Keyword.java
/* Copyright 2002-2016 CS Systèmes d'Information
* Licensed to CS Systèmes d'Information (CS) under one or more
* contributor license agreements. See the NOTICE file distributed with
* this work for additional information regarding copyright ownership.
* CS licenses this file to You under the Apache License, Version 2.0
* (the "License"); you may not use this file except in compliance with
* the License. You may obtain a copy of the License at
*
* http://www.apache.org/licenses/LICENSE-2.0
*
* Unless required by applicable law or agreed to in writing, software
* distributed under the License is distributed on an "AS IS" BASIS,
* WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
* See the License for the specific language governing permissions and
* limitations under the License.
*/
package org.orekit.files.ccsds;
/** Keywords for CCSDS orbit data messages. Only these should be used.
* @author sports
* @since 6.1
*/
public enum Keyword {
/** Comments specific to a ODM file. */
COMMENT,
/** CCSDS OPM format version. */
CCSDS_OPM_VERS,
/** CCSDS OMM format version. */
CCSDS_OMM_VERS,
/** File creation date in UTC. */
CCSDS_OEM_VERS,
/** CCSDS OEM format version. */
CREATION_DATE,
/** Creating agency or operator. */
ORIGINATOR,
/** Spacecraft name for which the orbit state is provided. */
OBJECT_NAME,
/** Object identifier of the object for which the orbit state is provided. */
OBJECT_ID,
/** Origin of reference frame. */
CENTER_NAME,
/** Name of the reference frame in which the state vector and optional Keplerian element data are given. */
REF_FRAME,
/** Epoch of reference frame, if not intrinsic to the definition of the reference frame. */
REF_FRAME_EPOCH,
/** Time system used for state vector, maneuver, and covariance data. */
TIME_SYSTEM,
/** Mean element theory. */
MEAN_ELEMENT_THEORY,
/** Epoch of state vector and optional Keplerian elements. */
EPOCH,
/** Position vector X-component. */
X,
/** Position vector Y-component. */
Y,
/** Position vector Z-component. */
Z,
/** Velocity vector X-component. */
X_DOT,
/** Velocity vector Y-component. */
Y_DOT,
/** Velocity vector Z-component. */
Z_DOT,
/** Orbit semi-major axis. */
SEMI_MAJOR_AXIS,
/** Mean Motion. */
MEAN_MOTION,
/** Orbit eccentricity. */
ECCENTRICITY,
/** Orbit inclination. */
INCLINATION,
/** Orbit right ascension of ascending node. */
RA_OF_ASC_NODE,
/** Orbit argument of pericenter. */
ARG_OF_PERICENTER,
/** Orbit true anomaly. */
TRUE_ANOMALY,
/** Orbit mean anomaly.*/
MEAN_ANOMALY,
/** Gravitational coefficient. */
GM,
/** Spacecraft mass. */
MASS,
/** Solar radiation pressure area. */
SOLAR_RAD_AREA,
/** Solar radiation pressure coefficient. */
SOLAR_RAD_COEFF,
/** Drag area. */
DRAG_AREA,
/** Drag coefficient. */
DRAG_COEFF,
/** Ephemeris type. */
EPHEMERIS_TYPE,
/** Classification type. */
CLASSIFICATION_TYPE,
/** NORAD catalogue number. */
NORAD_CAT_ID,
/** Element set number of the satellite. */
ELEMENT_SET_NO,
/** Revolution Number. */
REV_AT_EPOCH,
/** SGP/SGP4 drag-like coefficient. */
BSTAR,
/** First Time Derivative of the Mean Motion. */
MEAN_MOTION_DOT,
/** Second Time Derivative of the Mean Motion. */
MEAN_MOTION_DDOT,
/** Coordinate system for covariance matrix. Its value can either be RSW, RTN (both indicating
/* "Radial, Transverse, Normal") or TNW. */
COV_REF_FRAME,
/** Covariance matrix [1,1] element. */
CX_X,
/** Covariance matrix [2,1] element. */
CY_X,
/** Covariance matrix [2,2] element. */
CY_Y,
/** Covariance matrix [3,1] element. */
CZ_X,
/** Covariance matrix [3,2] element. */
CZ_Y,
/** Covariance matrix [3,3] element. */
CZ_Z,
/** Covariance matrix [4,1] element. */
CX_DOT_X,
/** Covariance matrix [4,2] element. */
CX_DOT_Y,
/** Covariance matrix [4,3] element. */
CX_DOT_Z,
/** Covariance matrix [4,4] element. */
CX_DOT_X_DOT,
/** Covariance matrix [5,1] element. */
CY_DOT_X,
/** Covariance matrix [5,2] element. */
CY_DOT_Y,
/** Covariance matrix [5,3] element. */
CY_DOT_Z,
/** Covariance matrix [5,4] element. */
CY_DOT_X_DOT,
/** Covariance matrix [5,5] element. */
CY_DOT_Y_DOT,
/** Covariance matrix [6,1] element. */
CZ_DOT_X,
/** Covariance matrix [6,2] element. */
CZ_DOT_Y,
/** Covariance matrix [6,3] element. */
CZ_DOT_Z,
/** Covariance matrix [6,4] element. */
CZ_DOT_X_DOT,
/** Covariance matrix [6,5] element. */
CZ_DOT_Y_DOT,
/** Covariance matrix [6,6] element. */
CZ_DOT_Z_DOT,
/** Epoch of ignition. */
MAN_EPOCH_IGNITION,
/** Maneuver duration (If = 0, impulsive maneuver). */
MAN_DURATION,
/** Mass change during maneuver (value is < 0). */
MAN_DELTA_MASS,
/** Coordinate system for velocity increment vector. Its value can either be RSW, RTN (both
* indicating "Radial, Transverse, Normal") or TNW. */
MAN_REF_FRAME,
/** First component of the velocity increment. */
MAN_DV_1,
/** Second component of the velocity increment. */
MAN_DV_2,
/** Third component of the velocity increment. */
MAN_DV_3,
/** 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. */
USER_DEFINED_X,
/** Keyword used to delineate the start of a metadata block. */
META_START,
/** Keyword used to delineate the end of a metadata block. */
META_STOP,
/** This keyword must appear before the first line of the covariance matrix data. */
COVARIANCE_START,
/** Start of total time span covered by ephemerides data and covariance data. */
START_TIME,
/** Start of useable time span covered by ephemerides data, it may be
* necessary to allow for proper interpolation. */
USEABLE_START_TIME,
/** End of useable time span covered by ephemerides data, it may be
* necessary to allow for proper interpolation. */
USEABLE_STOP_TIME,
/** End of total time span covered by ephemerides data and covariance data. */
STOP_TIME,
/** The interpolation method to be used. */
INTERPOLATION,
/** The interpolation degree. */
INTERPOLATION_DEGREE,
/** This keyword must appear after the last line of the covariance matrix data. */
COVARIANCE_STOP;
}