Add to ORKGThe problems of rejecting large amounts of heat from spacecraft were studied. Shuttle Space Laboratory heat rejection uses 1 kW for pumps and fans for every 5 kW (thermal) heat rejection. This is rather inefficient, and for future programs more efficient methods were examined. Two advanced systems were studied and compared to the present pumped-loop system. The advanced concepts are the air-cooled semipassive system, which features rejection of a large percentage of the load through the outer skin, and the heat pipe system, which incorporates heat pipes for every thermal control function
With future spacecraft power requirements expected to be in the order of 100 to 250 kilowatts and or...
Today, the exploration and exploitation of space continues to become a more common occurrence. All t...
It was determined that space tug will require the capability to perform its mission within a broad r...
Various heat pipe temperature control techniques are critically evaluated using characteristic featu...
Four advanced space radiator concepts that were pursued in an integrated effort to develop multi-mis...
Spacecraft thermal management is critical for ensuring mission success, as it affects the performanc...
Techniques for the management of the thermal energy of large space platforms using many hundreds of ...
The results of a parametric weight analysis of heat rejection systems for the space shuttle orbiter ...
A summary is given of a series of thermal vacuum tests designed to support the development of the or...
A two-part overview of progress in space radiator technologies is presented. The first part reviews ...
The technology involved in designing and fabricating a heat pipe thermal conditioning panel to satis...
A description of recent and planned thermal control technology developments at the Johnson Space Cen...
Guidance for the assessment and control of spacecraft temperatures is provided with emphasis on unma...
The development, fabrication, and evaluation of heat pipe thermal conditioning panels are discussed....
Combined passive and active methods for thermal control of manned orbital space station to reduce he...
With future spacecraft power requirements expected to be in the order of 100 to 250 kilowatts and or...
Today, the exploration and exploitation of space continues to become a more common occurrence. All t...
It was determined that space tug will require the capability to perform its mission within a broad r...
Various heat pipe temperature control techniques are critically evaluated using characteristic featu...
Four advanced space radiator concepts that were pursued in an integrated effort to develop multi-mis...
Spacecraft thermal management is critical for ensuring mission success, as it affects the performanc...
Techniques for the management of the thermal energy of large space platforms using many hundreds of ...
The results of a parametric weight analysis of heat rejection systems for the space shuttle orbiter ...
A summary is given of a series of thermal vacuum tests designed to support the development of the or...
A two-part overview of progress in space radiator technologies is presented. The first part reviews ...
The technology involved in designing and fabricating a heat pipe thermal conditioning panel to satis...
A description of recent and planned thermal control technology developments at the Johnson Space Cen...
Guidance for the assessment and control of spacecraft temperatures is provided with emphasis on unma...
The development, fabrication, and evaluation of heat pipe thermal conditioning panels are discussed....
Combined passive and active methods for thermal control of manned orbital space station to reduce he...
With future spacecraft power requirements expected to be in the order of 100 to 250 kilowatts and or...
Today, the exploration and exploitation of space continues to become a more common occurrence. All t...
It was determined that space tug will require the capability to perform its mission within a broad r...