Uses of Class
agi.foundation.propagators.J2Propagator

Packages that use J2Propagator

Package	Description
agi.foundation.propagators	Contains types used in producing the state of an object from a known element set.

Uses of J2Propagator in agi.foundation.propagators

Methods in agi.foundation.propagators that return J2Propagator

Modifier and Type	Method and Description
static J2Propagator	SpecializedOrbitSolver.createCriticallyInclinedOrbit(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double periapsisAltitude, double apoapsisAltitude, double longitudeAscendingNode, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, boolean isPosigrade) Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations.
static J2Propagator	SpecializedOrbitSolver.createCriticallyInclinedSunSynchronousOrbit(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double periapsisAltitude, double ascendingNodeLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, double planetaryMeanMotion, boolean isObliquityLessThan90Degrees) 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).
static J2Propagator	SpecializedOrbitSolver.createEarthCriticallyInclinedOrbit(JulianDate orbitEpoch, double periapsisAltitude, double apoapsisAltitude, double longitudeAscendingNode, boolean isPosigrade) Creates a critically-inclined orbit with an argument of periapsis that remains constant under J2 Perturbations.
static J2Propagator	SpecializedOrbitSolver.createEarthCriticallyInclinedSunSynchronousOrbit(JulianDate orbitEpoch, double periapsisAltitude, double ascendingNodeLongitude) 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).
static J2Propagator	SpecializedOrbitSolver.createEarthMolniyaOrbit(JulianDate orbitEpoch, double periapsisAltitude, double argumentOfPeriapsis, double apoapsisLongitude) 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).
static J2Propagator	SpecializedOrbitSolver.createEarthRepeatGroundTraceOrbitUsingApproximateAltitude(JulianDate orbitEpoch, double approximateAltitude, double inclination, int numberRevsToRepeat, double ascendingNodeLongitude) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createEarthRepeatGroundTraceOrbitUsingApproximateRevsPerDay(JulianDate orbitEpoch, double approximateRevsPerDay, double inclination, int numberRevsToRepeat, double ascendingNodeLongitude) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude(JulianDate guessOrbitEpoch, double approximateAltitude, Duration ascendingNodeLocalTime, int numberRevsToRepeat, double ascendingNodeLongitude) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createEarthRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay(JulianDate guessOrbitEpoch, double approximateRevsPerDay, Duration ascendingNodeLocalTime, int numberRevsToRepeat, double ascendingNodeLongitude) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createEarthSunSynchronousOrbitUsingAltitude(JulianDate orbitEpoch, double altitude, Duration ascendingNodeLocalTime) 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).
static J2Propagator	SpecializedOrbitSolver.createEarthSunSynchronousOrbitUsingInclination(JulianDate orbitEpoch, double inclination, Duration ascendingNodeLocalTime) 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).
static J2Propagator	SpecializedOrbitSolver.createGeostationaryOrbit(JulianDate orbitEpoch, double stationaryLongitude) Creates a geostationary orbit that always remains above the Earth at the desired Earth-fixed longitude.
static J2Propagator	SpecializedOrbitSolver.createMolniyaOrbit(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double periapsisAltitude, double argumentOfPeriapsis, double apoapsisLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, boolean isObliquityLessThan90Degrees) 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).
static J2Propagator	SpecializedOrbitSolver.createRepeatGroundTraceOrbitUsingApproximateAltitude(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double approximateAltitude, double inclination, int numberRevsToRepeat, double ascendingNodeLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createRepeatGroundTraceOrbitUsingApproximateRevsPerDay(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double approximateRevsPerDay, double inclination, int numberRevsToRepeat, double ascendingNodeLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createRepeatGroundTraceSunSynchronousOrbitUsingApproximateAltitude(JulianDate guessOrbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double approximateAltitude, Duration ascendingNodeLocalTime, int numberRevsToRepeat, double ascendingNodeLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, double planetaryMeanMotion, boolean isObliquityLessThan90Degrees) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createRepeatGroundTraceSunSynchronousOrbitUsingApproximateRevsPerDay(JulianDate guessOrbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double approximateRevsPerDay, Duration ascendingNodeLocalTime, int numberRevsToRepeat, double ascendingNodeLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, double planetaryMeanMotion, boolean isObliquityLessThan90Degrees) Creates a circular orbit that exactly repeats its ground trace after a specified number of revolutions under the influence of J2 perturbations.
static J2Propagator	SpecializedOrbitSolver.createStationaryOrbit(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double stationaryLongitude, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, boolean isObliquityLessThan90Degrees) Creates a stationary orbit that always remains above the central body at the desired body-fixed longitude.
static J2Propagator	SpecializedOrbitSolver.createSunSynchronousOrbitUsingAltitude(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double altitude, Duration ascendingNodeLocalTime, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, double planetaryMeanMotion, boolean isObliquityLessThan90Degrees) 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).
static J2Propagator	SpecializedOrbitSolver.createSunSynchronousOrbitUsingInclination(JulianDate orbitEpoch, ReferenceFrame inertialFrame, ReferenceFrame fixedFrame, double inclination, Duration ascendingNodeLocalTime, double gravitationalParameter, double j2UnnormalizedValue, double referenceDistance, double planetaryMeanMotion, boolean isObliquityLessThan90Degrees) 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).

Methods in agi.foundation.propagators that return types with arguments of type J2Propagator

Modifier and Type	Method and Description
WalkerConstellationResult<J2Propagator>	WalkerConstellation.createJ2Propagator(JulianDate orbitEpoch, ReferenceFrame referenceFrame, double j2UnnormalizedValue, double referenceDistance) Creates a nested collection of satellite propagators.

Methods in agi.foundation.propagators with parameters of type J2Propagator

Modifier and Type	Method and Description
protected boolean	J2Propagator.checkForSameDefinition(J2Propagator other) Checks to determine if another instance has the same definition as this instance and returns true if it does.

Constructors in agi.foundation.propagators with parameters of type J2Propagator

Constructor and Description
J2Propagator(J2Propagator existingInstance, CopyContext context) Initializes a new instance as a copy of an existing instance.