Keyword (ORbit Extrapolation KIT 6.1 API)

java.lang.Object
- java.lang.Enum<Keyword>
- - org.orekit.files.ccsds.Keyword

All Implemented Interfaces:

Serializable, Comparable<Keyword>
```
public enum Keyword
extends Enum<Keyword>
```
Keywords for CCSDS orbit data messages. Only these should be used.

Since:

6.1

Author:

sports

Enum Constant Summary

Enum Constants
Enum Constant and Description
`ARG_OF_PERICENTER` Orbit argument of pericenter.
`BSTAR` SGP/SGP4 drag-like coefficient.
`CCSDS_OEM_VERS` File creation date in UTC.
`CCSDS_OMM_VERS` CCSDS OMM format version.
`CCSDS_OPM_VERS` CCSDS OPM format version.
`CENTER_NAME` Origin of reference frame.
`CLASSIFICATION_TYPE` Classification type.
`COMMENT` Comments specific to a ODM file.
`COV_REF_FRAME` Coordinate system for covariance matrix.
`COVARIANCE_START` This keyword must appear before the first line of the covariance matrix data.
`COVARIANCE_STOP` This keyword must appear after the last line of the covariance matrix data.
`CREATION_DATE` CCSDS OEM format version.
`CX_DOT_X` Covariance matrix [4,1] element.
`CX_DOT_X_DOT` Covariance matrix [4,4] element.
`CX_DOT_Y` Covariance matrix [4,2] element.
`CX_DOT_Z` Covariance matrix [4,3] element.
`CX_X` Covariance matrix [1,1] element.
`CY_DOT_X` Covariance matrix [5,1] element.
`CY_DOT_X_DOT` Covariance matrix [5,4] element.
`CY_DOT_Y` Covariance matrix [5,2] element.
`CY_DOT_Y_DOT` Covariance matrix [5,5] element.
`CY_DOT_Z` Covariance matrix [5,3] element.
`CY_X` Covariance matrix [2,1] element.
`CY_Y` Covariance matrix [2,2] element.
`CZ_DOT_X` Covariance matrix [6,1] element.
`CZ_DOT_X_DOT` Covariance matrix [6,4] element.
`CZ_DOT_Y` Covariance matrix [6,2] element.
`CZ_DOT_Y_DOT` Covariance matrix [6,5] element.
`CZ_DOT_Z` Covariance matrix [6,3] element.
`CZ_DOT_Z_DOT` Covariance matrix [6,6] element.
`CZ_X` Covariance matrix [3,1] element.
`CZ_Y` Covariance matrix [3,2] element.
`CZ_Z` Covariance matrix [3,3] element.
`DRAG_AREA` Drag area.
`DRAG_COEFF` Drag coefficient.
`ECCENTRICITY` Orbit eccentricity.
`ELEMENT_SET_NO` Element set number of the satellite.
`EPHEMERIS_TYPE` Ephemeris type.
`EPOCH` Epoch of state vector and optional Keplerian elements.
`GM` Gravitational coefficient.
`INCLINATION` Orbit inclination.
`INTERPOLATION` The interpolation method to be used.
`INTERPOLATION_DEGREE` The interpolation degree.
`MAN_DELTA_MASS` Mass change during maneuver (value is < 0).
`MAN_DURATION` Maneuver duration (If = 0, impulsive maneuver).
`MAN_DV_1` First component of the velocity increment.
`MAN_DV_2` Second component of the velocity increment.
`MAN_DV_3` Third component of the velocity increment.
`MAN_EPOCH_IGNITION` Epoch of ignition.
`MAN_REF_FRAME` Coordinate system for velocity increment vector.
`MASS` Spacecraft mass.
`MEAN_ANOMALY` Orbit mean anomaly.
`MEAN_ELEMENT_THEORY` Mean element theory.
`MEAN_MOTION` Mean Motion.
`MEAN_MOTION_DDOT` Second Time Derivative of the Mean Motion.
`MEAN_MOTION_DOT` First Time Derivative of the Mean Motion.
`META_START` Keyword used to delineate the start of a metadata block.
`META_STOP` Keyword used to delineate the end of a metadata block.
`NORAD_CAT_ID` NORAD catalogue number.
`OBJECT_ID` Object identifier of the object for which the orbit state is provided.
`OBJECT_NAME` Spacecraft name for which the orbit state is provided.
`ORIGINATOR` Creating agency or operator.
`RA_OF_ASC_NODE` Orbit right ascension of ascending node.
`REF_FRAME` Name of the reference frame in which the state vector and optional Keplerian element data are given.
`REF_FRAME_EPOCH` Epoch of reference frame, if not intrinsic to the definition of the reference frame.
`REV_AT_EPOCH` Revolution Number.
`SEMI_MAJOR_AXIS` Orbit semi-major axis.
`SOLAR_RAD_AREA` Solar radiation pressure area.
`SOLAR_RAD_COEFF` Solar radiation pressure coefficient.
`START_TIME` Start of total time span covered by ephemerides data and covariance data.
`STOP_TIME` End of total time span covered by ephemerides data and covariance data.
`TIME_SYSTEM` Time system used for state vector, maneuver, and covariance data.
`TRUE_ANOMALY` Orbit true anomaly.
`USEABLE_START_TIME` Start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
`USEABLE_STOP_TIME` End of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
`USER_DEFINED_X` User defined parameter, where X is replaced by a variable length user specified character string.
`X` Position vector X-component.
`X_DOT` Velocity vector X-component.
`Y` Position vector Y-component.
`Y_DOT` Velocity vector Y-component.
`Z` Position vector Z-component.
`Z_DOT` Velocity vector Z-component.

