TriPoint VertexRSI 7200, Руководство по эксплуатации и обслуживанию

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7 2 0 0 OPERA TIO N
5 - 2 7
The non-geosynchronous parameters li sted i n Tab l e 5-9 prov i de OPT w i th the
capab ili ty to support track i ng a sate lli te i n non-geosynchronous orb i ts under certa i n
c i rcumstances. Improper use of these parameters w ill severe l y degrade OPT
performance. V ertex recommends that the user contact a Contro l Systems Group
eng i neer before attempt i ng to mod i fy these parameters.
TAB L E 5-9 NON-GEOSYNCH R ONOUS SU PP O R T P A R AMETE R S
P A R AMETE R DEFAU L T DESC R I P T I ON
Non-
geosynchronous
track
i ng
D i sab l ed A ll o w s the A C U to track sate lli tes that are not i n geosynchronous
orb i t. In th i s system, a geosynchronous orb i t i s def i ned to have a
per i od very c l ose to 1 s i derea l day (8 6 1 6 4 seconds) and an
eccentr i c i ty near zero (c i rcu l ar orb i t). Inc li ned orb i ts w i th these
character i st i cs are st ill geosynchronous.
For most app li cat i ons, th i s parameter shou l d be d i sab l ed. Un l ess an
operator i s certa i n that th i s parameter needs to be enab l ed, i t
shou l d be D i sab l ed. Th i s i s typ i ca ll y used for dr i ft orb i t support
(repos i t i on i ng a sate lli te to a ne w orb i ta l ass i gnment on the
geostat i onary arc), li m i ted transfer orb i t track i ng, and Mo l n i ya-type
orb i t track i ng.
If th i s parameter i s enab l ed,
a ll
other i tems i n th i s menu
must
be set
proper l y to beg i n track i ng. The va l ues shou l d be as accurate as
poss i b l e. W hen OPT gathers suff i c i ent steptrack data, i t w ill
compute i ts o w n va l ues for these parameters, and the va l ues i n th i s
menu w ill be dropped from use.
Orb i ta l per i od
[seconds]
8 6 1 6 4
seconds
Used i n con j unct i on w i th the steptrack data to bu il d OPT so l ut i ons.
The orb i ta l per i od i s the t i me i n w h i ch the sate lli te makes one
comp l ete revo l ut i on around the Earth. Un i ts are seconds.
Orb i ta l
eccentr i c i ty
0.0 0 0 0 0 Used i n con j unct i on w i th the steptrack data to bu il d OPT so l ut i ons.
The orb i ta l eccentr i c i ty def i nes the shape of the orb i t. The va l ue i s
non-d i mens i ona l .
Orb i t argument
of per i gee [deg]
0.0 0 0 Used i n con j unct i on w i th the steptrack data to bu il d OPT so l ut i ons i f
the eccentr i c i ty i s set greater than zero. The argument of per i gee i s
the angu l ar measurement, i n the p l ane of the sate lli te’s orb i t,
bet w een the ascend i ng node and the per i aps i s po i nt. Un i ts are
degrees.
NOTE: I f th e o r b i t a l i n c li n a t i on i s v e r y n ea r z e r o, th i s a ng l e i s
m ea su r e d f r om th e m ea n v e r n a l e qu i nox v ec to r to th e p e ri a ps i s po i nt.