Click or drag to resize

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: 22.2.414.0 (22.2.414.0)
Syntax
public static class SpecializedOrbitSolver

The SpecializedOrbitSolver type exposes the following members.

Methods
  NameDescription
Public methodStatic memberCreateCircularOrbit
Creates a circular orbit with the desired characteristics.
Public methodStatic memberCreateCriticallyInclinedOrbit
Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations.
Public methodStatic memberCreateCriticallyInclinedSunSynchronousOrbit
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).
Public methodStatic memberCreateEarthCircularOrbit
Creates a circular orbit using default Earth parameters with the desired characteristics.
Public methodStatic memberCreateEarthCriticallyInclinedOrbit
Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations. Uses Earth defaults.
Public methodStatic memberCreateEarthCriticallyInclinedSunSynchronousOrbit
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.
Public methodStatic memberCreateEarthMolniyaOrbit
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).
Public methodStatic memberCreateEarthRepeatGroundTraceOrbitUsingApproximateAltitude
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.
Public methodStatic memberCreateEarthRepeatGroundTraceOrbitUsingApproximateRevsPerDay
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.
Public methodStatic memberCreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude
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.
Public methodStatic memberCreateEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay
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.
Public methodStatic memberCreateEarthSunSynchronousOrbitUsingAltitude
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.
Public methodStatic memberCreateEarthSunSynchronousOrbitUsingInclination
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.
Public methodStatic memberCreateGeostationaryOrbit
Creates a geostationary orbit that always remains above the Earth at the desired Earth-fixed longitude.
Public methodStatic memberCreateMolniyaOrbit
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).
Public methodStatic memberCreateRepeatGroundTraceOrbitUsingApproximateAltitude
Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
Public methodStatic memberCreateRepeatGroundTraceOrbitUsingApproximateRevsPerDay
Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
Public methodStatic memberCreateRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude
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.
Public methodStatic memberCreateRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay
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.
Public methodStatic memberCreateStationaryOrbit
Creates a stationary orbit that always remains above the central body at the desired body-fixed longitude.
Public methodStatic memberCreateSunSynchronousOrbitUsingAltitude
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.
Public methodStatic memberCreateSunSynchronousOrbitUsingInclination
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.
Top
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.
See Also