TwoBodyStateTransitionMatrixPropagator Constructor (JulianDate, MotionCartesian, Double)

Initializes a new instance.

Namespace: AGI.Foundation.Propagators
Assembly: AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.2.419.0 (24.2.419.0)

Syntax

C++

Copy

public TwoBodyStateTransitionMatrixPropagator(
	JulianDate epoch,
	Motion<Cartesian> initialConditions,
	double gravitationalParameter
)

Public Sub New ( 
	epoch As JulianDate,
	initialConditions As Motion(Of Cartesian),
	gravitationalParameter As Double
)

public:
TwoBodyStateTransitionMatrixPropagator(
	JulianDate epoch, 
	Motion<Cartesian> initialConditions, 
	double gravitationalParameter
)

new : 
        epoch : JulianDate * 
        initialConditions : Motion<Cartesian> * 
        gravitationalParameter : float -> TwoBodyStateTransitionMatrixPropagator

Parameters

epoch: Type: AGI.Foundation.TimeJulianDate
The Julian date at which the initial conditions are defined.
initialConditions: Type: AGI.FoundationMotionCartesian
The orbital state of the spacecraft at the epoch.
gravitationalParameter: Type: SystemDouble
The gravitational parameter for the central body around which to propagate.

Reference

TwoBodyStateTransitionMatrixPropagator Class

TwoBodyStateTransitionMatrixPropagator Overload

AGI.Foundation.Propagators Namespace

TwoBodyStateTransitionMatrixPropagator Constructor (JulianDate, MotionAddLanguageSpecificTextSet("LST71B02E84_0?cs=&lt;|vb=(Of |cpp=&lt;|fs=&lt;'|nu=(");CartesianAddLanguageSpecificTextSet("LST71B02E84_1?cs=&gt;|vb=)|cpp=&gt;|fs=&gt;|nu=)");, Double)

Parameters

Reference

TwoBodyStateTransitionMatrixPropagator Constructor (JulianDate, MotionCartesian, Double)