Presentation is loading. Please wait.

Presentation is loading. Please wait.

EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 1 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding.

Published byJessie Adams Modified over 8 years ago

Similar presentations

Presentation on theme: "EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 1 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding."— Presentation transcript:

1 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 1 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

2 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 2 From MOP to MTG MTG MSG MOP 1977 2015 2002 UVS coordinated 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

3 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 3 From MOP to MTG 10 x 100 x 2 x 8 x 4 x MVIRI SEVIRI HRFI FDHSI IRS LI MTG Mission Objectives: Ambitions in line with expected future space systems evolution A quantum leap forward requiring significant development and programmatic efforts compared to the previous Meteosat systems Payload Budgets Evolution (Current Estimate)

4 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 4 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

5 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 5 MTG System Elements From MTG Mission needs to MTG System Elements

6 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 6 MTG Candidate Space Segment Concepts Instrument concepts derived from current observation mission needs require 3-axis stabilised platform. Heritage from 3-axis GEO telecom platforms not fully satisfactory for demanding EO missions Enhancements are needed MOP MSG MTG

7 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 7 MTG Candidate Space Segment Concepts Several space segment concepts considered during the trade off: 1. 4 satellites supporting one instrument each (would require up to 8 satellites - nominal + back-up - in orbit. Satellite launch mass not compatible with any low cost launcher) -> option discarded 2. 1 satellite supporting the full payload complement 3. 2 satellites supporting the payload complement Payload options: two separate imagers (HRFI+FDHSI) or single combined imager 1 2 3

8 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 8 Space Segment Concepts – Single Satellite Deployable Solar Array Launch Mass: ≈ 6000 kg Power: ≈ 2.6 kW Launchers: Ariane 5 (Atlas V5/ Delta 4) Raw Data Rate: > 350 Mbps Chemical Propulsion system Electric propulsion could be considered for station keeping and RW off-loading Body Mounted Solar Array Launch Mass: ≈ 7000 kg Power/raw data rate as per Deployable SA wing concept Reduced solar pressure torques No disturbances from solar array rotation Launch mass penalty of about 1 ton Critical configuration

9 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 9 Space Segment Concepts – Single Satellite Lifetime and mission availability requirements over 15 (+5) yrs require 2 (TBC) nominal satellites + 2 (TBC)hot back-up in orbit 05 10 15

10 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 10 A total of 8 imagers (4 HRFI + 4 FDHSI) would be required for the two imagers configuration A single combined imager fulfilling the HRFI/FDHSI mission need in a exclusive way will reduce the imagers complement by half and reduce the launch mass and complexity of the satellites, as well as possibly the launch cost. Estimated savings: 20-30 % on space segment/launcher costs Space Segment Concepts – Single Satellite FDHSI HRFI IRS LI FDHSI HRFI IRS LI FDHSI HRFI IRS LI FDHSI HRFI IRS LI Operational Spare HRFI + FDHSI COMBINED IMAGER Operational Spare C-Imager IRS LI C-Imager IRS LI C-Imager IRS LI C-Imager IRS LI Launch Mass: ≈ 6 tons Power: ≈ 2.6 kW Launch Mass: ≈ 5 tons Power: ≈ 2.2 kW 8 imagers: 4 HRFI + 4 FHSI 4 Combined Imagers

11 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 11 Space Segment Concepts – Two Satellites FDHSI HRFI Star Trackers UHF antenna X-band antenna North or South Earth LI IRS North or South Earth UHF antenna Ka-band antenna Star Trackers IRS radiator sunshield Baseline Launcher: Soyuz Back-up: Proton K Two imagers (HRFI + FDHSI) configuration

12 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 12 Space Segment Concepts – Two Satellites LI Combined imager North or South Earth UHF antenna X-band antenna 400 N thruster IRS North or South Earth UHF antenna Ka-band antenna 400 N thruster IRS radiator sunshield Baseline Launcher: Soyuz Back-up: Proton K Combined imager configuration

