[특허]Systems and methods for air vehicles

Systems and methods for air vehicles 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-039/00 B64D-039/06 B64D-039/04
출원번호	US-0846178 (2015-09-04)
등록번호	US-9573696 (2017-02-21)
우선권정보	IL-217364 (2012-01-04); IL-217365 (2012-01-04)
발명자 / 주소	Rix, Ohad
출원인 / 주소	ISRAEL AEROSPACE INDUSTRIES LTD.
대리인 / 주소	Dorsey & Whitney LLP
인용정보	피인용 횟수 : 0 인용 특허 : 69

초록 ▼

A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween.

대표청구항 ▼

1. A refueling device for use in in-flight refueling operation, comprising: a body having a longitudinal axis and configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling operation, and comprising a boom member having a boom axis and configured to enable fuel to be transferred from said fuel hose to a receiver aircraft along said boom axis during said in-flight refueling operation;wherein at least during said in-flight refueling, the boom axis is at a non-zero angular displacement with respect to the longitudinal axis of the body. 2. The refueling device according to claim 1, wherein the boom member is selectively pivotable with respect to the body between a first angular displacement and a second angular displacement different from said first angular displacement. 3. The refueling device according to claim 1, wherein said angular displacement is about 30°. 4. The refueling device according to claim 1, wherein said boom member is selectively reversibly telescopically deployable along said boom axis with respect to said body, and wherein the boom member comprising a fuel delivery nozzle, configured for engaging with a fuel receptacle provided in the receiver aircraft. 5. The refueling device according to claim 1, further comprising a spatial control system configured for enabling selectively maneuvering of said refueling device and/or providing stability for said refueling device at least when said refueling device is towed by the tanker aircraft in said forward direction via said fuel hose. 6. The refueling device according to claim 1, wherein said spatial control system includes a selectively controllable aerodynamic control system including at least one set of aerodynamic control surfaces mounted to said body. 7. The refueling device according to claim 1, further comprising a force generating arrangement configured for selectively generating a force along said boom axis in a direction towards said fuel delivery nozzle. 8. The refueling device according to claim 7, wherein said force generating arrangement includes a selectively deployable air brake arrangement. 9. The refueling device according to claim 1, wherein said body includes a fuel delivery lumen configured for fluid communication with said fuel hose and said boom member at least during the in-flight refueling operation, wherein said body includes a coupling having a hose interface configured for connecting said lumen to the fuel hose, said coupling configured for allowing relative rotation between the hose and said body in at least one degree of freedom while maintaining said fuel communication. 10. The refueling device according to claim 4, further comprising a data acquisition system configured for providing spatial data relating to a relative spatial disposition between said fuel delivery nozzle and said fuel receptacle, to enable selectively controlling the refueling device to provide automatic or autonomous or manual engagement of the fuel delivery nozzle to the fuel receptacle of the receiver aircraft. 11. The refueling device according to claim 1, further comprising a suitable controller for controlling operation thereof.

이 특허에 인용된 특허 (69)

Saggio, III,Frank; Ribbens,William B.; Ooi,Kean K., Active control of a drogue body.
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Ruzicka Dennis E., Actuated roll axis aerial refueling boom.
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Von Thal,German; Slusher,Harry W.; Stecko,Stephen M., In-flight refueling system and method for extending and retracting an in-flight refueling device.
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Schroeder, Steven B., In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components.
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Schroeder,Steven B., In-flight refueling system and method for facilitating emergency separation of in-flight refueling system components.
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Schroeder, Steven B., In-flight refueling system, alignment system, and method for automatic alignment and engagement of an in-flight refueling boom.
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Schuster,John H.; Wexler,Mark H., In-flight refueling system, bladder device and method for preventing oscillations in in-flight refueling system components.
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Von Thal,German; Slusher,Harry W., In-flight refueling system, boom, and method for extending range of motion of an in-flight refueling boom.
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Schroeder,Steven B., In-flight refueling system, damping device and method for damping oscillations in in-flight refueling system components.
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Schroeder,Steven B., In-flight refueling system, damping device and method for damping oscillations in in-flight refueling system components.
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Von Thal,German, In-flight refueling system, sensor system and method for damping oscillations in in-flight refueling system components.
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Jones,Philip E., Increasing the performance of aircraft on-board inert gas generating systems by turbocharging.
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Jones,Philip E., Increasing the performance of aircraft on-board inert gas generating systems by turbocharging.
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Jones,Philip E., Increasing the performance of aircraft on-board inert gas generating systems by turbocharging.
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Stratton Donald A., Interferometric trajectory reconstruction technique for flight inspection of radio navigation aids.
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Jones Philip E. (Columbus IN), Internal combustion engine with integral upper cylinder section and head.
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Taub Bernard (Williamsville NY) Harnish Daniel F. (Orchard Park NY) Jones Philip E. (Snyder NY), Manufacture of fluorocarbon expanded polystyrene.
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Jones Philip,GBX ; Thomas Howard,GBX ; Essam Keith,GBX ; Le Fleming Andrew,GBX, Method for determining handover in a multicellular communications system.
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Jones,Philip E.; O'Hara,Michael J.; Greenawalt,Brian P., System and method for monitoring the performance of an inert gas distribution system.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
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연합인증

Systems and methods for air vehicles 원문보기

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Systems and methods for air vehicles 원문보기

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