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SpecializedOrbitSolverCreateCriticallyInclinedSunSynchronousOrbit 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).

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 CreateCriticallyInclinedSunSynchronousOrbit(
	JulianDate orbitEpoch,
	ReferenceFrame inertialFrame,
	ReferenceFrame fixedFrame,
	double periapsisAltitude,
	double ascendingNodeLongitude,
	double gravitationalParameter,
	double j2UnnormalizedValue,
	double referenceDistance,
	double planetaryMeanMotion,
	bool isObliquityLessThan90Degrees


Type: AGI.Foundation.TimeJulianDate
The epoch associated with the initial conditions of the propagated orbit.
Type: AGI.Foundation.GeometryReferenceFrame
An inertial ReferenceFrame centered at the central body.
Type: AGI.Foundation.GeometryReferenceFrame
A fixed ReferenceFrame centered at the central body.
Type: SystemDouble
The distance of the periapsis of the orbit above the referenceDistance of the central body.
Type: SystemDouble
The longitude of the ascending node in the fixedFrame of the central body.
Type: SystemDouble
The gravitational parameter of the central body.
Type: SystemDouble
The non-normalized J2 parameter of the central body.
Type: SystemDouble
The equatorial radius of the central body that also serves as a reference distance for the J2 parameter.
Type: SystemDouble
The mean motion of the central body about the Sun. (The central body must be orbiting the Sun.)
Type: SystemBoolean
Sets the inclination to about 116.565 degrees if true (for Earth and other planets with posigrade rotations) or about 63.435 degrees if false (for Uranus with a retrograde rotation). Venus also has a retrograde rotation, but does not have strong enough J2 perturbations to support Sun-synchronous orbits.

Return Value

Type: J2Propagator
A J2Propagator object that is initialized at its ascending node with the desired orbit epoch, orbital elements, and gravity field.
ArgumentNullException Thrown if inertialFrame or fixedFrame is .
ArgumentOutOfRangeException Thrown if periapsisAltitude is negative or if planetaryMeanMotion is zero or negative.
ArithmeticException Thrown if a Sun-synchronous orbit does not exist for the given input conditions.
See Also