StkEphemerisFileCovarianceTimePosVelCreateBlender Method (StkEphemerisFileEphemerisTimePosVel, ReferenceFrame, NullableDouble)

Creates a two-body covariance blender from the orbit states ephemeris and the covariance data. Also, sets the Blender property to the created value.

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

Syntax

C++

Copy

public Covariance6By6TwoBodyBlender CreateBlender(
	StkEphemerisFileEphemerisTimePosVel orbitStates,
	ReferenceFrame inertialPropagationFrame,
	double? gravitationalParameter
)

Public Function CreateBlender ( 
	orbitStates As StkEphemerisFileEphemerisTimePosVel,
	inertialPropagationFrame As ReferenceFrame,
	gravitationalParameter As Double?
) As Covariance6By6TwoBodyBlender

public:
Covariance6By6TwoBodyBlender^ CreateBlender(
	StkEphemerisFileEphemerisTimePosVel^ orbitStates, 
	ReferenceFrame^ inertialPropagationFrame, 
	Nullable<double> gravitationalParameter
)

member CreateBlender : 
        orbitStates : StkEphemerisFileEphemerisTimePosVel * 
        inertialPropagationFrame : ReferenceFrame * 
        gravitationalParameter : Nullable<float> -> Covariance6By6TwoBodyBlender

Parameters

orbitStates: Type: AGI.Foundation.StkStkEphemerisFileEphemerisTimePosVel
The orbit states that are used for blending. These must be consistent with a spacecraft in a two-body orbital regime for the results to be correct.
inertialPropagationFrame: Type: AGI.Foundation.GeometryReferenceFrame
The inertial propagation frame that is used to propagate the orbitStates and the CovarianceData.
gravitationalParameter: Type: SystemNullableDouble
The gravitational parameter of the central body that the spacecraft described by orbitStates is orbiting.

Return Value

Type: Covariance6By6TwoBodyBlender
The created two-body covariance blender.

Reference

StkEphemerisFileCovarianceTimePosVel Class

CreateBlender Overload

AGI.Foundation.Stk Namespace