I have a trajectory (time, position and velocity are defined) from Earth to the Moon and cannot really define an orbit with this trajectory as such.
I have defined a variable of type SpacecraftState using AbsPVCoordinates.
I then use this variable as an input for PartialDerivativesEquations.setInitialJacobian(SpacecraftState)
However, I get an error of: orbit not defined, state rather contains an absolute position-velocity-acceleration when trying to compute the Jacobian matrix.
Orekit states that inputting a variable of type SpacecraftState to compute the Jacobian matrix is allowed and a SpacecraftState can be defined using AbsPVCoordinates but I still get this error. Could anyone identify what I’m doing incorrectly? Or is there another way of computing the Jacobian matrix - without having to define an orbit?