Pressurizer for a rocket engine

Power plants – Reaction motor – Liquid oxidizer

Reexamination Certificate

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Details

C060S257000, C417S393000, C417S401000

Reexamination Certificate

active

07082750

ABSTRACT:
A pressurizer for pressurizing a fluid includes: at least two storage tanks, where, for each storage tank, the pressurizer further includes: a propellant entrance valve, a propellant exit valve, a pressurant entrance valve, and a pressurant exit valve, where each of the storage tanks is configured to be filled with the fluid under a low pressure when its propellant entrance and pressurant exit valves are open and its propellant exit and pressurant entrance valves are closed, and to be drained of the fluid under a high pressure by the force of a pressurant when its valves are reversed, where its valves are configured to be opened and closed in a cycle to sequentially fill and drain the storage tank of the fluid, the cycle having a cycle time of between 1 and 500 milliseconds, and where the cycles of the valves of the storage tanks are out of phase with each other such that at some time in which one storage tank is being filled with the fluid, at least one other storage tank is being drained of the fluid. The pressurizer may be used as a propellant pump in a rocket engine.

REFERENCES:
patent: 2505798 (1950-05-01), Skinner
patent: 2701441 (1955-02-01), Mitchell
patent: 2898735 (1959-08-01), Carmody et al.
patent: 3213804 (1965-10-01), Sobey
patent: 3283508 (1966-11-01), Schulze
patent: 3302406 (1967-02-01), Braue, Jr.
patent: 3350886 (1967-11-01), Ferand et al.
patent: 3367271 (1968-02-01), Wilson
patent: 3400536 (1968-09-01), Richardson
patent: 3945203 (1976-03-01), Kayser
patent: 4880185 (1989-11-01), Apfel
patent: 5205722 (1993-04-01), Hammond
patent: 5471833 (1995-12-01), Pahl
patent: 5582001 (1996-12-01), Bradford et al.
patent: 5839463 (1998-11-01), Blackmon
patent: 5961074 (1999-10-01), Dunn
patent: 6213348 (2001-04-01), Le Grouyellec
patent: 6314978 (2001-11-01), Lanning
patent: 6325159 (2001-12-01), Peterman et al.
patent: 6499288 (2002-12-01), Knight
patent: 6505691 (2003-01-01), Judge et al.
patent: 6751945 (2004-06-01), Knight
Steve Harrington, “Pistonless Dual Chamber Rocket Fuel Pump”, AIAA-LA Section/SSTC Responsive Space Conference 2003-6003.
J. C. Whitehead, “Mars Ascent Propulsion Options for Small Sample Return Vehicles”, Jul. 1997, AIAA 97-2950.
J. C. Whitehead et al, Pumped Hydrazine Miniaturized Propulsion System; Jul. 1989, AIAA 89-2958.
J. C. Whitehead, “Free Piston Pumps for Miniature Rocket Propulsion”, Jun. 1991, AIAA 91-1837.
J. C. Whitehead, “Demand Thrust Pumped Propulsion with Automatic Warm Gas Valving”, Jul. 1992, AIAA 92-3539.
J.C. Whitehead, “Test Results for a Reciprocating Pump Powered by Decomposed Hydrogen Peroxide,” Jul. 2001, AIAA-2001-3839.
J.C. Whitehead, “Hydrogen Peroxide Gas Generator Cycle with a Reciprocating Pump”, Jul. 2002, AIAA 2002-3702.
J.C. Whitehead et al, “Design and Flight Testing of a Reciprocating Pump Fed Rocket,” Jun. 1994, AIAA 94-3031.
D.E. Eddleman et al, “Reciprocating Feed System for Advanced Space Propulsion Systems”, Apr. 2004, AIAA Student Conference.
W. Hammack, “XCOR Aerospace Announces New Rocket Engine Pump Design”, Apr. 27, 2002, www.xcor.com.
W. Hammack, “XCOR Passes Major Milestone on DARPA Piston Pump Contract”, Sep. 26, 2003, www.xcor.com.

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