Spacecraft Formation Flying Based On Halo Orbit

Spacecraft formation flying based on Halo orbit has a wide applying prospect. It is one of the research focuses in the fields of aerospace dynamics and control around the world. The spacecraft formation flying missions often require keeping precise relative positions and relative velocities. So it is a valuable research with practicable background to analyze the relative motion and orbital configuration of spacecraft formation flying based on Halo orbit. Both theoretical analysis and numerical simulation are used in this thesis.An effective method to compute Halo orbit, named differential corrections, is presented elaborately by this thesis. To compute Halo orbit using this method, the precision can reach to 10?1 0above. On the basis of this method, this thesis gives the basic orbital element relations by simulation charts.The approximate relative motion solution based on the same Halo orbit is generated from the three order approximate analytical solution described by Richardson, while the approximate relative motion solution based on the different Halo orbit by approximation and simplification. The applied amplitude domain of this solution is smaller than that based on the same Halo orbit. But, this thesis gives the approach to enlarge the solution's applying domain when amplitude increases, which need less omit and more precise expansion of the initial equations.The approximate relative motion solution based on the same Halo orbit is part of the approximate solution based on the different Halo orbit. The expression clearly divides the relative motion of different Halo orbit to two parts, one of which is generated from initial phrase only, and the other, amplitude difference only. Then this thesis discusses the transformation characteristic of the relative motion orbit. Finally, this thesis uses the results of foregoing chapters to designs the configuration of spacecraft formation flying based on Halo orbit and then, proposes the standard guide of configuration design. Two examples are showed in the use of the standard guide. The result shows that the error is small when using the standard guide.The method and conclusion in this thesis could be used as the reference to the mission designing of spacecraft formation flying based on Halo orbit. Also, they could help to control the spacecraft formation flying.