1   /* Copyright 2002-2016 CS Systèmes d'Information
2    * Licensed to CS Systèmes d'Information (CS) under one or more
3    * contributor license agreements.  See the NOTICE file distributed with
4    * this work for additional information regarding copyright ownership.
5    * CS licenses this file to You under the Apache License, Version 2.0
6    * (the "License"); you may not use this file except in compliance with
7    * the License.  You may obtain a copy of the License at
8    *
9    *   http://www.apache.org/licenses/LICENSE-2.0
10   *
11   * Unless required by applicable law or agreed to in writing, software
12   * distributed under the License is distributed on an "AS IS" BASIS,
13   * WITHOUT WARRANTIES OR CONDITIONS OF ANY KIND, either express or implied.
14   * See the License for the specific language governing permissions and
15   * limitations under the License.
16   */
17  package org.orekit.files.ccsds;
18  
19  /** Keywords for CCSDS orbit data messages. Only these should be used.
20   * @author sports
21   * @since 6.1
22   */
23  public enum Keyword {
24      /** Comments specific to a ODM file. */
25      COMMENT,
26      /** CCSDS OPM format version. */
27      CCSDS_OPM_VERS,
28      /** CCSDS OMM format version. */
29      CCSDS_OMM_VERS,
30      /** File creation date in UTC. */
31      CCSDS_OEM_VERS,
32      /** CCSDS OEM format version. */
33      CREATION_DATE,
34      /** Creating agency or operator. */
35      ORIGINATOR,
36      /** Spacecraft name for which the orbit state is provided. */
37      OBJECT_NAME,
38      /** Object identifier of the object for which the orbit state is provided. */
39      OBJECT_ID,
40      /** Origin of reference frame. */
41      CENTER_NAME,
42      /** Name of the reference frame in which the state vector and optional Keplerian element data are given. */
43      REF_FRAME,
44      /** Epoch of reference frame, if not intrinsic to the definition of the reference frame. */
45      REF_FRAME_EPOCH,
46      /** Time system used for state vector, maneuver, and covariance data. */
47      TIME_SYSTEM,
48      /** Mean element theory. */
49      MEAN_ELEMENT_THEORY,
50      /** Epoch of state vector and optional Keplerian elements. */
51      EPOCH,
52      /** Position vector X-component. */
53      X,
54      /** Position vector Y-component. */
55      Y,
56      /** Position vector Z-component. */
57      Z,
58      /** Velocity vector X-component. */
59      X_DOT,
60      /** Velocity vector Y-component. */
61      Y_DOT,
62      /** Velocity vector Z-component. */
63      Z_DOT,
64      /** Orbit semi-major axis. */
65      SEMI_MAJOR_AXIS,
66      /** Mean Motion. */
67      MEAN_MOTION,
68      /** Orbit eccentricity. */
69      ECCENTRICITY,
70      /** Orbit inclination. */
71      INCLINATION,
72      /** Orbit right ascension of ascending node. */
73      RA_OF_ASC_NODE,
74      /** Orbit argument of pericenter. */
75      ARG_OF_PERICENTER,
76      /** Orbit true anomaly. */
77      TRUE_ANOMALY,
78      /** Orbit mean anomaly.*/
79      MEAN_ANOMALY,
80      /** Gravitational coefficient. */
81      GM,
82      /** Spacecraft mass. */
83      MASS,
84      /** Solar radiation pressure area. */
85      SOLAR_RAD_AREA,
86      /** Solar radiation pressure coefficient. */
87      SOLAR_RAD_COEFF,
88      /** Drag area. */
89      DRAG_AREA,
90      /** Drag coefficient. */
91      DRAG_COEFF,
92      /** Ephemeris type. */
93      EPHEMERIS_TYPE,
94      /** Classification type. */
95      CLASSIFICATION_TYPE,
96      /** NORAD catalogue number. */
97      NORAD_CAT_ID,
98      /** Element set number of the satellite. */
99      ELEMENT_SET_NO,
100     /** Revolution Number. */
101     REV_AT_EPOCH,
102     /** SGP/SGP4 drag-like coefficient. */
103     BSTAR,
