Covariance6By6TwoBodyBlender Constructor (DateMotionCollectionCartesian, IDateMotionCollectionMatrix6By6Symmetric, ReferenceFrame, Axes, ReferenceFrame, Double)

Initializes a new instance.

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

Syntax

C++

Copy

public Covariance6By6TwoBodyBlender(
	DateMotionCollection<Cartesian> orbitStates,
	IDateMotionCollection<Matrix6By6Symmetric> covarianceData,
	ReferenceFrame orbitStatesFrame,
	Axes covarianceAxes,
	ReferenceFrame inertialPropagationFrame,
	double gravitationalParameter
)

Public Sub New ( 
	orbitStates As DateMotionCollection(Of Cartesian),
	covarianceData As IDateMotionCollection(Of Matrix6By6Symmetric),
	orbitStatesFrame As ReferenceFrame,
	covarianceAxes As Axes,
	inertialPropagationFrame As ReferenceFrame,
	gravitationalParameter As Double
)

public:
Covariance6By6TwoBodyBlender(
	DateMotionCollection<Cartesian>^ orbitStates, 
	IDateMotionCollection<Matrix6By6Symmetric^>^ covarianceData, 
	ReferenceFrame^ orbitStatesFrame, 
	Axes^ covarianceAxes, 
	ReferenceFrame^ inertialPropagationFrame, 
	double gravitationalParameter
)

new : 
        orbitStates : DateMotionCollection<Cartesian> * 
        covarianceData : IDateMotionCollection<Matrix6By6Symmetric> * 
        orbitStatesFrame : ReferenceFrame * 
        covarianceAxes : Axes * 
        inertialPropagationFrame : ReferenceFrame * 
        gravitationalParameter : float -> Covariance6By6TwoBodyBlender

Parameters

orbitStates: Type: AGI.FoundationDateMotionCollectionCartesian
The position and velocity vectors of the spacecraft at the same times as the covarianceData.
covarianceData: Type: AGI.FoundationIDateMotionCollectionMatrix6By6Symmetric
The covariance data that is used for blending.
orbitStatesFrame: Type: AGI.Foundation.GeometryReferenceFrame
The native reference frame of the orbitStates.
covarianceAxes: Type: AGI.Foundation.GeometryAxes
The native axes of the covarianceData.
inertialPropagationFrame: Type: AGI.Foundation.GeometryReferenceFrame
The inertial propagation frame that is used to propagate the orbitStates and the covarianceData.
gravitationalParameter: Type: SystemDouble
The gravitational parameter of the central body that the spacecraft is orbiting.

Exceptions

Exception	Condition
ArgumentNullException	Thrown when covarianceData is .

Reference

Covariance6By6TwoBodyBlender Class

Covariance6By6TwoBodyBlender Overload

AGI.Foundation.NumericalMethods Namespace