Publication Date:
2019-08-16
Description:
As CubeSat and SmallSat missions increase in complexity and power consumption they present innate thermal challenges. Science instruments may require thermal stability while a variety of factors such as high-powered components, sunlight and shadow on orbit, or tight spacecraft layout may produce a wide range of temperatures. The CubeSat Form Factor Thermal Control Louvers are a passive method of stabilizing the thermal environment inside of small spacecraft via miniature thermal louvers. These louvers are a patented design, with a technology demonstration version of the louvers operating correctly in flight on the Dellingr CubeSat in 2018. This paper will describe the methods used to develop and test this technology, as well as the results obtained and how this technology may be used in CubeSat and SmallSat missions.
Keywords:
Spacecraft Design, Testing and Performance; Fluid Mechanics and Thermodynamics
Type:
GSFC-E-DAA-TN69063
,
SmallSat Conference; Aug 03, 2019 - Aug 08, 2019; Logan, UT; United States
Format:
application/pdf
Permalink
