| Package | Description |
|---|---|
| agi.foundation.access |
Contains types used in performing access calculations.
|
| agi.foundation.aircraftpropagation |
Contains types for propagating an aircraft through various maneuvers subject to
flight phase performance models and wind effects.
|
| agi.foundation.ccsds |
Contains types for interoperating with data formats supported by
The Consultative Committee for Space Data Systems (CCSDS).
|
| agi.foundation.celestial |
Contains types used in modeling characteristics of celestial objects and celestial phenomena.
|
| agi.foundation.cesium |
Contains types used for defining graphical properties of definitional objects to be written out as CZML.
|
| agi.foundation.cesium.advanced |
Contains less-often used types for generating CZML.
|
| agi.foundation.communications |
Contains types for representing electromagnetic signals and propagating them along communication links.
|
| agi.foundation.coordinates |
Contains types for quantifying and converting between various coordinate representations.
|
| agi.foundation.geometry |
Contains types for expressing the motion of fundamental geometric objects such as points, axes, and reference frames;
the manner in which they are related; and transformations between representations.
|
| agi.foundation.geometry.discrete |
Contains types which define discretization algorithms and metadata for analysis of spatial geometry.
|
| agi.foundation.graphics |
Provides commonly used and instantiated graphics types related to 3D scene management, terrain and imagery, and more.
|
| agi.foundation.numericalmethods |
Contains general numerical algorithms.
|
| agi.foundation.platforms |
Contains types used in modeling various mechanical platforms such as satellites, facilities, aircraft, etc.
|
| agi.foundation.propagators |
Contains types used in producing the state of an object from a known element set.
|
| agi.foundation.propagators.advanced |
Contains types used to create more specialized propagation scenarios.
|
| agi.foundation.segmentpropagation |
Contains types for modeling a trajectory in segments, where the type of propagation varies for each segment.
|
| agi.foundation.stk |
Contains types for interoperating with the STK desktop application and related data.
|
| agi.foundation.terrain |
Contains types for reading and analyzing terrain data.
|
| agi.foundation.tracking |
Contains types for acquiring, analyzing and archiving dynamic data, such as those found in real-time feeds or simulation environments.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
LinkSpeedOfLight.getInertialFrame()
Gets the inertial frame in which the light path is modeled.
|
ReferenceFrame |
AccessComputation.getInertialFrameForLightTravel()
Gets the inertial reference frame in which light travel is modeled.
|
| Modifier and Type | Method and Description |
|---|---|
static Evaluator<JulianDate> |
AccessConstraintSampling.getNextStepFromRelativeMotionEvaluator(ReferenceFrame observer,
Point target,
double maximumAngularMotion,
EvaluatorGroup group)
Gets an evaluator that determines the next time at which to sample a constraint function
based on the relative motion between two objects and a maximum relative motion per step.
|
void |
LinkSpeedOfLight.setInertialFrame(ReferenceFrame value)
Sets the inertial frame in which the light path is modeled.
|
void |
AccessComputation.setInertialFrameForLightTravel(ReferenceFrame value)
Sets the inertial reference frame in which light travel is modeled.
|
| Constructor and Description |
|---|
LinkSpeedOfLight(IServiceProvider transmitter,
IServiceProvider receiver,
ReferenceFrame inertialFrame)
Initializes a new instance which only accounts for light travel time (not aberration) in determining the
displacement vectors between the two objects.
|
LinkSpeedOfLight(IServiceProvider transmitter,
IServiceProvider receiver,
ReferenceFrame inertialFrame,
double lightTravelTimeConvergenceTolerance)
Initializes a new instance which only accounts for light travel time (not aberration) in determining the
displacement vectors between the two objects.
|
LinkSpeedOfLight(IServiceProvider transmitter,
IServiceProvider receiver,
ReferenceFrame inertialFrame,
double lightTravelTimeConvergenceTolerance,
VectorVelocity transmitterVelocityOfMovingFrame,
VectorVelocity receiverVelocityOfMovingFrame)
Initializes a new instance which accounts for aberration in addition to light travel time in determining the
displacement vectors between the two objects.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
AircraftMotionIntegrationPoint.getIntegrationFrame()
Gets the
ReferenceFrame used to define the state during integration. |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
CcsdsOrbitEphemerisMessageSegment.getReferenceFrame()
Gets or sets the reference frame in which the ephemeris data is given.
|
| Modifier and Type | Method and Description |
|---|---|
void |
CcsdsOrbitEphemerisMessageSegment.setReferenceFrame(ReferenceFrame value)
Gets or sets the reference frame in which the ephemeris data is given.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
MagneticFieldVector.getDefinedInFrame()
Gets the reference frame for the magnetic field.
|
ReferenceFrame |
VestaCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
VenusCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
UranusCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
TritonCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
TitaniaCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
TitanCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
TethysCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
SunCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
SaturnCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
RheaCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
PlutoCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
PhoebeCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
PhobosCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
NeptuneCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
MoonCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
MimasCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
MercuryCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
MarsCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
JupiterCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
IoCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
IapetusCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
HyperionCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
GanymedeCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
EuropaCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
EnceladusCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
EarthCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
DioneCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
DeimosCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
CharonCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
CeresCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
abstract ReferenceFrame |
CentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
CallistoCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
ArielCentralBody.getFixedFrame()
Gets the default Fixed frame that corresponds to the surface features of this central body.
|
ReferenceFrame |
VestaCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
VenusCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
UranusCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
TritonCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
TitaniaCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
TitanCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
TethysCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
SunCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
SolarSystemBarycenter.getInertialFrame()
Gets the default inertial frame for this solar system.
|
ReferenceFrame |
ScalarOccultation.getInertialFrame()
Gets or sets an alternate inertial reference frame.
|
ReferenceFrame |
SaturnCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
RheaCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
PlutoCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
PlanetarySystemBarycenter.getInertialFrame()
Gets the default inertial frame for this planetary system.
|
ReferenceFrame |
PhoebeCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
PhobosCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
NeptuneCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
MoonCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
MimasCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
MercuryCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
MarsCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
JupiterCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
IoCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
IapetusCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
HyperionCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
GanymedeCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
EuropaCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
EnceladusCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
EarthCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
DioneCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
DeimosCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
CharonCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
CeresCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
abstract ReferenceFrame |
CentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
CallistoCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
ArielCentralBody.getInertialFrame()
Gets the default Inertial frame for this central body.
|
ReferenceFrame |
ScalarVariableAreaArgumentLatitude.getIntegrationFrame()
|
ReferenceFrame |
EarthCentralBody.getInternationalCelestialReferenceFrame()
Gets the International Celestial Reference Frame.
|
ReferenceFrame |
SunCentralBody.getJ2000Frame()
Gets the J2000 frame centered at the Sun.
|
ReferenceFrame |
EarthCentralBody.getJ2000Frame()
Gets the J2000 Reference Frame.
|
ReferenceFrame |
EarthCentralBody.getMeanEclipticMeanEquinoxFrame()
Gets the Mean Ecliptic Mean Equinox Reference Frame.
|
ReferenceFrame |
EarthCentralBody.getMeanEclipticTrueEquinoxFrame()
Gets the Mean Ecliptic True Equinox Reference Frame.
