[특허]Weight-on-gear sensor

Textron Innovations 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

Weight-on-gear sensor

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64C-025/52
미국특허분류(USC)	244/108; 244/100R
출원번호	US-0640064 (2009-12-17)
등록번호	US-8226030 (2012-07-24)
발명자 / 주소	Mast, James Grant Covington, Charles Eric Darden, Paul Eugene McKeown, William L.
출원인 / 주소	Textron Innovations Inc.
대리인 / 주소	Walton, James E.
인용정보	피인용 횟수 : 4 인용 특허 : 12

초록
▼

A weight-on-gear sensor for use on an aircraft with landing skids having a bracket and a displacement sensor attached to the bracket is disclosed. The bracket has a center member connecting a first end member to a second end member. The center member has a centerline and the end members extend from the centerline of the center member. Mounting members extend along the centerline of the center member to facilitate attachment of the bracket to a cross tube. The displacement sensor connects the first end member to the second end member. The displacement sen...

대표
청구항
▼

1. An aircraft, comprising: opposing landing skids connected by a cross tube; anda weight-on-gear sensor attached to the cross tube, the weight-on-gear sensor comprising: a bracket with a center member connecting a first end member to a second end member the center member having a centerline and the end members extending from the centerline of the center member, mounting members extending along the centerline of the center member; anda first displacement sensor connecting the first end member to the second end member, the first displacement sensor being parallel to, and offset from, the centerline of the center member such that when a bending moment is applied to the center member the first displacement sensor is either elongated or shortened. 2. The aircraft according to claim ,1 further comprising: a second displacement sensor connecting the first end member to the second end member, the second displacement sensor being parallel to, and offset from, the centerline of the center member. 3. The aircraft according to claim 2, wherein the second displacement sensor is on the same side of the centerline of the center member as the first displacement sensor such that when a bending moment is applied to the center member both the first displacement sensor and the second displacement sensor, are either elongated or shortened. 4. The aircraft according to claim 2, wherein the second displacement sensor is opposite the first displacement sensor with respect to the centerline, such that when a bending moment is applied to the center member if the first displacement sensor is elongated then the second displacement sensor is shortened, and if the first displacement sensor is shortened then the second displacement sensor is elongated. 5. The aircraft according to claim 2, wherein the first displacement sensor comprises: a linear motion sensor connected to the first end member; anda connecting rod connected to the second end member and the linear motion sensor;wherein the second displacement sensor comprises: a linear motion sensor connected to the first end member; anda connecting rod connected to the second end member and the linear motion sensor. 6. The aircraft according to claim 2, wherein the first displacement sensor comprises: a linear motion sensor connected to the first end member; anda connecting rod connected to the second end member and the linear motion sensor;wherein the second displacement sensor comprises: a linear motion sensor connected to the second end member, anda connecting rod connected to the first end member and the linear motion sensor. 7. The aircraft according to claim 1, wherein the first displacement sensor comprises: a linear motion sensor connected to the first end member; anda connecting rod connected to the second end member and the linear motion sensor. 8. An aircraft, comprising: opposing landing skids connected by a cross tube;a bracket coupled to the cross tube through a first fitting and a second fitting, thereby defining a bracket length, the bracket length extending between the first fitting and the second fitting approximately parallel to the axis of the cross tube; anda first linear displacement sensor coupled to the bracket and positioned between the first fitting and the second fitting to detect flexure in the cross tube as an indication of weight-on-gear status;wherein a bending moment acting on the cross tube is transferred through the bracket to the first linear displacement sensor, the bending moment causing the bracket to flex between the first and the second fitting. 9. The aircraft according to claim 8, wherein the first linear displacement sensor is approximately parallel with a centerline of the cross tube. 10. The aircraft according to claim 9, further comprising: a second linear displacement sensor approximately parallel with the centerline of the cross tube, the second linear displacement sensor coupled to the bracket and positioned between the first fitting and the second fitting. 11. The aircraft according to claim 10, wherein the first linear displacement sensor is positioned above the centerline of the cross tube and the second linear displacement sensor is positioned below the centerline of the cross tube. 12. The aircraft according to claim 10, wherein the first linear displacement sensor and the second linear displacement sensor are positioned on the same side of the centerline of the cross tube. 13. The aircraft according to claim 8, wherein the first linear displacement sensor is configured to detect linear movement resulting from change in shape of the bracket. 14. The aircraft according to claim 8, wherein the first linear displacement sensor is either linearly compressed or linearly elongated when the cross tube is subjected to a change in load. 15. An aircraft, comprising: a cross tube included in a landing gear;a weight-on-gear sensor coupled to the cross tube, the weight-on-gear sensor comprising: a first fitting and a second fitting coupled to the cross tube;a first linear displacement sensor configured to detect bending flexure in the cross tube as an indication of weight-on-gear status, the first linear displacement sensor located between the first fitting and the second fitting; anda bracket extending between the first and the second fitting approximately parallel to the axis of the cross tube and configured to fixedly attach the first linear displacement sensor to the cross tube, the bracket being configured to flex in response to a bending moment acting on the cross tube;wherein the bending moment acting on the cross tube is transferred through the bracket to the first linear displacement sensor and is detected as a linear displacement by the first linear displacement sensor. 16. The aircraft according to claim 15, wherein the weight-on-gear sensor further comprises: a second linear displacement sensor attached to the bracket between the first and the second fittings and configured to function with the first linear displacement sensor to detect bending flexure in the cross tube as an indication of weight-on-gear status. 17. The aircraft according to claim 15, wherein the bracket comprises: a center member having a centerline. 18. The aircraft according to claim 15, wherein the first linear displacement sensor is either linearly compressed or linearly elongated when the cross tube is subjected to a change in load. 19. The aircraft according to claim 15, wherein the weight-on-gear sensor further comprises: a second linear displacement sensor attached to the bracket between the first and the second fittings and configured to detect bending flexure in the cross tube as an indication of weight-on-gear status. 20. The aircraft according to claim 19, wherein the first linear displacement sensor and the second linear displacement sensor are approximately parallel to each other.

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 4

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

Weight-on-gear sensor

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 4

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

Weight-on-gear sensor

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (12)

이 특허를 인용한 특허 피인용횟수: 4

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