Advantech INTRAC-305 Manual De Usuario
INTRAC-305
TECHNICAL DESCRIPTION
© 2011 Advantech Wireless
INTRAC-305 MANUAL - Issue 3.2
Page 61
5
negative when entering from the front panel. This only applies
to the LMO data field.
to the LMO data field.
NORAD data
The NORAD ephemeris data consists of a string of 166
characters. The first 160 characters are split into two “Card
Element Sets” of 80 characters each. The next two characters
(161 & 162) comprise the Minutes Interval and characters 163
& 164 comprise the Period of Validity of the ephemeris. The
final two characters (165 & 166) are the check sum.
characters. The first 160 characters are split into two “Card
Element Sets” of 80 characters each. The next two characters
(161 & 162) comprise the Minutes Interval and characters 163
& 164 comprise the Period of Validity of the ephemeris. The
final two characters (165 & 166) are the check sum.
There are ten blocks of orbital element parameters contained
in the NORAD ephemeris character string :-
in the NORAD ephemeris character string :-
Charas.
Data
Description
19 - 32
EPOCH
format - YYDDD.DDDDDDDD
34 - 43
XNDT20 1st rate of change (rev/day/day)
45 - 52
XNDD60 2nd rate of change (rev/day/day/day)
54 - 61
BSTAR
damping factor (er**-1)
89 - 96
XINCL
inclination (deg)
98 - 105
XNODEO ascending node (deg)
107 - 113 EO
eccentricity
115 - 122 OMEGAO argument of perigee (deg)
124 - 131 XMO
mean anomaly (deg)
133 - 143 XNO
mean motion (rev/day)
RAPID MODEL GENERATION
The INTRAC-305 can use the IESS-412 or NORAD data to
build the satellite’s orbit model instead of having to learn the
orbit over a 24hr period.
orbit over a 24hr period.
The IESS-412 data is selected for the Rapid Model Generation
in the Models menu and ENTER pressed. The orbit model is
calculated and the INTRAC enters Tracking Mode.
in the Models menu and ENTER pressed. The orbit model is
calculated and the INTRAC enters Tracking Mode.
For the NORAD data there are five choices of NORAD
algorithm. These are SGP, SGP4, SGP8, SDP4 & SDP8 and
each gives a slightly different Az/El pointing for the same
NORAD data.
algorithm. These are SGP, SGP4, SGP8, SDP4 & SDP8 and
each gives a slightly different Az/El pointing for the same
NORAD data.
SGP
the original NORAD algorithm
SGP4
applies to Near Earth Orbits
SGP8
applies to Near Earth Orbits
SDP4
applies to Deep Space Orbits
SDP8
applies to Deep Space Orbits
Orbits are differentiated by their period. Those of less than 225
minutes are Near Earth Orbits and those of more then 225
minutes are Deep Space Orbits. Geostationary satellites are in
Deep Space Orbit.
minutes are Near Earth Orbits and those of more then 225
minutes are Deep Space Orbits. Geostationary satellites are in
Deep Space Orbit.
It is assumed that the user know which algorithm applies to the
data to be used. However INTRAC will not allow a Near Earth
Orbit algorithm to be used with Deep Space Orbit data and
vice-versa.
data to be used. However INTRAC will not allow a Near Earth
Orbit algorithm to be used with Deep Space Orbit data and
vice-versa.