Abstract
We consider series of manoeuvres computed in order to reach a given orbit. The characteristics of each manoeuvre are calculated using the results of an orbit determination. Inaccuracy of this orbit determination induces inaccuracy in manoeuvre calculation. The manoeuvre is then carried out using an imperfect AOCS (attitude and orbit control systems). This also induces discrepancies between the target orbit and the realized one. Our problem is to determine the accuracy with which the final goal will be reached, as a function of initial orbit dispersion, orbit determination errors, realization errors and strategy of manoeuvre. A simple analytical solution can be found by linearization of state and manoeuvre with respect to dispersion around the “nominal state”. This method allows one to know the evolution through manoeuvres of the covariance of every possible states without using any simulations. We have then applied this method to TDF 1 satellite transfer orbit circularization.
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