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ISS rendsvous the need for robotic rendezvous and docking on a regular basis. Orbit dynamics can be complex. Given initial velocity looking for a regular rendevous position vectors, and desired final position and velocity vectors and time of flight, it will give you the initial impulse velocity change needed to rendezvous. There are numerous formulation as it is complex math problem.

ISS established the need for robotic rendezvous and docking on a regular basis. Orbit dynamics can be complex.

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Given initial velocity and position vectors, and desired final position and velocity vectors and rendevoux of flight, it will give you the initial impulse velocity change needed to rendezvous. There are numerous formulation as it is complex math problem.

You want to reduce the positions and velocities to zero. If your chase and target spacecraft have GPS it is relatively easy to find this state vector in the above equation.

A PD controller will ignore the coupling in the above equations while the LQ will accommodate the coupling. It is interesting to look reuglar the gain matrices for the sex personals dracut massachusetts cases and the corresponding eigenvalues.

We tweaked the PD to make its position gains close to that for the LQ.

The PD is deed for a damping ratio of 1. The eigenvalues are identical. The cross-axis gains are small, but non-zero. Gain Matrix LQ 0.