Annex I System Description|
The European Meteorological Satellite System will continue the preoperational METEOSAT programme of geostationary satellites. The nominal position of the satellite will be over the O° meridian. The system will comprise a space segment and a ground segment. The design of the spacecraft will be based on that of METEOSAT. The ground segment will also make use of the experience gained during the preoperational METEOSAT programme and will provide for the tracking and control of the spacecraft and for central processing of the data.
2. Functional Description
2.1. Space segment
The satellite will be equipped with the following capabilities:
2.2. Ground segment
The ground segment will provide the following functions, most of which have to be performed in near real-time to meet meteorological requirement,
3. Technical performance
3.1. Space segment
The detailed performance specification for the spacecraft will be decided by the Council but will not be inferior to the specification for the preoperational METEOSATs except that the facility for "interrogating" data collection platforms through a dedicated down-link will be omitted.
The following improvements are foreseen:
3.2. Ground segment
The technical performance for the functions listed in 2.2. shall at least be that of the preoperational system. The system will, however, be updated with the aim of improving reliability and reducing operating costs.
4. Bridging activities
The operation of the existing system, including METEOSAT F1 and F2 and the satellite P2 (if launched within the framework of the preoperational programme) will also be incorporated with the operational programme with effect from 24 November 1983.
5. Launch Schedule
5.1. The operational programme will cover the procurement of components and building of sub-units necessary for three new flight models (MO1, MO2, MO3) and one spare.
Only one integration team will be used and the spacecraft will be integrated sequentially.
MO1 will be launched when ready, in principle in the first half of 1987.
MO2 will be launched about one and a half years later, in principle in the second half of 1988.
MO3 will be launched in principle in the second half of 1990.
This launch date could be moved as warranted by the status of the programme and the availability of launchers at decision time.
Insurance of the launches of MO1 and MO2 will be arranged in order to allow for integration and launch of an additional flight unit if necessary.
5.2. The maximum amount referred to in Annex II assumes that all launches will share a dual launch on ARIANE. The Council may decide by unanimous vote to use single launches if the programme requires it.
6. Duration of the programme
The use of the operational satellites resulting from the tentative schedule is expected to be 8.5 years starting with the launch of MO1 in 1986/1987. In addition there will be bridging activities using existing satellites and providing operation of those satellites (F1, F2, P2) as available during the period from 24 November 1983 until the launch of MO1 in 1986/1987. The expected overall duration of the programme is 12.5 years from beginning 1983 until mid 1995.