Object File for Mars Observer Magnetometer
ABSTRACT: The Object File contains descriptive information about symbols
representing program variables.
SUMMARY: The Object File is ascii text, in a "KEYWORD = VALUE" format
which is similar to that used by NAIF, readable by man and machine.
The analysis program attempts to write records to stdout, which records
include values for each of the variables called for in the command line
input by symbol. Each symbol may represent an integer, real, or character
variable, and each may be a scalar or vector quantity; this object file
provides this information to the analysis program. In addition, this file
expresses a preference for a particular output format. Additional information
may be included here (e.g., "units = nT") which will be reproduced in the
file header of the output files generated - to assist in automatic label
generation on plots and so on. Note that the MG ANalysis program can provide
any of the following output parameters, in addition to any scalar quantity
residing in the integer pool (packet variables) or the dble precision pool
maintained by MGAN. For those scalars not listed here, MGAN will simply
adopt the generic real or integer output format, depending on whether the
variable was located in the integer pool or the dble precision pool.
Primitive variables (integer variables, mostly) are described in the
flight software documentation.
FORMAT: The Object File DOES NOT conform to the format of JPL
naif kernel files. The format is SIMILAR TO that of the JPL NAIF files.
For example, in this file, commas are necessary and cannot by treated
by the reader as whitespace (as in NAIF text kernel files).
Additional information on file format and reading routines (Fortran)
can be found in the naif libraries (/SFOC/naif/toolkit/etc/spicelib/env0)
AUTHOR: J. E. P. Connerney, code 695 NASA/GSFC
DATE: 20-OCT-1992
REV: 29-OCT-1992: Added integer vectors (JEPC)
13-NOV-1992: Added ascii variable (JEPC)
15-NOV-1992: Added ephemeris time (JEPC)
21-JAN-1993: Added vector housekeeping object (JEPC)
15-FEB-1993: Added calender format time (t) variable (JEPC)
02-MAR-1993: Added raw counts (JEPC)
26-APR-1993: Added units information for plots (JEPC)
03-MAY-1993: Substituted more readable aliases (JEPC)
25-MAY-1993: Revised aliases (JEPC)
26-MAY-1993: Added pointing matrix, associated ephemeris t (JEPC)
03-JUN-1993: Added position vector, lighttime correction (JEPC)
04-JUN-1993: Added target-body, spacecraft angles (JEPC)
01-AUG-1993: Added transformation matrix (inertial to body-fixed) (JEPC)
02-AUG-1993: Added state vector (position, velocity) wrt target (JEPC)
05-AUG-1993: Added ambient field vector B (currently = OB_BS ) (JEPC)
06-AUG-1993: Reduce ambient field to three vector; quality in QA (JEPC)
22-AUG-1993: Add documentation to describe quantity (JEPC)
29-AUG-1997: Update documentation to reflect MGS; matrix notes (JEPC)
05-SEP-1997: Add earth_sc angles (JEPC)
12-SEP-1997: Add ob, ib B expressed in inertial J2000 coord. sys. (JEPC)
13-SEP-1997: Add ob, ib B expressed in payload coordinates (JEPC)
18-NOV-1997: Add ob, ib RMS in sensor coordinates (JEPC)
28-NOV-1997: Add transformation matrix sensor to payload coord. (JEPC)
06-JAN-1999: Revise format for B to accomodate larger values (JEPC)
==============================================================================
The vectors OB_BS (IB_BS) are four-vectors of the magnetic field in sensor
(payload) coordinates as measured by the outboard (inboard) sensor. The
range word for the sensor is carried as a fourth component; this range word
denotes both the range and operating mode. If the instrument is in autorange
mode, the range word is incremented by 8 (auto range enable bit is on). In
manual mode, ranges are 0 to 7; in autorange mode, 8 to 15 (see mo_mags.ker).
\begindata
OBJECT = VECTOR
NAME = OB_BS
ALIAS = OUTBOARD_B_SENSOR
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IB_BS
ALIAS = INBOARD_B_SENSOR
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
\begintext
The RMS (Root Mean Squared) fluctuation is the square root of the
sum of the squared difference field values divided by N, the number
of difference field values. Nominally, only the outboard magnetometer
has difference words. There is one RMS value for each full word that
is followed by difference words, and the estimate sums over all of
the difference words between consecutive full words. The estimate is
provided in sensor coordinates.
\begindata
OBJECT = VECTOR
NAME = OB_RMS
ALIAS = OUTBOARD_RMS
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IB_RMS
ALIAS = INBOARD_RMS
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
\begintext
The ambient field is the variable B. This is to be the ambient field of the
environment, as determined using the field at each sensor and any additional
ancillary data, e.g., s/c engineering data (solar array current, and so on).
