[특허]Lightweight air vehicle and pneumatic launcher

AAI Corporation

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 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

Lightweight air vehicle and pneumatic launcher

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F41B-011/00
미국특허분류(USC)	244/063; 124/065; 124/085
출원번호	US-0509659 (2004-02-19)
등록번호	US-7410124 (2008-08-12)
국제출원번호	PCT/US04/004720 (2004-02-19)
§371/§102 date	20050629 (20050629)
국제공개번호	WO05/023642 (2005-03-17)
발명자 / 주소	Miller,Stephen W. Velazquez,Matthew T.
출원인 / 주소	AAI Corporation
대리인 / 주소	Venable LLP
인용정보	피인용 횟수 : 8 인용 특허 : 5

초록
▼

A portable unmanned air vehicle and launcher system including a foldable unmanned air vehicle with a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston ...

대표
청구항
▼

We claim: 1. A launcher for launching a foldable unmanned air vehicle having a pressure tube, the pressure tube being open at a rear end and closed at a front end, the launcher comprising: a launch gas reservoir for holding launch gas; a launch tube positioned within the air vehicle and operatively connected to the launch gas reservoir and having a free end for inserting into the open end of the pressure tube of the air vehicle; a free floating piston positioned within the launch tube to reduce noise during launch; and a free piston stop to prevent the free piston from leaving the launch tube, wherein a first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop, and the movement of the free piston from the initial position toward the end position in the launch tube occurs as the air vehicle launches. 2. The launcher of claim 1, wherein the launch tube is tubular. 3. The launcher of claim 1, wherein the launch tube is configured for use with an air vehicle having a tubular pressure tube. 4. The launcher of claim 1, further comprising an air vehicle containment tube for containing the air vehicle in a folded position prior to launching and during an initial period of launching. 5. The launcher of claim 1, wherein the free piston fits in the launch tube such that a second portion of launch gas can move past the free piston and exit the launch tube through the free end prior to the free piston reaching the end position. 6. The launcher of claim 5, wherein, during launching, less than 10% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 7. The launcher of claim 6, wherein, during launching, less than 5% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 8. The launcher of claim 7, wherein, during launching, less than 2% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 9. The launcher of claim 1, wherein the launch tube is for inserting into a fuselage of the air vehicle. 10. The launcher of claim 1, further comprising a valve system that prevents the launch gas in the launch gas reservoir from entering the launch tube and permits venting of the launch gas in the launch tube to outside of the launch tube so that the free piston returns to the initial position. 11. The launcher of claim 1, further comprising a hold back mechanism for engaging a feature on the air vehicle and preventing the air vehicle from moving relative to the launcher; and a trigger mechanism for releasing the hold back mechanism from the feature of the air vehicle. 12. A portable unmanned air vehicle and launcher system comprising: a foldable unmanned air vehicle having a pressure tube, the pressure tube being open at a rear end and closed at a front end; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube, wherein a first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop, and the movement of the free piston from the initial position toward the end position in the launch tube occurs as the air vehicle launches. 13. The system of claim 12 wherein the launch tube is tubular. 14. The system of claim 12, wherein the pressure tube is tubular. 15. The system of claim 12, further comprising an air vehicle containment tube that contains the air vehicle in a folded position prior to launching and during an initial period of launching. 16. The system of claim 12, wherein the free piston fits in the launch tube such that a second portion of launch gas can move past the free piston and exit the launch tube through the free end prior to the free piston reaching the end position. 17. The system of claim 16, wherein, during launching, less than 10% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 18. The system of claim 17, wherein, during launching, less than 5% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 19. The system of claim 18, wherein, during launching, less than 2% of the launch gas held in the launch gas reservoir exits the launch tube through the free end prior to the free piston reaching the end position. 20. The system of claim 12, wherein the pressure tube is a portion of a fuselage of the air vehicle. 21. The system of claim 12, further comprising a valve system that prevents the launch gas in the launch gas reservoir from entering the launch tube and permits venting of the launch gas in the launch tube to outside of the launch tube so that the free piston returns to the initial position. 22. The system of claim 12, further comprising a hold back mechanism that engages a feature on the air vehicle and prevents the air vehicle from moving relative to the launcher; and a trigger mechanism that releases the hold back mechanism from the feature of the air vehicle. 23. A foldable unmanned air vehicle, comprising: a fuselage having a pressure tube portion for receiving a launch tube of a pneumatic launcher; two wings, each wing being pivotably connected to the fuselage such that it pivots about a pivot point; a wing retention mechanism that holds the wings in a folded position; a foldable tail connected to the fuselage; a tail retention mechanism that holds the tail in a folded position; and a linkage that links the wing retention mechanism to the tail retention mechanism such that release of one of the tail retention mechanism and the wing retention mechanism releases the other of the tail retention mechanism and the wing retention mechanism. 24. The air vehicle of claim 23, wherein release of the tail retention mechanism releases the wing retention mechanism. 25. The air vehicle of claim 23, wherein the air vehicle is configured for launching from a containment tube with the wings and the tail in their folded positions. 26. The air vehicle of claim 25, further comprising a tail retention mechanism trigger for triggering the release of the tail retention mechanism when the air vehicle exits the containment tube. 27. The air vehicle of claim 26, wherein the tail retention mechanism trigger comprises spring loaded cams for pressing against the launch tube through holes in the pressure tube, wherein the spring loaded cams are released from engagement with the tail when the launch tube is removed from the pressure tube.

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (8)

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

Lightweight air vehicle and pneumatic launcher

초록
▼

대표
청구항
▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (8)

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

Lightweight air vehicle and pneumatic launcher

초록 ▼

대표청구항 ▼

이 특허에 인용된 특허 (5)

이 특허를 인용한 특허 (8)

IPC 상위 출원인

과제정보

상세정보조회

원문조회

IPC 상세정보(version : 201201)

연구과제 성과물(0)

참여연구원의 다른 문헌(0)

처리중입니다.

잠시만 기다려주세요.

초록
▼

대표
청구항
▼