• satellite
• electric propulsion
• attitude
• control
• mission analysis

The D3SAT (Drag make-up and Deorbiting Demonstration Satellite) technology demonstration mission aims to carry out comprehensive performance characterization of SITAEL's low power HT-100D thruster in-orbit ,by mounting it on a microsatellite which has a mass less than 40 kilograms. This thesis deals with the analysis of orbital operations required for performance evaluation,namely drag compensation and end-of-life deorbiting. The mission profile is then proposed, based on constraints imposed by the launch vehicle and by the thruster. The operating phases of the Attitude Determination and Control Subsystem (ADCS) based on the mission are described, and the requirements for each phase are derived. Preliminary design and specification of the ADCS to meet these requirements is then carried out. Interaction of the ADCS with other subsystems is analysed, and the contribution of the ADCS to the conceptual design of the D3SAT is specified. The ADCS is found to be compliant with the stringent volume and power requirements on-board small satellites. The HT-100D is found to efficiently satisfy the mission requirements with very low power requirements and low propellant consumption, thereby proving to be an ideal candidate to enhance the capabilities of small satellites.