|
ReferenceFrame |
EarthCentralBody.getMeanEquatorMeanEquinoxFrame()
Gets the Mean Equator Mean Equinox Reference Frame, also
known as the "Mean of Date" reference frame.
|
ReferenceFrame |
JplDE440.getMoonFixedFrame()
Uses the JplDE440 data to return the orientation and position of the Moon's principal axes of inertia to define a fixed
frame.
|
ReferenceFrame |
JplDE430.getMoonFixedFrame()
Uses the JplDE430 data to return the orientation and position of the Moon's principal axes of inertia to define a fixed
frame.
|
ReferenceFrame |
JplDE421.getMoonFixedFrame()
Uses the JplDE421 data to return the orientation and position of the Moon's principal axes of inertia to define a fixed
frame.
|
ReferenceFrame |
JplDE405.getMoonFixedFrame()
Uses the JplDE405 data to return the orientation and position of the Moon's principal axes of inertia to define a fixed
frame.
|
ReferenceFrame |
JplDE403.getMoonFixedFrame()
Uses the JplDE403 data to return the orientation and position of the Moon's principal axes of inertia to define a fixed
frame.
|
ReferenceFrame |
JplDE440.getMoonTopographicFixedFrame()
Uses the JplDE440 data to return the orientation and position of the Moon's "Mean Earth" axes which define a fixed
frame with the z-axis pointing toward the mean axis of rotation, the x-axis pointing toward the mean
direction to the Earth, and the y-axis orthogonal.
|
ReferenceFrame |
JplDE430.getMoonTopographicFixedFrame()
Uses the JplDE430 data to return the orientation and position of the Moon's "Mean Earth" axes which define a fixed
frame with the z-axis pointing toward the mean axis of rotation, the x-axis pointing toward the mean
direction to the Earth, and the y-axis orthogonal.
|
ReferenceFrame |
JplDE421.getMoonTopographicFixedFrame()
Uses the JplDE421 data to return the orientation and position of the Moon's "Mean Earth" axes which define a fixed
frame with the z-axis pointing toward the mean axis of rotation, the x-axis pointing toward the mean
direction to the Earth, and the y-axis orthogonal.
|
ReferenceFrame |
JplDE405.getMoonTopographicFixedFrame()
Uses the JplDE405 data to return the orientation and position of the Moon's "Mean Earth" axes which define a fixed
frame with the z-axis pointing toward the mean axis of rotation, the x-axis pointing toward the mean
direction to the Earth, and the y-axis orthogonal.
|
ReferenceFrame |
JplDE403.getMoonTopographicFixedFrame()
Uses the JplDE403 data to return the orientation and position of the Moon's "Mean Earth" axes which define a fixed
frame with the z-axis pointing toward the mean axis of rotation, the x-axis pointing toward the mean
direction to the Earth, and the y-axis orthogonal.
|
ReferenceFrame |
VestaCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
VenusCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
UranusCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
TritonCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
TitaniaCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
TitanCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
TethysCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
SunCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
SaturnCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
RheaCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
PlutoCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
PhoebeCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
PhobosCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
NeptuneCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
MoonCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
MimasCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
MercuryCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
MarsCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
JupiterCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
IoCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
IapetusCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
HyperionCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
GanymedeCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
EuropaCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
EnceladusCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
EarthCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
DioneCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
DeimosCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
CharonCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
CeresCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
abstract ReferenceFrame |
CentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
CallistoCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
ArielCentralBody.getPrincipalFrame()
Gets the default Fixed frame that corresponds to the gravity frame of this central body.
|
ReferenceFrame |
EarthCentralBody.getPseudoFixedFrame()
Gets the pseudo-fixed reference frame.
|
ReferenceFrame |
CentralBody.getReferenceFrame() |
ReferenceFrame |
EarthCentralBody.getTrueEquatorMeanEquinoxFrame()
Gets the True Equator, Mean Equinox (TEME) Reference Frame.
|
ReferenceFrame |
EarthCentralBody.getTrueEquatorTrueEquinoxFrame()
Gets the True Equator True Equinox Reference Frame, also
known as the "True of Date" reference frame.
|
| Modifier and Type | Method and Description |
|---|---|
void |
MagneticFieldVector.setDefinedInFrame(ReferenceFrame value)
Sets the reference frame for the magnetic field.
|
void |
VestaCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
VenusCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
UranusCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
TritonCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
TitaniaCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
TitanCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
TethysCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
SunCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
SaturnCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
RheaCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
PlutoCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
PhoebeCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
PhobosCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
NeptuneCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
MoonCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
MimasCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
MercuryCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
MarsCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
JupiterCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
IoCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
IapetusCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
HyperionCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
GanymedeCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
EuropaCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
EnceladusCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
EarthCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
DioneCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
DeimosCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
CharonCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
CeresCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
abstract void |
CentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
CallistoCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
ArielCentralBody.setFixedFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the surface features of this central body.
|
void |
VestaCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
VenusCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
UranusCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
TritonCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
TitaniaCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
TitanCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
TethysCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
SunCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
SolarSystemBarycenter.setInertialFrame(ReferenceFrame value)
Sets the default inertial frame for this solar system.
|
void |
ScalarOccultation.setInertialFrame(ReferenceFrame value)
Gets or sets an alternate inertial reference frame.
|
void |
SaturnCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
RheaCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
PlutoCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
PlanetarySystemBarycenter.setInertialFrame(ReferenceFrame value)
Sets the default inertial frame for this planetary system.
|
void |
PhoebeCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
PhobosCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
NeptuneCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
MoonCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
MimasCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
MercuryCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
MarsCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
JupiterCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
IoCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
IapetusCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
HyperionCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
GanymedeCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
EuropaCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
EnceladusCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
EarthCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
DioneCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
DeimosCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
CharonCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
CeresCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
abstract void |
CentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
CallistoCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
ArielCentralBody.setInertialFrame(ReferenceFrame value)
Sets the default Inertial frame for this central body.
|
void |
ScalarVariableAreaArgumentLatitude.setIntegrationFrame(ReferenceFrame value)
|
void |
EarthCentralBody.setInternationalCelestialReferenceFrame(ReferenceFrame value)
Sets the International Celestial Reference Frame.
|
void |
SunCentralBody.setJ2000Frame(ReferenceFrame value)
Sets the J2000 frame centered at the Sun.
|
void |
EarthCentralBody.setJ2000Frame(ReferenceFrame value)
Sets the J2000 Reference Frame.
|
void |
EarthCentralBody.setMeanEclipticMeanEquinoxFrame(ReferenceFrame value)
Sets the Mean Ecliptic Mean Equinox Reference Frame.
|
void |
EarthCentralBody.setMeanEclipticTrueEquinoxFrame(ReferenceFrame value)
Sets the Mean Ecliptic True Equinox Reference Frame.
|
void |
EarthCentralBody.setMeanEquatorMeanEquinoxFrame(ReferenceFrame value)
Sets the Mean Equator Mean Equinox Reference Frame, also
known as the "Mean of Date" reference frame.
