layer. The first structure has a first plurality of channels extending towards a number of edges of the first structure. The second structure has a second plurality of channels extending towards a number of edges of the second structure. A first side of the first structure is connected to a first side of the second structure. The first plurality of channels and the second plurality of channels have an orientation with respect to each other. The first layer is connected to a second side of the first structure. The second layer is connected to a second side of the second structure.
대표청구항▼
1. A fuel system of a platform selected from one of a spacecraft, an aircraft, a submarine, and a surface ship, the fuel system of the platform comprising: a first fuel tank configured to hold a first liquid and a second fuel tank configured to hold a second liquid, the first fuel tank and the secon
1. A fuel system of a platform selected from one of a spacecraft, an aircraft, a submarine, and a surface ship, the fuel system of the platform comprising: a first fuel tank configured to hold a first liquid and a second fuel tank configured to hold a second liquid, the first fuel tank and the second fuel tank separated by a common wall, the common wall comprising:a first structure comprising a first plurality of flutes, wherein the flutes form a first plurality of channels extending towards a first number of edges of the first structure;a second structure comprising a second plurality of flutes, wherein the flutes form a second plurality of channels extending towards a second number of edges of the second structure, wherein a first side of the first structure is connected to a second side of the second structure and wherein the first plurality of channels and the second plurality of channels have an orientation with respect to each other;a first layer connected to a third side of the first structure that is opposite the first side, the first layer comprising a first composite facesheet facing a first inside of the first fuel tank, the first layer being permeable to a first fuel stored in the first fuel tank; anda second layer connected to a fourth side of the second structure that is opposite the second side, the second layer comprising a second composite facesheet facing a second inside of the second fuel tank, the second layer being permeable to a second fuel stored in the second fuel tank, and wherein the first side and the second side are connected at a third layer that separates the first fuel and the second fuel, wherein the first structure, the second structure, the first layer, and the second layer form a wall, and wherein the wall is a common wall between the first fuel tank and the second fuel tank. 2. The fuel system of claim 1, wherein the first structure, the second structure, the first layer, and the second layer form the common wall and wherein the first plurality of channels and the second plurality of channels have the orientation with respect to each other such that the common wall is configured to carry a desired load. 3. The fuel system of claim 1, wherein the orientation of the first plurality of channels and the second plurality of channels with respect to each other is about ninety degrees. 4. The fuel system of claim 1 further comprising: a third layer located between the first structure and the second structure, wherein the third layer connects the second side of the second structure to the first side of the first structure. 5. The fuel system of claim 1 further comprising: a gas purge system connected to a first portion of the first plurality of channels and a second portion of the second plurality of channels, wherein the gas purge system is configured to move gas from a first edge of the first portion of the first plurality of channels to a second edge of the first portion of the first plurality of channels and move the gas from a third edge of the second portion of the second plurality of channels to a fourth edge of the second portion of the second plurality of channels. 6. The fuel system of claim 1, wherein the first plurality of channels and the second plurality of channels have a cross section with a shape selected from at least one of a square, a rectangle, a trapezoid, and a hexagon. 7. The fuel system of claim 4, wherein the third layer is comprised of a composite material selected to have a desired level of thermal insulation. 8. A platform selected from one of a spacecraft, an aircraft, a submarine, and a surface ship, the platform further comprising: a bulkhead forming a common wall between a first fuel tank and a second fuel tank, the bulkhead comprising:a first structure comprising first flutes arranged substantially parallel to each other and forming a first plurality of substantially parallel channels extending towards a first number of edges of the first structure;a second structure comprising second flutes arranged substantially parallel to each other and forming a second plurality of substantially parallel channels extending towards a second number of edges of the second structure, wherein a first side of the first structure is connected to a second side of the second structure and wherein the first plurality of substantially parallel channels and the second plurality of substantially parallel channels have an orientation with respect to each other such that the channels of the first plurality of substantially parallel channels are not parallel to the channels of the second plurality of substantially parallel channels;a first layer connected to a third side of the first structure that is opposite the first side, the first layer comprising a first composite facesheet facing a first inside of the first fuel tank, the first layer being permeable to a first fuel stored in the first fuel tank;a second layer connected to a fourth side of the second structure that is opposite the second side, the second layer comprising a second composite facesheet facing a second inside of the second fuel tank, the second layer being permeable to a second fuel stored in the second fuel tank, and wherein the first side and the second side are connected at a third layer that separates the first fuel and the second fuel; anda third layer located between the first structure and the second structure, the third layer impermeable to the first fuel and the second fuel, wherein the first structure, the second structure, the first layer, the second layer, and the third layer form the common wall, and wherein the common wall between the first fuel tank and the second fuel tank. 9. A fuel tank system of a platform selected from one of a spacecraft, an aircraft, a submarine, and a surface ship, the fuel tank system comprising: a first fuel tank having a first side comprising a first plurality of elongate structures and having a first plurality of channels extending towards a first number of edges of the first structure;a second fuel tank having a second side comprising a second plurality of elongate structures and having a second plurality of channels extending towards a second number of edges of the second structure, wherein the first side of the first tank is connected to the second side of the second tank and wherein the first plurality of channels and the second plurality of channels have an orientation with respect to each other;a first layer connected to the first side of the first structure that is opposite the first side, the first layer comprising a first composite facesheet facing a first inside of the first fuel tank, the first layer being permeable to a first fuel stored in the first fuel tank;a second layer connected to the second side of the second structure that is opposite the second side, the second layer comprising a second composite facesheet facing a second inside of the second fuel tank, the second layer being permeable to a second fuel stored in the second fuel tank, and wherein the first side and the second side are connected at a third layer that separates the first fuel and the second fuel; anda third layer comprising a composite material that provides thermal insulation and located between the first structure and the second structure, the third layer impermeable to the first fuel and the second fuel, wherein the first structure, the second structure, the first layer, the second layer, and the third layer form the common wall, and wherein the common wall between the first fuel tank and the second fuel tank. 10. The fuel system of claim 1, wherein each flute of the first flutes and the second flutes comprises an elongate structure having a number of walls that form a channel of the flute, wherein the channel of the flute is open at both ends of the channel of the flute. 11. The fuel system of claim 1, wherein the first tank is a first longitudinal section of a cylindrical rocket, wherein the second tank is a second longitudinal section of the cylindrical rocket, adjacent the first longitudinal section, and wherein the first structure and the second structure together separate the first longitudinal section and the second longitudinal section.
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