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SpecializedOrbitSolverCreateMolniyaOrbit Method

Creates an elliptical orbit with an argument of periapsis that remains constant under J2 perturbations (critically-inclined) and has an orbital period that is exactly half the rotation period of the central body (semi-synchronous).

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 CreateMolniyaOrbit(
	JulianDate orbitEpoch,
	ReferenceFrame inertialFrame,
	ReferenceFrame fixedFrame,
	double periapsisAltitude,
	double argumentOfPeriapsis,
	double apoapsisLongitude,
	double gravitationalParameter,
	double j2UnnormalizedValue,
	double referenceDistance,
	bool isObliquityLessThan90Degrees
)

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.
periapsisAltitude
Type: SystemDouble
The distance of the periapsis of the orbit above the referenceDistance of the central body.
argumentOfPeriapsis
Type: SystemDouble
The argument of periapsis of the orbit.
apoapsisLongitude
Type: SystemDouble
The longitude of the apoapsis 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.
isObliquityLessThan90Degrees
Type: SystemBoolean
Sets the inclination to about 63.435 degrees if true (for Earth and most other planets and moons with posigrade rotations) or about 116.565 degrees if false (for Uranus, Venus, Neptune's moon Triton, and other central bodies with retrograde rotations).

Return Value

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