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SpecializedOrbitSolverCreateEarthCircularOrbit Method

Creates a circular orbit using default Earth parameters with the desired characteristics.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 25.1.421.0 (25.1.421.0)
Syntax
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public static J4Propagator CreateEarthCircularOrbit(
	JulianDate orbitEpoch,
	double altitude,
	double inclination,
	double rightAscensionOfAscendingNode
)

Parameters

orbitEpoch
Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
altitude
Type: SystemDouble
The distance of the circular orbit above the equatorial radius of the Earth.
inclination
Type: SystemDouble
The inclination of the orbit.
rightAscensionOfAscendingNode
Type: SystemDouble
The right ascension of the ascending node of the orbit.

Return Value

Type: J4Propagator
A J4Propagator object that is initialized at its ascending node with the desired orbit epoch and orbital elements.
Exceptions
ExceptionCondition
ArgumentOutOfRangeException Thrown when altitude is negative.
ArgumentOutOfRangeException Thrown when inclination is less than zero or greater than π.
Remarks
Uses constants from the EarthGravitationalModel2008 for gravitational parameter, J2, J4, and reference distance. The inertial reference frame is defined by the instance of EarthCentralBody in the CentralBodiesFacet of the CalculationContext.
See Also