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Collision avoidance is a topic of growing importance for any satelliteorbiting Earth. Especially those satellites without thrusting capabilities facethe problem of not being able to perform impulsive collision avoidancemanoeuvres. For satellites in Low Earth Orbits, though, perturbingaccelerations due to aerodynamic drag may be used to influence theirtrajectories, thus offering a possibility to avoid collisions without consumingpropellant. Here, this manoeuvring option is investigated for the satelliteFlying Laptop of the University of Stuttgart, which orbits the Earth atapproximately 600 km. In a first step, the satellite is aerodynamicallyanalysed making use of the tool ADBSat. By employing an analytic equation fromliterature, in-track separation distances can then be derived following avariation of the ballistic coefficient through a change in attitude. A furtherexamination of the achievable separation distances proves the feasibility ofaerodynamic collision avoidance manoeuvres for the Flying Laptop for moderateand high solar and geomagnetic activity. The predicted separation distances arefurther compared to flight data, where the principle effect of the manoeuvre onthe satellite trajectory becomes visible. The results suggest an applicabilityof collision avoidance manoeuvres for all satellites in comparable andespecially in lower orbits than the Flying Laptop, which are able to vary theirballistic coefficient.

Analysis of collision avoidance manoeuvres using aerodynamic drag for the Flying Laptop satellite