$\require{mediawiki-texvc}$
  • 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"
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

Orbit attitude control device, and method of controlling orbit attitude

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) B64G-001/26    B64G-001/36    F02K-009/86   
출원번호 US-0018667 (2013-09-05)
등록번호 US-9242745 (2016-01-26)
우선권정보 JP-2012-260142 (2012-11-28)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Wenderoth, Lind & Ponack, L.L.P.
인용정보 피인용 횟수 : 0  인용 특허 : 17
초록

An orbit attitude control device includes a divert thruster including a plurality of nozzles. First group nozzles inject combustion gas in opposite directions along a first axis. Second group nozzles inject combustion gas in opposite directions along a second axis. A control section calculates correction values for opening degree commands based on a detection value of a pressure of the combustion chamber and a command value of the pressure, and corrects the opening degree command values by the correction values. The device further includes a first axis a...

대표
청구항

1. An orbit attitude control device, comprising: a pressure sensor configured to detect a pressure of a combustion chamber to generate a pressure detection value;a first axis acceleration sensor configured to detect an acceleration in a first axis direction as a first axis acceleration;a second axis acceleration sensor configured to detect an acceleration in a second axis direction as a second axis acceleration;a plurality of nozzles respectively having a plurality of valves and configured to emit combustion gas generated in said combustion chamber throu...

이 특허에 인용된 특허 (17)

  1. Douglass, Randle; Jacquin, H. George; Chewey, Paul M.; Galvan, Paul A.; Naragon, Richard S.. Dual pressure solid propellant control system. USP1985114550888.
  2. Uken Arthur H. (Brigham City UT). Energy efficient solid propellant attitude control system. USP1988114786019.
  3. Smith Peter (Portsmouth GB2). Gas thruster. USP1988114787579.
  4. Rolf E. Hamke ; Eric M. Rohrbaugh. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines. USP2002056393830.
  5. Chilan, Christian. Method for maintaining pose of spacecraft. USP2012088244417.
  6. Morris Joseph W. (Rancho Cordova CA) Carlson Russell W. (Folsom CA) Peterson Kevin L. (Sacramento CA) Reich Edward M. (Orangevale CA). Multiple pintle nozzle propulsion control system. USP1995105456425.
  7. Preston, Kenneth G.; Leal, Michael A.; Wilson, Rondell J.; Hussey, Richard C.. Propulsion and maneuvering system with axial thrusters and method for axial divert attitude and control. USP2014058735788.
  8. Blount Dale H. (Huntsville AL). Propulsion apparatus and method using boil-off gas from a cryogenic liquid. USP1986044585191.
  9. Cover, Cary Lee; Stroud, Sean Scott; Piovoso, Michael Joseph; Kelly, Timothy James. Propulsion thrust control system and method. USP2010057716912.
  10. Baker, Mark H.; Abel, Steve; Woessner, George. Solid propellant gas control system and method. USP2013098528316.
  11. Michael F. Barsky ; Thomas M. Tanner ; Loren I. Slafer ; Paul D. Williams ; George B. Semeniuk ; Joseph M. Allard GB. Stationkeeping method utilizing open-loop thruster pulses and closed-loop authority limited momentum storage devices. USP2002016340138.
  12. Mayersak Joseph R. (Ashburn VA). Thrust maneuver system. USP1995105456429.
  13. Smith Peter (Portsmouth GB2). Thrusters. USP1989024802333.
  14. Abel, Stephen G.; Christensen, Donald J.. Two stage gas pilot valve controlling gas flow to a reaction jet nozzle. USP2003076598385.
  15. Barkats Grard (Lotissement Persepolis ; Domaine de Candou 06530 Peymeinade FRX). Two-liquid propulsive system for an artificial satellite and utilization of said system for ejecting the satellite. USP1990054923152.
  16. Voigt Allan A.. Variable coupling arrangement for an integrated missile steering system. USP2001116315239.
  17. Wang Qinghong W. ; Barsky Michael F.. Wobble and nutation control, and spin stabilization for a spacecraft using momentum conserving devices. USP2000056062512.

이 특허 조회수 및 차트

  • 상단의 제목을 클릭 시 조회수 및 차트가 조회됩니다.