FieldAbstractIntegratedPropagator.MainStateEquations (ORbit Extrapolation KIT 9.3 API)

Enclosing class:

FieldAbstractIntegratedPropagator<T extends org.hipparchus.RealFieldElement<T>>
```
public static interface FieldAbstractIntegratedPropagator.MainStateEquations<T extends org.hipparchus.RealFieldElement<T>>
```
Differential equations for the main state (orbit, attitude and mass).

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.

- Method Detail
  - 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 to computeDerivatives(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 to initialState.getDate().
  - computeDerivatives
```
T[] computeDerivatives(FieldSpacecraftState<T> state)
```
    Compute differential equations for main state.
    
    Parameters:
    
    state - current state
    
    Returns:
    
    derivatives of main state