Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
Status of Meteosat Third Generation (MTG) Pre-Phase A System Architecture Studies
Paolo Bensi, Earth Observation Future Programme DepartmentEuropean Space Agency
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
• 2015: NOMINAL NEED DATE FOR MTG
• 2009-2015 : PHASE C/D DEVELOPMENT/ON-GROUND TEST OF MTG SYSTEM
• 2008-2009: PHASE B COORDINATED ESA & EUM PREPARATORY PROGRAMMES
Approval of EUMETSAT and ESA MTG development programmes
• 2006-2007: MTG PHASE A STUDIES FOR SELECTED MISSION CONCEPTS(critical technologies pre-developments)
• 2001-2005: “USER CONSULTATION PROCESS” & PRE-PHASE A STUDIES
– 2004 - 2005 PHASE 2: PRE-PHASE A STUDIES, EVALUATION/PRE-SELECTION OF MISSION CONCEPTS
– 2001 - 2003: PHASE 1: HIGH LEVEL USER NEEDS & PRIORITIES AGREED, PREPARATION OF PRE-PHASE A STUDIES
Planning: Meteosat Third Generation (MTG)
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
Pre-Phase A System Architecture studies
Mid-Term Review (MTR)
Mar/Apr 20052nd MTG UCW Locarno
Mission Architecture Review (MAR)Sep/Oct 2005
KO October 2004
Programmatic Aspects Wrap-up System Update
Planning &ROM estimates
CriticalAreas
Close-out:Nov/Dec 2005
Detailed Analysis and Definition
ObservationPayload
Non Observ.Payload
Spacecraft& Launcher
Mission &Operations
G/S conceptData Flow
Architecture Consolidation and Justification
Requirements and Concepts
Requirements &Trade-off tree
Candidate ConceptsCharacterisation
Selection mission / systemArchitecture (s) concepts
2 Parallel Studies – 14 months durationALCATEL ALENIA SPACE EADS ASTRIUM GmbH
v
v
In progress
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MTG Observation Missions Requirements
FDHSI HRFI LI IRS UVS
BRC
λ
Δx
Full Disk: 10 min6x18 deg: 10/3 min
6x18 deg: 5 min6x6 deg: 5/3 min
16 deg shifted N10-3 sec
Full Disk: 30 min6x18 deg: 10 min
18x6 deg: 30 min6x6 deg: 10 min
15 core channels in the range 0.4-13.9 μmFD-OPT1: 4 channelsO2 absorption band (0.755-0.775 μm)FD-OPT-2: 4 channels CO2absorption band (13.03-14.07 μm)FD-OPT-3: 2 channels Aerosol/true colour imagery (0.44--0.55 μm)
5 channels in the range 0.6-11.2 μm
1 channel in the neutral Oxygen line (774.4 nm) bandwidth: 0.34 nm
9 bands in the range 4-15 μm. Synchronous imaging (sub-pixel characterisation): 1 VIS channel (0.5 km Δx) + 2 IR channels (1 km Δx)
10 bands in the range 290-777 nm. Polarisation measurements along two orthogonal planes for two bands in the range 310-335 nm or polarisation insensitive instrument (TBC). 3 bands in the O2 absorption band (752.5-777.5 nm)
VNIR-SWIR: 1 kmMWIR-TIR: 2 km
VNIR-SWIR: 0.5 kmMWIR-TIR: 1 km
10 km (over Europe)
4-8.3 μm: 3 km8.3-15 μm: 6 km
6 km
λ: spectral range/channels; Δx: spatial resolution at sub-satellite point (SSP); BRC: basic repeat cycle
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
From MOP to MTG
MTGMSG
1977 20152002
UVScoordinated with GMES Sentinel 4
5 observation missions:- HRFI: 5 channels- FDHSI: 22 channels- Lightning Imager- Infra-Red Sounder-3-axis stabilised satellite(s)
1 observation mission:-MVIRI: 3 channels-Spinning satellite 2 observation missions:
- SEVIRI: 12 channels- GERB- Spinning satellite
MOP
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
• The following concept was selected for detailed analysis:
Implementation of the imaging mission through the combined imager
• 1 imager instead of 2 on each satellite
• Simpler satellite configuration, reduced launch mass
• Significant cost savings (space segment/launcher)
Payload accommodation (Combined Imager, IRS, LI) on multiple satellites
•Flexible system deployment and development approach
• Decoupling of higher risk sounding mission from the higher priority imaging mission
• Reduced complexity of key platform subsystems IRS
Combined Imager
LI
HRFI FDHSI
Combined Imager
System Concept Selection at MTR
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Combined Imager
Baseplate
Earth face
N/S Face
E/W Face
Entry Baffle
Calibration Slot•10 min. FD coverage (3.3 min LAC)•15 core channels (22 with options)• ≈ 250 Kg• ≈ 250 W• Data Rate ≈ 50 Mbs (all options)• Active cooling (driven by LW channels)• 2 axes scan mechanism
Development Issues
• Detector arrays for the IR (LWIR) channels• Scan Mechanism (complexity, lifetime)• Cryo-coolers• Optical elements (coatings, filters)• Solar inputs effects (thermo-elastic deformations -> mission availability)
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Infrared Sounder
opd = time
TelescopeOptics
Michelsoninterferometer
Imagingoptics
Collimatingoptics
Detectorarray
Mecanism
Spectralsample λ0
Wavelengthλ0
Slit
Wavelengthλ = λ0
Dispersivesystem
Detectorarray
Band-passfilter
Cold stop
Two instrument concepts analysed. Final selection still open
Fourier Transform Spectrometer (FTS) Dispersive Spectrometer (DS)
Step and Stare “scanning” Pushbroom scanning in EW direction256 x 256 FPA at 6.5 sec dwell time Array size depends on band
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Infrared Sounder
Baseplate
Earth face
N/S Face
E/W Face
DS FTS• ≈ 280-320 Kg 280-330 Kg• ≈ 350 W 350-480 W(1)
• ≈ 400 Mbps ≈ 3 Gbps (2)
• Active cooling (driven by LW channels)• 2 axes scan mechanism
(1) Depending on level of data processing and implementation (instrument/DHSS)(2) Raw Instrument data rate before processing
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Infrared Sounder
Development Issues
• LWIR detectors array requires major pre-development (in different direction for the DS and the FTS)• interferometer design (FTS), gratings (DS)• Processing loads (FTS)• Cryo-coolers • Scan Mechanism (but driven by the combined imager)• Solar inputs effects (thermo-elastic deformations -> mission availability)
Preliminary Concept Assessment
• The engineering challenges are different between the DS and FTS concepts but of the same level of complexity at instrument level;• The FPA array/cooler technologies require development for both DS and FTS but in different directions• DS shows better radiometric performances for most bands whereas FTS seems better for LWIR bands;• Spectral calibration requirements more constraining for the DS concept• FTS instrument is more difficult to accommodate (data rate, pointing stability)
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Lightning Imager
radiator
baffle
telescope
prox. el.
