Aerospace Systems Dynamics

Autonomous station keeping of a satellite
1.1 Objectives
The problem studied in this design office is that of autonomous station keeping of a satellite in low earth orbit. The aim is to synthesize a robust control law that can maintain a satellite in a reference orbit, despite the various perturbing forces that can move it away from this orbit.
The proposed method for tackling this problem involves several stages. First, a non-linear model governing the absolute motion of the satellite will be developed. This model, known as the validation model, will then be used to assess the validity of the control law. Secondly, the validation model will be approximated around the reference orbit by a linear model. This simplified model, known as the synthesis model, will be used to calculate the control law.
The controller will be synthesized during another design phase from the synthesis model, and its validity will be assessed using the validation model.

1.2 Practical aspects
As with the Vehicle Dynamics Design Phase (BEDV), two four-hour sessions are scheduled. These sessions precede those of the Synthèse Frèquentielle de Commande Robuste (SCFR) and Synthèse de Commande Robuste par Optimisation (SCRO) design offices.
At the end of the last session, it is imperative that a synthesis model be validated and that the simulator corresponding to the validation model be completed.
Validation of the controller on the validation model will be carried out outside the hours of the modeling design offices, these ending before the synthesis design offices.

1.3 Evaluation
The evaluation of the modeling studies is carried out jointly with the bibliographic project and the robust control synthesis study, on the basis of a report and a presentation.

Automatic