[특허]Gyro-stabilized air vehicle

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

Gyro-stabilized air vehicle

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-017/00
미국특허분류(USC)	244/093; 244/012.4; 244/023.A; 244/012.1; 244/012.3; 244/017.23; 244/017.25; 244/023.R
출원번호	UP-0384167 (2006-03-17)
등록번호	US-7520466 (2009-07-01)
발명자 / 주소	Bostan, Nicolae
대리인 / 주소	Knobbe, Martens, Olson & Bear, LLP
인용정보	피인용 횟수 : 24 인용 특허 : 44

초록
▼

A vertical takeoff and landing (VTOL) air vehicle disclosed. The air vehicle can be manned or unmanned. In one embodiment, the air vehicle includes two shrouded propellers, a fuselage and a gyroscopic stabilization disk installed in the fuselage. The gyroscopic stabilization disk can be configured to provide sufficient angular momentum, by sufficient mass and/or sufficient angular velocity, such that the air vehicle is gyroscopically stabilized during various phases of flight. In one embodiment the fuselage is fixedly attached to the shrouded propellers...

대표
청구항
▼

What is claimed is: 1. An aircraft for vertical, horizontal or stationary flight, comprising: a fuselage; two shrouded propulsion assemblies; a plurality of control surfaces attached to the shrouded propulsion assemblies for controlling the flight of the aircraft; an engine mounted to the fuselage having an engine shaft arranged to rotate about a longitudinal axis of the aircraft; two propellers one in each shrouded propulsion assembly that produces thrust such that the aircraft is in flight and such that air flow is created over the plurality of control surfaces; a gyroscopic stabilization member attached to the engine shaft via a gear box such that the gyroscopic stabilization member rotates with an angular momentum that is selected, with respect to the moment of inertia of the aircraft about the axis of rotation of the gyroscopic stabilization member, such that the aircraft is gyroscopically stabilized during flight. 2. The aircraft of claim 1, wherein the gyroscopic stabilization member is a disk rotating about longitudinal axis of the aircraft. 3. The aircraft of claim 1, wherein the fuselage housing the gyroscopic stabilization member is solidly attached to the shrouds. 4. The aircraft of claim 1, wherein the gyroscopic stabilization member is a disk rotating about the yaw axis of the aircraft. 5. The aircraft of claim 1, wherein, the fuselage housing the gyroscopic stabilization member is pivotably attached between the shrouds. 6. An aircraft comprising: a fuselage; two shrouded propulsion assemblies defining flight surfaces wherein the fuselage is mounted solidly between the two shrouded propulsion assemblies; a plurality of control surfaces attached to the shrouded propulsion assemblies for controlling the flight of the aircraft; an engine mounted in the fuselage; two propellers, one mounted in each shrouded propulsion assembly, actuated by the engine via belt drives or gear boxes, that produce thrust such that the aircraft is in flight and such that the airflow is created over the plurality of control surfaces wherein the engine provides sufficient thrust via the propellers so as to power the aircraft wherein the engine provides sufficient thrust via the propellers so as to power the aircraft through a flight envelope that includes vertical take off and landing and horizontal flight and transitions there between; a gyroscopic stabilization member comprising a disk structure actuated via a gear box by the engine, the disk structure situated in the fuselage in between the two shrouded propulsion assemblies. 7. The aircraft of claim 6, wherein the disk has a relatively small cross section, wherein no portion of the disk extends into the opening of the two shrouds. 8. An aircraft comprising: a fuselage; two shrouded propulsion assemblies defining flight surfaces wherein the fuselage is mounted pivotably between the two shrouded propulsion assemblies; a plurality of control surfaces attached to the shrouded propulsion assemblies for controlling the flight of the aircraft; an engine mounted in the fuselage; two propellers, one mounted in each shrouded propulsion assembly, actuated by the engine via interconnecting shafts and gear boxes that produce thrust such that the aircraft is in flight and such that the airflow is created over the plurality of control surfaces wherein the engine provides sufficient thrust via the propellers so as to power the aircraft wherein the engine provides sufficient thrust via the propellers so as to power the aircraft through a flight envelope that includes vertical take off and landing and horizontal flight and transitions there between; a gyroscopic stabilization member comprising a disk structure actuated via a gear box by the engine, the disk structure situated in the fuselage in between the two shrouded propulsion assemblies. 9. The aircraft of claim 8, wherein the disk has a relatively small cross section, wherein no portion of the disk extends into the opening of the two shrouds. 