|
void |
VestaCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
VenusCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
UranusCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
TritonCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
TitaniaCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
TitanCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
TethysCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
SunCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
SaturnCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
RheaCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
PlutoCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
PhoebeCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
PhobosCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
NeptuneCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
MoonCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
MimasCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
MercuryCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
MarsCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
JupiterCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
IoCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
IapetusCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
HyperionCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
GanymedeCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
EuropaCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
EnceladusCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
EarthCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
DioneCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
DeimosCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
CharonCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
CeresCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
abstract void |
CentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
CallistoCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
ArielCentralBody.setPrincipalFrame(ReferenceFrame value)
Sets the default Fixed frame that corresponds to the gravity frame of this central body.
|
void |
EarthCentralBody.setPseudoFixedFrame(ReferenceFrame value)
Sets the pseudo-fixed reference frame.
|
void |
EarthCentralBody.setTrueEquatorMeanEquinoxFrame(ReferenceFrame value)
Sets the True Equator, Mean Equinox (TEME) Reference Frame.
|
void |
EarthCentralBody.setTrueEquatorTrueEquinoxFrame(ReferenceFrame value)
Sets the True Equator True Equinox Reference Frame, also
known as the "True of Date" reference frame.
|
| Constructor and Description |
|---|
ScalarVariableAreaArgumentLatitude(int interpolationOrder,
Map<Double,Double> areaData,
Point integrationPoint,
ReferenceFrame integrationFrame)
Initializes a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
CesiumReferenceFrameExtension.getCesiumReferenceFrame()
Gets the reference frame in which an object's CZML position will be written.
|
| Modifier and Type | Method and Description |
|---|---|
void |
CesiumReferenceFrameExtension.setCesiumReferenceFrame(ReferenceFrame value)
Sets the reference frame in which an object's CZML position will be written.
|
| Constructor and Description |
|---|
CesiumReferenceFrameExtension(ReferenceFrame graphicsReferenceFrame)
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
ICesiumReferenceFrameService.getCesiumReferenceFrame()
Gets the reference frame in which an object's CZML position will be written.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
CommunicationLinkCollection.getDefaultInertialFrame()
Gets the default inertial frame in which the light path is modeled
for new
LinkSpeedOfLight instances created by the collection. |
| Modifier and Type | Method and Description |
|---|---|
void |
CommunicationLinkCollection.setDefaultInertialFrame(ReferenceFrame value)
Sets the default inertial frame in which the light path is modeled
for new
LinkSpeedOfLight instances created by the collection. |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
ReferenceFrameAdapter.getCurrentReferenceFrame()
Gets the
ReferenceFrame that the
ElementIdentification (get / set)
in the state will be in once the state is adapted. |
ReferenceFrame |
ReferenceFrameAdapter.getPreviousReferenceFrame()
Gets the
ReferenceFrame that the
ElementIdentification (get / set)
in the previous state is defined in. |
| Modifier and Type | Method and Description |
|---|---|
void |
ReferenceFrameAdapter.setCurrentReferenceFrame(ReferenceFrame value)
Sets the
ReferenceFrame that the
ElementIdentification (get / set)
in the state will be in once the state is adapted. |
void |
ReferenceFrameAdapter.setPreviousReferenceFrame(ReferenceFrame value)
Sets the
ReferenceFrame that the
ElementIdentification (get / set)
in the previous state is defined in. |
| Constructor and Description |
|---|
ReferenceFrameAdapter(String elementIdentification,
ReferenceFrame currentReferenceFrame)
Initializes a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
VectorEllipsoidSurfaceNormal.getEllipsoidFixedFrame()
Gets a reference frame fixed to the ellipsoid.
|
ReferenceFrame |
PointFixedAtJulianDate.getFixedWithRespectTo()
|
ReferenceFrame |
ScalarDeltaSphericalElement.getFrame()
Gets the
ReferenceFrame that the FromPoint (get / set)
and the ToPoint (get / set) will be evaluated in. |
ReferenceFrame |
ScalarSphericalElement.getFrame()
|
ReferenceFrame |
ScalarPointElement.getFrame()
|
ReferenceFrame |
ScalarModifiedKeplerianElement.getFrame()
Gets the
ReferenceFrame to compute the point in. |
ReferenceFrame |
ScalarKozaiIzsakMeanElement.getFrame()
Gets the
ReferenceFrame to compute the point in. |
ReferenceFrame |
ScalarEquinoctialElement.getFrame()
Gets the
ReferenceFrame to compute the point in. |
ReferenceFrame |
ScalarDelaunayElement.getFrame()
Gets the
ReferenceFrame to compute the point in. |
ReferenceFrame |
PointInReferenceFrame.getFrame()
|
ReferenceFrame |
PointFixedOffset.getFrame()
Gets the reference frame in which the point is defined.
|
ReferenceFrame |
DynamicModifiedKeplerianElements.getFrame()
|
ReferenceFrame |
DynamicKozaiIzsakMeanElements.getFrame()
|
ReferenceFrame |
DynamicEquinoctialElements.getFrame()
|
ReferenceFrame |
DynamicDelaunayElements.getFrame()
|
ReferenceFrame |
VectorApparentDisplacement.getInertialFrame()
Gets the inertial frame in which the light path is modeled.
|
ReferenceFrame |
PointPropagationParameter.getIntegrationFrame()
Gets the
ReferenceFrame used to define the state during integration. |
ReferenceFrame |
AxesPropagationParameter.getIntegrationFrame()
Gets the
ReferenceFrame used to define the state during integration. |
ReferenceFrame |
VectorBPlane.getParentReferenceFrame()
|
ReferenceFrame |
AxesBPlane.getParentReferenceFrame()
|
ReferenceFrame |
ScalarSquintAngle.getReferenceFrame()
Gets the reference frame in which the objects are observed.
|
ReferenceFrame |
ScalarDopplerConeAngle.getReferenceFrame()
Gets the reference frame in which the moving object will be observed.
|
ReferenceFrame |
AxesVehicleVelocityLocalHorizontal.getReferenceFrame()
Gets the reference frame relative to which this axes is defined.
|
ReferenceFrame |
AxesLocalVerticalLocalHorizontal.getReferenceFrame()
Gets the reference frame in which this points motion is to be observed.
|
ReferenceFrame |
VectorVelocity.getReferenceFrame()
Gets the reference frame.
|
ReferenceFrame |
VectorAcceleration.getReferenceFrame()
Gets the reference frame.
|
ReferenceFrame |
PointInterpolator.getReferenceFrame()
Gets the reference frame in which the interpolated point is defined.
|
ReferenceFrame |
ParameterizedPoint.getReferenceFrame()
Gets the
ReferenceFrame used to define the state during integration. |
ReferenceFrame |
ParameterizedOnStatePoint.getReferenceFrame()
Gets the
ReferenceFrame that the elements of
this point in the parameterized state are represented in. |
ReferenceFrame |
ParameterizedOnEvaluatorPoint.getReferenceFrame()
Gets the
ReferenceFrame in which this point is defined. |
ReferenceFrame |
IKinematicStateService.getReferenceFrame()
Gets the reference frame that describes both the position and orientation of this object.
