Software Practical"Initial Satellite Orbit Determination with Nonsingular Kepler Elements"carried out by: Jamin Hass DescriptionAfter a satellite has been launched, it is often unclear whether the satellite is following the expected trajectory. In order to determine on which trajectory the satellite actually is, a parameter estimation problem using measurement data from observing ground stations is formulated. The unknowns of this parameter estimation problem may either be a six-dimensional state vector (three coordinates for both position and velocity) or the Kepler elements of the ellipsoidal orbit. It is already known that at least in some cases the latter formulation can be of some advantage. In particular, for the PROBA scenario provided to the IWR by the ESA it turns out that the convergence region of the Gauß-Newton method is significantly larger if the Kepler formulation is used. However, since the trajectory of the satellite is almost circular, some of the Kepler elements are almost undefined. It is the purpose of this software practical to investigate whether a reformulation to non-singular Kepler elements can further improve the convergence behaviour. AimThe focus of the software practical is on the application. The following tasks have to be carried out:
Size of the projectThis project is suited for one or two students as an advanced practical. Requirements
Further reading
Contact
Dipl.-Phys. Simon Lenz
e-mail: simon.lenz@iwr.uni-heidelberg.de back |