FEB 2003
0302.0
GLOBAL SET
----+----1----+----2----+----3----+----4----+----5----+----6----+----7----+----8
SATPAR 76039010.28274 411.000
----+----0----+----0----+----0----+----0----+----0----+----0----+----0----+----0
COLUMNS FORMAT DESCRIPTION DEFAULT VALUE & UNITS
1-6 A6 SATPAR - Specifies spacecraft identi-
fication number (Satellite ID), cross
sectional area and mass. Also specifies
maximum degree of gravitational
coefficients to be considered significant
for this spacecraft.
7 I1 0 - Obtain average S/C cross sectional 0
area and S/C mass from columns
25-59 of this card.
1 - Obtain same from S/C parameters
file.
8 I1 0 - No tables of S/C cross section or : 0
solar radiation to be obtained :
from S/C parameter file. :
1 - Only drag cross section tables :
used from S/C parameter file. :N/A
2 - Only solar radiation tables used :
from S/C parameters file. :
3 - Both drag cross section and solar :
radiation tables used from S/C :
parameters file. :
9 I1 Twelve parameter state combination
identifier. If this index is present
there must be one more SATPAR card in
the unit 5 setup to form the pair. For
the fisrt satellite the index must be
1 and for the second 2. For the
satellites forming a pair with these
indices on col. 9, the following
ELEMS1 and ELEMS2 cards contain 6 (six)
each of the twelve state vector
combination parameters. The first SATPAR
with the index 1 is followed by ELEMS
cards featuring the mid-point parameters,
and the second SATPAR is followed by
ELEMS cards featuring baseline parameters
(Ref. NOTE [2]). Any following VARCOV
cards for these two satellites feature
the sigmas of the 12 state combination
parameters.
10-11 I2 Spacecraft attitude control algorithm 0
0 - Cannonball(no attitude control)
2 - TOPEX/Poseidon
3 - SPOT-2
4 - GPS
5 - ERS-1
6 - Mars Observer Mapping Phase
7 - Mars Observer Cruise Phase
8 - TDRSS
9 - Magnetically stabilized S/C
10 - GFO
11 - TRMM
12 - EUVE
13 - VCL
12 I1 Requests external attitude for this
satellite: 0
0 - No external attitude
9 - External attitude (See Volume 5
for a description of the external
attitude file)
13 I1 Local gravity application switch: : 0
0 - Consider gravity anomaly, surface:
density and geoid height local :
gravity terms to be significant :N/A
for this spacecraft. :
1 - Consider local gravity terms to :
be insignificant for this :
spacecraft. :
15-17 I3 Maximum degree of gravitational coefficients Max. of Model
to be considered significant for this S/C.
18-24 I7 Satellite ID (satellite ID is required). 0
25-44 D20.8 S/C cross sectional area. See col. 7 M**2
45-59 D15.3 S/C mass. See col. 7 Kg
UNITS: KM =Kilometers; M =Meters ; S =Seconds ; Kg =Kilograms
DEG=Degrees ; RAD=Radians ; AS =Arc seconds; MAS=Milli-arc seconds
NOTES:
[1] If more than one satellite is used in an arc than the four lines
SATPAR, EPOCH, ELEMS1 ELEMS2 - are repeated for each satellite.
SATPAR --
EPOCH | These four lines are repeated for
ELEMS1 | each satellite in the arc
ELEMS2 --
[2] A full description for the baseline representation of the
initial epoch state parameters may be found in the following
reference:
"Short-arc analysis of intersatellite tracking data in a gravity
mapping mission", D.D.Rowlands, R.D.Ray, D.S.Chinn, F.G.Lemoine,
Journal of Geodesy (2002)76:307-316
IF CARD OMITTED: Run will abnormally terminate