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SpecializedOrbitSolverCreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude Method

Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Its right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). The combination of the two effects enables this orbit to revisit its exact original ascending node longitude at exactly the same local solar time (and therefore the same lighting conditions) after the specified number of revolutions is completed. Uses Earth defaults.

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 CreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude(
	JulianDate guessOrbitEpoch,
	double approximateAltitude,
	Duration ascendingNodeLocalTime,
	int numberRevsToRepeat,
	double ascendingNodeLongitude
)

Parameters

guessOrbitEpoch
Type: AGI.Foundation.TimeJulianDate
An initial guess for the epoch associated with the initial conditions of the propagated orbit.
approximateAltitude
Type: SystemDouble
The approximate desired altitude for the repeat ground trace orbit. The method iterates to find the closest exact match.
ascendingNodeLocalTime
Type: AGI.Foundation.TimeDuration
The local solar time of the ascending node in seconds past midnight.
numberRevsToRepeat
Type: SystemInt32
The number of revolutions until the ground trace exactly repeats.
ascendingNodeLongitude
Type: SystemDouble
The longitude of the ascending node in the Earth-fixed frame.

Return Value

Type: J2Propagator
A J2Propagator object that is initialized at its ascending node with the desired local solar time of ascending node and orbital elements. Usually, its epoch will be different from the input guess epoch unless the longitude of the ascending node, the local solar time at ascending node, and the input guess epoch are consistent with each other by design or chance.
Exceptions
ExceptionCondition
ArgumentOutOfRangeException Thrown when approximateAltitude is negative or when numberRevsToRepeat is zero or negative.
ArithmeticException Thrown when a Sun-synchronous orbit does not exist for the given input conditions.
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