Rządowy projekt ustawy o ratyfikacji Konwencji w sprawie ustanowienia Europejskiej Organizacji Eksploatacji Satelitów Meteorologicznych (EUMETSAT), sporządzonej w Genewie dnia 24 maja 1983 r.

Convention

Annex I Chapter A



The following improvements are foreseen:


-
Improved lifetime as regards electric power and propellant.


-
Improved reliability of radiometer and electronics.


-
Water vapour channel to be brought to the same standard of design and
manufacture as the other two channels; noise (interference) to be reduced.


-
Simultaneous operation of the infra-red window channel, the water vapour
channel and both visible channels.


-
"In flight" calibration of the water vapour channel.


-
Temperature control of calibrating black body.


-
Modification of transponder to allow for distribution of digital data to earth
stations in addition to pre-operational Meteosat functions.

3.2 Ground
Segment


The technical performance for the functions listed in 2.2 shall at least be that of the
pre-operational 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 pre-operational 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.
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Convention

Annex I Chapter A



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.

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 1986-87. 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 1986-87. The expected overall duration of the programme is 12.5 years from
beginning 1983 until mid 1995.
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Convention

Annex I Chapter B



CHAPTER B

GENERAL
BUDGET


The General Budget will constitute the programmatic frame for all EUMETSAT core and
prospective activities in 1990 and subsequent years.

Core activities shall be defined as those which are not linked to a specific programme. They
represent the basic technical and administrative infrastructure of EUMETSAT including core
staff, buildings and equipment.

Prospective activities mean preliminary activities authorised by Council in preparation of future
programmes which are not yet approved.







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Annex I Chapter C


CHAPTER C

METEOSAT TRANSITION PROGRAMME


1 INTRODUCTION


The Meteosat Transition Programme will ensure the continuation of the service provided
by meteorological satellites in geostationary orbit after 30 November 1995 at least until
31 December 2003.

2
THE GROUND SEGMENT


A Ground Segment will be developed to take over operations of the MOP and MTP
satellites in December 1995. The Ground Segment will be used to provide routine
operations support at least until 31 December 2003.

3 SPACE
SEGMENT


The MTP Space Segment consists of a single new satellite of the same design as the
latest Meteosat satellite (MOP-3), with a launch date scheduled for late 1995. In addition,
advance activities will be performed to ensure the possibility of a future decision to
manufacture a second new satellite.

4 IMPLEMENTATION
PLAN


That the programme will be implemented in two slices. The first slice includes the
manufacture of one new satellite, advance activities for a possible second satellite,
definition of the Ground Segment and programme management.


The second slice includes the implementation of the Ground Segment, the satellite launch
and the operation of Space and Ground Segments at least for 8 years.


The authorisation to proceed with the second slice of activities will take into account
relevant results from the first slice.
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Convention

Annex I Chapter D


CHAPTER
D


PREPARATORY PROGRAMME FOR METEOSAT SECOND GENERATION:

PHASE
A

1 INTRODUCTION


Phase A of the MSG Preparatory Programme corresponds to the definition a
geostationary satellite system to ensure operational continuity of the present Meteosat
system.


This phase is foreseen for one year, starting from the 1 January 1991.


Phase A, in 1991/1992/1993/1994, will study the feasibility of a spin satellite system
embarking a visible and infra-red imaging radiometer (SEVIRI) in support of a
multispectral high resolution imagery mission and of an atmospheric instability
monitoring mission as well as complementary instruments which will neither become
design drivers nor cost drivers for the system as described.

2 SYSTEM
DESCRIPTION

2.1
The MSG space segment will consist in a series of spin-stabilised satellites in
geostationary orbit at 0 Degree N-0 Degree E and operable between the limits of ± 45
Degree longitude.

2.2
This system, based on two satellites in orbit simultaneously (one operational and one
back-up) will be designed for a 12 years operation period after commissioning of the first
flight model.

2.3
In accordance with EUM/C/Res.XXIII, all satellites will carry a core payload, consisting
of the following sub-systems:


a)
An imaging radiometer, referred to as SEVIRI (Spinning Enhanced Visible and
Infra-Red Imager), in support of both basic and high resolution imagery missions
as well as of air mass analysis.


b)
Meteorological communication payload (MCP) for dissemination and relay of
images as well meteorological and environmental data and products.

2.4
A complementary payload, experimental or operational, which should not become a
design driver for the system.

∗ This preparatory programme has expired.

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