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특허 상세정보

Steerable, intermittently operable rocket propulsion system

국가/구분 United States(US) Patent 등록
국제특허분류(IPC7판) F02K-009/00   
미국특허분류(USC) 060/253; 060/204
출원번호 US-0728733 (2003-12-05)
등록번호 US-7281367 (2007-10-16)
발명자 / 주소
출원인 / 주소
대리인 / 주소
    TraskBritt
인용정보 피인용 횟수 : 12  인용 특허 : 18
초록

A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a solid fuel propellant may be used to release combustion products for creating axial thrust. A plurality of proportional maneuver control valves in communication with the pressure vessel and having associated maneuver control thrusters may be selectively actuated in different modes of operation...

대표
청구항

What is claimed is: 1. A propulsion system, comprising: a pressure vessel containing a propellant, wherein the propellant comprises at least one solid propellant grain; at least one axial thrust valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propellant within the pressure vessel to directly provide axial thrust; and at least one maneuver control valve in communication with the pressure vessel and configured for selectively releasing gases generated by combustion of the propel...

이 특허에 인용된 특허 (18)

  1. Douglass, Randle; Jacquin, H. George; Chewey, Paul M.; Galvan, Paul A.; Naragon, Richard S.. Dual pressure solid propellant control system. USP1985114550888.
  2. Kirschner ; Jr. Thomas J. (Port Deposit MD). Gas generator or rocket motor with selective discrete time vs. output profiles. USP1977034011720.
  3. Herbert Stephen Jones ; Joseph Paul Arves ; Darren Andrew Kearney ; Ryan Earl Roberts ; Rory Nell McLeod. Hybrid injection thrust vector control. USP2002036354074.
  4. Herbert Stephens Jones ; Joseph Paul Arves ; Darren Andrew Kearney ; Ryan Earl Roberts ; Rory Nell McLeod. Hybrid injection thrust vector control. USP2002106470669.
  5. Rolf E. Hamke ; Eric M. Rohrbaugh. Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines. USP2002056393830.
  6. Smirra Karl,DEX. Lateral-thrust control arrangement for missiles with solid-fuel hot-gas generator. USP2001096289669.
  7. Fling Michael (Mesa AZ) Puckett William R. (Decatur AL). Membrane seal for application to pulsed rocket motors. USP1989094866930.
  8. Jacobson Michael D. ; Burgner Gary R.. Multi-ignition controllable solid-propellant gas generator. USP2001066250072.
  9. McDonald Allan J. (Pleasant View UT). Multiple propellant solid rocket motor. USP1989064840024.
  10. Kevin W. Smith ; Theodore C. Slack, Jr. ; Korey R. Kline ; Thomas O. Bales, Jr.. Propulsion system containing a mixed-phase propellant and a method for propelling an object with the same. USP2002046367244.
  11. LeFebvre Clarence A. (San Jose CA). Reduction of depressurization thrust termination jolt. USP1976123999379.
  12. Onojima, Noboru; Tezuka, Hitoshi; Osada, Akira; Yamaguchi, Ichiro. Side thruster of flying object. USP2003016502384.
  13. Johnston Ian M.,GB2 ; Gill Raymond C.,GB2. Solid propellant combustion apparatus. USP1998095808231.
  14. Dombrowski Daniel C. (Elkton MD) Frey Thomas J. (Elkton MD) Nevrincean Andrew G. (Elkton MD) Carr ; Jr. Clyde E. (Lincoln University PA). Solid propellant dual pulse rocket motor loaded case and ignition system and method of manufacture. USP1997025600946.
  15. Goddard Charles W. (San Jose CA) Lucas John T. (Los Altos CA) Galvan Paul A. (San Jose CA). Solid-propellant-powered maneuvering system for spacecraft. USP1991115062593.
  16. Dillinger Robert B. (Ridgecrest CA) Stone W. James (China Lake CA). Steerable extraction rocket. USP1977044017040.
  17. Denoel Jean Denis,FRX ; Dumortier Andre,FRX. System for controlling a space vehicle by gating gas. USP1998065765367.
  18. Bennett James (Stevenage GBX) Heath Martin R. (Stevenage GBX) Foulsham Peter G. (Stevenage GBX). Thruster system. USP1989054826104.

이 특허를 인용한 특허 피인용횟수: 12

  1. Olden, Thomas A.; Wrigglesworth, Walter. Flight vehicles including electrically-interconnective support structures and methods for the manufacture thereof. USP2014098826640.
  2. Kishida, Tomohiro; Tsunezumi, Yukihiro; Mihara, Chiyako; Suzuki, Tasuku; Ieki, Katsunori. Ignition device for two-pulse rocket motor with thermal barrier membrane. USP2016069371801.
  3. Caubet, Pascal; Ferrant, Aurore. In-flight attitude control and direct thrust flight control system of a vehicle and craft comprising such a system. USP2015119194332.
  4. Olden, Thomas A.; Cavalleri, Robert J.. Modular divert and attitude control system. USP2012088242422.
  5. Mihara, Chiyako; Suzuki, Tasuku; Ieki, Katsunori. Multi-pulse rocket motor and pulse unit thereof. USP2017079702320.
  6. Olden, Thomas A.; Cavalleri, Robert J.. Pellet-loaded multiple impulse rocket motor. USP2014038667776.
  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. Vuillamy, Didier; Gazave, Robert. Rocket engine nozzle system. USP2012098266887.
  9. Olden, Thomas A.; Wrigglesworth, Walter. Systems and methods for composite structures with embedded interconnects. USP2014088809689.
  10. Mihara, Chiyako; Suzuki, Tasuku; Ieki, Katsunori. Three-pulse gas generator and operation method thereof. USP20180610006408.
  11. Hill, David G.. Turbine powered electromechanical actuation system. USP2014058727284.
  12. Suzuki, Tasuku; Mihara, Chiyako; Ieki, Katsunori. Two-pulse gas generator and operation method thereof. USP20190410247139.