|
static ReferenceFrame |
GeometryTransformer.Advanced.unwrap(ReferenceFrame frame)
|
| Modifier and Type | Method and Description |
|---|---|
protected static TimeIntervalCollection1<ReferenceFrame> |
PointEvaluator.createConstantDefinedIn(ReferenceFrame definedIn)
Creates a
TimeIntervalCollection indicating that the ReferenceFrame that this Point is
defined in is the same for all possible times. |
TimeIntervalCollection1<ReferenceFrame> |
ReferenceFrameEvaluator.getDefinedInIntervals()
Gets a
TimeIntervalCollection1 where the Data (get) property of
each interval is the ReferenceFrame in which this ReferenceFrame is defined over the interval. |
abstract TimeIntervalCollection1<ReferenceFrame> |
PointEvaluator.getDefinedInIntervals()
Gets a
TimeIntervalCollection where the Data (get) property of
each interval is the ReferenceFrame in which this Point is defined over the interval. |
| Modifier and Type | Method and Description |
|---|---|
Point |
InternationalTerrestrialReferenceFrameTransformer.convertPoint(ReferenceFrame fromFrame,
Point point)
Converts a
Point such that the ITRF transformation is applied when it is evaluated. |
protected static TimeIntervalCollection1<ReferenceFrame> |
PointEvaluator.createConstantDefinedIn(ReferenceFrame definedIn)
Creates a
TimeIntervalCollection indicating that the ReferenceFrame that this Point is
defined in is the same for all possible times. |
Vector |
Point.createVectorAcceleration(ReferenceFrame frame)
Constructs a vector which represents the second derivative of this point's position.
|
Vector |
Point.createVectorDerivative(ReferenceFrame frame,
int order)
Constructs a vector which represents the requested order of the derivative of this point's position.
|
Vector |
PointPropagationParameter.createVectorVelocity(ReferenceFrame frame)
Constructs a vector which represents the derivative of this point's position.
|
Vector |
Point.createVectorVelocity(ReferenceFrame frame)
Constructs a vector which represents the derivative of this point's position.
|
static ReferenceFrameEvaluator |
GeometryTransformer.getReferenceFrameTransformation(ReferenceFrame from,
ReferenceFrame to)
Gets an evaluator that can evaluate the transformation between two reference frames.
|
static ReferenceFrameEvaluator |
GeometryTransformer.getReferenceFrameTransformation(ReferenceFrame from,
ReferenceFrame to,
EvaluatorGroup group)
Gets an evaluator that can evaluate the transformation between two reference frames.
|
Scalar |
Point.getScalarElement(CartesianElement element,
ReferenceFrame referenceFrame)
Returns a
Scalar representing the X, Y, Z, or Magnitude
of this point. |
Scalar |
Point.getScalarElement(CartesianElement element,
ReferenceFrame referenceFrame,
int order)
Returns a
Scalar representing the X, Y, Z, or Magnitude, or any derivative of
those elements of this point. |
static PointEvaluator |
GeometryTransformer.observePoint(Point point,
ReferenceFrame inFrame)
Gets an evaluator that can be used to find the
Motion<Cartesian>
of this point in the new Frame (get / set) at a given JulianDate. |
static PointEvaluator |
GeometryTransformer.observePoint(Point point,
ReferenceFrame inFrame,
EvaluatorGroup group)
Gets an evaluator that can be used to find the
Motion<Cartesian>
of this point in the new Frame (get / set) at a given JulianDate. |
void |
VectorEllipsoidSurfaceNormal.setEllipsoidFixedFrame(ReferenceFrame value)
Sets a reference frame fixed to the ellipsoid.
|
void |
PointFixedAtJulianDate.setFixedWithRespectTo(ReferenceFrame value)
|
void |
ScalarDeltaSphericalElement.setFrame(ReferenceFrame value)
Sets the
ReferenceFrame that the FromPoint (get / set)
and the ToPoint (get / set) will be evaluated in. |
void |
ScalarSphericalElement.setFrame(ReferenceFrame value)
|
void |
ScalarPointElement.setFrame(ReferenceFrame value)
|
void |
ScalarModifiedKeplerianElement.setFrame(ReferenceFrame value)
Sets the
ReferenceFrame to compute the point in. |
void |
ScalarKozaiIzsakMeanElement.setFrame(ReferenceFrame value)
Sets the
ReferenceFrame to compute the point in. |
void |
ScalarEquinoctialElement.setFrame(ReferenceFrame value)
Sets the
ReferenceFrame to compute the point in. |
void |
ScalarDelaunayElement.setFrame(ReferenceFrame value)
Sets the
ReferenceFrame to compute the point in. |
void |
PointInReferenceFrame.setFrame(ReferenceFrame value)
|
void |
PointFixedOffset.setFrame(ReferenceFrame value)
Sets the reference frame in which the point is defined.
|
void |
DynamicModifiedKeplerianElements.setFrame(ReferenceFrame value)
|
void |
DynamicKozaiIzsakMeanElements.setFrame(ReferenceFrame value)
|
void |
DynamicEquinoctialElements.setFrame(ReferenceFrame value)
|
void |
DynamicDelaunayElements.setFrame(ReferenceFrame value)
|
void |
VectorApparentDisplacement.setInertialFrame(ReferenceFrame value)
Sets the inertial frame in which the light path is modeled.
|
void |
PointPropagationParameter.setIntegrationFrame(ReferenceFrame value)
Sets the
ReferenceFrame used to define the state during integration. |
void |
AxesPropagationParameter.setIntegrationFrame(ReferenceFrame value)
Sets the
ReferenceFrame used to define the state during integration. |
void |
VectorBPlane.setParentReferenceFrame(ReferenceFrame value)
|
void |
AxesBPlane.setParentReferenceFrame(ReferenceFrame value)
|
void |
ScalarSquintAngle.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the objects are observed.
|
void |
ScalarDopplerConeAngle.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the moving object will be observed.
|
void |
AxesVehicleVelocityLocalHorizontal.setReferenceFrame(ReferenceFrame value)
Sets the reference frame relative to which this axes is defined.
|
void |
AxesLocalVerticalLocalHorizontal.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which this points motion is to be observed.
|
void |
VectorVelocity.setReferenceFrame(ReferenceFrame value)
Sets the reference frame.
|
void |
VectorAcceleration.setReferenceFrame(ReferenceFrame value)
Sets the reference frame.
|
void |
PointInterpolator.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the interpolated point is defined.
|
void |
ParameterizedPoint.setReferenceFrame(ReferenceFrame value)
Sets the
ReferenceFrame used to define the state during integration. |
void |
ParameterizedOnStatePoint.setReferenceFrame(ReferenceFrame value)
Sets the
ReferenceFrame that the elements of
this point in the parameterized state are represented in. |
void |
ParameterizedOnEvaluatorPoint.setReferenceFrame(ReferenceFrame value)
Sets the
ReferenceFrame in which this point is defined. |
static ReferenceFrame |
GeometryTransformer.Advanced.unwrap(ReferenceFrame frame)
|
| Constructor and Description |
|---|
AxesBPlane(Point location,
CentralBody centralBody,
double gravitationalParameter,
ReferenceFrame parentReferenceFrame)
Initializes a new instance.
|
AxesLocalVerticalLocalHorizontal(ReferenceFrame frame,
Point point)
Initializes a new instance with the specified parameters.
|
AxesPropagationParameter(ReferenceFrame frame)
Initializes a new instance with the given frame of integration.
|
AxesVehicleVelocityLocalHorizontal(ReferenceFrame referenceFrame,
Point point)
Initializes a new instance with the specified parameters.
