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SpecializedOrbitSolverCreateEarthCriticallyInclinedSunSynchronousOrbit Method

Creates an orbit with an argument of periapsis that remains constant under J2 perturbations (critically-inclined) and a right ascension of the ascending node that drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). Uses Earth defaults.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.1.418.0 (24.1.418.0)
public static J2Propagator CreateEarthCriticallyInclinedSunSynchronousOrbit(
	JulianDate orbitEpoch,
	double periapsisAltitude,
	double ascendingNodeLongitude


Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
Type: SystemDouble
The distance of the periapsis of the orbit above the Earth's equatorial radius.
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 orbit epoch and orbital elements
ArgumentOutOfRangeException Thrown if periapsisAltitude is negative.
ArithmeticException Thrown if a Sun-synchronous orbit does not exist for the given input conditions.
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