I have created a variable thrust maneuver which implements
AdditionalEquations. This is because thrust and Isp depends on tank pressure (defined as a
SpacecraftState.additionalState) which is a parameter that evolves along the propagation.
As I am obliged to define my maneuver as an
AdditionalEquations and not as a
ForceModel I don’t know how I could perform a Thrust Calibration in Orbit Determination as my maneuver is not a
ForceModel (where the derivative of the acceleration with respect to the parameter to calibrate is computed from
ForceModel.acceleration(FieldSpacecraftState<T> s, T parameters)). So that is my question, how could I carry out a Thrust Calibration from a maneuver which has to be defined as an
AdditionalEquations. Is there any other alternative ?
Thank you so much.