Thermal Interaction Between a Heat Pipe Radiator and a Coolant Fluid Header

Karam, Robert D.; Hwangbo, Han

doi:10.1016/b978-0-08-027284-9.50049-8

Cited by 4 publications

(4 citation statements)

References 2 publications

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“…This technique is exact when saddles are negligibly small, and inaccuracies increase progressively as saddle lengths grow. Comparison with finite element solutions 43 suggests the validity of the procedure when the saddle length is about 1/50 or less of total header length.…”

Section: Application: Thermal Interaction Between a Heat Pipe Radiatomentioning

confidence: 96%

“…The sketches show a coolant fluid being continuously pumped through a header as it collects heat from a satellite and transfers it to the radiator heat pipes. The discussion is a follow-up on previous work, 43 and the object is to obtain relationships among flow and geometric parameters as a basis for sizing the radiator to satisfy a temperature specification at a given heat load and allowable pressure.…”

Section: Application: Thermal Interaction Between a Heat Pipe Radiatomentioning

confidence: 99%

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Satellite Thermal Control for Systems Engineers

Karam¹

1998

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Section: Application: Thermal Interaction Between a Heat Pipe Radiatomentioning

confidence: 96%

Section: Application: Thermal Interaction Between a Heat Pipe Radiatomentioning

confidence: 99%

Satellite Thermal Control for Systems Engineers

Karam¹

1998

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“…The heat transfer characteristics of a heat pipe/honeycomb radiation panel were successfully modelled using a finite element technique. 23 The tube and fluid elements were modelled using PTUBE and PFTUBE elements of the NASTRAN thermal analyser program.24 (The ROD and FLUID ROD elements of the code may also be used.) Each pipe was treated as an evaporator tube element, three condenser tube element, and one vapour node (may be simulated by the ENCLOSURE ROD element of CAFE) represented isothermal vapour along the entire length.…”

Section: Special Analysis Featuresmentioning

confidence: 99%

Spacecraft thermal modelling

Chin

Panczak

Fried

1992

Numerical Meth Engineering

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SUMMARYThermal modelling of spacecraft requires approaches which can handle dominant radiative heat transfers and many special thermal control components. Present network-type thermal analysers allow simulation, especially for components with rectangular geometries, but at the expense of considerable awkwardness and much error-prone manual input. The user interfaces for pre-and postprocessing for these analysers are also very deficient. Finite element thermal analysers solve some of the analytical difficulties, but are not widely used because they lack the flexibility to simulate special operations. The Galerkin finite element method (GFEM) distributes the contributions within an element to the element nodal points. The assembly of the contributions from all elements yields a system of energy balance equations for the nodal points of the system. Monte Carlo raytracing, in conjunction with a GFEM energy distribution to element nodal points, yields a procedure of consistent nowisothermal surface radiation exchange. This procedure reduces a source of simulation error caused by non-uniform element illumination and shading. Orbital heating, fluid flow and special analysis features are discussed. The main analysis program is interfaced to the preprocessing and postprocessing modules. Example results are given.

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“…Future satellites, with electrical power in the kilowatts range, are envisioned carrying large, deployable radiators with intricate fluid networks for distributing and rejecting waste heat. A number of ideas in promoting such systems have been advanced, [1,2,3,4] all proposing heat pipes and other devices that profit from phase change heat transfer and capillary pumping. One of the greater challenges in this effort has been the mechanical design of stowable systems with flexible joints and interfaces that sustain continuity of heat and fluid flow after deployment.…”

Section: Introductionmentioning

confidence: 99%

Simulation of Satellite Heat Pipe Radiator

Fathy¹,

Afify²,

Elshazly³

2011

International Conference on Aerospace Sciences and Aviation Tec

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Heat pipes are widely used in the thermal control system of satellites. A coolant fluid, being pumped through a header, collects heat from the satellite components and transfer it to the radiator heat pipes. The object of this work is to obtain relationships among the heat load of radiator, the mass flow rate of coolant fluid and the main dimensions of the radiator, in order to satisfy the temperature ranges necessary for the operation of satellite components. A mathematical model was used to simulate a heat pipe radiator. Karam's data [5] has bean used to verify the validity of the program, with header length of 8 m, radiator height of 3.16 m, evaporator length of 0.15 m, number of heat pipes of 53 and satellite load of 6250 W. The output result concerning the heat transport capability of the radiator, given by the simulation program, are identical to karam's analytical results. The program was used to study the effect of some parameters like the header length, the satellite heat load and the environmental load. Changing the header length from 2 m to 10 m, it has been seen that the output coolant temperature decreases as header length increases which improves the thermal control of satellite. Changing the satellite load from 3000 W to 10000 W, it has been seen that the heat transport per pipe increases as the satellite thermal load increases. The results also showed that increasing the environmental load could stop the radiator function and consequently it should be insulated from the surrounding to work property.

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Thermal Interaction Between a Heat Pipe Radiator and a Coolant Fluid Header

Cited by 4 publications

References 2 publications

Satellite Thermal Control for Systems Engineers

Satellite Thermal Control for Systems Engineers

Spacecraft thermal modelling

Simulation of Satellite Heat Pipe Radiator

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