Perturbations and Errors Simulation
Satellite Navigation
103
User Manual 1178.6379.02 ─ 01
ellite thus carries the reference time of ephemeris t
0e
, six orbit elements and three rate
parameters describing the linear time-dependent changes [1].
Figure 12-1: Satellite orbit (GPS): Understanding the displayed information
1 = Reference time, t
0e
2 = Orbit elements
3 = Rate parameters
In GPS, Galileo, BeiDou and QZSS, the perturbations are seen as variations of the
orbital elements. In the navigation message, they are described by three pairs of sinus-
oidal (cosine and sine) corrections C
C
and C
S
, each pair describing the difference in
latitude C
U
, orbital radius C
r
and inclination C
i
.
GLONASS satellites, on the other hand, broadcast their PZ coordinates and velocity at
reference epoch time t
b
as well as the moon and sun acceleration components [1].
About the Errors Sources