[특허]Cycloidal VTOL UAV

Information Systems Laboratories, Inc.

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

검색도움말
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

연합인증

연합인증 가입 기관의 연구자들은 소속기관의 인증정보(ID와 암호)를 이용해 다른 대학, 연구기관, 서비스 공급자의 다양한 온라인 자원과 연구 데이터를 이용할 수 있습니다.

이는 여행자가 자국에서 발행 받은 여권으로 세계 각국을 자유롭게 여행할 수 있는 것과 같습니다.

연합인증으로 이용이 가능한 서비스는 NTIS, DataON, Edison, Kafe, Webinar 등이 있습니다.

한번의 인증절차만으로 연합인증 가입 서비스에 추가 로그인 없이 이용이 가능합니다.

다만, 연합인증을 위해서는 최초 1회만 인증 절차가 필요합니다. (회원이 아닐 경우 회원 가입이 필요합니다.)

연합인증 절차는 다음과 같습니다.

최초이용시에는
ScienceON에 로그인 → 연합인증 서비스 접속 → 로그인 (본인 확인 또는 회원가입) → 서비스 이용

그 이후에는
ScienceON 로그인 → 연합인증 서비스 접속 → 서비스 이용

연합인증을 활용하시면 KISTI가 제공하는 다양한 서비스를 편리하게 이용하실 수 있습니다.

특허 상세정보

MyON담기

내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Cycloidal VTOL UAV

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-027/22
미국특허분류(USC)	244/009; 244/019; 244/020; 244/012.2; 244/023.C
출원번호	US-0690284 (2003-10-21)
발명자 / 주소	Tierney, Glenn Martin
출원인 / 주소	Information Systems Laboratories, Inc.
대리인 / 주소	Nydegger &
인용정보	피인용 횟수 : 7 인용 특허 : 5

초록
▼

A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of t...

대표
청구항
▼

1. A system for moving an aerial vehicle along a flight path, said system comprising:a substantially disk-shaped hub mounted on the vehicle for rotation about a hub axis, with said hub lying in a plane substantially perpendicular to the hub axis; an airfoil shaped blade positioned on said hub for rotation therewith, wherein said blade travels on a blade path around the hub axis during rotation of said hub, said blade defining a blade axis and a chord line; a gear assembly, said gear assembly including a blade gear, with said blade fixedly attached thereto, said blade gear being mounted on said hub for rotation around the blade axis and for rotation with said blade around the hub axis, a center gear oriented on said hub for rotation around a center gear axis with the center gear axis substantially parallel to the hub axis, and a mid-gear rotationally interconnecting said blade gear with said center gear, wherein said gear assembly is changeable between a first modality (curtate flight) wherein the chord line of said blade is maintained generally tangential to the blade path during rotation of said hub, and a second modality (prolate flight) wherein the chord line of said blade is maintained generally parallel to the flight path of the vehicle during rotation of said hub; and a means for moving the center gear to vary a distance between the center gear axis and the blade axis to rotate the chord line of said blade about said blade axis to alter the angle of attack of said blade and generate forces for moving the vehicle along the flight path. 2. A system as recited in claim 1 further comprising:a first link having a first end and a second end with the first end thereof pivotally mounted on said blade gear and the second end thereof pivotally mounted on said mid-gear; and a second link having a first end and a second end with the first end thereof pivotally mounted on said mid-gear and the second end thereof pivotally mounted on said center gear. 3. A system as recited in claim 2 wherein said center gear has a diameter and the center gear axis is moveable within a radial range from the hub axis between a location wherein the center gear axis is coaxial with the hub axis and a location wherein the center gear axis is approximately at a one half center gear diameter from the hub axis.4. A system as recited in claim 1 wherein the blade axis is substantially perpendicular to the chord line, and wherein the blade axis is substantially parallel to the hub axis during rotation of said blade on the blade path around the hub axis.5. A system as recited in claim 1 further comprising a means for selectively holding said center gear stationary relative to said hub axis to establish said gearing means in the second modality.6. A system as recited in claim 1 further comprising a means for holding said hub stationary relative to the vehicle to change said gear assembly into a third modality (fixed wing flight).7. A system as recited in claim 6 wherein said chord line rotating means comprises a means for rotating said center gear while said gear assembly is in the third modality.8. A system as recited in claim 1 wherein said blade, said blade gear, and said mid-gear, in combination, comprise a blade orientation unit and said system comprises:a plurality of said blade orientation units; and plurality of center gears with each said center gear connected to a respective blade orientation unit. 9. A cycloidal propulsion and control system for moving an aerial vehicle along a flight path which comprises:a first hub and a second hub, said first and, second hubs being respectively mounted on the vehicle for rotation about a common hub axis; a first plurality of elongated airfoil blades defining respective chord lines and mounted on said first hub substantially parallel to the hub axis for rotation about the hub axis; a second plurality of elongated airfoil blades defining respective chord lines and mounted on said second hub substantially parallel to the hub axis for rotation about the hub axis; a gear assembly mounted on each said hub, wherein each gear assembly includes a blade gear, with a single said airfoil blade fixedly attached thereto, and wherein said airfoil blade defines a blade axis, said blade gear being mounted on said hub for rotation around the blade axis and for rotation with said blade around the hub axis, a center gear oriented on said hub for rotation around a center gear axis with the center gear axis substantially parallel to the hub axis, and a mid-gear rotationally interconnecting said blade gear with said center gear; and a means for moving the center gear of each gear assembly to vary a distance between the center gear axis and the blade axis to individually and selectively vary an orientation for each chord line of each said airfoil blade for propelling and controlling the vehicle while the vehicle is on the flight path. 10. A system as recited in claim 9 wherein each rotating airfoil blade travels on a blade path around the hub axis and wherein each gear assembly is changeable between a first modality (curtate flight) wherein the chord line of said blade is maintained generally tangential to the blade path during rotation of said hub, and a second modality (prolate flight) wherein the chord line of said blade is maintained generally parallel to the flight path of the vehicle during rotation of said hub.11. A system as recited in claim 9 wherein three gear assemblies are mounted on each said hub.12. A system as recited in claim 11 wherein each center gear has a respective start point for establishing a same orientation for the chord line of each airfoil blade at a predetermined point on the blade path.13. A system as recited in claim 12 wherein said respective start points of said three center gears are mutually off-set from each other by an arc of 120° (curtate mode).14. A system as recited in claim 12 wherein said respective start points of said three center gears are substantially aligned with each other (prolate mode).15. A method for moving an aerial vehicle along a flight path which comprises the steps of:mounting a first plurality of elongated airfoil blades on a first hub, wherein each airfoil blade defines a chord line and is mounted on said first hub substantially parallel to a hub axis of rotation; mounting a second plurality of elongated airfoil blades on a second hub, wherein each airfoil blade defines a chord line and is mounted on said second hub substantially parallel to the hub axis of rotation; selectively rotating the first and second plurality of airfoil blades about the hub axis; individually and selectively varying an orientation for each chord line of each said airfoil blade for changing between a first modality (curtate flight) wherein the chord line of said blade is maintained generally tangential to the blade path during rotation of said hub, and a second modality (prolate flight) wherein the chord line of said blade is maintained generally parallel to the flight path of the vehicle during rotation of said hub; and holding said hub stationary relative to the vehicle to change said gear assembly into a third modality (fixed wing flight).

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 7

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

연합인증

특허 상세정보

Cycloidal VTOL UAV

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

ScienceON Chatbot

연합인증

특허 상세정보

Cycloidal VTOL UAV

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 피인용횟수: 7

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