$\require{mediawiki-texvc}$
  • 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

Advanced designs for high pressure, high performance solid propellant rocket motors

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) C06B-045/10    C06B-045/08   
미국특허분류(USC) 14/901.99 ; 14/901.92 ; 14/901.94 ; 14/901.95 ; 14/902.0
출원번호 US-0165304 (1998-10-02)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    Intellectual Property Group Pillsbury Madison & Sutro LLP
인용정보 피인용 횟수 : 11  인용 특허 : 12
초록

A solid rocket propellant formulation with a burn rate slope of less than about 0.15 ips/psi over a substantial portion of a pressure range of about 1,000 psi to about 7,000 psi and a temperature sensitivity of less than about 0.15%/.degree. F. is provided. A high performance solid propellant rocket motor including the solid rocket propellant formulation is also provided. The rocket motor is encased in a high strength low weight motor casing which is further equipped with a nozzle throat constructed of material that has an erosion rate not more than abou...

대표
청구항

[ What is claimed is:] [1.] A solid propellant formulation comprising:from about 25% to about 55% by weight ammonium perchlorate particles having an average size of about 200 .mu.m;from about 25% to about 40% by weight ammonium perchlorate particles having an average size in a range of from about 2 .mu.m to about 50 .mu.m;from about 7% to about 15% by weight of at least one energetic polymeric binder, which further comprises a polymeric binder and an energetic plasticizer; andfrom about 1% to about 4% by weight of at least one ballistic modifier;wherein ...

이 특허에 인용된 특허 (12)

  1. Taylor ; Jr. Robert H. ; Hinshaw Carol J.. Aluminized plateau-burning solid propellant formulations and methods for their use. USP1998065771679.
  2. Wallace ; II Ingvar A. (Brigham City UT). Ambient temperature mix, cast, and cure composite propellant formulations. USP1995125472532.
  3. McCulloch Charles R. (Shalimar FL) Moy Bertram K. (Shalimar FL). Composite propellants containing critical pressure increasing additives. USP1976103986910.
  4. Taylor ; Jr. Robert H. (Harvest AL). Controlled burn rate, reduced smoke, solid propellant formulations. USP1994085334270.
  5. Corley Robert C. (Lancaster CA) Myers ; Jr. Frederick F. (Manassas VA). Copper containing ballistic additives. USP1983074391660.
  6. Chang Marguerite S. (Forest Heights MD) Mackne Richard K. (Oxon Hill MD) Mycka ; Jr. Anthony (Waldorf MD) Myers ; Jr. Carl L. (Alexandria VA). Extrusion method for obtaining high strength composite propellants. USP1988104776993.
  7. Japs ; Archie B.. Gas generator and solid propellant with a silicon-oxygen compound as a burning rate modifier, and method for making the. USP1978074099376.
  8. Martin Bernard (Ballancourt FRX) Lefumeux Alain (Orsay FRX). Ignition-sensitive low-vulnerability propellent powder. USP1995115468312.
  9. Chi Minn-Shong (New Castle DE). Low pressure exponent propellants containing boron. USP1991125074938.
  10. Stephens William D. (Vienna VA) Ashmore Charles I. (Reva VA). Solid propellant containing diferrocenyl ketone. USP1982034318760.
  11. Goleniewski John R. (Salt Lake County UT) Roberts James A. (Salt Lake County UT). Solid propellant with non-crystalline polyether/inert plasticizer binder. USP1994095348596.
  12. Taylor ; Jr. Robert H. (Harvest AL). Use of controlled burn rate, reduced smoke, biplateau solid propellant formulations. USP1996125579634.

이 특허를 인용한 특허 피인용횟수: 11

  1. Petersen, Eric; Small, Jennifer; Stephens, Metthew; Arvanetes, Jason; Seal, Sudipta; Deshpande, Sameer. Burn rate sensitization of solid propellants using a nano-titania additive. USP2011118066834.
  2. Dulligan, Michael; Lake, James; Adkison, Paul; Spanjers, Greg; White, David; Nguyen, Hieu. Electrically controlled extinguishable solid propellant motors. USP2010097788900.
  3. Chan, May L.; Turner, Alan D.. Insensitive high energy booster propellant. USP2004016682615.
  4. Chan, May L.; Turner, Alan D.. Insensitive high energy booster propellant. USP2004016682614.
  5. Chan, May L.; Turner, Alan D.. Insensitive high energy booster propellant. USP2003066576072.
  6. Dulligan, Michael; Lake, James; Adkison, Paul; Spanjers, Greg; White, David; Nguyen, Hieu. Methods of controlling solid propellant ignition, combustion, and extinguishment. USP2010087770380.
  7. Bruno, Salvatore Thomas; Koch, Christopher Anthony; Mantilla, Yazdan Paul; Prasad, Sanjay B.; Wittenauer, Jerome Paul; Yaney, Deborah Lynn; Zegarski, Joseph. Net molded tantalum carbide rocket nozzle throat. USP2003016510694.
  8. Bruno, Salvatore Thomas; Koch, Christopher Anthony; Mantilla, Yazdan Paul; Prasad, Sanjay B.; Wittenauer, Jerome Paul; Yaney, Deborah Lynn; Zegarski, Joseph. Net molded tantalum carbide rocket nozzle throat and method of making. USP2004016673449.
  9. Boyd, Durrell; Bazil, Ray. Propellant. USP2004016679959.
  10. Amtower, II,Paul K.. Propellant formulation. USP2006037011722.
  11. Petersen, Eric L.; Seal, Sudipta; Stephens, Matthew; Reid, David L.; Carro, Rodolphe; Sammet, Thomas; Lepage, Alex. Solid propellant rocket motor having self-extinguishing propellant grain and systems therefrom. USP2012128336287.