Method Summary

Methods
Modifier and Type	Method and Description
`static Keyword`	`valueOf(String name)` Returns the enum constant of this type with the specified name.
`static Keyword[]`	`values()` Returns an array containing the constants of this enum type, in the order they are declared.

Methods inherited from class java.lang.Enum
clone, compareTo, equals, finalize, getDeclaringClass, hashCode, name, ordinal, toString, valueOf

Methods inherited from class java.lang.Object
getClass, notify, notifyAll, wait, wait, wait

- Enum Constant Detail
  - COMMENT
```
public static final Keyword COMMENT
```
    Comments specific to a ODM file.
  - CCSDS_OPM_VERS
```
public static final Keyword CCSDS_OPM_VERS
```
    CCSDS OPM format version.
  - CCSDS_OMM_VERS
```
public static final Keyword CCSDS_OMM_VERS
```
    CCSDS OMM format version.
  - CCSDS_OEM_VERS
```
public static final Keyword CCSDS_OEM_VERS
```
    File creation date in UTC.
  - CREATION_DATE
```
public static final Keyword CREATION_DATE
```
    CCSDS OEM format version.
  - ORIGINATOR
```
public static final Keyword ORIGINATOR
```
    Creating agency or operator.
  - OBJECT_NAME
```
public static final Keyword OBJECT_NAME
```
    Spacecraft name for which the orbit state is provided.
  - OBJECT_ID
```
public static final Keyword OBJECT_ID
```
    Object identifier of the object for which the orbit state is provided.
  - CENTER_NAME
```
public static final Keyword CENTER_NAME
```
    Origin of reference frame.
  - REF_FRAME
```
public static final Keyword REF_FRAME
```
    Name of the reference frame in which the state vector and optional Keplerian element data are given.
  - REF_FRAME_EPOCH
```
public static final Keyword REF_FRAME_EPOCH
```
    Epoch of reference frame, if not intrinsic to the definition of the reference frame.
  - TIME_SYSTEM
```
public static final Keyword TIME_SYSTEM
```
    Time system used for state vector, maneuver, and covariance data.
  - MEAN_ELEMENT_THEORY
```
public static final Keyword MEAN_ELEMENT_THEORY
```
    Mean element theory.
  - EPOCH
```
public static final Keyword EPOCH
```
    Epoch of state vector and optional Keplerian elements.
  - X
```
public static final Keyword X
```
    Position vector X-component.
  - Y
```
public static final Keyword Y
```
    Position vector Y-component.
  - Z
```
public static final Keyword Z
```
    Position vector Z-component.
  - X_DOT
```
public static final Keyword X_DOT
```
    Velocity vector X-component.
  - Y_DOT
```
public static final Keyword Y_DOT
```
    Velocity vector Y-component.
  - Z_DOT
```
public static final Keyword Z_DOT
```
    Velocity vector Z-component.
  - SEMI_MAJOR_AXIS
```
public static final Keyword SEMI_MAJOR_AXIS
```
    Orbit semi-major axis.
  - MEAN_MOTION
```
public static final Keyword MEAN_MOTION
```
    Mean Motion.
  - ECCENTRICITY
```
public static final Keyword ECCENTRICITY
```
    Orbit eccentricity.
  - INCLINATION
```
public static final Keyword INCLINATION
```
    Orbit inclination.
  - RA_OF_ASC_NODE
```
public static final Keyword RA_OF_ASC_NODE
```
    Orbit right ascension of ascending node.
  - ARG_OF_PERICENTER
```
public static final Keyword ARG_OF_PERICENTER
```
    Orbit argument of pericenter.
  - TRUE_ANOMALY
```
public static final Keyword TRUE_ANOMALY
```
    Orbit true anomaly.
  - MEAN_ANOMALY
```
public static final Keyword MEAN_ANOMALY
```
