Hybrid propulsion system
Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer t...
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Main Authors | , |
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Format | Patent |
Language | English |
Published |
04.07.2006
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Online Access | Get full text |
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Abstract | Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the nozzle. A pressure regulator is coupled to the conduit and is interposed between the supply of oxidizer and the nozzle, wherein the pressure regulator regulates the pressure of oxidizer flowing through the conduit and downstream of the pressure regulator to a pressure at or below the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the nozzle. The conduit supplies oxidizer from the supply of oxidizer to a hybrid rocket motor. |
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AbstractList | Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direction from the supply of oxidizer toward and into the nozzle. A pressure regulator is coupled to the conduit and is interposed between the supply of oxidizer and the nozzle, wherein the pressure regulator regulates the pressure of oxidizer flowing through the conduit and downstream of the pressure regulator to a pressure at or below the pressure required to maintain the oxidizer in a gas state to ensure that the any oxidizer flowing through the conduit is in a gas state prior to entering the nozzle. The conduit supplies oxidizer from the supply of oxidizer to a hybrid rocket motor. |
Author | Macklin, Frank Grainger, Chris |
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References | Schuler et al. (5099645) 19920300 Jones (5572864) 19961100 Smith (4802333) 19890200 Knuth et al. (6601380) 20030800 Smith et al. (5715675) 19980200 Knuth et al. (5010730) 19910400 Holzman (4424679) 19840100 Fix et al. (3507296) 19700400 Kline et al. (6679049) 20040100 Whitehead et al. (5026259) 19910600 Jacobson et al. (6250072) 20010600 Hamke et al. (6393830) 20020500 Space Daily "Surrey Fires Micro Electric Thruster," Oct. 25, 1999, http://www.spacedaily.com/news/microsat-99j.html, viewed Mar. 8, 2006. Apfel (4880185) 19891100 Kline et al. (6640536) 20031100 Kline et al. (6684625) 20040200 |
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Snippet | Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the... |
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