과제명
NTIS 과제연계
과제기간
총연구비
- 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" |
특허 상세정보
Missile with aerodynamic control
| 국가/구분 | United States(US) Patent 등록 |
|---|---|
| 국제특허분류(IPC7판) | F41G-007/00 |
| 미국특허분류(USC) | 244/31 ; 244/321 |
| 출원번호 | US-0069434 (1987-07-02) |
| 우선권정보 | DE-3628152 (1986-08-19) |
| 발명자 / 주소 | |
| 출원인 / 주소 | |
| 인용정보 | 피인용 횟수 : 15 인용 특허 : 2 |
초록
A missile, and in particular a shell flying at supersonic velocity, having aerodynamic control. The missile comprises a missile housing and a missile tip which is tiltably connected to the missile housing. Between the missile housing and the shell tip, a positioning device consisting of at least one piezoelectric positioning member and a control circuit is arranged which comprises a voltage source. By applying a voltage to the piezoelectric positioning members, their lengths are changed, whereby the tilting motion of the shell tip is executed.
대표
청구항
A missile, particularly a shell flying at supersonic velocity, having a missile housing and an aerodynamic control system wherein a forward part of the missile can be tilted relative to the missile housing at least in one plane by means of a positioning device for fixing the part into desired positions relative to the missile housing, the positioning device comprising at least one piezoelectric positioning member and electric control means for controlling said positioning member.
이 특허에 인용된 특허 (2)
이 특허를 인용한 특허 피인용횟수: 15
- O'Shea, Hank. Aerial vehicle with variable aspect ratio deployable wings. USP2010117841559.
- Nedderman,William H.. Apparatus for changing the attack angle of a cavitator on a supercavatating underwater research model. USP2008097428870.
- Wayne V. Spate ; Robert J. Adams ; Donald P. Williams. Articulated nose missile control actuation system. USP2002046364248.
- Kranz Walter (Taufkirchen DEX). Flight path control apparatus for missiles. USP1990054925130.
- Domzalski David B. ; Straub Friedrich K. ; Kennedy Dennis K.. Helicopter rotor blade flap actuator government interest. USP2000106135713.
- Roger P. Berry ; Daniel F. Lawless ; Stephen C. Cayson ; Lamar M. Auman. Magnetostrictive missile guidance system. USP2002106467722.
- Facciano, Andrew B.; Moore, Robert T.; Hlavacek, Gregg J.; Seasly, Craig D.. Missile airframe and structure comprising piezoelectric fibers and method for active structural response control. USP2011118049148.
- Kaiserman, Michael J.; Rodack, Michael T.; Schneider, Arthur J.; Spate, Wayne V.; Weesner, Jennifer B.; Winetrobe, Stanton L.. Modular missile and method of assembly. USP2003056568330.
- Head Robert E. (Tempe AZ). Piezoelectric actuator. USP1997055626312.
- Facciano, Andrew B.; Moore, Robert T.; Hlavacek, Gregg J.; Seasly, Craig D.. Piezoelectric fiber, active damped, composite electronic housings. USP2010087767944.
- Komerath Narayanan M. ; Darden Leigh Ann ; Magill John C. ; Peterson Kevin G.. Stagnation point vortex controller. USP1998085794887.
- Malmuth, Norman D.; Fedorov, Alexander; Shalaev, Vladimir; Zharov, Vladimir; Shalaev, Ivan; Maslov, Anatoly; Soloviev, Victor. Surface plasma discharge for controlling forebody vortex asymmetry. USP2004096796532.
- Clingman, Dan J.. System and method for controlling high spin rate projectiles. USP2010117834301.
- Yu-Hang Ho. System and method for deflecting an aerodynamic control surface. USP2002116481667.
- Tyree, Anthony K.. System and method for navigating an object. USP2013088502126.