    Orbit mean anomaly.
  - GM
```
public static final Keyword GM
```
    Gravitational coefficient.
  - MASS
```
public static final Keyword MASS
```
    Spacecraft mass.
  - SOLAR_RAD_AREA
```
public static final Keyword SOLAR_RAD_AREA
```
    Solar radiation pressure area.
  - SOLAR_RAD_COEFF
```
public static final Keyword SOLAR_RAD_COEFF
```
    Solar radiation pressure coefficient.
  - DRAG_AREA
```
public static final Keyword DRAG_AREA
```
    Drag area.
  - DRAG_COEFF
```
public static final Keyword DRAG_COEFF
```
    Drag coefficient.
  - EPHEMERIS_TYPE
```
public static final Keyword EPHEMERIS_TYPE
```
    Ephemeris type.
  - CLASSIFICATION_TYPE
```
public static final Keyword CLASSIFICATION_TYPE
```
    Classification type.
  - NORAD_CAT_ID
```
public static final Keyword NORAD_CAT_ID
```
    NORAD catalogue number.
  - ELEMENT_SET_NO
```
public static final Keyword ELEMENT_SET_NO
```
    Element set number of the satellite.
  - REV_AT_EPOCH
```
public static final Keyword REV_AT_EPOCH
```
    Revolution Number.
  - BSTAR
```
public static final Keyword BSTAR
```
    SGP/SGP4 drag-like coefficient.
  - MEAN_MOTION_DOT
```
public static final Keyword MEAN_MOTION_DOT
```
    First Time Derivative of the Mean Motion.
  - MEAN_MOTION_DDOT
```
public static final Keyword MEAN_MOTION_DDOT
```
    Second Time Derivative of the Mean Motion.
  - COV_REF_FRAME
```
public static final Keyword COV_REF_FRAME
```
    Coordinate system for covariance matrix. Its value can either be RSW, RTN (both indicating /* "Radial, Transverse, Normal") or TNW.
  - CX_X
```
public static final Keyword CX_X
```
    Covariance matrix [1,1] element.
  - CY_X
```
public static final Keyword CY_X
```
    Covariance matrix [2,1] element.
  - CY_Y
```
public static final Keyword CY_Y
```
    Covariance matrix [2,2] element.
  - CZ_X
```
public static final Keyword CZ_X
```
    Covariance matrix [3,1] element.
  - CZ_Y
```
public static final Keyword CZ_Y
```
    Covariance matrix [3,2] element.
  - CZ_Z
```
public static final Keyword CZ_Z
```
    Covariance matrix [3,3] element.
  - CX_DOT_X
```
public static final Keyword CX_DOT_X
```
    Covariance matrix [4,1] element.
  - CX_DOT_Y
```
public static final Keyword CX_DOT_Y
```
    Covariance matrix [4,2] element.
  - CX_DOT_Z
```
public static final Keyword CX_DOT_Z
```
    Covariance matrix [4,3] element.
  - CX_DOT_X_DOT
```
public static final Keyword CX_DOT_X_DOT
```
    Covariance matrix [4,4] element.
  - CY_DOT_X
```
public static final Keyword CY_DOT_X
```
    Covariance matrix [5,1] element.
  - CY_DOT_Y
```
public static final Keyword CY_DOT_Y
```
    Covariance matrix [5,2] element.
  - CY_DOT_Z
```
public static final Keyword CY_DOT_Z
```
    Covariance matrix [5,3] element.
  - CY_DOT_X_DOT
```
public static final Keyword CY_DOT_X_DOT
```
    Covariance matrix [5,4] element.
  - CY_DOT_Y_DOT
```
public static final Keyword CY_DOT_Y_DOT
```
    Covariance matrix [5,5] element.
  - CZ_DOT_X
```
public static final Keyword CZ_DOT_X
```
    Covariance matrix [6,1] element.
  - CZ_DOT_Y
```
public static final Keyword CZ_DOT_Y
```
    Covariance matrix [6,2] element.
  - CZ_DOT_Z
```
public static final Keyword CZ_DOT_Z
```
    Covariance matrix [6,3] element.
  - CZ_DOT_X_DOT
```
public static final Keyword CZ_DOT_X_DOT
```
    Covariance matrix [6,4] element.
  - CZ_DOT_Y_DOT
```
public static final Keyword CZ_DOT_Y_DOT
