GravityEngine2.KeplerCOEPropagator Class Reference

Propagation using classical Kepler (two-body) dynamics, with state kept in COE form. More...

Classes
struct	PropInfo

Static Public Member Functions
static int	EvolveAll (double t_to, ref GEPhysicsCore.GEBodies bodies, ref NativeArray< PropInfo > propInfo, in NativeArray< GEPhysicsCore.PatchInfo > patchInfo, in NativeArray< int > indices, int lenIndices)
static void	EvolveRelative (double t_to, int propId, ref NativeArray< PropInfo > propInfo, ref GEBodyState state)
static bool	IsParabolic (double e)
static double3 double3 v	KeplerProp (ref NativeArray< PropInfo > propInfo, int index, double dtsec)
static void	ManeuverPropagator (int bodyIndex, double time, ref GEPhysicsCore.GEBodies bodies, ref NativeArray< PropInfo > kProps)

Static Public Attributes
static double3	r
const int	STATUS_EARLY_PROPAGATION_ERROR = 1
const int	STATUS_OK = 0

Detailed Description

Propagation using classical Kepler (two-body) dynamics, with state kept in COE form.

The code here is based on the KeplerCOE algorithm from Vallado.

This propogator has several differences from the KeplerPropagator: 1) It is computationally simpler than the universal variable approach. 2) It allow propagation of the COE to times before the start time. 3) It is best used for eccentricities that are not close to 1 (the universal variable approach is better for this).

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The documentation for this class was generated from the following file:

• ge2/GE2/Assets/GravityEngine2/Runtime/Core/Propagators/KeplerCOEPropagator.cs