TwoBodyStateTransitionMatrixPropagatorGetEvaluator Method (EvaluatorGroup)

Gets an evaluator that can propagate the state transition matrix to individual dates.

This evaluator propagates the orbit state transition matrix. The result of evaluating will be a Motion<Matrix> corresponding to the orbital state transition matrix at the given JulianDate.

Note: when evaluating with this evaluator, it may be more efficient to specify times using an arithmetically safe TimeStandard to avoid the need to convert in order to perform the propagation. The length of a time step may be different in different TimeStandards. So be careful when specifying times.

Namespace: AGI.Foundation.Propagators
Assembly: AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 25.1.421.0 (25.1.421.0)

Syntax

C++

Copy

public DynamicMatrixEvaluator GetEvaluator(
	EvaluatorGroup group
)

Public Function GetEvaluator ( 
	group As EvaluatorGroup
) As DynamicMatrixEvaluator

public:
DynamicMatrixEvaluator^ GetEvaluator(
	EvaluatorGroup^ group
)

member GetEvaluator : 
        group : EvaluatorGroup -> DynamicMatrixEvaluator

Parameters

group: Type: AGI.FoundationEvaluatorGroup
The group with which to associate the new evaluator. By grouping evaluators that are often evaluated at the same Julian dates, common computations can be performed only once for the entire group instead of multiple times for each evaluator.

Return Value

Type: DynamicMatrixEvaluator
The evaluator.

Reference

TwoBodyStateTransitionMatrixPropagator Class

GetEvaluator Overload

AGI.Foundation.Propagators Namespace

TwoBodyStateTransitionMatrixPropagatorAddLanguageSpecificTextSet("LSTCD29FED7_0?cpp=::|nu=.");GetEvaluator Method (EvaluatorGroup)

Parameters

Return Value

Reference

TwoBodyStateTransitionMatrixPropagatorGetEvaluator Method (EvaluatorGroup)