13 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 13 Space Segment Concepts – Two Satellites 05 10 15 Sat 1 Sat 2 Lifetime and mission availability requirements over 15 (+5) yrs require 4 (TBC) nominal satellites + 4 (TBC)hot back-up in orbit A total of 8 imagers (4 HRFI + 4 FDHSI) would be required for the two imagers configuration. A single combined imager fulfilling the HRFI/FDHSI mission needs in an exclusive way will reduce the imagers complement by half and reduce the launch mass and complexity of the satellites, as well as possibly the launch cost. Estimated savings: 20-30 % on space segment/launcher costs

14 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 14 Space Segment Concepts – Mission Communication Raw data rate from observation payload in excess of 300 Mbps => A factor 100 growth compared to MSG Communication payload architecture and selection of downlink frequencies depend on selected space segment concepts and apportionment of observation payload to the platforms Drivers: InfraRed Sounding Mission data rate (>200 Mbps depending on instrument concept – dispersive vs. FTS – and level of on-board processing/compression techniques) Even considering high order modulation schemes improving the bandwidth efficiency, L band downlink capacity would be limited to 50-60 Mbps => higher frequency bands (X, Ka, Ku) Atmospheric attenuation effects at high frequencies and impact on the link availability may require considering adaptive data rate solutions based on the priorities of mission data => impact on the overall operational availability

15 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 15 Ground Segment and Data Dissemination The ground segment design is impacted by: High data volumes (100 X MSG) associated to near real time timeliness (=> processing) requirements Data dissemination services to full scale real time users (National Met services, regional processing centers), data volumes estimates in the order of 200 Mbps after lossless compression. Realistic implementation scenarios based on dedicated terrestrial communication infrastructures Data dissemination to local real time users (subset of full MTG data set) through commercial services and low cost user terminals requires the definition of realistic dissemination scenarios to bring the data rate down to reasonable figures (20-30 Mbps) compatible with commercial dissemination system capabilities at reasonable costs in the 2015 time frame.

16 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 16 Ground Segment and Data Dissemination Ground Segment architecture elements Terrestrial multi Gbps network (GEANT 2004)

17 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 17 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

18 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 18 Critical requirements and system drivers The need date for ensuring the continuity of the operational meteorological service in geostationary orbit with high availability is 2015 => short development time for the full mission System complexity significantly higher than MSG Observation payload concepts require development of new technologies (detectors, active coolers) to meet the performance requirements with high reliability and present different development risks Programmatic requirements advise a flexible system deployment strategy tailored to the observation mission priorities The mission availability required for an operational service with the specified availability will be challenging to achieve with a 3-axis stabilised platform (lessons learned from GOES, intrinsic concept limitation, limited heritage from previous Meteosat systems) System pointing accuracy and stability (from spatial resolution and geometric accuracy requirements), thermal control (active cooling, limitations due to 3-axis platform stabilisation) and data handling (high raw data rate and on-board processing) are the major drivers at satellite level

19 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 19 Full payload complement accommodation on a single satellite is challenging in terms of: Overall platform configuration Availability of radiative surfaces Disturbances introduced by instruments (combined imager, infrared sounder) with different scanning laws impacting the satellite pointing performances Complexity of key subsystems (thermal control, AOCS, data handling, mission communication payload) AIT complexity and risks In addition: No flexible system deployment strategy Launch failure implies total mission loss Development risks (beside platform specific risks) driven by the most critical payload element, the IRS, which has lower priority than the imaging mission Space segment concept – single satellite

20 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 20 Space segment concept – two satellites IRS Combined Imager LI Simplified satellite configuration, LI accommodation not critical Decoupling of the IRS (second mission priority but higher development and system level criticality, e.g. pointing stability, thermal control, data handling ) Flexible and phased development and deployment (as well as financial) strategies are possible, in accordance with the programmatic requirements and the observing mission priorities Design drivers on key subsystems are kept within reasonable levels Operational system complexity is adversely affected (2 operational + 2 stand-by satellites)

