For the upcoming formation flying technology demonstration mission NetSat a relative orbit propagator as well as a relative orbit controller were developed. The formation will consist of four equal nano-satellites with an electric propulsion system for orbit correction manoeuvres. This demands the use of continuous low-thrust models for relative orbit control, which is a novel field. A software framework was developed which allows orbit simulations of the whole fleet in a fully non-linear environment. The final on-board relative propagator is based on the Gim-Alfriend STM and incorporates eccentricity and the non-spherical shape of the Earth. The controller uses control Lyapunov function-based design and model predictive control, depending on the task. The guidance and control system is able to safely govern the relative motion for one-, two and three-dimensional formation configurations with inter-satellite distances as low as 50m. Based on these results, a complete mission plan is proposed.

In the scope of this master thesis work, the proposed design for NetSat was analyzed for mission and system requirements with respect to structural and thermal limitations. Different load case scenarios for structural and thermal analysis were considered during the process which have been discussed. Based on results, the design is qualified and expected to satisfy all mission and system requirements with regards to structural and thermal limitations.

This thesis proposes a distributed robust control approach for low-thrust nanosatellite formation flying. The presented control approach is the further development of an already existing approach which combines robust control and distributed control using the consensus approach. The adjustments presented in this thesis are intended to enable the usage of the control approach in nanosatellite missions such as the upcoming NetSat mission. Stability criteria, optimization goals and constraints such as the limited maximum thrust are formulated with the help of Linear Matrix Inequalities (LMIs). In addition, the presented control approach includes methods for exploiting the maximum thrust and for collision avoidance. Due to the design as a distributed controller based on the consensus approach, a satellite formation can be maintained even in the case of the failure of the propulsion system and/or Attitude Determination and Control System (ADCS) of a single satellite. To verify the design of the control approach, simulations of the formation scenarios planned for the NetSat mission are performed with a satellite formation simulation framework based on Orekit and MATLAB®.