|
DynamicDelaunayElements(Point location,
double gravitationalParameter,
ReferenceFrame frame)
Initializes a new instance.
|
DynamicEquinoctialElements(Point location,
double gravitationalParameter,
ReferenceFrame frame)
Initializes a new instance.
|
DynamicKozaiIzsakMeanElements(Point location,
double gravitationalParameter,
ReferenceFrame frame,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
DynamicModifiedKeplerianElements(Point location,
double gravitationalParameter,
ReferenceFrame frame)
Initializes a new instance.
|
ParameterizedOnEvaluatorPoint(PointEvaluatorParameter parameter,
ReferenceFrame referenceFrame)
Initializes a new instance.
|
ParameterizedOnEvaluatorPoint(ReferenceFrame referenceFrame)
Initializes a new instance.
|
ParameterizedOnStatePoint(TimeBasedStateParameter parameter,
ReferenceFrame referenceFrame,
String elementIdentification)
Initializes a new instance.
|
ParameterizedPoint(CartesianParameter parameter,
ReferenceFrame referenceFrame)
Initializes a new instance.
|
ParameterizedPoint(ReferenceFrame referenceFrame)
Initializes a new instance.
|
PointFixedAtJulianDate(Point fixedPoint,
ReferenceFrame fixedWithRespectTo,
ValueDefinition<JulianDate> fixedAt)
Initializes a new instance.
|
PointFixedOffset(ReferenceFrame frame,
Cartesian offset)
Initializes a new instance of the
PointFixedOffset class using the
provided offset with respect to the provided frame. |
PointInReferenceFrame(Point point,
ReferenceFrame frame)
Initializes a new instance.
|
PointInterpolator(ReferenceFrame referenceFrame,
InterpolationAlgorithm interpolationAlgorithm,
int degree,
DateMotionCollection1<Cartesian> data)
Initializes a new instance of the
PointInterpolator class from the provided parameters. |
PointInterpolator(ReferenceFrame referenceFrame,
InterpolationAlgorithm interpolationAlgorithm,
int degree,
DateMotionCollection1<Cartesian> data,
List<JulianDate> segmentBoundaryTimes)
Initializes a new instance of the
PointInterpolator class from the provided parameters. |
PointInterpolator(ReferenceFrame referenceFrame,
InterpolationAlgorithmType algorithmType,
int degree,
DateMotionCollection1<Cartesian> data)
Initializes a new instance of the
PointInterpolator class from the provided parameters. |
PointInterpolator(ReferenceFrame referenceFrame,
InterpolationAlgorithmType algorithmType,
int degree,
DateMotionCollection1<Cartesian> data,
List<JulianDate> segmentBoundaryTimes)
Initializes a new instance of the
PointInterpolator class from the provided parameters. |
PointInterpolator(ReferenceFrame referenceFrame,
TranslationalMotionInterpolator interpolator)
Initializes a new instance of the
PointInterpolator class from the provided parameters. |
PointPropagationParameter(ReferenceFrame frame)
Initializes a new instance with the given frame of integration.
|
ScalarDelaunayElement(double gravitationalParameter,
Point location,
DelaunayElement element,
ReferenceFrame frame)
Initializes a new instance.
|
ScalarDeltaSphericalElement(Point fromPoint,
Point vertex,
Point toPoint,
ReferenceFrame frame,
SphericalElement element)
Initializes a new instance.
|
ScalarDopplerConeAngle(IServiceProvider link,
LinkRole movingLinkEnd,
ReferenceFrame frame)
Initializes a doppler cone angle scalar.
|
ScalarEquinoctialElement(double gravitationalParameter,
Point location,
EquinoctialElement element,
ReferenceFrame frame)
Initializes a new instance.
|
ScalarKozaiIzsakMeanElement(double gravitationalParameter,
Point location,
KozaiIzsakMeanElement element,
ReferenceFrame frame,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
ScalarModifiedKeplerianElement(double gravitationalParameter,
Point location,
KeplerianElement element,
ReferenceFrame frame)
Initializes a new instance.
|
ScalarPointElement(Point location,
CartesianElement element,
ReferenceFrame frameOfPoint)
Initializes a new instance.
|
ScalarSphericalElement(Point location,
ReferenceFrame frame,
SphericalElement element)
Initializes a new instance.
|
ScalarSquintAngle(IServiceProvider viewingObject,
IServiceProvider targetObject,
ReferenceFrame referenceFrame)
Initializes a new instance.
|
VectorAcceleration(Point point,
ReferenceFrame referenceFrame)
Initializes a new instance of the
VectorAcceleration class to represent the
acceleration of a given point in a given reference frame. |
VectorApparentDisplacement(Point initialPoint,
Point finalPoint,
ReferenceFrame inertialFrame)
Initializes a new instance of the
VectorApparentDisplacement class which only accounts for light travel time. |
VectorApparentDisplacement(Point initialPoint,
Point finalPoint,
ReferenceFrame inertialFrame,
SignalDirection direction,
double lightTravelTimeConvergenceTolerance)
Initializes a new instance of the
VectorApparentDisplacement class which only accounts for light travel time. |
VectorApparentDisplacement(Point initialPoint,
Point finalPoint,
ReferenceFrame inertialFrame,
SignalDirection direction,
double lightTravelTimeConvergenceTolerance,
VectorVelocity velocityOfMovingFrame)
Initializes a new instance of the
VectorApparentDisplacement class which accounts for aberration in addition to light travel time. |
VectorApparentDisplacement(Point initialPoint,
Point finalPoint,
ReferenceFrame inertialFrame,
VectorVelocity velocityOfMovingFrame)
Initializes a new instance of the
VectorApparentDisplacement class which accounts for aberration in addition to light travel time. |
VectorBPlane(Point location,
CentralBody centralBody,
double gravitationalParameter,
ReferenceFrame parentReferenceFrame)
Initializes a new instance.
|
VectorEllipsoidSurfaceNormal(Ellipsoid ellipsoid,
ReferenceFrame ellipsoidFixedFrame,
Point point)
Initializes a new instance.
|
VectorVelocity(Point point,
ReferenceFrame frame)
Initializes a new instance of the
VectorVelocity class to represent the
velocity of a given point in a given reference frame. |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
SpecifiedCoverageGrid.getReferenceFrame() |
ReferenceFrame |
ICoverageGrid.getReferenceFrame()
Gets the reference frame in which this grid is defined.
|
ReferenceFrame |
GeometricPrimitiveCoverageGrid.getReferenceFrame()
Gets the reference frame in which this grid is defined.
|
ReferenceFrame |
CoverageGridPoint.getReferenceFrame()
Gets the reference frame in which this grid point is defined.
|
ReferenceFrame |
CentralBodyCoverageGrid.getReferenceFrame()
|
| Modifier and Type | Method and Description |
|---|---|
void |
GeometricPrimitiveCoverageGrid.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which this grid is defined.
|
| Constructor and Description |
|---|
ConeCoverageGrid(Bounds clockAngleBounds,
Bounds baseRadiusBounds,
Bounds heightBounds,
ICoverageGriddingTechnique angleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cone grid with the specified parameters.
