SpecializedOrbitSolver Class

Create propagators that model specialized orbit types, including: circular, critically-inclined, stationary, Molniya, repeat ground trace, and Sun-synchronous.

Inheritance Hierarchy

SystemObject
AGI.Foundation.PropagatorsSpecializedOrbitSolver

Namespace: AGI.Foundation.Propagators
Assembly: AGI.Foundation.Models (in AGI.Foundation.Models.dll) Version: 24.3.420.0 (24.3.420.0)

Syntax

C++

Copy

public static class SpecializedOrbitSolver

Public NotInheritable Class SpecializedOrbitSolver

public ref class SpecializedOrbitSolver abstract sealed

[<AbstractClassAttribute>]
[<SealedAttribute>]
type SpecializedOrbitSolver =  class end

The SpecializedOrbitSolver type exposes the following members.

Methods

	Name	Description
	CreateCircularOrbit	Creates a circular orbit with the desired characteristics.
	CreateCriticallyInclinedOrbit	Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations.
	CreateCriticallyInclinedSunSynchronousOrbit	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).
	CreateEarthCircularOrbit	Creates a circular orbit using default Earth parameters with the desired characteristics.
	CreateEarthCriticallyInclinedOrbit	Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations. Uses Earth defaults.
	CreateEarthCriticallyInclinedSunSynchronousOrbit	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). Uses Earth defaults.
	CreateEarthMolniyaOrbit	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 Earth (semi-synchronous).
	CreateEarthRepeatGroundTraceOrbitUsingApproximateAltitude	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Uses Earth defaults.
	CreateEarthRepeatGroundTraceOrbitUsingApproximateRevsPerDay	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Uses Earth defaults.
	CreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Its right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). The combination of the two effects enables this orbit to revisit its exact original ascending node longitude at exactly the same local solar time (and therefore the same lighting conditions) after the specified number of revolutions is completed. Uses Earth defaults.
	CreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Its right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). The combination of the two effects enables this orbit to revisit its exact original ascending node longitude at exactly the same local solar time (and therefore the same lighting conditions) after the specified number of revolutions is completed. Uses Earth defaults.
	CreateEarthSunSynchronousOrbitUsingAltitude	Creates a circular orbit whose right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). Thus, the orbit would revisit its ascending node at exactly the same local solar time (and therefore the same lighting conditions) every orbit. However, it would revisit its ascending node at differing longitudes with no exact resonance.
	CreateEarthSunSynchronousOrbitUsingInclination	Creates a circular orbit whose right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). Thus, the orbit would revisit its ascending at exactly the same local solar time (and therefore the same lighting conditions) every orbit. However, it would revisit its ascending node at differing longitudes with no exact resonance. Uses Earth defaults.
	CreateGeostationaryOrbit	Creates a geostationary orbit that always remains above the Earth at the desired Earth-fixed longitude.
	CreateMolniyaOrbit	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).
	CreateRepeatGroundTraceOrbitUsingApproximateAltitude	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
	CreateRepeatGroundTraceOrbitUsingApproximateRevsPerDay	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
	CreateRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Its right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). The combination of the two effects enables this orbit to revisit its exact original ascending node longitude at exactly the same local solar time (and therefore the same lighting conditions) after the specified number of revolutions is completed.
	CreateRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay	Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations. Its right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). The combination of the two effects enables this orbit to revisit its exact original ascending node longitude at exactly the same local solar time (and therefore the same lighting conditions) after the specified number of revolutions is completed.
	CreateStationaryOrbit	Creates a stationary orbit that always remains above the central body at the desired body-fixed longitude.
	CreateSunSynchronousOrbitUsingAltitude	Creates a circular orbit whose right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). Thus, the orbit would revisit its ascending node at exactly the same local solar time (and therefore the same lighting conditions) every orbit. However, it would revisit its ascending node at differing longitudes with no exact resonance.
	CreateSunSynchronousOrbitUsingInclination	Creates a circular orbit whose right ascension of the ascending node drifts under J2 perturbations at the same rate as the central body's orbit around the Sun (Sun-synchronous). Thus, the orbit would revisit its ascending at exactly the same local solar time (and therefore the same lighting conditions) every orbit. However, it would revisit its ascending node at differing longitudes with no exact resonance.

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Remarks

The CreateCircularOrbit static method creates a J4Propagator object with initial Keplerian elements consistent with the inputs and circular orbit characteristics. The other static methods create J2Propagator objects with initial Keplerian elements consistent with their inputs and orbital characteristics. The ModifiedKeplerianElements of each created propagator object can be obtained from their InitialConditions property. The OrbitEpoch is another property that can be obtained from these objects. Finally, PropagatorPoint objects can be created from these propagators using the method CreatePoint.

Reference

AGI.Foundation.Propagators Namespace