Cryogenic propellant depot and deployable sunshield

Inactive Publication Date: 2010-07-29
UNITED LAUNCH ALLIANCE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Benefits of technology

[0012]By the robust design of the present cryogenic depot and integral sunshield, inter-planetary space missions are no longer limited by launch vehicle performance. Smaller, less costly launch vehicles can be used, and space explorations can be extended much farther into the solar system. The depot of the present invent

Problems solved by technology

Space exploration is limited by a number of factors that prohibit the distance to which space vehicles can travel from the earth

Method used

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  • Cryogenic propellant depot and deployable sunshield
  • Cryogenic propellant depot and deployable sunshield
  • Cryogenic propellant depot and deployable sunshield

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Example

[0033]FIG. 1 illustrates a first embodiment of the present invention including a cryogenic propellant depot and integral sunshield system 10. A sunshield 12 is secured to a cryogenic tank 14 that is placed into earth orbit by a launch vehicle (not shown). The sunshield 12 surrounds the tank to form a truncated cone shape. The sunshield is secured to the tank adjacent an equipment deck 24, and the sunshield extends beyond a length of the tank in a diverging fashion thus forming the cone shape. The sunshield 12 can have multiple layers of reflective material 13 to provide optimum protection to the tank 14. The shield is shown broken away in FIG. 1 to illustrate the covered tank 14. The open end of the sunshield provides a view factor to deep space allowing re-radiation of energy to the cold of deep space from the sun shield and tank.

[0034]FIGS. 2 and 3 illustrate another preferred embodiment of the cryogenic propellant depot and integral sunshield system 10 of the present invention. I...

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Abstract

A cryogenic propellant depot and sunshield are provided for operation in earth orbit to fuel or refuel other space vehicles. The sunshield is deployed to effectively mitigate solar radiation emanating from the earth and the sun thereby providing a long term storage solution for cryogenic fluids prone to boil-off. The depot has supporting subsystems to include station keeping equipment and communication equipment so that the depot can be independently controlled. Inflatable booms are used to deploy the sunshield in a desired pattern around the depot.

Description

FIELD OF THE INVENTION[0001]The present invention relates to cryogenic propellant depots used for the fueling of space vehicles in earth orbit, other orbits, deep space or near celestial bodies, and more particularly, to a cryogenic propellant depot placed in space having an integral sunshield to optimize storage of liquid cryogens by shielding the depot from solar radiation.BACKGROUND OF THE INVENTION[0002]Space exploration is limited by a number of factors that prohibit the distance to which space vehicles can travel from the earth to the rest of the solar system. One obvious limitation is the size of a payload that can be placed into earth orbit and beyond. Tremendous power and fuel requirements are required to place larger payloads into earth orbit, and to then project those payloads to other locations in the solar system, such as the moon or Mars. The proposed NASA Ares-5 rocket is capable of delivering approximately 69 tons to earth escape velocity. However, NASA's current arc...

Claims

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Application Information

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IPC IPC(8): B64G1/52B64G1/64B64G1/44F17C1/00
CPCB64G1/1078B64G1/222B64G2001/224B64G1/58B64G1/402B64G1/2227
Inventor KUTTER, BERNARD FRIEDRICHZEGLER, FRANK CHARLESWILLEY, CLIFF E.LIN, JOHN K.RAGAB, MOHAMED M.DEW, MICHAEL W.
Owner UNITED LAUNCH ALLIANCE
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