Radiator concepts for high power systems in space

Feig, Jason R.

doi:10.2514/6.1984-55

Cited by 6 publications

(3 citation statements)

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“…Hence, radiation from 0 to surrounding deep space (0 K) is 40-outside = ^-outside = ^^WO Therefore, in a long, thin cylindrical shell with no discernable temperature difference across its thickness, the total net radiation (watts per square meter) from a point on the shell to the whole of its surroundings iŝ -wholesurroundings = As indicated in Fig. 2.1, the sun's radiation coming from a great distance impinges as a heating flux vector (normal component near Earth is nominally S = 1350 W/m 2 ).…”

Section: Application: Temperature Distribution In a Cylindrical Shellmentioning

confidence: 99%

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Satellite Thermal Control for Systems Engineers

Karam¹

1998

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Section: Application: Temperature Distribution In a Cylindrical Shellmentioning

confidence: 99%

“…40 Passive area and heater power to keep the temperature of ADS hybrid louvered/passive radiator between 0°C and maximum hot case value. balance equations.…”

mentioning

confidence: 99%

Satellite Thermal Control for Systems Engineers

Karam¹

1998

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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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