Session
Pre-Conference Poster Session II
Location
Utah State University, Logan, UT
Abstract
The paper explains the design of an active thermal control system which would work as per the needs of the current operational mode of the satellite. The modes of the satellite have been classified into two major groups: the normal modes and the emergency modes. The modes of interest to the thermal control system are three of the emergency modes and the image capture mode, which is one of the normal modes. The electrical loop of the system will be dynamically controlled by the TI MSP430 microcontroller of the Electrical Power System (EPS) as per the present mode of operation set by the On-Board Computer (OBC). The dynamic control loop ensures that the imager is heated to its optimal working range from its storage range during the image capture mode. A separate dynamic control loop is also used to maintain the optimal temperature for the satellite’s batteries as per the mode of operation. Redundancy has been established using a mechanical thermostat-based control loop in addition to the already planned dynamic control loop. This ensures the protection from thermal failure of the components during the emergency modes.
Dynamic Active Thermal Control of a LEO Nanosatellite Based on its Mode of Operation
Utah State University, Logan, UT
The paper explains the design of an active thermal control system which would work as per the needs of the current operational mode of the satellite. The modes of the satellite have been classified into two major groups: the normal modes and the emergency modes. The modes of interest to the thermal control system are three of the emergency modes and the image capture mode, which is one of the normal modes. The electrical loop of the system will be dynamically controlled by the TI MSP430 microcontroller of the Electrical Power System (EPS) as per the present mode of operation set by the On-Board Computer (OBC). The dynamic control loop ensures that the imager is heated to its optimal working range from its storage range during the image capture mode. A separate dynamic control loop is also used to maintain the optimal temperature for the satellite’s batteries as per the mode of operation. Redundancy has been established using a mechanical thermostat-based control loop in addition to the already planned dynamic control loop. This ensures the protection from thermal failure of the components during the emergency modes.
