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SpecializedOrbitSolverCreateEarthMolniyaOrbit Method

Creates an elliptical orbit with an argument of periapsis that remains constant under J2 perturbations (critically-inclined) and has an orbital period that is exactly half the rotation period of the Earth (semi-synchronous).

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.2.419.0 (24.2.419.0)
Syntax
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public static J2Propagator CreateEarthMolniyaOrbit(
	JulianDate orbitEpoch,
	double periapsisAltitude,
	double argumentOfPeriapsis,
	double apoapsisLongitude
)

Parameters

orbitEpoch
Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
periapsisAltitude
Type: SystemDouble
The distance of the periapsis of the orbit above Earth's equatorial radius.
argumentOfPeriapsis
Type: SystemDouble
The argument of periapsis of the orbit.
apoapsisLongitude
Type: SystemDouble
The longitude of the apoapsis in the Earth-fixed frame.

Return Value

Type: J2Propagator
A J2Propagator object that is initialized at its periapsis with the desired orbit epoch, orbital elements, and gravity field.
Exceptions
ExceptionCondition
ArgumentOutOfRangeException Thrown when periapsisAltitude is negative.
Remarks
Uses constants from the EarthGravitationalModel2008 for gravitational parameter, J2, and reference distance. The inertial and fixed reference frames are defined by the instance of EarthCentralBody in the CentralBodiesFacet of the CalculationContext.
See Also