```
    Covariance matrix [6,5] element.
  - CZ_DOT_Z_DOT
```
public static final Keyword CZ_DOT_Z_DOT
```
    Covariance matrix [6,6] element.
  - MAN_EPOCH_IGNITION
```
public static final Keyword MAN_EPOCH_IGNITION
```
    Epoch of ignition.
  - MAN_DURATION
```
public static final Keyword MAN_DURATION
```
    Maneuver duration (If = 0, impulsive maneuver).
  - MAN_DELTA_MASS
```
public static final Keyword MAN_DELTA_MASS
```
    Mass change during maneuver (value is < 0).
  - MAN_REF_FRAME
```
public static final Keyword MAN_REF_FRAME
```
    Coordinate system for velocity increment vector. Its value can either be RSW, RTN (both indicating "Radial, Transverse, Normal") or TNW.
  - MAN_DV_1
```
public static final Keyword MAN_DV_1
```
    First component of the velocity increment.
  - MAN_DV_2
```
public static final Keyword MAN_DV_2
```
    Second component of the velocity increment.
  - MAN_DV_3
```
public static final Keyword MAN_DV_3
```
    Third component of the velocity increment.
  - USER_DEFINED_X
```
public static final Keyword USER_DEFINED_X
```
    User defined parameter, where X is replaced by a variable length user specified character string. Any number of user defined parameters may be included, if necessary to provide essential information that cannot be conveyed in COMMENT statements.
  - META_START
```
public static final Keyword META_START
```
    Keyword used to delineate the start of a metadata block.
  - META_STOP
```
public static final Keyword META_STOP
```
    Keyword used to delineate the end of a metadata block.
  - COVARIANCE_START
```
public static final Keyword COVARIANCE_START
```
    This keyword must appear before the first line of the covariance matrix data.
  - START_TIME
```
public static final Keyword START_TIME
```
    Start of total time span covered by ephemerides data and covariance data.
  - USEABLE_START_TIME
```
public static final Keyword USEABLE_START_TIME
```
    Start of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
  - USEABLE_STOP_TIME
```
public static final Keyword USEABLE_STOP_TIME
```
    End of useable time span covered by ephemerides data, it may be necessary to allow for proper interpolation.
  - STOP_TIME
```
public static final Keyword STOP_TIME
```
    End of total time span covered by ephemerides data and covariance data.
  - INTERPOLATION
```
public static final Keyword INTERPOLATION
```
    The interpolation method to be used.
  - INTERPOLATION_DEGREE
```
public static final Keyword INTERPOLATION_DEGREE
```
    The interpolation degree.
  - COVARIANCE_STOP
```
public static final Keyword COVARIANCE_STOP
```
    This keyword must appear after the last line of the covariance matrix data.
- Method Detail
  - values
```
public static Keyword[] values()
```
    Returns an array containing the constants of this enum type, in the order they are declared. This method may be used to iterate over the constants as follows:
```
for (Keyword c : Keyword.values())
    System.out.println(c);
```
    Returns:
    an array containing the constants of this enum type, in the order they are declared
  - valueOf
```
public static Keyword valueOf(String name)
```
    Returns the enum constant of this type with the specified name. The string must match exactly an identifier used to declare an enum constant in this type. (Extraneous whitespace characters are not permitted.)
    