|
ConeCoverageGrid(double baseRadius,
double coneHeight,
double angularResolution,
double radialResolution,
double heightResolution,
ReferenceFrame referenceFrame)
Initializes a cone grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
ConeCoverageGrid(double baseRadius,
double coneHeight,
double angularResolution,
double radialResolution,
double heightResolution,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cone grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
ConeCoverageGrid(double baseRadius,
double coneHeight,
ICoverageGriddingTechnique angleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cone grid with the specified parameters.
|
ConeCoverageGrid(double coneBaseRadius,
double coneHeight,
int numberOfAngularPoints,
int numberOfRadialPoints,
int numberOfHeightPoints,
ReferenceFrame referenceFrame)
Initializes a cone grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
ConeCoverageGrid(double baseRadius,
double coneHeight,
int numberOfAngularPoints,
int numberOfRadialPoints,
int numberOfHeightPoints,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cone grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
CoverageGridPoint(Point position,
Scalar weight,
ICoverageGridCell coverageGridCell,
ReferenceFrame referenceFrame)
Creates a new instance based on the given point, weight, grid cell, and reference frame.
|
CoverageGridPoint(Point position,
Scalar weight,
ICoverageGridCell coverageGridCell,
ReferenceFrame referenceFrame,
CentralBody centralBody)
Creates a new instance based on the given point, weight, grid cell, central body, and reference frame.
|
CoverageGridPoint(Point position,
Scalar weight,
ReferenceFrame referenceFrame)
Creates a new instance based on the given point, weight, and reference frame.
|
CoverageGridPoint(Point position,
Scalar weight,
ReferenceFrame referenceFrame,
CentralBody centralBody)
Creates a new instance based on the given point, weight, central body, and reference frame.
|
CuboidCoverageGrid(Bounds xAxisBounds,
Bounds yAxisBounds,
Bounds zAxisBounds,
ICoverageGriddingTechnique xAxisGriddingTechnique,
ICoverageGriddingTechnique yAxisGriddingTechnique,
ICoverageGriddingTechnique zAxisGriddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cuboid grid with a single gridding technique used for each coordinate.
|
CuboidCoverageGrid(Bounds xAxisBounds,
Bounds yAxisBounds,
Bounds zAxisBounds,
ICoverageGriddingTechnique griddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cuboid grid with a single gridding technique used for each coordinate.
|
CuboidCoverageGrid(double xAxisLength,
double yAxisLength,
double zAxisLength,
double uniformResolution,
ReferenceFrame frame)
Initializes a cuboid grid with a uniform resolution in each coordinate.
|
CuboidCoverageGrid(double xAxisLength,
double yAxisLength,
double zAxisLength,
double uniformResolution,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cuboid grid with a uniform resolution in each coordinate.
|
CuboidCoverageGrid(double xAxisLength,
double yAxisLength,
double zAxisLength,
ICoverageGriddingTechnique griddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cuboid grid with a single gridding technique used for each coordinate.
|
CuboidCoverageGrid(double xAxisLength,
double yAxisLength,
double zAxisLength,
int numberOfPoints,
ReferenceFrame frame)
Initializes a cuboid grid with each coordinate gridded by the specified number of points.
|
CuboidCoverageGrid(double xAxisLength,
double yAxisLength,
double zAxisLength,
int numberOfPoints,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cuboid grid with each coordinate gridded by the specified number of points.
|
CylinderCoverageGrid(Bounds clockAngleBounds,
Bounds radialBounds,
Bounds heightBounds,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cylinder grid with the specified parameters.
|
CylinderCoverageGrid(double radius,
double height,
double angularResolution,
double radialResolution,
double heightResolution,
ReferenceFrame frame)
Initializes a cylinder grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
CylinderCoverageGrid(double radius,
double height,
double angularResolution,
double radialResolution,
double heightResolution,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cylinder grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
CylinderCoverageGrid(double radius,
double height,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame frame)
Initializes a cylinder grid with the specified parameters.
|
CylinderCoverageGrid(double radius,
double height,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cylinder grid with the specified parameters.
|
CylinderCoverageGrid(double radius,
double height,
int numberOfAngularPoints,
int numberOfRadialPoints,
int numberOfHeightPoints,
ReferenceFrame frame)
Initializes a cylinder grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
CylinderCoverageGrid(double radius,
double height,
int numberOfAngularPoints,
int numberOfRadialPoints,
int numberOfHeightPoints,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a cylinder grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
Bounds heightBounds,
ICoverageGriddingTechnique zxAngleGriddingTechnique,
ICoverageGriddingTechnique zyAngleGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a rectangular pyramid grid with the specified parameters.
|
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
double zxAngleResolution,
double zyAngleResolution,
double heightResolution,
ReferenceFrame referenceFrame)
Initializes a rectangular pyramid grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
double zxAngleResolution,
double zyAngleResolution,
double heightResolution,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a rectangular pyramid grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
ICoverageGriddingTechnique zxAngleGriddingTechnique,
ICoverageGriddingTechnique zyAngleGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame referenceFrame)
Initializes a rectangular pyramid grid with the specified parameters.
|
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
ICoverageGriddingTechnique zxAngleGriddingTechnique,
ICoverageGriddingTechnique zyAngleGriddingTechnique,
ICoverageGriddingTechnique heightGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a rectangular pyramid grid with the specified parameters.
|
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
int numberOfZXAnglePoints,
int numberOfZYAnglePoints,
int numberOfHeightPoints,
ReferenceFrame referenceFrame)
Initializes a rectangular pyramid grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
RectangularPyramidCoverageGrid(double xAxisLength,
double yAxisLength,
double height,
int numberOfZXAnglePoints,
int numberOfZYAnglePoints,
int numberOfHeightPoints,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a rectangular pyramid grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
SpecifiedCoverageGrid(ReferenceFrame referenceFrame,
List<CoverageGridPoint> points)
Initializes the grid with the specified parameters.
|
SpecifiedCoverageGrid(ReferenceFrame referenceFrame,
List<Point> gridPoints,
List<Scalar> weights)
Initializes the grid with the specified parameters.
|
SpheroidCoverageGrid(Bounds clockAngleBounds,
Bounds coneAngleBounds,
Bounds radialBounds,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique coneAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a spheroid grid with the specified parameters.
|
SpheroidCoverageGrid(double radius,
double clockAngleResolution,
double coneAngleResolution,
double radialResolution,
ReferenceFrame frame)
Initializes a spheroid grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
SpheroidCoverageGrid(double radius,
double clockAngleResolution,
double coneAngleResolution,
double radialResolution,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a spheroid grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
SpheroidCoverageGrid(double radius,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique coneAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ReferenceFrame frame)
Initializes a spheroid grid with the specified parameters.
|
SpheroidCoverageGrid(double radius,
ICoverageGriddingTechnique clockAngleGriddingTechnique,
ICoverageGriddingTechnique coneAngleGriddingTechnique,
ICoverageGriddingTechnique radialGriddingTechnique,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a spheroid grid with the specified parameters.
