Interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends CalculusFieldElement<T>>
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- Type Parameters:
T
- type of the field element
- Enclosing class:
- FieldAbstractIntegratedPropagator<T extends CalculusFieldElement<T>>
public static interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends CalculusFieldElement<T>>
Differential equations for the main state (orbit, attitude and mass).
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Method Summary
All Methods Instance Methods Abstract Methods Modifier and Type Method Description T[]
computeDerivatives(FieldSpacecraftState<T> state)
Compute differential equations for main state.void
init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the equations at the start of propagation.
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Method Detail
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init
void init(FieldSpacecraftState<T> initialState, FieldAbsoluteDate<T> target)
Initialize the equations at the start of propagation. This method will be called before any calls tocomputeDerivatives(FieldSpacecraftState)
.The default implementation of this method does nothing.
- Parameters:
initialState
- initial state information at the start of propagation.target
- date of propagation. Not equal toinitialState.getDate()
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computeDerivatives
T[] computeDerivatives(FieldSpacecraftState<T> state)
Compute differential equations for main state.- Parameters:
state
- current state- Returns:
- derivatives of main state
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