AIPS HELP file for OBTAB in 31DEC18
As of Sat Jul 21 20:59:18 2018
OBTAB: Task to calculate various orbital information
INNAME Input UV file name (name)
INCLASS Input UV file name (class)
INSEQ 0.0 9999.0 Input UV file name (seq. #)
INDISK 0.0 9.0 Input UV file disk unit #
INVERS 0.0 9999.0 Input OB table version
0 => last
SUBARRAY Subarray number; 0 => 1
ANTENNAS List of antenna to update
All 0 => update all
antennae with mount type
set to orbiting
APARM Orbital parameters
1: semi-major axis in meters
3: inclination (deg)
4: RA of ascending node
5: argument of perigee (deg)
6: mean anomaly at 0h on
the observing date (deg)
APARM(1) < 6.37812E6 =>
calculate elements from OB
Use: Use OBTAB to add the orbital elements for orbiting
antennae to an AN table. The elements may be supplied
explicitly as APARMs or may be calculated automatically
from an orbit (OB) table if one is present. The
recommended method is to calculate the orbit from the OB
table. If an OB table is used to calculate the orbital
parameters then it will be assumed to correspond to a
single orbiter and any blanked fields will be be filled
with recalculated values.
INNAME.....Input UV file name (name). Standard defaults.
INCLASS....Input UV file name (class). Standard defaults.
INSEQ......Input UV file name (seq. #). 0 => highest.
INDISK.....Disk drive # of input UV file. 0 => any.
INVERS.....Input OB table version; 0 => last
SUBARRAY...Subarray number; 0 => 1
This denotes the AN table that will be updated.
ANTENNAS...A list of antennas for which the orbital elements
will be updated. The mount types for these
antennae will be forced to "orbiting". If all of
the entries are less than or equal to zero then the
orbital elements will be updated for all antennae
that already have a mount type of "orbiting".
1: The semimajor axis of the orbit in meters. If
this value is less than the equatorial radius of
the earth then the elements will be calculated
from the OB table.
2: The orbital eccentricity
3: The inclination of the orbit to the equator in
4: The right ascension of the ascending node in
5: The argument of perigee in degrees.
6: Mean anomaly at 0h on the observing date.
OBTAB: Task to calculate orbital parameters
DOCUMENTER: Chris Flatters, NRAO
RELATED PROGRAMS: UVPLT, VPLOT, SLIME
OBTAB inserts the orbital elements of orbiting antennae
into an AN table, allowing models to be plotted for baselines
including orbiting antennae at times where there is no data.
The normal mode of operation is to calculate the orbital
elements using the Cartesian coordinates and velocity vector
of the satellite given as a function of time in an OB table.
If there is no OB table present then orbital elements may be
OBTAB will update several antennae in one pass but will
assume that all of the antennae being updated are aliases for
a single orbiter. The user may supply a list of antenna
numbers to update. If no list is supplied then all antennae
that have a mount type of orbiting (MNTSTA=2) will be updated;
this will not be what you want if there is more than one real
OB tables from the VLBA correlator are incomplete. Given
an incomplete OB table, OBTAB will fill out the missing
information. If the subarray number in the OB table is set
to zero then it will be set to the SUBARRAY used by OBTAB.
If the antenna number is zero in the OBTAB then it will be
set to the first positive entry in ANTENNAS, if any, or the
lowest numbered antenna with MNTSTA=2 if there is no
positive element in ANTENNAS. Other missing information
will be recalculated.
Normally, entries from the OB table will only be used
to calculate the orbital elements if there subarray number
matches the subarray being processed and their antenna ID
number corresponds to one of the antennae being processed
but zero subarray and antenna entries are assumed to be
"wildcards" that match any subarray or antenna. This has the
consequence that orbital elements will be calculated incorrectly
if an OB table contains data for more than one orbiter and has
zero subarray or antenna entries.
OBTAB is currently uses a better-safe-than-sorry approach
to calculating eclipse parameters that results in it probably
performing far more computations than it needs to. This makes
it very slow.
"Orbital Motion, 3rd Edn", A.E. Roy, Institute of Physics
AIPS Memo Number 93, L. Kogan.