|
SpheroidCoverageGrid(double radius,
int numberOfClockAnglePoints,
int numberOfConeAnglePoints,
int numberOfRadialPoints,
ReferenceFrame frame)
Initializes a spheroid grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
SpheroidCoverageGrid(double radius,
int numberOfClockAnglePoints,
int numberOfConeAnglePoints,
int numberOfRadialPoints,
ReferenceFrame frame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a spheroid grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
TorusCoverageGrid(double majorRadius,
Bounds minorRadiusBounds,
Bounds majorClockAngleBounds,
Bounds minorClockAngleBounds,
ICoverageGriddingTechnique circleRadiusGriddingTechnique,
ICoverageGriddingTechnique majorClockAngleGriddingTechnique,
ICoverageGriddingTechnique minorClockAngleGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a torus grid with the specified parameters.
|
TorusCoverageGrid(double majorRadius,
double minorRadius,
double circleRadiusResolution,
double majorClockAngleResolution,
double minorClockAngleResolution,
ReferenceFrame referenceFrame)
Initializes a torus grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
TorusCoverageGrid(double majorRadius,
double minorRadius,
double circleRadiusResolution,
double majorClockAngleResolution,
double minorClockAngleResolution,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a torus grid with the specified parameters, where each coordinate uses a
SpecifiedResolutionCoverageGriddingTechnique with a tolerance of Constants.Epsilon10. |
TorusCoverageGrid(double majorRadius,
double minorRadius,
ICoverageGriddingTechnique circleRadiusGriddingTechnique,
ICoverageGriddingTechnique majorClockAngleGriddingTechnique,
ICoverageGriddingTechnique minorClockAngleGriddingTechnique,
ReferenceFrame referenceFrame)
Initializes a torus grid with the specified parameters.
|
TorusCoverageGrid(double majorRadius,
double minorRadius,
ICoverageGriddingTechnique circleRadiusGriddingTechnique,
ICoverageGriddingTechnique majorClockAngleGriddingTechnique,
ICoverageGriddingTechnique minorClockAngleGriddingTechnique,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a torus grid with the specified parameters.
|
TorusCoverageGrid(double majorRadius,
double minorRadius,
int numberOfMinorRadiusPoints,
int numberOfMajorClockAnglePoints,
int numberOfMinorClockAnglePoints,
ReferenceFrame referenceFrame)
Initializes a torus grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
TorusCoverageGrid(double majorRadius,
double minorRadius,
int numberOfMinorRadiusPoints,
int numberOfMajorClockAnglePoints,
int numberOfMinorClockAnglePoints,
ReferenceFrame referenceFrame,
boolean useCellVolumeForWeight,
boolean saveGridCell)
Initializes a torus grid with the specified parameters, where each coordinate uses a
SpecifiedNumberOfPointsCoverageGriddingTechnique. |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
Camera.getPositionReferenceFrame()
Gets the
ReferenceFrame that the Position is returned in. |
ReferenceFrame |
ProjectedRaster.getReferenceFrame()
Gets the reference frame that the
Projection
is defined in. |
ReferenceFrame |
Primitive.getReferenceFrame()
Gets the reference frame this primitive is defined and rendered in.
|
ReferenceFrame |
DistanceToPositionDisplayCondition.getReferenceFrame()
Gets the reference frame that
Position is defined in. |
ReferenceFrame |
Camera.getReferencePointReferenceFrame()
Gets the
ReferenceFrame that the ReferencePoint is returned in. |
| Modifier and Type | Method and Description |
|---|---|
void |
ProjectedRaster.setReferenceFrame(ReferenceFrame value)
Sets the reference frame that the
Projection
is defined in. |
void |
Primitive.setReferenceFrame(ReferenceFrame value)
Sets the reference frame this primitive is defined and rendered in.
|
void |
OrderedCompositePrimitive.setReferenceFrame(ReferenceFrame value) |
void |
DistanceToPositionDisplayCondition.setReferenceFrame(ReferenceFrame value)
Sets the reference frame that
Position is defined in. |
void |
CompositePrimitive.setReferenceFrame(ReferenceFrame value) |
void |
AxesPrimitive.setReferenceFrame(ReferenceFrame value) |
Visibility |
Camera.visibilityTest(ReferenceFrame referenceFrame,
BoundingSphere sphere)
Gets the visibility of a sphere against the view frustum and any occluding central bodies.
|
| Constructor and Description |
|---|
AxesPrimitive(ReferenceFrame sys,
Axes axes,
GraphicsFont font)
Initializes an axes primitive with the specified ISystem
sys as its source. |
DistanceToPositionDisplayCondition(ReferenceFrame referenceFrame,
Cartesian position,
double minimumDistance,
double maximumDistance)
Initializes a distance display condition with the inclusive distance interval
[
minimumDistance, maximumDistance]. |
VectorPrimitive(ReferenceFrame sys,
Vector dir,
GraphicsFont font)
Initializes a vector primitive with the specified ISystem
sys as its source and pointing in direction dir. |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
Covariance6By6TwoBodyBlender.getInertialPropagationFrame()
|
ReferenceFrame |
Covariance6By6TwoBodyBlender.getOrbitStatesFrame()
|
| Modifier and Type | Method and Description |
|---|---|
void |
Covariance6By6TwoBodyBlender.setInertialPropagationFrame(ReferenceFrame value)
|
void |
Covariance6By6TwoBodyBlender.setOrbitStatesFrame(ReferenceFrame value)
|
| Constructor and Description |
|---|
Covariance6By6TwoBodyBlender(DateMotionCollection1<Cartesian> orbitStates,
DateMotionCollection1<Matrix> covarianceData,
ReferenceFrame orbitStatesFrame,
Axes covarianceAxes,
ReferenceFrame inertialPropagationFrame,
double gravitationalParameter)
Initializes a new instance.
|
Covariance6By6TwoBodyBlender(DateMotionCollection1<Cartesian> orbitStates,
IDateMotionCollection1<Matrix6By6Symmetric> covarianceData,
ReferenceFrame orbitStatesFrame,
Axes covarianceAxes,
ReferenceFrame inertialPropagationFrame,
double gravitationalParameter)
Initializes a new instance.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
PointGraphicsParameter.getInFrame()
|
ReferenceFrame |
Platform.getReferenceFrame()
Gets the reference frame of this platform formed by the combination of
the platform's location and orientation.
|
| Modifier and Type | Method and Description |
|---|---|
void |
PointGraphicsParameter.setInFrame(ReferenceFrame value)
|
| Constructor and Description |
|---|
PointGraphicsParameter(Point point,
ReferenceFrame inFrame)
Initializes a new instance with the specified point and frame.
|
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
PropagationNewtonianPoint.getIntegrationFrame()
Gets the inertial
ReferenceFrame in which the position, velocity, and forces are defined. |
ReferenceFrame |
PropagationEulerianAxes.getIntegrationFrame()
Gets the inertial
ReferenceFrame in which the attitude is defined. |
protected ReferenceFrame |
NavstarISGps200DPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
GpsRinexPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
WaypointPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
TwoBodyPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
SimpleAscentPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
Sgp4Propagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
J4Propagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
J2Propagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected abstract ReferenceFrame |
CartesianOnePointPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
protected ReferenceFrame |
BallisticPropagator.getMotionReferenceFrame()
Gets the reference frame in which the motion is defined.
|
ReferenceFrame |
OrbitLifetimeResults.getPropagationFrame()
Gets the frame in which the time history of the orbit was propagated.
