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W2072212813 abstract "Maintaining cryogenic fluorine at a -189 C during the interplanetary cruise period to Mars is a major thermal problem. At this low temperature the heat rejection by radiation is severely limited and the allowable thermal load to the fluorine tank is less than approximately 8 watts. Previous studies generally constrain the spacecraft to an inline tank configuration which tends to maximize the fluorine tank's view and heat rejection to space. With the Inertial Upper Stage, sufficient stack height may not be available on the Shuttle for an inline tank configuration. Therefore, this study addresses the more thermally constraining side by side tank configuration." @default.
W2072212813 created "2016-06-24" @default.
W2072212813 creator A5035135554 @default.
W2072212813 date "1978-05-24" @default.
W2072212813 modified "2023-10-02" @default.
W2072212813 title "Thermal analysis of a high energy propulsion system /hydrazine and liquid fluorine/ for a rover class Mars Orbiter" @default.
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W2072212813 doi "https://doi.org/10.2514/6.1978-888" @default.
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