When the quality of this estimate is known, it will be indicated by the
variable QA.
THIS VARIABLE IS CURRENTLY A PLACE HOLDER ONLY. THE AMBIENT FIELD IS UNKNOWN.
\begindata
OBJECT = VECTOR
NAME = B
ALIAS = B_AMBIENT
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
END_OBJECT
OBJECT = SCALAR
NAME = QA
ALIAS = QUALITY_OF_B
TYPE = REAL
FORMAT = F4.0
END_OBJECT
\begintext
Below we add the field measured by ob and ib sensors as expressed
in inertial J2000 coordinates.
\begindata
OBJECT = VECTOR
NAME = OB_B
ALIAS = OUTBOARD_B_J2000
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IB_B
ALIAS = INBOARD_B_J2000
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = OB_BPL
ALIAS = OUTBOARD_B_PAYLOAD
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IB_BPL
ALIAS = INBOARD_B_PAYLOAD
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F9.3
UNITS = NT
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,F4.0
END_OBJECT
END_OBJECT
\begintext
The raw data words from the inboard and outboard magnetometers are available
with the following variables. These and other primitive variables (integer
variables) are described in the flight software documentation.
\begindata
OBJECT = VECTOR
NAME = IB_CNTS
ALIAS = INBOARD_COUNTS
TYPE = INTEGER
OBJECT = SCALAR
NAME = X
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,I3
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = OB_CNTS
ALIAS = OUTBOARD_COUNTS
TYPE = INTEGER
OBJECT = SCALAR
NAME = X
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,I4
UNITS = COUNTS
END_OBJECT
OBJECT = SCALAR
NAME = RANGE
FORMAT = 1X,I3
END_OBJECT
END_OBJECT
\begintext
The packet sequence number is used to keep track of missiong packets; this is
telemetered to the ground with the data. The processor will reset this counter
each time it initializes. The first few packets following such an event will
consist of instrument memory dumps, not read routinely.
\begindata
OBJECT = SCALAR
NAME = PKT_SEQ
ALIAS = PACKET_SEQUENCE
TYPE = INTEGER
FORMAT = I5
UNITS = COUNTS
END_OBJECT
\begintext
The packet time is an integer representing spacecraft clock "tics" maintained
by the spacecraft clock. It is approximately equal to seconds past a reference
time prior to launch. It is not exactly equal to seconds past this reference
time, since it is adjusted for drift from time to time. Conversion to UTC time
also requires observation of "leapseconds" which are introduced frequently;
see NAIF documentation for discussion of time conversion.
\begindata
OBJECT = SCALAR
NAME = PKT_TIME
ALIAS = PACKET_TIME
TYPE = INTEGER
FORMAT = I12
UNITS = COUNTS
END_OBJECT
OBJECT = VECTOR
NAME = N_SATS
ALIAS = N_SATURATED_DIFF
TYPE = INTEGER
UNITS = COUNTS
OBJECT = SCALAR
NAME = Q1
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = Q2
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = Q3
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = Q4
FORMAT = 1X,I2
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = SH_STAT
ALIAS = SHIFT_STATUS
TYPE = INTEGER
UNITS = COUNTS
OBJECT = SCALAR
NAME = Q1
FORMAT = 1X,I1
END_OBJECT
OBJECT = SCALAR
NAME = Q2
FORMAT = 1X,I1
END_OBJECT
OBJECT = SCALAR
NAME = Q3
FORMAT = 1X,I1
END_OBJECT
OBJECT = SCALAR
NAME = Q4
FORMAT = 1X,I1
END_OBJECT
END_OBJECT
\begintext
The generic integer and generic real variables are provided to allow the
output of variables (scalars) which appear in the integer symbol table or
the real variable symbol table, but which were not known at the time this
file was prepared. These variables will not be labelled, but the program
will pass them through to each record with the default formats declared below.
\begindata
OBJECT = SCALAR
NAME = GENERIC_INTEGER
ALIAS = GENERIC_INTEGER
TYPE = INTEGER
FORMAT = I6
END_OBJECT
OBJECT = SCALAR
NAME = GENERIC_REAL
ALIAS = GENERIC_REAL
TYPE = REAL
FORMAT = F8.3
END_OBJECT
\begintext
The character variable cstring is an oddity; it applies to the character
identification of the decommutated engineering data that appears in the
packet headers. Since this variable may be any of 16 or 32 possible
engineering measurements, all appearing in the packet under the "hsk"
variable name, it must be further identified. The cstring variable provides
this identity (see mo_hsk.ker).
\begindata
OBJECT = SCALAR
NAME = CSTRING
ALIAS = CHARACTER_STRING
TYPE = ASCII
FORMAT = A
END_OBJECT
\begintext
Ephemeris time is seconds before J2000; this is the time upon which all
ephemeris information is based. See NAIF documentation for more details.
