Aeronautics and astronautics – Spacecraft – With fuel system details
Reexamination Certificate
1999-03-01
2001-07-31
Jordan, Charles T. (Department: 3641)
Aeronautics and astronautics
Spacecraft
With fuel system details
Reexamination Certificate
active
06267330
ABSTRACT:
TECHNICAL FIELD OF THE INVENTION
This invention relates to space launch vehicles, and more particularly to propulsion systems for space launch vehicles.
BACKGROUND OF THE INVENTION
A space launch vehicle typically has two propellant tanks, one for fuel and one for oxidizer, arranged along its longitudinal axis. This arrangement, however, leaves one tank, the second tank, between the first tank and the engine. Therefore, the feedlines that supply propellant from the first tank to the engine must avoid the second tank.
Routing the feedlines to avoid the second tank produces many problems. For example, traditional external routings produce complicated configurations having elbows where propellant can cavitate and increased length that contributes to excessive propellant boil off. In addition, these configurations typically route the feedlines outside of the vehicle's aerodynamic slipstream. The Saturn V ameliorated some of these problems by forming the feedlines integral with the second tank.
Unfortunately, integrating the feedlines with the second tank presents its own set of problems. When a large temperature differential exists between the propellants, propellant in the second tank that is near the feedlines may degrade in quality, and structural problems may develop at the seals between the feedlines and the second tank due to different thermal expansion characteristics of the feedlines, the seals, and the second tank. Also, the engine and the tanks may experience different loads during launch, producing undesirable stresses on the feedlines.
SUMMARY OF THE INVENTION
In accordance with the present invention, the disadvantages and problems associated with previous feedline designs have been substantially reduced or eliminated. The present invention provides a feedline configuration that reduces stresses on a feedline and reduces the impact of temperature differentials between propellant in the feedline and tanks.
In one embodiment, a feedline for transporting propellant from a tank of a launch vehicle to an engine includes a first conduit coupled to the tank, a second conduit coupled to the engine, and a flexible joint connecting the first conduit to the second conduit. The flexible joint provides fluid communication between the first conduit and the second conduit.
In another embodiment, a launch vehicle includes a first tank, a second tank having a passageway, an engine, and a feedline coupled to the first tank and the engine. The feedline passes through the passageway of the second tank and includes a first conduit coupled to the first tank, a second conduit coupled to the engine, and a flexible joint connecting the first conduit to the second conduit. The flexible joint provides fluid communication between the first conduit and the second conduit.
The present invention includes several important technical features and advantages. First, routing the feedline through a passageway formed by the second tank creates a short, simple feedline configuration, reducing boil off and cavitation. In addition, including a flexible joint in the feedline lessens the loads generated by the engine on certain parts of the feedline. In a particular embodiment, a gimbal may be included in the feedline to correct alignment errors and to further reduce stresses on the feedline. In other embodiments, cryogenic insulation may cover portions of the outside of the feedline to assist in preventing cold propellant in the feedline from degrading the quality of the propellant in the second tank. Other technical advantages will be readily apparent to one skilled in the art from the following figures, description, and claims.
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Patrick J. G. Steinnon, “Two Stage Launch Vehicle and Launch Trajectory Method,” Aug. 7, 1994, 18 pages.
Christensen O'Connor Johnson & Kindness PLLC
Dinh Tien
Jordan Charles T.
Kistler Aerospace Corporation
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