Carbon nanotubes (CNTs) have attracted much attention due to their extraordinary mechanical and unique electronic properties. CNTs are being studied for applications in high-strength/low-weight composites and other applications. In order to alter the CNT properties for particular applications, chemical...

After many years of use of Tropical Rainfall Measurement Mission (TRMM) and CloudSat data, focus groups within the cloud and precipitation science community produced requirements for the next generation of missions. The first draft of Aerosol-Cloud-Ecosystem mission requirements was formalized in 2009,...

Radiator panels are the baseline heat rejection approach for most space systems. This approach is sound, but requires a large amount of surface area to radiate the anticipated heat load. The large panels require support structures to hold them in place and prevent damage. These structures impact mass and cost....

Spacecraft thermal control systems typically perform three key functions — heat acquisition, heat transport, and heat rejection — in addition to those of insulation, heat generation, and heat storage. In a typical pumped fluid-loop spacecraft thermal control system, heat is acquired from...

The Orion Crew Module has a pressurized cabin of approximately 20 m3 in volume. There are a number of cold plates within the Crew Module for thermal management. An optical communication type of payload...

A highly reflective, white conductive coating system was developed using various layered coatings to maximize the structural, electrical, and optical reflectance properties for spacecraft radiators. The top layer of the system contains a highly reflective white pigment within a dissipative...

Communicating the current International Space Station (ISS) configuration and also potential ISS configurations is a necessity during ISS trade studies and Ops Con development. Often, multiple configuration options will need to be communicated. Doing so without a means of displaying...

For space exploration missions that may require extended stays and extensive extra-vehicular activity (EVA) operations, the temperature control system must be lightweight, rugged, non-venting, and repairable in space.

Thermal requirements and a need for a very flat mechanical interface led to the development of a copper doubler for the titanium vault on the Juno Spacecraft. The vault is designed to contain the science instruments on the spacecraft, protecting them from damage due to the extreme...

Ammonia leaks are a significant concern for the International Space Station (ISS). The ISS has external transport lines that direct liquid ammonia to radiator panels where the ammonia is cooled and then brought back to thermal control units. These transport lines and radiator panels are...

Development of the DeCoM comes from the requirement of analyzing the performance of a condenser. A component of a loop heat pipe (LHP), the condenser, is interfaced with the radiator in order to reject heat. DeCoM simulates the condenser, with certain input parameters. Systems Improved Numerical Differencing...

An imager or sounder on satellites, such as the Geostationary Operational Environmental Satellite (GOES), in geostationary orbit (GEO) has a scan mirror and motor in the scan cavity. The GEO orbit is 24 hours long. During part of the orbit, direct...

The optimum radiator configuration in hot lunar thermal environments is one in which the radiator is parallel to the ground and has no view to the hot lunar surface. However, typical spacecraft configurations have limited real estate available for top-mounted radiators, resulting...

Adding phase change material (PCM) to a mission payload can maintain its temperature above the cold survival limit, without power, for several hours in space. For the International Space Station, PCM is melted by heaters just prior to the payload...

A document discusses a thermal radiator design consisting of lightweight composite materials and low-emittance metal coatings for use on the James Webb Space Telescope (JWST) structure. The structure will have a Thermal Subsystem unit to provide passive cooling...