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SpecializedOrbitSolverCreateRepeatGroundTraceOrbitUsingApproximateAltitude Method

Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.

Namespace:  AGI.Foundation.Propagators
Assembly:  AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.3.420.0 (24.3.420.0)
Syntax
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public static J2Propagator CreateRepeatGroundTraceOrbitUsingApproximateAltitude(
	JulianDate orbitEpoch,
	ReferenceFrame inertialFrame,
	ReferenceFrame fixedFrame,
	double approximateAltitude,
	double inclination,
	int numberRevsToRepeat,
	double ascendingNodeLongitude,
	double gravitationalParameter,
	double j2UnnormalizedValue,
	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.
fixedFrame
Type: AGI.Foundation.GeometryReferenceFrame
A fixed ReferenceFrame centered at the central body.
approximateAltitude
Type: SystemDouble
The approximate desired altitude for the repeat ground trace orbit. The method iterates to find the closest exact match.
inclination
Type: SystemDouble
The inclination of the orbit.
numberRevsToRepeat
Type: SystemInt32
The number of revolutions until the ground trace exactly repeats.
ascendingNodeLongitude
Type: SystemDouble
The longitude of the ascending node in the fixedFrame of the central body.
gravitationalParameter
Type: SystemDouble
The gravitational parameter of the central body.
j2UnnormalizedValue
Type: SystemDouble
The non-normalized J2 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 parameter.

Return Value

Type: J2Propagator
A J2Propagator object that is initialized at its ascending node with the desired orbit epoch, orbital elements, and gravity field.
Exceptions
ExceptionCondition
ArgumentNullException Thrown when inertialFrame or fixedFrame is .
ArgumentOutOfRangeException Thrown when approximateAltitude is negative, when numberRevsToRepeat is zero or negative, or when inclination is less than zero or greater than π.
ArithmeticException Thrown when calculated rotation rate is zero due to incorrect inertial or fixed frame input.
See Also