TPX for In-Orbit Demonstration of Two-Phase Heat Transport Technology-Evaluation of Flight &amp; amp; Post-Flight Experiment Results

Delil, A.A.M.; Heemskerk, J.F.; Mastenbroek, O.; Dubois, M.; Oost, Stéphane Van; Coesel, M.; Supper, W.; Aceti, R.

doi:10.4271/951510

Cited by 20 publications

(12 citation statements)

References 7 publications

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“…By combining cross-sections of figures like 7 (Hamme, 1997) one can create flow pattern maps for a chosen g-level. A comparison of the latter two maps and maps produced during the Cyrene experiment (Lebaigue, 1998) and TPX I (Delil et al, 1995) indicate that they partly contradict each other. A comparison between the figures suggests that the transition to annular flow occurred in these three systems more or less at the same j v -value 0.2-0.25 m/s, but at different j l -values.…”

Section: Flow Pattern Issuesmentioning

confidence: 92%

“…-The development of two-phase (R114, NH 3 , ethanol, and CO 2 ) test rigs for experimentation and calibration of components developed (vapour quality sensors, a high-efficiency low pressure drop condenser, (in-)direct radiators. -Development, testing, the in-orbit demonstration of two-phase technology, and the evaluation of flight results of ESA's In-Orbit Technology Demonstration TPX (Delil 1995) and the Loop Heat Pipe Flight eXperiment (Bienert 1998). The latter was by a team led by Dynatherm, consisting of the Naval Research Laboratory and two USAF Laboratories, BMDO, three NASA Institutes, Hughes Space & Communications, and NLR.…”

Section: Figure 2 Schematic Of Mechanically Pumped Two-phasementioning

confidence: 99%

“…Therefore several in-orbit experiments were carried out. 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%

“…Such thermal management systems for future large spacecraft have to transport large amounts of dissipated power (gathered at many dissipating stations) over large distances to the heat sinks, the radiator(s), where the heat is radiated to the cold space environment. Pumping pressures can be achieved by mechanical (powered) pumps, capillary action or other means, like osmotic pumps/compressors (Almgren, 1981;Stalmach, 1982;Delil, 1984Delil, , 1995. Conventional single-phase thermal busses are mechanically pumped.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

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: Flow Pattern Issuesmentioning

confidence: 92%

Section: Figure 2 Schematic Of Mechanically Pumped Two-phasementioning

confidence: 99%

Section: Figure 2 Schematic Of Mechanically Pumped Two-phasementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

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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“…Small-scale CPLs were tested inside the GAS (get away special) cylindrical container. This is the case of the CPL1, 2 tested in June 1985, and of the European TPX (two-phase experiment), 3 tested in February 1994. The power was supplied by batteries, which were experiment dedicated and located inside the container.…”

Section: Literature Reviewmentioning

confidence: 99%

Solar Absorber Plates: Design and Application to Microgravity Capillary-Pumped-Loop Experiments

Mantelli

Bazzo

2000

Journal of Spacecraft and Rockets

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An absorber plate is proposed to collect solar energy to be supplied to experiments in space. Its performance depends on the geometry of the satellite, on the incident environmental heat loads (solar, albedo, and Earth infrared radiation), and on the temperature level of the plate, which is usually an outcome of the microgravity experiment. A steady-state mathematical model is proposed to estimate the temperature distribution along the plate. Finite difference numerical models are developed for the steady-state and transient conditions and compared with the analytical model. Average temperatures and the net heat absorbed are determined. An experimental setup is developed to generate data to be compared with the theoretical models. A good agreement is observed among the experimental data, the analytical, and the numerical results. The procedure is applied to the small-scale capillarypumped-loop experiment, which will y aboard the French Brazilian Microsatellite. This experiment is described. Solar absorbers can be considered as a reliable alternative to improve the available heat power for experiments in space. Nomenclaturea = half the length of the capillary pump, m B = bias error b = half the length of the border of the plate, x direction, m C n , CC n = integration constant (n variable) C p = speci c heat, constant pressure, kW/kg¢ K c = half the length of the border of the plate, y direction, m d f = degrees of freedom h r = radiative heat transfer coef cient, W/m 2 ¢ K k = thermal conductivity, W/m¢ K; time-iteration counting variable m, n = node numbering (x and y directions, respectively) N = maximum number of series terms, number of elements P = electrical power, W q = thermal power, W/m 2 R = electrical resistance, X S = environmental total heat load, W/m 2 ; standard deviation T = temperature, K T f = uid temperature, K T s = space temperature, K t = thickness of the plate, m; time, s; Student t multiplying factor U = uncertainty interval V = voltage, V x, y, z = orthogonal directions, Cartesian system a = absorptivity ² = emissivity h , H , U , W = temperature difference, (T ¡ T f ) k , l = eigenvalue q = density, kg/m 3 r = Stefan-Boltzmann constant, 5.67 £ 10 ¡ 8 W/m 2 ¢ K 4

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Capillary heat loop technology: Space applications and recent Canadian activities

Wang

Mishkinis

Nikanpour

2008

Applied Thermal Engineering

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TPX for In-Orbit Demonstration of Two-Phase Heat Transport Technology-Evaluation of Flight & amp; Post-Flight Experiment Results

Cited by 20 publications

References 7 publications

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

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

Solar Absorber Plates: Design and Application to Microgravity Capillary-Pumped-Loop Experiments

Capillary heat loop technology: Space applications and recent Canadian activities

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