Speaker
Description
ALEASAT is a 1U In-Orbit Demonstration (IOD) CubeSat intended for Earth Observation. Like other such projects, ALEASAT is generally characterized by higher risk of acceptance profile, low level of complexity (relative to other ESA space projects), low cost and short schedule, short operational lifetime (typically < 5 years in LEO), acceptance of single point failures, and robust safe mode (thermal and power safe in any attitude). In order to assess the thermal environment within ALEASAT, a thermal model (TM) was constructed in which the structure was decomposed into a number of discrete regions with specified thermal characteristics. Earlier this year, an extensive series of thermal tests were conducted at ESA’s CubeSat Support Facility in Belgium to verify this model and inform the spacecraft system engineering process. In the case of ALEASAT, this testing was conducted earlier in the development phase and in more detail than is usual for similar projects. Here, we present the results of such testing including thermal balance testing to provide data for model correlation and thermal cycle testing in which functional testing of the payload module and power amplifier at hot and cold temperatures was used to characterize performance of mission critical components. The results will inform the thermal modelling of other CubeSat projects as well as provide useful insights concerning the impact of thermal issues on both ALEASAT’s camera and RF power amplifier.