Abstract
This thesis looks at the effectiveness of using nanosatellite class star trackers to perform optical navigation. Although star trackers used for these missions lack the accuracy and sensitivity of sensors employed on larger spacecraft, they offer great resolution relative to its compact size. Two Extended Kalman Filter-based navigation filters illustrate the applications of this class of sensor. The first filter looks at horizon-based techniques using observations of Mars and its moons to assist the navigation filter in a hyperbolic approach. Results show low position (< 300 m) and velocity (< 0:15 m/s) errors as spacecraft reaches periapse. The filter formulation serves as a basis for a design case study exploring different possible sensor configurations for this mission type. The second filter looks at landmark-based techniques using absolute and relative landmarks as observations. Measurement frequency appears as a key parameter in this study, simulation results show position errors in the order of tens of kilometers, or better even if absolute landmarks are only available every 30 minutes. The accuracy of the results are validated through series of Monte Carlo simulation.
Highlights
Over the past decades, optical navigation has become an increasingly popular technique to orbital estimation and guidance with scores of examples of successful missions
Earth orbit satellites have the ability to rely on ground tracking for orbital information
This section reviews some of the previous missions where optical navigation techniques were applied, paying attention to the techniques used
Summary
Optical navigation has become an increasingly popular technique to orbital estimation and guidance with scores of examples of successful missions These techniques can provide autonomous and self-contained navigation estimates for satellites orbiting the Earth or other planets such as Mars. We provide some background knowledge on the contents of this thesis It starts off with a historical overview on optical navigation. Following with an explanation on the mathematical notations used in this thesis It provides a description of the primary sensor used for this research, ST-16 star tracker. OpNav grants the spacecraft its own orbit determination capabilities, providing autonomous and self-contained navigation estimates for the spacecraft, and reducing the reliance on ground-based tracking stations. With this in mind, the ability of the satellite to have its own orbit determination capabilities becomes highly important
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