Status of Meteosat Third Generation (MTG) Pre-Phase A ... · Nationaler Nutzerworkshop...

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



• 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)


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


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


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


• 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


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)


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



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



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)


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


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


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


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


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


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

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Status of Meteosat Third Generation (MTG) Pre-Phase A ... · Nationaler Nutzerworkshop...

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