LambertOrbitSolverSolveMinimumEccentricityTransfer Method (Cartesian, Cartesian, Cartesian)

Solves the constrained Lambert problem given the input. The solver is constrained to return the minimum eccentricity orbit.

Namespace: AGI.Foundation.Propagators
Assembly: AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.3.420.0 (24.3.420.0)

Syntax

C++

Copy

public LambertResult SolveMinimumEccentricityTransfer(
	Cartesian initialPosition,
	Cartesian finalPosition,
	Cartesian orbitalPlaneVector
)

Public Function SolveMinimumEccentricityTransfer ( 
	initialPosition As Cartesian,
	finalPosition As Cartesian,
	orbitalPlaneVector As Cartesian
) As LambertResult

public:
LambertResult^ SolveMinimumEccentricityTransfer(
	Cartesian initialPosition, 
	Cartesian finalPosition, 
	Cartesian orbitalPlaneVector
)

member SolveMinimumEccentricityTransfer : 
        initialPosition : Cartesian * 
        finalPosition : Cartesian * 
        orbitalPlaneVector : Cartesian -> LambertResult

Parameters

initialPosition: Type: AGI.Foundation.CoordinatesCartesian
The first position in the transfer orbit.
finalPosition: Type: AGI.Foundation.CoordinatesCartesian
The final position in the transfer orbit.
orbitalPlaneVector: Type: AGI.Foundation.CoordinatesCartesian
A vector that is used in conjunction with the initial position of the spacecraft to define the orbital plane in the case of ambiguity. Typically, the velocity at the initial position if known.

Return Value

Type: LambertResult

Reference

LambertOrbitSolver Class

SolveMinimumEccentricityTransfer Overload

AGI.Foundation.Propagators Namespace

LambertOrbitSolverAddLanguageSpecificTextSet("LST90F2B608_0?cpp=::|nu=.");SolveMinimumEccentricityTransfer Method (Cartesian, Cartesian, Cartesian)

Parameters

Return Value

Reference

LambertOrbitSolverSolveMinimumEccentricityTransfer Method (Cartesian, Cartesian, Cartesian)