21 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 21 Concept Selection The following concept is selected for detailed analysis: Implementation of the imaging mission through the combined imager 4 imagers instead of 8 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 HRFIFDHSI Combined Imager

22 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 22 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

23 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 23 Objectives and Guidelines - I Due to complexity and detailed definition of the observing mission requirements, the focus in the first part of the study has been given to: Mission Requirement Analysis Candidate Instrument Concept Definition For the second part (up to the Mission Architecture Review – MAR): Focus on system aspects and other elements of the mission architecture Consolidation of instrument concepts Definition of interface requirements Identification of critical technologies Consolidation of system performance, operability and availability as required by the operational nature of the system

24 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 24 Objectives and Guidelines - II Preliminary assessment of system complexity and critical technologies: Mission requirement can only be fulfilled with the implementation of the observation payload on 3-axis stabilised platform Limited heritage from previous generation of Meteosat Systems Critical Technologies detectors, active coolers (actions initiated) Platform thermo-elastic stability, micro-vibrations, AOCS, thermal control Operational deployment of the complete MTG system with the current mission objectives by 2015 is judged extremely critical, alternative deployment strategies will be studied Activities in the frame of the second part of the study shall include the evaluation of simpler mission concepts aimed at ensuring the continuity of the MSG imaging mission (with enhanced requirements) by 2015 with reasonable development and programmatic risks

25 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 25 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding Mission (IRS) Lightning Imagery Mission (LI) UV/Visible Sounding Mission Summary MTG System Concepts From MOP to MTG: Mission Evolution Candidate System Concepts Concept Evaluation and Selection Objectives and Guidelines for the second part of the study Conclusion

26 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 26 Conclusion - I The two MTG system studies at pre-phase A level are progressing according to schedule Mid-Term Review completed in March 2005 Objectives for the first part of the study have been achieved: Definition of candidate payload and system concepts Simplified concepts at payload level (combined imager) and risk reduction at system level (multiple satellite concepts) proposed and selected for detailed analysis in the second part of the study

27 EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 27 Conclusion - II Full MTG System deployment by 2015 will require significant development and financial efforts Phased system development and deployment approach in compliance with the MTG mission priorities will mitigate risks while satisfying the user requirements Further focusing on simplified mission concepts to ensure continuity of the imaging mission in the Post-MSG era (2015) with reduced development risks and affordable programmatic constraints Identified options shall be analysed in details at pre-feasibility level in the second part of the study (concept consolidation and preliminary design, performance evaluation, ROM cost estimates and required technology developments) Study results and parallel evolution of programmatic and financial requirements/constraints will allow EUMETSAT and ESA to select at the Mission Definition Review (MDR) the most appropriate mission concepts to be analysed at feasibility level in the Phase A system studies (2006-2007)

Download ppt "EUMETSAT 2 nd MTG User Consultation Workshop Locarno, 13-15 April 2005 1 Introduction Observation Payload Imagery Missions (HRFI and FDHSI) Infra-Red Sounding."

Similar presentations

© GEO Secretariat Virtual Constellations..new planning process which takes account of international users and their requirements from the outset of satellite.

© GEO Secretariat Virtual Constellations..new planning process which takes account of international users and their requirements from the outset of satellite.
GEOSS Workshop 20 September 2013 ESRIN P. Bargellini, Ground Segment and Mission Operations Department, Earth Observation Programmes Directorate, European.

GEOSS Workshop 20 September 2013 ESRIN P. Bargellini, Ground Segment and Mission Operations Department, Earth Observation Programmes Directorate, European.
World Meteorological Organization Working together in weather, climate and water WMO OMM WMO www.wmo.int/sat Barbara J. Ryan Director, WMO Space Programme.

