Cryogenic fuel tanks for use in aircraft structures
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64D-037/02
B64D-037/04
B64D-037/12
B64D-037/30
B64C-003/34
출원번호
US-0025437
(2013-09-12)
등록번호
US-9493246
(2016-11-15)
발명자
/ 주소
Barmichev, Sergey D.
Sankrithi, Mithra M. K. V.
Stuhr, Victor K.
출원인 / 주소
THE BOEING COMPANY
대리인 / 주소
Hanley, Flight and Zimmerman, LLC.
인용정보
피인용 횟수 :
0인용 특허 :
8
초록
Cryogenic fuels tanks for use in aircraft structures are disclosed herein. An example apparatus disclosed herein an airfoil-shaped structure disposed outboard of a fuselage of an aircraft. The example apparatus also includes a first cryogenic fuel tank disposed inside the airfoil-shaped structure.
대표청구항▼
1. An apparatus, comprising: an airfoil-shaped structure disposed outboard of a fuselage of an aircraft;a first cryogenic fuel tank disposed inside the airfoil-shaped structure; anda second cryogenic fuel tank disposed inside the airfoil-shaped structure, a surface of the second cryogenic fuel tank
1. An apparatus, comprising: an airfoil-shaped structure disposed outboard of a fuselage of an aircraft;a first cryogenic fuel tank disposed inside the airfoil-shaped structure; anda second cryogenic fuel tank disposed inside the airfoil-shaped structure, a surface of the second cryogenic fuel tank coupled to a surface of the first cryogenic fuel tank to form a wall extending between the first cryogenic fuel tank and the second cryogenic fuel tank along a longitudinal axis defined by the surface of the first cryogenic fuel tank and the surface of the second cryogenic fuel tank, the wall coupled to the airfoil-shaped structure to support a portion of at least one of an aerodynamic load or a structural load applied to the airfoil-shaped structure. 2. The apparatus of claim 1, wherein the airfoil-shaped structure is at least one of a wing, a horizontal stabilizer, a vertical stabilizer, an engine pylon, a wing strut, a canard or an empennage strut. 3. The apparatus of claim 1, wherein the first cryogenic fuel tank extends spanwise relative to the aircraft. 4. The apparatus of claim 1 further comprising a baffle disposed in the first cryogenic fuel tank to impede fuel flow in a spanwise direction. 5. The apparatus of claim 1, further including a support extending through the first cryogenic fuel tank. 6. The apparatus of claim 1, wherein the first cryogenic fuel tank is to support a first portion of the at least one of the aerodynamic load or the structural load applied to the airfoil-shaped structure. 7. The apparatus of claim 6, wherein the second cryogenic fuel tank is to support a second portion of the at least one of the aerodynamic load or the structural load. 8. The apparatus of claim 1, further comprising a rib coupled to the first cryogenic fuel tank and the airfoil-shaped structure. 9. The apparatus of claim 8, wherein a fuel passageway of the first cryogenic fuel tank extends through the rib. 10. An apparatus, comprising: a housing of an aircraft, the housing disposed outboard of a fuselage of the aircraft;a first cryogenic fuel tank disposed inside the housing; anda second cryogenic fuel tank disposed inside the housing, a surface of the second cryogenic fuel tank coupled to a surface of the first cryogenic fuel tank to form a wall extending between the first cryogenic fuel tank and the second cryogenic fuel tank along a longitudinal axis defined by the surface of the first cryogenic fuel tank and the surface of the second cryogenic fuel tank, the wall coupled to the housing to support a portion of at least one of an aerodynamic load or a structural load applied to the housing. 11. The apparatus of claim 10, wherein a first portion of the first cryogenic fuel tank extends substantially parallel to a second portion of the second cryogenic fuel tank. 12. The apparatus of claim 10 further comprising a rib coupled to the first cryogenic fuel tank and the housing, wherein a first fuel passageway of the first cryogenic fuel tank extends through a first aperture defined by the rib. 13. The apparatus of claim 12, wherein a second fuel passageway of the second fuel tank extends through a second aperture defined by the rib. 14. The apparatus of claim 10, wherein the first cryogenic fuel tank includes a first section and a second section, the second section outboard of the first section. 15. The apparatus of claim 14, wherein the second section is a cap. 16. The apparatus of claim 14, wherein the first section is cylindrical and the second section is tapered. 17. The apparatus of claim 14, wherein the first section is in a first orientation relative to the fuselage and the second section is in a second orientation different than the first orientation relative to the fuselage. 18. An apparatus, comprising: a housing of an aircraft, the housing disposed outboard of a fuselage of the aircraft; anda cryogenic fuel tank bundle substantially filling a space inside the housing, the cryogenic fuel tank bundle including a first cryogenic fuel tank and a second cryogenic fuel tank, a surface of the second cryogenic fuel tank coupled to a surface of the first cryogenic fuel tank to form a wall extending between the first cryogenic fuel tank and the second cryogenic fuel tank along a longitudinal axis defined by the surface of the first cryogenic fuel tank and the surface of the second cryogenic fuel tank, the wall coupled to the housing to support a portion of at least one of an aerodynamic load or a structural load applied to the housing. 19. The apparatus of claim 18, wherein a chord of the housing at least one of increases or decreases along a portion of a span of the housing. 20. The apparatus of claim 18, wherein the cryogenic fuel tank bundle includes a network of supports arranged in a lattice along a longitudinal axis of the fuel tank bundle. 21. The apparatus of claim 18, wherein the cryogenic fuel tank is disposed in an array. 22. An apparatus, comprising: an airfoil-shaped structure disposed outboard of a fuselage of an aircraft, the airfoil-shaped structure having a first surface coupled to the fuselage and a second surface coupled to the fuselage, the first surface spaced apart from the second surface;a first cryogenic fuel tank disposed inside the airfoil-shaped structure; anda second cryogenic fuel tank disposed inside the airfoil-shaped structure, the first surface and the second surface defining a first axis extending between the first surface and the second surface and passing through the first cryogenic fuel tank and the second cryogenic fuel tank, the first axis parallel to a second axis defined by the fuselage, the second axis extending through the fuselage perpendicular to at least a portion of the first surface and at least a portion of the second surface.
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이 특허에 인용된 특허 (8)
Buchheit, Catherine, Aircraft provided with a fuel cell system.
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