104     /** First Time Derivative of the Mean Motion. */
105     MEAN_MOTION_DOT,
106     /** Second Time Derivative of the Mean Motion. */
107     MEAN_MOTION_DDOT,
108     /** Coordinate system for covariance matrix. Its value can either be RSW, RTN (both indicating
109     /* "Radial, Transverse, Normal") or TNW. */
110     COV_REF_FRAME,
111     /** Covariance matrix [1,1] element. */
112     CX_X,
113     /** Covariance matrix [2,1] element. */
114     CY_X,
115     /** Covariance matrix [2,2] element. */
116     CY_Y,
117     /** Covariance matrix [3,1] element. */
118     CZ_X,
119     /** Covariance matrix [3,2] element. */
120     CZ_Y,
121     /** Covariance matrix [3,3] element. */
122     CZ_Z,
123     /** Covariance matrix [4,1] element. */
124     CX_DOT_X,
125     /** Covariance matrix [4,2] element. */
126     CX_DOT_Y,
127     /** Covariance matrix [4,3] element. */
128     CX_DOT_Z,
129     /** Covariance matrix [4,4] element. */
130     CX_DOT_X_DOT,
131     /** Covariance matrix [5,1] element. */
132     CY_DOT_X,
133     /** Covariance matrix [5,2] element. */
134     CY_DOT_Y,
135     /** Covariance matrix [5,3] element. */
136     CY_DOT_Z,
137     /** Covariance matrix [5,4] element. */
138     CY_DOT_X_DOT,
139     /** Covariance matrix [5,5] element. */
140     CY_DOT_Y_DOT,
141     /** Covariance matrix [6,1] element. */
142     CZ_DOT_X,
143     /** Covariance matrix [6,2] element. */
144     CZ_DOT_Y,
145     /** Covariance matrix [6,3] element. */
146     CZ_DOT_Z,
147     /** Covariance matrix [6,4] element. */
148     CZ_DOT_X_DOT,
149     /** Covariance matrix [6,5] element. */
150     CZ_DOT_Y_DOT,
151     /** Covariance matrix [6,6] element. */
152     CZ_DOT_Z_DOT,
153     /** Epoch of ignition. */
154     MAN_EPOCH_IGNITION,
155     /** Maneuver duration (If = 0, impulsive maneuver). */
156     MAN_DURATION,
157     /** Mass change during maneuver (value is < 0). */
158     MAN_DELTA_MASS,
159     /** Coordinate system for velocity increment vector. Its value can either be RSW, RTN (both
160      * indicating "Radial, Transverse, Normal") or TNW. */
161     MAN_REF_FRAME,
162     /** First component of the velocity increment. */
163     MAN_DV_1,
164     /** Second component of the velocity increment. */
165     MAN_DV_2,
166     /** Third component of the velocity increment. */
167     MAN_DV_3,
168     /** User defined parameter, where X is replaced by a variable length user specified character
169      *  string. Any number of user defined parameters may be included, if necessary to provide
170      *  essential information that cannot be conveyed in COMMENT statements. */
171     USER_DEFINED_X,
172     /** Keyword used to delineate the start of a metadata block. */
173     META_START,
174     /** Keyword used to delineate the end of a metadata block. */
175     META_STOP,
176     /** This keyword must appear before the first line of the covariance matrix data. */
177     COVARIANCE_START,
178     /** Start of total time span covered by ephemerides data and covariance data. */
179     START_TIME,
180     /** Start of useable time span covered by ephemerides data, it may be
181      * necessary to allow for proper interpolation. */
182     USEABLE_START_TIME,
183     /** End of useable time span covered by ephemerides data, it may be
184      * necessary to allow for proper interpolation. */
185     USEABLE_STOP_TIME,
186     /** End of total time span covered by ephemerides data and covariance data. */
187     STOP_TIME,
188     /** The interpolation method to be used. */
189     INTERPOLATION,
190     /** The interpolation degree. */
191     INTERPOLATION_DEGREE,
192     /** This keyword must appear after the last line of the covariance matrix data. */
193     COVARIANCE_STOP;
194 }