A component for the in-scene representation of a body to be evolved with GE via a GravitySceneController. More...

Inheritance diagram for GravityEngine2.GSBody:

Public Member Functions
GSBinary	Binary ()
	If this body is a member of a GSBinary then the GSBinary object will have the details on the joint orbit and the mass fractions etc.

void	BinarySet (GSBinary gsBinary)

GSBody	CenterBody ()

Orbital.COE	COEFromBID ()

int	Id ()

void	IdSet (int id)

override string	ToString ()

Public Attributes
BodyInitData	bodyInitData = new BodyInitData()

GSBody	centerBody

string	ephemFilename

bool	ephemRelative

double	mass

bool	optionalDataFoldout

bool	patched

GEPhysicsCore.Propagator	propagator = GEPhysicsCore.Propagator.GRAVITY

double	radius

Vector3	rotationAxis = Vector3.up

double	rotationRate = 0.0

Static Public Attributes
static int	NO_ID = -1
	GravityData id. Assigned when added to GE.

Detailed Description

A component for the in-scene representation of a body to be evolved with GE via a GravitySceneController.

The initial state of the body can be represented in a number of ways: 1) Absolute position/velocity in world space 2) Relative position/velocity with respect to another GSBody 3) In orbit relative to a center body. The orbit is specified via the "classical orbital elements (COE)" or variations (where e.g. apoapsis and periapsis can be used instead of major axis and ecentricity. Note apoapsis is the general form of apogee, which is for the Earth) 4) In orbit around the Earth via the Spacetrack two line element format. This is a commonly used general format specifying the orbit parameters and epoch time. It can be retreived from e.g. Celestrak

The GSBody component also allows the specification of how GE will propagate the body. The general case is to use N-body evolution (GRAVITY). Other choices are: FIXED: don't move it at all (suitable for e.g. a central star) KEPLER: Keep object "on-rails" around a center body and evolve with Kepler's equation SGP4: Move according to a model that incorporates Earth oblateness, atmospheric drag, Moon, Sun. This is only valid for a center body that is modelling the Earth. PKEPLER: An Earth orbit model that incorporates non-spherical Earth only (e.g. for Sun synchronous orbits. These rely on the non-spherical orbit perturbation. Only valid for Earth orbits.

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

ge2/GE2/Assets/GravityEngine2/Runtime/InScene/GSBody.cs

Public Member Functions

Public Attributes

Static Public Attributes

Detailed Description