Code to propagate SGP4 satellites i.e. satellites in Earth orbit with modeling for atmosphere, oblate gravity, moon, sun etc. More...

Static Public Member Functions
static bool	Evolve (double t, ref GEPhysicsCore.GEBodies bodies, ref NativeArray< PropInfo > propInfo, in NativeArray< GEPhysicsCore.PatchInfo > patchInfo, in NativeArray< int > indices, double scaleToKm, double scaleKmsecToV, double startTimeJD)
	GE entry point, to evolve a set of SGP4 bodies as defined by the indices index list.

static int double3 double3 Orbital.COEStruct coe	RVforTime (ref SGP4SatData satData, double timeJD, double scaleToKm, double scaleKmsecToV)

Static Public Attributes
static int	error
	Used in direct propagation mode, typically with an explicitly create SGP4 propagator that was created in test or user code (and not from within GE).

static int double3	r

static int double3 double3	v

Detailed Description

Code to propagate SGP4 satellites i.e. satellites in Earth orbit with modeling for atmosphere, oblate gravity, moon, sun etc.

This code assumes the Earth is at the center of physics space.

Not hard to C&P the center body code from Kepler but seems like an uncommon use-case, so wait until someone asks....

Member Function Documentation

static bool GravityEngine2.SGP4Propagator.Evolve	(	double	t,
		ref GEPhysicsCore::GEBodies	bodies,
		ref NativeArray< PropInfo >	propInfo,
		in NativeArray< GEPhysicsCore::PatchInfo >	patchInfo,
		in NativeArray< int >	indices,
		double	scaleToKm,
		double	scaleKmsecToV,
		double	startTimeJD )

static

GE entry point, to evolve a set of SGP4 bodies as defined by the indices index list.

Parameters

int GravityEngine2.SGP4Propagator.error

static

Used in direct propagation mode, typically with an explicitly create SGP4 propagator that was created in test or user code (and not from within GE).

Parameters

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