[특허]System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control

Aurora Flight Sciences Corporation

검색어에 아래의 연산자를 사용하시면 더 정확한 검색결과를 얻을 수 있습니다.
검색연산자

검색연산자	기능	검색시 예
()	우선순위가 가장 높은 연산자	예1) (나노 (기계 \| machine))
공백	두 개의 검색어(식)을 모두 포함하고 있는 문서 검색	예1) (나노 기계) 예2) 나노 장영실
\|	두 개의 검색어(식) 중 하나 이상 포함하고 있는 문서 검색	예1) (줄기세포 \| 면역) 예2) 줄기세포 \| 장영실
!	NOT 이후에 있는 검색어가 포함된 문서는 제외	예1) (황금 !백금) 예2) !image
*	검색어의 *란에 0개 이상의 임의의 문자가 포함된 문서 검색	예) semi*
""	따옴표 내의 구문과 완전히 일치하는 문서만 검색	예) "Transform and Quantization"

과학기술 지식인프라 ScienceON

특허 상세정보

MyON담기

내보내기

System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control

국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-015/12
미국특허분류(USC)	244/012.4; 244/012.5; 244/056
출원번호	UP-0313997 (2005-12-22)
등록번호	US-7857254 (2011-02-24)
발명자 / 주소	Parks, Robert
출원인 / 주소	Aurora Flight Sciences Corporation
대리인 / 주소	Katten Muchin Rosenman LLP
인용정보	피인용 횟수 : 26 인용 특허 : 30

초록
▼

A system and method are provided for a short take-off and landing/vertical take-off and landing aircraft that stores required take-off power in the form of primarily an electric fan engine, and secondarily in the form of an internal combustion engine, wherein the combined power of the electric fan and internal combustion engines can cause the STOL/VTOL A/C to take-off in substantially less amount of time and space than other STOL/VTOL A/C, and further wherein the transition from vertical to horizontal thrust is carefully executed to rapidly rise from the...

대표
청구항
▼

What is claimed is: 1. A vertical take-off and landing (VTOL) aircraft, comprising: a tiltable primary engine configured to produce thrust for forward flight and thrust for hovering, said tiltable primary engine being disposed on a center of gravity of said aircraft and vertically tiltable with respect to an aircraft center line; a plurality of electrically-driven fans arranged about a periphery of an airframe of the VTOL aircraft, said plurality of electrically-driven fans consisting of (i) a first fan disposed at a nose of the VTOL aircraft, (ii) a second fan disposed at a left wing tip of the VTOL aircraft, and (iii) a third fan disposed at a right wing tip of the VTOL aircraft, the second fan and the third fan each being disposed closer to a tip than a root of the respective wing, said plurality of electrically-driven fans being disposed equidistant from said aircraft center of gravity; wherein airflow provided by each of the electrically-driven fans is oriented substantially perpendicular to the fuselage of the VTOL aircraft for producing thrust for hovering; a thrust control circuit in communication with each of the plurality of electrically-driven fans, wherein the thrust control circuit is configured to independently control the thrust for hovering provided by each of the plurality of electrically-driven fans to alter a total thrust for hovering provided by the plurality of electrically-driven fans and to alter pitch and roll moments of the VTOL aircraft while hovering; a plurality of vanes located in a fan exhaust of each of the plurality of electrically-driven fans; and an attitude control circuit in communication with each of the plurality of vanes and the thrust control circuit, wherein the attitude control circuit is configured to independently control deflection of each of the plurality of vanes for re-directing the thrust for hovering provided by each of the plurality of electrically-driven fans to control a yaw moment of the VTOL aircraft while hovering. 2. The VTOL aircraft of claim 1, wherein the primary engine is configured to be tilted to a position substantially perpendicular to the fuselage of the VTOL aircraft to produce thrust for hovering. 3. The VTOL aircraft of claim 1, wherein a nozzle of the primary engine is configured to be re-directed to produce thrust for hovering. 4. The VTOL aircraft of claim 1, wherein each of the plurality of electrically-driven fans comprises an airflow area that is greater than the primary engine. 5. The VTOL aircraft of claim 1, wherein the plurality of electrically-driven fans are oriented such that the airflow provided by the plurality of electrically-driven fans prevents re-ingestion of exhaust from the primary engine into an air inlet of the primary engine. 6. The VTOL aircraft of claim 1, wherein the plurality of electrically-driven fans are oriented such that the airflow provided by the plurality of electrically-driven fans prevents high-speed exhaust from the primary engine from creating a low pressure region under the VTOL aircraft while the VTOL aircraft is grounded. 7. The VTOL aircraft of claim 1, wherein the thrust control circuit controls the thrust for hovering provided by each of the plurality of electrically-driven fans by varying a RPM of a respective electrically-driven fan. 8. The VTOL aircraft of claim 1, wherein the thrust control circuit controls the thrust for hovering provided by each of the plurality of electrically-driven fans by varying a fan rotor pitch of a respective electrically-driven fan. 9. The VTOL aircraft of claim 1, wherein the thrust control circuit controls the thrust for hovering provided by each of the plurality of electrically-driven fans by deflecting drag-producing flaps located in the fan exhaust of a respective electrically-driven fan. 10. The VTOL aircraft of claim 1, wherein the plurality of vanes are oriented with pivot axes substantially radial to a center of mass of the VTOL aircraft. 11. The VTOL aircraft of claim 1, wherein the plurality of vanes are oriented with pivot axes substantially parallel to the fuselage of the VTOL aircraft. 12. The VTOL aircraft of claim 1, wherein electricity for powering each of the plurality of electrically-driven fans is provided by an electrical generator powered by the primary engine. 13. The VTOL aircraft of claim 1, wherein the primary engine comprises a fuel-powered engine. 14. The VTOL aircraft of claim 13, wherein the fuel-powered engine comprises a turbo jet engine. 15. The VTOL aircraft of claim 13, wherein the fuel-powered engine comprises a turbo fan engine. 16. The VTOL aircraft of claim 1, wherein the plurality of electrically-driven fans comprises three electrically-driven fans. 17. The VTOL aircraft of claim 16, wherein the three electrically-driven fans are located at substantially equally-spaced angles about a center of the VTOL aircraft. 18. The VTOL aircraft of claim 1, wherein electricity for powering each of the plurality of electrically-driven fans is provided by an electricity storage unit associated with the plurality of electrically-driven fans. 19. The VTOL aircraft of claim 18, wherein the electricity storage unit comprises batteries. 20. A vertical take-off and landing aircraft, comprising: a plurality of electrically-driven fans consisting of (i) a first electrically-driven fan disposed at a nose of the aircraft and configured to provide vertical downward thrust; (ii) a second electrically-driven fan disposed at an end of a left wing of the aircraft and configured to provide vertical downward thrust; and (iii) a third electrically-driven fan disposed at an end of a right wing of the aircraft and configured to provide vertical downward thrust; and a tiltable internal-combustion engine disposed on a center of gravity of the aircraft and equidistant from said first, second, and third electrically-driven fans and configured to provide downward thrust and forward thrust, said tiltable internal-combustion engine being vertically tiltable in a plane passing through a central axis of the vertical take-off and landing aircraft. 21. A vertical take-off and landing aircraft according to claim 20, wherein said tiltable internal-combustion engine is disposed substantially at an aircraft center of gravity. 22. A vertical take-off and landing aircraft according to claim 20, wherein said engine comprises an internal combustion engine tiltable between a horizontal, forward-facing position, and a vertical upward-facing position. 23. A vertical take-off and landing aircraft according to claim 20, wherein said engine is disposed substantially centrally of said first, second, and third electrically-driven fans. 24. A vertical take-off and landing aircraft according to claim 20, further comprising, for each electrically-driven fan, a fan door configured to be open during hover and closed during horizontal flight. 25. A vertical take-off and landing aircraft according to claim 20, wherein said first, second, and third electrically-driven fans are mounted stationary. 26. A vertical take-off and landing aircraft according to claim 20 wherein each fan comprises a reversible fan. 27. A vertical take-off and landing aircraft according to claim 20, wherein each fan includes a controller. 28. A vertical take-off and landing aircraft according to claim 20, further comprising a flight control computer having an air volume control circuit configured to control a tilt angle of said tiltable internal-combustion engine. 29. A vertical take-off and landing aircraft according to claim 20, wherein the left and right wings are disposed with a negative dihedral angle. 30. A vertical take-off and landing aircraft according to claim 20, wherein the left and right wings are disposed with a zero dihedral angle. 31. A vertical take-off and landing aircraft according to claim 20, wherein said engine is tiltable about a substantially horizontal axis. 32. A vertical take-off and landing aircraft according to claim 31, wherein said horizontal axis is substantially perpendicular to a centerline of the aircraft. 33. A vertical take-off and landing aircraft according to claim 20, further comprising a left wing vane disposed on said left wing substantially adjacent said second electrically-driven fan, and a right wing vane disposed on said right wing substantially adjacent said third electrically-driven fan. 34. A vertical take-off and landing aircraft according to claim 33, further comprising a nose vane disposed on said nose substantially adjacent said first electrically-driven fan.

