$\require{mediawiki-texvc}$
  • 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"

과학기술 지식인프라 ScienceON

상세검색 다국어 입력
도움말도움말
쳇봇 이모티콘
안녕하세요!
ScienceON 챗봇입니다.
궁금한 것은 저에게 물어봐주세요.

특허 상세정보

MyON담기
내보내기

Dual pressure solid propellant control system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F41G-007/00   
미국특허분류(USC) 244/003.22; 244/169
출원번호 US-0392830 (1982-06-28)
발명자 / 주소
대리인 / 주소
    Beers, R. F.Curry, C. D.Daubenspeck, W. C.
인용정보 피인용 횟수 : 22  인용 특허 : 0
초록

A dual pressure solid propellant control system capable of operating at temperatures of approximately 3000° F. and at multiple pressures. A solid propellant gas generator is connected to a plurality of valve clusters by a manifold, the valves and manifold being of a high temperature material and each valve being independently operable. A pressure feedback loop maintains the system pressure at a commanded value by effectively increasing or decreasing the gas exit area by varying the pulse duration modulation of the valves.

대표
청구항
▼

1. A method for controlling the attitude and velocity of an aerospace platform having a post boost control system of the type including (1) a solid propellant gas generator for providing a hot gas output, the burn rate of said propellant being related directly to the pressure of said gas output so that the rate of said gas output is directly related to the gas pressure of said gas output, (2) valve clusters disposed symmetrically around the platform, each said valve cluster having a first high thrust nozzle oriented to produce thrust in a first direction...

이 특허를 인용한 특허 피인용횟수: 22

  1. Bchele-Buecher Sigfrid (Meerbusch-Strmp DEX). Device for the limitation of gas pressure in a combustion chamber provided inside a projectile. USP1989024803925.
  2. Dulligan, Michael; Lake, James; Adkison, Paul; Spanjers, Greg; White, David; Nguyen, Hieu. Electrically controlled extinguishable solid propellant motors. USP2010097788900.
  3. Uken Arthur H. (Brigham City UT). Energy efficient solid propellant attitude control system. USP1988114786019.
  4. Hallum, Charles E.. Integrated valve assembly. USP199209H001098.
  5. Perdu Michel (Frejus FRX). Method and system for monitoring the propellant consumption of a space vehicle. USP1990124979119.
  6. Dulligan, Michael; Lake, James; Adkison, Paul; Spanjers, Greg; White, David; Nguyen, Hieu. Methods of controlling solid propellant ignition, combustion, and extinguishment. USP2010087770380.
  7. Cover, Cary Lee; Stroud, Sean Scott; Piovoso, Michael Joseph; Kelly, Timothy James. Methods of controlling thrust in a rocket motor. USP2013098539751.
  8. Samario Edward J. (Los Gatos CA). Modified null flow modulator. USP1987054662581.
  9. Fujita, Toshiharu; Hayakawa, Nobuaki. Orbit attitude control device, and method of controlling orbit attitude. USP2016019242745.
  10. Fujita, Toshiharu; Hayakawa, Nobuaki. Orbit attitude control device, and method of controlling orbit attitude. USP2016109469419.
  11. Fujita, Toshiharu; Hayakawa, Nobuaki. Orbit attitude control device, and method of controlling orbit attitude. USP2017079696726.
  12. Fujita, Toshiharu; Hayakawa, Nobuaki. Orbit attitude control device, and method of controlling orbit attitude. USP2016049302790.
  13. Fujita, Toshiharu; Hayakawa, Nobuaki. Orbit attitude control device, and method of controlling orbit attitude. USP2016069365300.
  14. Starken, George M.. Post boost control power assembly. USP2011017875838.
  15. Mayersak Joseph R.. Precision guidance system for aircraft launched bombs. USP2001076254031.
  16. Dunn Michael J. (Auburn WA). Projectile with integrated propulsion system. USP1987124711414.
  17. 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.
  18. Cover, Cary Lee; Stroud, Sean Scott; Piovoso, Michael Joseph; Kelly, Timothy James. Propulsion thrust control system and method. USP2010057716912.
  19. Singer Victor (Newark DE) Kerrigan Barry E. (Newark DE). Rocket propelled vehicle forward end control method and apparatus. USP1989044819426.
  20. Baker, Mark H.; Abel, Steve; Woessner, George. Solid propellant gas control system and method. USP2013098528316.
  21. Rohrbaugh,Eric M.; White,Jeffrey M.. Steerable, intermittently operable rocket propulsion system. USP2007107281367.
  22. Smith, Gregory H.; Martinez, Julio C.; Teran, Fernando C.; Reyes, Romy Andrade; Pauley, B. Wayne; Watkins, Randall W.. Valve controller for pressure stabilization. USP2017059650996.

IPC 상위 출원인

이 특허 조회수 및 차트

  • 상단의 제목을 클릭 시 조회수 및 차트가 조회됩니다.