bench
radiator
baffle
telescope
prox. el.
bench
• 4 cameras 16 deg coverage (shifted N)• 160 mm aperture• ≈ 100 Kg• ≈ 60-100 W• Data Rate ≈ 100 kbps
Development Issues
• Not a “small” instrument, current concept based on reduced DE performances (DE>90% from 6 mJ.m-2.sr-1 )• APS detector with smart pixel (extraction of lightning flash events) and narrow band filter (160 mm) are technologies to be developed• Lightning flash models (at signal level) are essential for assessing the spatial and temporal coupling of the flash event with the detection process. Different assumptions have a significant impact on the instrument sizing
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Space Segment
Combined Imager
LightningImager
UHF patch
L-band antenna
North or
South
Earth
Xs
Zs
Ys
Xs
Zs
Ys
IR-Sounder
X-BandAntenna
S-BandAntenna
XNadirLaunch Direction
DeepSpace
Y
Z
Main Body
Imaging Satellite (MTG-I) Sounding Satellite (MTG-S)
• Payload accommodation on two satellites: MTG-I (CI, LI, DCS) and MTG-S (IRS DS/FTS)• Common S/C bus except communication payload and Data Handling, heritage from Telecom buses• Launch mass: 3+ tons• Power: 1+ kW• PDT: L/X band for MTG-I, X/Ku band for MTG-S (on-board processing, DS/FTS selection)• Launchers: Soyuz (3t), Ariane 5• S band TT&C
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Space Segment
MTG Satellite concept – Main Features
• AOCS concept heritage from recent telecom development with improved sensor performances
• CPS for orbit acquisition and station keeping, EPS options for wheels unloading (and possibly N/S S/K)
• Asymmetric solar wing and 2-yearly yaw flip (instrument thermal control)
• High thermo-mechanical stability to minimise thermo-elastic distortion in orbit and particularly at eclipse transitions
• Micro-vibration impacts (Reaction wheels, active coolers) on observing missions performance to be analysed in details in the coming development phases
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – System deployment assumptions
50
10 15
MTG-I satelliteMTG-S satellite
1-year commissioning
Earliest date
Latest date
8 satellites (2 MTG-I nominal + 2 MTG-I back-up; 2 MTG-S nominal + 2 MTG-S back-up)to cover the required mission lifetime (15 years + 5 years extension)
Phased deployment approach (first MTG-S two years after the first MTG-I) to cope withthe critical IRS development schedule and to provide programmatic flexibility
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
Real time users
Non real time users
Meteo dataproviders
GOS partners
Primary ground station- Tracking, Telemetry & Command (TTC)- Observation and DCP data acquisition- Level 0 processing- Back-up control centre
Back-up ground station(s)
ArchiveAnd on-line user services
SAF’s- Level 2 processing
Terrestial network
Imager satelliteSounder satellite
0.6 to 1 deg
TT&C (S-band)
ITM (L-band)
ITM (X-band)TT&C (S-band)
Control Center
Data Processing & Quality Control
Facility
Data Dissemination Facility
Core facility (Darmstadt)
Real time users
Non real time users
Meteo dataproviders
GOS partners
Primary ground station- Tracking, Telemetry & Command (TTC)- Observation and DCP data acquisition- Level 0 processing- Back-up control centre
Back-up ground station(s)
ArchiveAnd on-line user services
SAF’s- Level 2 processing
Terrestial network
Terrestial network
Imager satelliteSounder satellite
0.6 to 1 deg
TT&C (S-band)
ITM (L-band)
ITM (X-band)TT&C (S-band)
Control Center
Data Processing & Quality Control
Facility
Data Dissemination Facility
Core facility (Darmstadt)
MAR status – Ground Segment
Nationaler Nutzerworkshop “Operationelle Satellitensysteme der Erdüberwachung”7-9 November 2005, Tagungsstätte Walberberg
MAR status – Conclusion
• The pre-phase A studies have identified suitable instrument/system concepts for the implementation of the MTG system, based on the present definition of user/mission requirements
• The mission is ambitious and demanding, major technology pre-developments are required (partially already initiated by ESA)
• Phased system development and deployment approach will mitigate the risk in compliance with the MTG mission priorities
• Programmatic inputs to be analysed soon. Affordability consideration will probably drive the consolidation of mission/system requirements applicable to the coming feasibility studies at phase A level
• The operational deployment of the MTG imagery mission by 2015 is judged feasible but challenging. MTG technical and programmatic requirements to be consolidated soon in line with the objective of starting Phase A and major pre-developments by 2006