이 특허에 인용된 특허 (30)

이 특허를 인용한 특허 피인용횟수: 26

IPC 상위 출원인

내보내기

상세정보
내보내기 구분	파일저장 인쇄 메일전송
구성항목	관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표IPC 관리번호, 국가코드, 자료구분, 상태, 출원번호, 출원일자, 공개번호, 공개일자, 공고번호, 공고일자, 등록번호, 등록일자, 발명명칭(한글), 발명명칭(영문), 출원인(한글), 출원인(영문), 출원인코드, 대표출원인, 출원인국적, 출원인주소, 발명자, 발명자E, 발명자코드, 발명자주소, 발명자 우편번호, 발명자국적, 대표IPC, IPC코드, 요약, 미국특허분류, 대리인주소, 대리인코드, 대리인(한글), 대리인(영문), 국제공개일자, 국제공개번호, 국제출원일자, 국제출원번호, 우선권, 우선권주장일, 우선권국가, 우선권출원번호, 원출원일자, 원출원번호, 지정국, Citing Patents, Cited Patents
저장형식	Text(ASCII format) Excel format PIAS분석(.xls)
메일정보	받는사람 (필수) @ 보내는사람 (선택) @ 제목 내용 KISTI 검색결과 이메일 서비스
안내	> 총 건의 자료가 검색되었습니다. > 다운받으실 자료의 인덱스를 입력하세요. (1-10,000) > 검색결과의 순서대로 최대 10,000건 까지 다운로드가 가능합니다. > 데이타가 많을 경우 속도가 느려질 수 있습니다.(최대 2~3분 소요) > 다운로드 파일은 UTF-8 형태로 저장됩니다. 파일의 내용이 제대로 보이지 않을실 때는 웹브라우저 상단의 보기 -> 인코딩 -> 자동선택 여부를 확인하십시오 > ~ > Text(ASCII format) Excel format

과학기술 지식인프라 ScienceON

ScienceON Chatbot

특허 상세정보

System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (30)

이 특허를 인용한 특허 피인용횟수: 26

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

특허 상세정보

System and method for utilizing stored electrical energy for VTOL aircraft thrust enhancement and attitude control

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (30)

이 특허를 인용한 특허 피인용횟수: 26

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