Interface AbstractIntegratedPropagator.MainStateEquations
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- Enclosing class:
- AbstractIntegratedPropagator
public static interface AbstractIntegratedPropagator.MainStateEquations
Differential equations for the main state (orbit, attitude and mass).
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Method Summary
All Methods Instance Methods Abstract Methods Default Methods Modifier and Type Method Description double[]
computeDerivatives(SpacecraftState state)
Compute differential equations for main state.default void
init(SpacecraftState initialState, AbsoluteDate target)
Initialize the equations at the start of propagation.
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Method Detail
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init
default void init(SpacecraftState initialState, AbsoluteDate target)
Initialize the equations at the start of propagation. This method will be called before any calls tocomputeDerivatives(SpacecraftState)
.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
double[] computeDerivatives(SpacecraftState state)
Compute differential equations for main state.- Parameters:
state
- current state- Returns:
- derivatives of main state
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