Galileo OS SIS ICD.indd - GSA - Europa
Galileo OS SIS ICD.indd - GSA - Europa
Galileo OS SIS ICD.indd - GSA - Europa
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5. Message Data Contents<br />
This section describes the data items above mentioned. Semantics, formats and other<br />
characteristics are provided for all items to be transmitted inside frames.<br />
5.1. Navigation Data<br />
The navigation data contain all the parameters that enable the user to perform<br />
positioning service. They are stored on board each satellite with a validity duration and<br />
broadcast world-wide by all the satellites of the <strong>Galileo</strong> constellation. The 4 types of<br />
data needed to perform positioning:<br />
5.1.1. Ephemeris<br />
● Ephemeris which are needed to indicate the position of the satellite to the user<br />
receiver<br />
● Time and clock correction parameters which are needed to compute pseudo-range<br />
● Service parameters which are needed to identify the set of navigation data, satellites,<br />
and indicators of the signal health<br />
● Almanac which are needed to indicate the position of all the satellites in the<br />
constellation with a reduced accuracy<br />
The ephemeris for each <strong>Galileo</strong> satellite is composed of 16 parameters, which are:<br />
● 6 keplerian parameters<br />
● 6 harmonic coeffi cients<br />
● 1 orbit inclination rate correction parameter<br />
● 1 LAN rate correction parameter<br />
● 1 mean motion correction parameter, and<br />
● 1 reference time parameter t 0e for the ephemeris data set<br />
The ephemeris for each <strong>Galileo</strong> satellite is according to the characteristics stated in<br />
Table 61.<br />
Parameter Defi nition Bits Scale<br />
factor<br />
44 © European Union 2010<br />
Document subject to terms of use and disclaimers p. ii-iii<br />
OD <strong>SIS</strong> <strong>ICD</strong>, Issue 1, February 2010<br />
Unit<br />
M 0 Mean anomaly at reference time 32* 2 -31 semi-circles**<br />
∆n Mean motion difference from computed value 16* 2 -43 semi-circles/s**<br />
e Eccentricity 32 2 -33 N/A<br />
A 1/2 Square root of the semi-major axis 32 2 -19 meters1/2<br />
Ω 0<br />
Longitude of ascending node of orbital plane<br />
at weekly epoch<br />
32* 2 -31 semi-circles**<br />
i 0 Inclination angle at reference time 32* 2 -31 semi-circles**<br />
ω Argument of perigee 32* 2 -31 semi-circles**