Spacecraft power system architecture to mitigate spacecraft char

Details Spacecraft power system architecture to mitigate spacecraft char Spacecraft power system architecture to mitigate spacecraft char

1995-08-10

1997-01-14

Nguyen, Matthew V.

Electricity: power supply or regulation systems

Output level responsive

Using a three or more terminal semiconductive device as the...

G05F 156

Patent

active

055943250

ABSTRACT:
A power system architecture for a spacecraft and a method of a power supply for a spacecraft are presented which take advantage of the reduced plasma interaction associated with positive ground high voltage photovoltaic arrays and provide a negative ground power supply for electrical loads of the spacecraft. They efficiently convert and regulate power to the load bus and reduce power system mass and complexity. The system and method ground the positive terminal of the solar arrays to the spacecraft hull, and using a power converter to invert the electric sign, permit a negative ground for the electrical distribution bus and electrical components. A number of variations including a load management system and a battery management system having charging and recharging devices are presented.

REFERENCES:
patent: 4691159 (1987-09-01), Ahrens et al.
patent: 4899269 (1990-02-01), Rouzies
patent: 5394075 (1995-02-01), Ahrens et al.
patent: 5444358 (1995-08-01), Delepaunt
patent: 5451858 (1995-09-01), Van Duyne et al.
NASA Technical Memorandum 103717, Findings of the Joint Workshop on Evaluation of Impacts of Space Station Freedom Ground Configurations, Dale C. Ferguson, David B. Snyder R. Carruth Oct. 9, 1990.
Sputtering and SSF Implications, D. C. Ferguson Aerospace Technology Research Project Review NASA Lewis Research Center, Aerospace Technology Directora Power Technology Division Mar. 6, 1991.

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