In this paper the preliminary results of the phase-A study of the guidance, navigation and control subsystem for a reduced-scale demonstrator of CIRA Sub-orbital Re-entry Test (SRT) mission is presented. A baseline guidance law is defined, in order to satisfy SRT mission objectives and constraints, on two candidate system configurations. A supplementary, higher performance, higher risk guidance solution is identified, providing qualitative insight on vehicle and system constraints impact on the overall attainable mission objectives. Evaluation of the performance of a commercial-off-the-shelf GPS-aided, miniature inertial navigation system over the baseline trajectories is also conducted.
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