Thermal control issues for nano- and picosatellites
- Paper number
IAC-06-B5.6.07
- Author
Mr. Jeroen Rotteveel, Technical University of Delft (TUDelft), The Netherlands
- Coauthor
Mr. Abe Bonnema, Technical University of Delft (TUDelft), The Netherlands
- Year
2006
- Abstract
The tendency for ever smaller satellites culminated in the development of highly integrated compact systems with a mass as low as one kilogram. Miniaturization and improved performance of components allow for much smaller design, not only in the satellite payloads but also in the supporting subsystems. However, in the thermal control of such small spacecraft there are few options that can be explored. The small size of the spacecraft limits the design freedom of the thermal engineer. The main reason for this limitation is that a passive thermal control subsystem is usually implemented as a results of limited mass and power budgets. However, several other limitations impact the thermal control subsystem design for such satellites.\\ The outer surface area of a nanosatellite is usually covered with Solar cells in order to have as much power available as possible. As Solar cells act more or less as a flat absorber and cover most of the outer surface, the optical properties of the outer spacecraft are difficult to alter. Apart from the solar cells the interface with the launch adapter takes up a relatively large portion of the available surface area when compared to larger satellites. Due to the high level of integration of electronics for small satellites, printed circuit boards endure relative high heat loads and it is difficult to provide heat dissipation capability for components such as power amplifiers. Integration solutions for picosatellites for example are mainly driven by reduced mass and design for integration, which leaves little room for cold plates or radiators. Another aspect of the thermal control for pico- and nanosatellites is that these spacecraft are almost exclusively used in low Earth orbit, which results in a relatively large number of thermal cycles. As the outer surfaces are usually more or less identical in optical properties, except perhaps for the nadir pointing surface, there are no stringent attitude control requirements from a thermal control point of view as there is no room for dedicated radiator and insulation panels.\\ The above mentioned issues will be addressed by example of several nano-satellites. The paper elaborates on the specific thermal control issues regarding nano- and picosatellites. Also a number of thermal control solutions will be presented that are currently employed in these satellites. The student nanosatellite of the Technical University of Delft in particular will serve as a design example in order to point out the specific design issues in thermal control for nano- and picosatellites. Simulation results and design solutions are presented.
- Abstract document
- Manuscript document
IAC-06-B5.6.07.pdf (🔒 authorized access only).
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