AbstractIntegratedPropagator.MainStateEquations (OREKIT 12.2 API)

Enclosing class:

AbstractIntegratedPropagator
```
public static interface AbstractIntegratedPropagator.MainStateEquations
```
Differential equations for the main state (orbit, attitude and mass).

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.

- Method Detail
  - init
```
default void init(SpacecraftState initialState,
                  AbsoluteDate target)
```
    Initialize the equations at the start of propagation. This method will be called before any calls to computeDerivatives(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 to initialState.getDate().
  - computeDerivatives
```
double[] computeDerivatives(SpacecraftState state)
```
    Compute differential equations for main state.
    
    Parameters:
    
    state - current state
    
    Returns:
    
    derivatives of main state