Design of Accumulators and Liquid/Gas Charging of Single Phase Mechanically Pumped Fluid Loop Heat Rejection Systems

Bhandari, Pradeep; Dudik, Brenda; Birur, Gajanana C.; Karlmann, Paul; Bame, David; Mastropietro, A. J.

doi:10.2514/6.2012-3515

Cited by 4 publications

(2 citation statements)

References 6 publications

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“…The local liquid pressure minus the saturation vapor pressure must be greater than the net positive suction head to avoid pump cavitation and damage to the impeller to ensure adequate pump performance. 1 The system is designed to accommodate small leaks with excess working fluid stored in the accumulator. Acceptable leak rates, verified during the build process, are determined based on this excess accumulator fluid volume, mission life, and quantity of potential leak locations.…”

Section: Leak Mitigationmentioning

confidence: 99%

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

Miller

Birur

Bame

et al. 2013

43rd International Conference on Environmental Systems

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Mechanically pumped fluid loops (MPFLs) are increasingly considered for spacecraft thermal control. A concern for long duration space missions is the leak of fluid leading to performance degradation or potential loop failure. An understanding of leak rate through analysis, as well as destructive and non-destructive testing, provides a verifiable means to quantify leak rates. The system can be appropriately designed to maintain safe operating pressures and temperatures throughout the mission. Two MPFLs on the Mars Science Laboratory Spacecraft, launched November 26, 2011, maintain the temperature of sensitive electronics and science instruments within a -40°C to 50°C range during launch, cruise, and Mars surface operations. With over 100 meters of complex tubing, fittings, joints, flex lines, and pumps, the system must maintain a minimum pressure through all phases of the mission to provide appropriate performance. This paper describes the process of design, qualification, test, verification, and validation of the components and assemblies employed to minimize risks associated with excessive fluid leaks from pumped fluid loop systems. NomenclatureCFC = Chlorofluorocarbon CHRS = Cruise Heat Rejection System CIPAS = Cruise Integrated Pump Assembly System FEM = Finite Element Model GHe = Gaseous Helium HRS = Heat Rejection System JPL = Jet Propulsion Laboratory MMPDS = Metallic Materials Properties Development and Standardization MMRTG = Multi-Mission Radioisotope Thermoelectric Generator MPFL = Mechanically Pumped Fluid Loop MSL = Mars Science Laboratory RAMP = Rover Avionics Mounting Plate RHRS = Rover Heat Rejection System RIPAS = Rover Integrated Pump Assembly System SCC = Standard Cubic Centimeter

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Section: Leak Mitigationmentioning

confidence: 99%

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

Miller

Birur

Bame

et al. 2013

43rd International Conference on Environmental Systems

Self Cite

View full text Add to dashboard Cite

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“…Papers describing the function of the Rover HRS in detail have been previously published. [1][2][3][4][5][6][7][8] Figures 7 and 8 are schematics showing the HRS system and its major components. In the cold case, the HRS pumps liquid Freon through tubes in hot plate heat exchangers, located on either side of the MMRTG, to pick up radiated waste heat from the MMRTG and bring it into the RAMP.…”

Section: B Brief Description Of Msl Rover Thermal Designmentioning

confidence: 99%

Thermal Performance of the Mars Science Laboratory Rover During Mars Surface Operations

Novak

Kempenaar

Liu

et al. 2013

43rd International Conference on Environmental Systems

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On November 26, 2011, NASA launched a large (900 kg) rover as part of the Mars Science Laboratory (MSL) mission to Mars. Eight months later, on August 5, 2012, the MSL rover (Curiosity) successfully touched down on the surface of Mars. As of the writing of this paper, the rover had completed over 200 Sols of Mars surface operations in the Gale Crater landing site (4.5°S latitude). This paper describes the thermal performance of the MSL Rover during the early part of its two Earth-0.year (670 Sols) prime surface mission. Curiosity landed in Gale Crater during early Spring (Ls=151) in the Southern Hemisphere of Mars. This paper discusses the thermal performance of the rover from landing day (Sol 0) through Summer Solstice (Sol 197) and out to Sol 204. The rover surface thermal design performance was very close to pre-landing predictions. The very successful thermal design allowed a high level of operational power dissipation immediately after landing without overheating and required a minimal amount of survival heating. Early morning operations of cameras and actuators were aided by successful heating activities. MSL rover surface operations thermal experiences are discussed in this paper. Conclusions about the rover surface operations thermal performance are also presented.

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A highly self-adaptive cold plate for the single-phase mechanically pumped fluid loop for spacecraft thermal management

Wang

Zhang

et al. 2016

Energy Conversion and Management

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Design of Accumulators and Liquid/Gas Charging of Single Phase Mechanically Pumped Fluid Loop Heat Rejection Systems

Cited by 4 publications

References 6 publications

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

Leak Mitigation in Mechanically Pumped Fluid Loops for Long Duration Space Missions

Thermal Performance of the Mars Science Laboratory Rover During Mars Surface Operations

A highly self-adaptive cold plate for the single-phase mechanically pumped fluid loop for spacecraft thermal management

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