Operation
The non-geosynchronous parameters listed in Table 5-11 provide OPT with the
capability to support tracking a satellite in non-geosynchronous orbits under certain
circumstances. Improper use of these parameters will severely degrade OPT
performance. General Dynamics recommends that the user contact a General
Dynamics engineer before attempting to modify these parameters.
TABLE 5-11 NON-GEOSYNCHRONOUS SUPPORT PARAMETERS
PARAMETER DEFAULT DESCRIPTION
Non-
geosynchronous
tracking
Disabled
Allows the ACU to track satellites that are not in geosynchronous orbit. In
this system, a geosynchronous orbit is defined to have a period very close
to 1 sidereal day (861
64 seconds) and an eccentricity near zero (circular
orbit). Inclined orbits with these characteristics are still geosynchronous.
For most applications, this parameter should be disabled. Unless an
operator is certain that this parameter needs to be en
abled, it should be
Disabled. This is typically used for drift orbit support (repositioning a
satellite to a new orbital assignment on the geostationary arc), limited
transfer orbit tracking, and Molniya-type orbit tracking.
If this parameter is enabled, all other items in this menu must
be set
properly to begin tracking. The values should be as accurate as possible.
When OPT gathers sufficient steptrack data, it will compute its own values
for these parameters, and the values in this menu will be dropped from use.
Orbital period
[seconds]
86164
seconds
Used in conjunction with the steptrack data to build OPT solutions. The
orbital period is the time in which the satellite makes one complete
revolution around the Earth. Units are seconds.
Orbital
eccentricity
0.00000
Used in conjunction with the steptrack data to build OPT solutions. The
orbital eccentricity defines the shape of the orbit. The value is non-
dimensional.
Orbit argument of
perigee [deg]
0.000
Used in conjunction with the steptrack dat
a to build OPT solutions if the
eccentricity is set greater than zero. The argument of perigee is the angular
measurement, in the plane of the satellite's orbit, between the ascending
node and the periapsis point. Units are degrees.
NOTE: If the orbital inclination is very near zero, this angle is measured from
the mean vernal equinox vector to the periapsis point.
5-27
To Next Page
Loading...
Need help?
General