\begindata
OBJECT = SCALAR
NAME = ET
ALIAS = EPHEMERIS_TIME
TYPE = REAL
FORMAT = F15.3
END_OBJECT
OBJECT = SCALAR
NAME = DDAY
ALIAS = DECIMAL_DAY
TYPE = REAL
FORMAT = F13.9
END_OBJECT
OBJECT = SCALAR
NAME = PKT_ET
ALIAS = PACKET_EPHEMERIS_TIME
TYPE = REAL
FORMAT = F15.3
END_OBJECT
\begintext
The light time is returned along with the position of the spacecraft or the
state of the spacecraft, represents the light travel time from the sc to the
target body (see options in mgan).
\begindata
OBJECT = SCALAR
NAME = LT
ALIAS = LIGHT_TIME
TYPE = REAL
FORMAT = F15.3
END_OBJECT
\begintext
The position of the spacecraft or the state of the spacecraft, relative to the
target body specified in the command line, is returned in cartesian
coordinates. The coordinate system for position, state, and b are as
specified in the options list on the command line.
\begindata
OBJECT = VECTOR
NAME = POSN
ALIAS = SC_POSITION
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
END_OBJECT
\begintext
The state vector (state of the spacecraft, relative to the
target body specified in the command line) is returned in cartesian
coordinates. The state vector consists of three components of the
position vector followed by three components of the velocity vector.
The coordinate system for position, state, and b are as specified in
the options list on the command line.
\begindata
OBJECT = VECTOR
NAME = STATE
ALIAS = SC_STATE
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F13.3
UNITS = KILOMETERS
END_OBJECT
OBJECT = SCALAR
NAME = VX
FORMAT = 1X,F8.3
UNITS = KILOMETERS/SEC
END_OBJECT
OBJECT = SCALAR
NAME = VY
FORMAT = 1X,F8.3
UNITS = KILOMETERS/SEC
END_OBJECT
OBJECT = SCALAR
NAME = VZ
FORMAT = 1X,F8.3
UNITS = KILOMETERS/SEC
END_OBJECT
END_OBJECT
\begintext
The position of ob or ib sensors relative to the spacecraft body
is returned in cartesian coordinates. Similarly for the Electron
reflectometer and solar array "plus" and "minus", e.g., SAM and
SAP. Since the sensors are mounted on the ends of the solar array
we need to compute their position as a function of time using
special c kernels for the solar arrays.
\begindata
OBJECT = VECTOR
NAME = OB_POSN
ALIAS = OB_SENSOR_POSITION
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IB_POSN
ALIAS = IB_SENSOR_POSITION
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = SAP_POSN
ALIAS = SOLAR_ARRAY_P_POSITION
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = SAM_POSN
ALIAS = SOLAR_ARRAY_M_POSITION
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = METERS
END_OBJECT
END_OBJECT
\begintext
Pointing phemeris time is also seconds before J2000; this is the time for
which the requested pointing information (e.g., the pointing matrix, or pmx)
is valid. Depending on the type of the c-kernel, this time will be either
close to the requested time, or identically equal to the requested time.
\begindata
OBJECT = SCALAR
NAME = PET
ALIAS = POINTING_EPHEMERIS_TIME
TYPE = REAL
FORMAT = F15.3
END_OBJECT
\begintext
The transformation matrix from inertial (J2000) coordinates to the payload
coordinate system. This matrix is computed using a specified c kernel (see
NAIF documentation).
PMX is a rotation matrix that transforms the components of a
vector expressed in the inertial frame specified by REF to
components expressed in the spacecraft payload frame.
Thus, if a vector v has components x, y, z in the inertial frame,
then v has components x', y', z' in the instrument-fixed frame
at time:
[ x' ] [ ] [ x ]
| y' | = | PMX | | y |
[ z' ] [ ] [ z ]
If you know x', y', z', use the transpose of the C-matrix to
determine x, y, z as follows:
[ x ] [ ]T [ x' ]
| y | = | PMX | | y' |
[ z ] [ ] [ z' ]
(Transpose of CMX)
You want to use the transpose of this matrix to transform
a vector rendered in the payload coordinate system to one in inertial space.
\begindata
OBJECT = VECTOR
NAME = PMX
ALIAS = POINTING_MATRIX
TYPE = REAL
OBJECT = SCALAR
NAME = (1,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,3)
FORMAT = 1X,F9.6
END_OBJECT
END_OBJECT
\begintext
Transformation matrix elements are ordered as follows:
| (1,1) (1,2) (1,3) |
MX = | (2,1) (2,2) (2,3) |
| (3,1) (3,2) (3,3) |
\begindata
\begintext
The transformation matrix from inertial (J2000) to the chosen coordinate
system. The coordinate system is specified by the options list on the command
line.