    Parameters:
    name - the name of the enum constant to be returned.
    
    Returns:
    the enum constant with the specified name
    
    Throws:
    
    IllegalArgumentException - if this enum type has no constant with the specified name
    
    NullPointerException - if the argument is null

Enum Keyword

Enum Constant Summary

Method Summary

Methods inherited from class java.lang.Enum

Methods inherited from class java.lang.Object

Enum Constant Detail

COMMENT

CCSDS_OPM_VERS

CCSDS_OMM_VERS

CCSDS_OEM_VERS

CREATION_DATE

ORIGINATOR

OBJECT_NAME

OBJECT_ID

CENTER_NAME

REF_FRAME

REF_FRAME_EPOCH

TIME_SYSTEM

MEAN_ELEMENT_THEORY

EPOCH

X

Y

Z

X_DOT

Y_DOT

Z_DOT

SEMI_MAJOR_AXIS

MEAN_MOTION

ECCENTRICITY

INCLINATION

RA_OF_ASC_NODE

ARG_OF_PERICENTER

TRUE_ANOMALY

MEAN_ANOMALY

GM

MASS

SOLAR_RAD_AREA

SOLAR_RAD_COEFF

DRAG_AREA

DRAG_COEFF

EPHEMERIS_TYPE

CLASSIFICATION_TYPE

NORAD_CAT_ID

ELEMENT_SET_NO

REV_AT_EPOCH

BSTAR

MEAN_MOTION_DOT

MEAN_MOTION_DDOT

COV_REF_FRAME

CX_X

CY_X

CY_Y

CZ_X

CZ_Y

CZ_Z

CX_DOT_X

CX_DOT_Y

CX_DOT_Z

CX_DOT_X_DOT

CY_DOT_X

CY_DOT_Y

CY_DOT_Z

CY_DOT_X_DOT

CY_DOT_Y_DOT

CZ_DOT_X

CZ_DOT_Y

CZ_DOT_Z

CZ_DOT_X_DOT

CZ_DOT_Y_DOT

CZ_DOT_Z_DOT

MAN_EPOCH_IGNITION

MAN_DURATION

MAN_DELTA_MASS

MAN_REF_FRAME

MAN_DV_1

MAN_DV_2

MAN_DV_3

USER_DEFINED_X

META_START

META_STOP