|
ReferenceFrame |
SinglePointStoppablePropagatorDefinition.getPropagationFrame()
Gets the
ReferenceFrame to propagate in. |
protected ReferenceFrame |
SinglePointStoppablePropagator.getPropagationFrame()
Gets the
ReferenceFrame to propagate the point in. |
ReferenceFrame |
NavstarISGps200DPropagator.getReferenceFrame()
Gets the Earth Fixed reference frame, which is the frame that the GPS satellite orbital positions
are referenced to.
|
ReferenceFrame |
GpsRinexPropagator.getReferenceFrame()
Gets the Earth Fixed reference frame, which is the frame that the GPS satellite orbital positions
are referenced to.
|
ReferenceFrame |
WaypointPropagator.getReferenceFrame()
Gets the reference frame in which ephemeris information is produced.
|
ReferenceFrame |
TwoBodyPropagator.getReferenceFrame()
Gets the reference frame in which the ephemeris is produced.
|
ReferenceFrame |
Sgp4Propagator.getReferenceFrame()
Gets True Equator, Mean Equinox (TEME) reference frame, the coordinate system in which SGP4 produces ephemeris.
|
ReferenceFrame |
J4Propagator.getReferenceFrame()
Gets the reference frame in which the ephemeris is produced.
|
ReferenceFrame |
J2Propagator.getReferenceFrame()
Gets the reference frame in which the ephemeris is produced.
|
| Modifier and Type | Method and Description |
|---|---|
static J4Propagator |
SpecializedOrbitSolver.createCircularOrbit(JulianDate orbitEpoch,
ReferenceFrame inertialFrame,
double altitude,
double inclination,
double rightAscensionOfAscendingNode,
double gravitationalParameter,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Creates a circular orbit with the desired characteristics.
|
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).
|
WalkerConstellationResult<J2Propagator> |
WalkerConstellation.createJ2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
double j2UnnormalizedValue,
double referenceDistance)
Creates a nested collection of satellite propagators.
|
WalkerConstellationResult<J4Propagator> |
WalkerConstellation.createJ4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Creates a nested collection of satellite propagators.
|
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).
|
WalkerConstellationResult<TwoBodyPropagator> |
WalkerConstellation.createTwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame)
Creates a nested collection of satellite propagators.
|
DateMotionCollection1<Cartesian> |
CartesianOnePointPropagator.propagate(JulianDate startDate,
JulianDate stopDate,
Duration timeStep,
int order,
ReferenceFrame outputReferenceFrame)
Calculates position (and zero or more derivatives) for regular time steps over an interval.
|
DateMotionCollection1<Cartesian> |
CartesianOnePointPropagator.propagate(JulianDate startDate,
JulianDate stopDate,
Duration timeStep,
int order,
ReferenceFrame outputReferenceFrame,
ITrackCalculationProgress tracker)
Calculates position (and zero or more derivatives) for regular time steps over an interval.
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void |
PropagationNewtonianPoint.setIntegrationFrame(ReferenceFrame value)
Sets the inertial
ReferenceFrame in which the position, velocity, and forces are defined. |
void |
PropagationEulerianAxes.setIntegrationFrame(ReferenceFrame value)
Sets the inertial
ReferenceFrame in which the attitude is defined. |
void |
OrbitLifetimeResults.setPropagationFrame(ReferenceFrame value)
Sets the frame in which the time history of the orbit was propagated.
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void |
SinglePointStoppablePropagatorDefinition.setPropagationFrame(ReferenceFrame value)
Sets the
ReferenceFrame to propagate in. |
void |
TwoBodyPropagator.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the ephemeris is produced.
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void |
J4Propagator.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the ephemeris is produced.
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void |
J2Propagator.setReferenceFrame(ReferenceFrame value)
Sets the reference frame in which the ephemeris is produced.
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| Constructor and Description |
|---|
J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
DelaunayElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
KeplerianElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
Motion1<Cartesian> initialConditions,
double gravitationalParameter,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
DelaunayElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
KeplerianElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
Motion1<Cartesian> initialConditions,
double gravitationalParameter,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
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PropagationEulerianAxes(String id,
ReferenceFrame propagationFrame,
UnitQuaternion initialAttitudeQuaternion,
Cartesian initialAngularVelocity,
Matrix3By3Symmetric inertiaMatrix)
Initializes a new instance.
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PropagationNewtonianPoint(String id,
ReferenceFrame propagationFrame,
Cartesian initialPosition,
Cartesian initialVelocity)
Initializes a new instance.
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TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
DelaunayElements elements)
Initializes a new instance.
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TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements elements)
Initializes a new instance.
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TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
KeplerianElements elements)
Initializes a new instance.
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TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements elements)
Initializes a new instance.
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TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
Motion1<Cartesian> initialConditions,
double gravitationalParameter)
Initializes a new instance.
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TwoBodyStoppablePropagator(double gravitationalParameter,
String propagationPointIdentification,
ReferenceFrame propagationFrame,
Duration step)
Initializes a new instance.
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| Modifier and Type | Method and Description |
|---|---|
abstract ReferenceFrame |
PropagationPointElement.getIntegrationFrame()
Gets the frame of the integrated point.
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| Modifier and Type | Method and Description |
|---|---|
abstract void |
PropagationPointElement.setIntegrationFrame(ReferenceFrame value)
Sets the frame of the integrated point.
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| Modifier and Type | Method and Description |
|---|---|
DateMotionCollection1<Cartesian> |
SegmentResults.getDateMotionCollectionOfOverallTrajectory(String element,
ReferenceFrame frame)
Gets a
DateMotionCollection1 of the element in the specified
ReferenceFrame from the EphemerisForOverallTrajectory (get). |
DateMotionCollection1<Cartesian> |
SegmentListResults.getDateMotionCollectionOfOverallTrajectory(String element,
ReferenceFrame frame)
Gets a
DateMotionCollection1 of the element in the specified
ReferenceFrame from the EphemerisForOverallTrajectory (get). |
| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
StkEphemerisFile.EphemerisTimePos.getCoordinateSystem()
Gets the reference frame in which the data is defined.
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| Modifier and Type | Method and Description |
|---|---|
Covariance6By6TwoBodyBlender |
StkEphemerisFile.CovarianceTimePosVel.createBlender(StkEphemerisFile.EphemerisTimePosVel orbitStates,
ReferenceFrame inertialPropagationFrame,
Double gravitationalParameter)
Creates a two-body covariance blender from the orbit states ephemeris and the
covariance data.
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void |
StkEphemerisFile.EphemerisTimePos.setCoordinateSystem(ReferenceFrame value)
Sets the reference frame in which the data is defined.
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| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
TerrainProvider.getShapeFixedFrame()
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| Modifier and Type | Method and Description |
|---|---|
protected void |
TerrainProvider.setShapeFixedFrame(ReferenceFrame value)
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| Constructor and Description |
|---|
EllipsoidTerrainProvider(Ellipsoid shape,
ReferenceFrame shapeFixedFrame)
Initializes a new instance with the specified shape and fixed frame.
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| Modifier and Type | Method and Description |
|---|---|
ReferenceFrame |
IEntityPositionDescriptor.getPositionReferenceFrame()
Gets the reference frame in which
Position (get) is defined. |