\begindata
OBJECT = VECTOR
NAME = TMX
ALIAS = TRANSFORMATION_MATRIX
TYPE = REAL
OBJECT = SCALAR
NAME = (1,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,3)
FORMAT = 1X,F9.6
END_OBJECT
END_OBJECT
\begintext
The transformation matrix from each sensor to payload coordinate
system. The coordinate system is specified by the options list on the command
line, either 'OBMX' or 'IBMX'.
\begindata
OBJECT = VECTOR
NAME = OBMX
ALIAS = OB_TO_PAYLOAD_MATRIX
TYPE = REAL
OBJECT = SCALAR
NAME = (1,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,3)
FORMAT = 1X,F9.6
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = IBMX
ALIAS = IB_TO_PAYLOAD_MATRIX
TYPE = REAL
OBJECT = SCALAR
NAME = (1,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,1)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,2)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (1,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (2,3)
FORMAT = 1X,F9.6
END_OBJECT
OBJECT = SCALAR
NAME = (3,3)
FORMAT = 1X,F9.6
END_OBJECT
END_OBJECT
\begintext
This is a time vector based upon decimal day of the year. The time variable
is unusual in that the time provided is the time associated with the next
non-time variable on the command line. Think of it as a timetag function
which returns the time of the next variable in the argument list. If that
variable is magnetic field, then time corresponds to the center of the
interval over which the average is taken, and the timetags expand so that
there is one for each b field value (timestep). If the next argument on the
command line is any other variable, the time returned is the converted packet
time.
\begindata
OBJECT = VECTOR
NAME = TIME
ALIAS = TIME
TYPE = INTEGER
OBJECT = SCALAR
NAME = YEAR
FORMAT = 1X,I4
END_OBJECT
OBJECT = SCALAR
NAME = DOY
FORMAT = 1X,I3
END_OBJECT
OBJECT = SCALAR
NAME = HOUR
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = MIN
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = SEC
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = MSEC
FORMAT = 1X,I3
END_OBJECT
END_OBJECT
\begintext
This is a time vector based upon calander day. The time variable
is unusual in that the time provided is the time associated with the next
non-time variable on the command line. Think of it as a timetag function
which returns the time of the next variable in the argument list. If that
variable is magnetic field, then time corresponds to the center of the
interval over which the average is taken, and the timetags expand so that
there is one for each b field value (timestep). If the next argument on the
command line is any other variable, the time returned is the converted packet
time.
Note that t and time are not both available on the same record, a limitation
which conserves space in the integer pool of variables.
\begindata
OBJECT = VECTOR
NAME = T
ALIAS = CALENDER_TIME
TYPE = INTEGER
OBJECT = SCALAR
NAME = YEAR
FORMAT = 1X,I4
END_OBJECT
OBJECT = SCALAR
NAME = MONTH
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = DAY
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = HOUR
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = MIN
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = SEC
FORMAT = 1X,I2
END_OBJECT
OBJECT = SCALAR
NAME = MSEC
FORMAT = 1X,I3
END_OBJECT
END_OBJECT
\begintext
Instrument engineering data from the packet headers is available via the hsk
variable. Since this variable may be any of 16 or 32 possible
engineering measurements, all appearing in the packet under the "hsk"
variable name, it must be further identified. The cstring variable provides
this identity (see mo_hsk.ker).
\begindata
OBJECT = VECTOR
NAME = HSK
ALIAS = HOUSEKEEPING
TYPE = REAL
OBJECT = SCALAR
NAME = MAG
FORMAT = 1X,F8.3
END_OBJECT
OBJECT = SCALAR
NAME = ER
FORMAT = 1X,F8.3
END_OBJECT
END_OBJECT
\begintext
The sun_sc and mars_sc angle variables provide the angle in degrees between
the spacecraft x axis and the sun, the spacecraft y axis and the sun, and
the spacecraft z axis and the sun (or mars). Similarly, the earth_sc angle
variable provides the angle between the spacecraft x axis and the earth,
spacecraft y axis and the earth, and spacecraft z axis and the earth.
\begindata
OBJECT = VECTOR
NAME = SUN_SC
ALIAS = SUN_SC_ANGLE
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = MARS_SC
ALIAS = MARS_SC_ANGLE
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
END_OBJECT
OBJECT = VECTOR
NAME = EARTH_SC
ALIAS = EARTH_SC_ANGLE
TYPE = REAL
OBJECT = SCALAR
NAME = X
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Y
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
OBJECT = SCALAR
NAME = Z
FORMAT = 1X,F8.3
UNITS = DEGREES
END_OBJECT
END_OBJECT
\begintext