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SpecializedOrbitSolverCreateCircularOrbit Method

Creates a circular orbit with the desired characteristics.

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 J4Propagator CreateCircularOrbit(
	JulianDate orbitEpoch,
	ReferenceFrame inertialFrame,
	double altitude,
	double inclination,
	double rightAscensionOfAscendingNode,
	double gravitationalParameter,
	double j2UnnormalizedValue,
	double j4UnnormalizedValue,
	double referenceDistance
)

Parameters

orbitEpoch
Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
inertialFrame
Type: AGI.Foundation.GeometryReferenceFrame
An inertial ReferenceFrame centered at the central body.
altitude
Type: SystemDouble
The distance of the circular orbit above the referenceDistance of the central body.
inclination
Type: SystemDouble
The inclination of the orbit.
rightAscensionOfAscendingNode
Type: SystemDouble
The right ascension of the ascending node of the orbit.
gravitationalParameter
Type: SystemDouble
The gravitational parameter of the central body.
j2UnnormalizedValue
Type: SystemDouble
The non-normalized J2 parameter of the central body.
j4UnnormalizedValue
Type: SystemDouble
The non-normalized J4 parameter of the central body.
referenceDistance
Type: SystemDouble
The equatorial radius of the central body that also serves as a reference distance for the J2 and J4 parameters.

Return Value

Type: J4Propagator
A J4Propagator object that is initialized at its ascending node with the desired orbit epoch, orbital elements, and gravity field.
Exceptions
ExceptionCondition
ArgumentNullException Thrown when inertialFrame is .
ArgumentOutOfRangeException Thrown when altitude is negative.
ArgumentOutOfRangeException Thrown when inclination is less than zero or greater than π.
See Also