Spacecraft Relative Motion
An online implementation of different algorithms to solve the spacecraft relative motion problem is presented. It focuses on the theory of asynchronous relative motion, that provides simple mechanisms for introducing nonlinear terms in the solution. The relative state vector is projected onto the Euler-Hill rotating reference frame. The relative velocity is referred to the rotating frame as well.
The program computes the error with respect to a reference solution. The error is measured as the offset in position and velocity. The reference solution is computed by solving the unperturbed two-body problem for the leader and follower, and then subtracting the absolute state-vectors. The error in position is given col. 15 and the error in velocity in col. 16. At the end of the file the mean values of the error in position and velocity are provided. The exact solution is written in cols. 9-11 and cols. 12-14 (relative position and velocity vectors, respectively).