10. An aircraft, comprising: a fuselage having a longitudinal axis; two shrouded propeller assemblies coupled to the fuselage, wherein each shrouded propeller assembly is spaced laterally from the fuselage and provides thrust, and has one or more control surfaces that direct at least a portion of air flow of the thrust so as to provide flight control of the aircraft; an engine positioned within the fuselage and coupled to and providing power to the two shrouded propeller assemblies by a power transfer mechanism; and a gyroscopic stabilization member positioned within the fuselage and coupled to the power transfer mechanism such that the gyroscopic stabilization member rotates about a rotational axis so as to yield a selected angular momentum with respect to the longitudinal axis and a moment of inertia of the aircraft, and thereby provide gyroscopic stabilization of the aircraft during flight. 11. The aircraft of claim 10, wherein each of the two shrouded propulsion assemblies are mounted to the fuselage in a fixed manner such that axes of rotation of the propellers are substantially fixed with respect to the longitudinal axis of the fuselage. 12. The aircraft of claim 11, wherein the aircraft is a Class II UAV. 13. The aircraft of claim 12, further comprising wings that extend laterally from the two shrouded propulsion assemblies so as to provide additional lifting surface during horizontal fight of the aircraft. 14. The aircraft of claim 10, wherein each of the two shrouded propulsion assemblies are mounted to the fuselage in a pivotable manner such that axes of rotation of the propellers can vary with respect to the longitudinal axis of the fuselage. 15. The aircraft of claim 14, wherein the aircraft is a Class III UAV. 16. The aircraft of claim 15, further comprising wings that extend laterally from the two shrouded propulsion assemblies so as to provide additional lifting surface during horizontal fight of the aircraft. 17. The aircraft of claim 10, wherein the power transfer mechanism includes an engine shaft, and wherein the gyroscopic stabilization member is driven by the engine shaft via a gear box. 18. The aircraft of claim 10, wherein the rotational axis of the gyroscopic stabilization member is substantially parallel to the longitudinal axis of the fuselage. 19. The aircraft of claim 10, wherein the rotational axis of the gyroscopic stabilization member is substantially perpendicular to the longitudinal axis of the fuselage. 20. The aircraft of claim 10, wherein the gyroscopic stabilization member comprises a disk. 21. The aircraft of claim 20, wherein the disk has a mass distribution that varies with radial distance from its rotational axis. 22. The aircraft of claim 20, wherein the disk spinning at an operational rotational rate has an angular momentum that is about 10 to 20 times or greater than the static moment of inertia of the aircraft about the rotational axis of the disk. 23. The aircraft of claim 10, further comprising a flight control component configured to receive an input signal indicative of a need or a desire to change an attitude of the aircraft, and generate an output signal for effectuating movement of the one or more control surfaces. 24. The aircraft of claim 23, wherein the movement of the one or more control surfaces induces a precession of the selected angular momentum of the gyroscopic stabilization member. 25. The aircraft of claim 10, wherein the fuselage between the two propulsion units provides a space suitable for a payload. 26. The aircraft of claim 25, wherein the total thrust provided by the two propulsion devices is substantially greater than a thrust from a single propulsion device that is substantially similar to each of the two propulsion devices, such that use of two propulsion devices and the fuselage allows for improved payload of the aircraft. 27. An aircraft, comprising: a fuselage having a longitudinal axis; two propulsion devices coupled to the fuselage, wherein each propulsion device provides thrust and has one or more control surfaces that directs at least a portion of air flow of the thrust so as to provide flight control of the aircraft; and a gyroscopic stabilization member coupled to a power source such that the gyroscopic stabilization member rotates about a rotational axis so as to yield a selected angular momentum with respect to the longitudinal axis and a moment of inertia of the aircraft, and thereby provide gyroscopic stabilization of the aircraft during flight.

이 특허에 인용된 특허 (44)

이 특허를 인용한 특허 피인용횟수: 24

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

Gyro-stabilized air vehicle

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (44)

이 특허를 인용한 특허 피인용횟수: 24

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

Gyro-stabilized air vehicle

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (44)

이 특허를 인용한 특허 피인용횟수: 24

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