Emerging Loop Heat Pipe Applications for Small-Sat, MARS Mission and ISS

Bodendieck, Frank; Schlitt, R.; Brand, Oliver; Labuhn, Dirk; Goncharov, K. A.; Golovin, Vladimir Kalesnikovand Oleg

doi:10.4271/2002-01-2464

Cited by 4 publications

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“…Examples are: ESA's Two-Phase eXperiment TPX I (Delil et al, 1995), NASA's CApillary Pumped Loop experiments CAPL 1&2&3 (Butler, 1995;Ottenstein, 2002), the Loop Heat Pipe Flight eXperiment LHPFX (Bienert, 1998), the all US Loop Heat Pipe with Ammonia ALPHA, the Cryogenic Capillary Pumped Loop CCLP (Hagood, 1998) and the Two-Phase Flow experiment TPF (Ottenstein, 1998). Other experiments are planned for future flights: A re-flight of TPF (with a miniature LHP as piggy bag), the French technology demonstration satellite STENTOR (Amadieu, 2001), COM2PLEX (Bodendieck et al, 2002).…”

Section: Figure 2 Schematic Of Mechanically Pumped Two-phasementioning

confidence: 99%

Tutorial on Quantification of Differences between Single- and Two-Component Two-Phase Flow and Heat Transfer

Delil¹

2003

AIP Conference Proceedings

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Section: Figure 2 Schematic Of Mechanically Pumped Two-phasementioning

confidence: 99%

Tutorial on Quantification of Differences between Single- and Two-Component Two-Phase Flow and Heat Transfer

Delil¹

2003

AIP Conference Proceedings

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Thermal Control of Spacecraft

Savage

2011

Spacecraft Systems Engineering

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INTRODUCTIONSpacecraft thermal control-that is the control of spacecraft equipment and structural temperatures-is required for two main reasons: (1) electronic and mechanical equipment usually operate efficiently and reliably only within relatively narrow temperature ranges and (2) most materials have non-zero coefficients of thermal expansion and hence temperature changes imply thermal distortion.Spacecraft equipment is designed to operate most effectively at or around room temperature. The main reason for this is that most of the components used in spacecraft equipment, whether electronic or mechanical, were originally designed for terrestrial use. It is also much easier and cheaper to perform equipment development and, eventually, qualification and flight acceptance testing at room temperature. Typically, operating electronic equipment requires to be maintained in a temperature range between about −15 • C and +50 • C, rechargeable batteries between about 0 • C and +20 • C and mechanisms (solar array drives, momentum wheels, gyroscopes etc.) between about 0 • C and +50 • C. There are, of course, exceptions to this-for example, some detectors within astronomical telescopes that need to be cooled to very low temperatures.Many spacecraft payloads require very high structural stability, and therefore thermally induced distortion must be minimized or strictly controlled. For example, the search for ever-higher resolution from space-based telescopes means that temperatures stable to within a fraction of a Kelvin are often required within telescope systems several metres in size.Heat is generated both within the spacecraft and by the environment. Components producing heat include rocket motors, electronic devices and batteries. Initial ascent heating effects are minimized by the launch vehicle's nose fairing. Heat from the space environment is largely the result of solar radiation. Heat is lost from the spacecraft by radiation. The balance between heat gained and lost will determine the spacecraft temperatures.

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