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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**

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