World Meteorological Organization Working together in weather, climate and water WMO OMM WMO Barbara J. Ryan Director, WMO Space Programme.
SATELLITE DATA LINK SYSTEM (SDLS)

SATELLITE DATA LINK SYSTEM (SDLS)
Israeli Universal Spacecraft Bus Characteristics and Design Trade-Offs

Israeli Universal Spacecraft Bus Characteristics and Design Trade-Offs
E arth Observation Information Day, Bruxelles 3rd October 2000 ESA EARTH WATCH STRATEGY OUTLOOKS L. Marelli Head of EO Earth Watch strategy.

E arth Observation Information Day, Bruxelles 3rd October 2000 ESA EARTH WATCH STRATEGY OUTLOOKS L. Marelli Head of EO Earth Watch strategy.
Lightning Imager and its Level 2 products Jochen Grandell Remote Sensing and Products Division.

Lightning Imager and its Level 2 products Jochen Grandell Remote Sensing and Products Division.
Geospace Electrodynamic Connections (GEC) Mission The GEC mission has been in the formulation phase as part of NASA’s Solar Terrestrial Probe program for.

Geospace Electrodynamic Connections (GEC) Mission The GEC mission has been in the formulation phase as part of NASA’s Solar Terrestrial Probe program for.
Systems Analysis and Design Feasibility Study. Introduction The Feasibility Study is the preliminary study that determines whether a proposed systems.

Systems Analysis and Design Feasibility Study. Introduction The Feasibility Study is the preliminary study that determines whether a proposed systems.
07/07/2005 Coupling with PF2012: No existing PF “as is” able to accommodate Karin On going study in France to develop a new generation of PF product line.

07/07/2005 Coupling with PF2012: No existing PF “as is” able to accommodate Karin On going study in France to develop a new generation of PF product line.
PLATO Phase A/B1 Status TOU Meeting Catania 28 Feb 2011 PLAnetary Transits and Oscillation of stars.

PLATO Phase A/B1 Status TOU Meeting Catania 28 Feb 2011 PLAnetary Transits and Oscillation of stars.
1 ESAIL proof of concept mission Juha-Pekka Luntama Pekka Janhunen Petri Toivanen.

1 ESAIL proof of concept mission Juha-Pekka Luntama Pekka Janhunen Petri Toivanen.
Polar Highly Elliptical / Molniya Orbit Science (PHEMOS) Mission Phase 0/A Studies Mid-Term Review Meetings January 12-14th, 2011.

Polar Highly Elliptical / Molniya Orbit Science (PHEMOS) Mission Phase 0/A Studies Mid-Term Review Meetings January 12-14th, 2011.
ISIS Turnkey Missions ISIS designs, manufactures, launches and operates affordable, capable, nanosatellites ISIS provides turnkey missions for institutional,

ISIS Turnkey Missions ISIS designs, manufactures, launches and operates affordable, capable, nanosatellites ISIS provides turnkey missions for institutional,
GALILEO INTERIM SUPPORT STRUCTURE EUROPEAN COMMISSION International Civil Aviation Organization GALILEO CAR/SAM ATN/GNSS Seminar Varadero, Cuba, 6 to 9.

GALILEO INTERIM SUPPORT STRUCTURE EUROPEAN COMMISSION International Civil Aviation Organization GALILEO CAR/SAM ATN/GNSS Seminar Varadero, Cuba, 6 to 9.
14/06/20151 MORE Requirements seen from ESA Pedro Pablos 1 st MORE Team Meeting 27 Febrero 2007.

14/06/20151 MORE Requirements seen from ESA Pedro Pablos 1 st MORE Team Meeting 27 Febrero 2007.
EEE440 Modern Communication Systems Satellite Systems.

EEE440 Modern Communication Systems Satellite Systems.
VENUS (Vegetation and Environment New µ-Spacecraft) A demonstration space mission dedicated to land surface environment (Vegetation and Environment New.

VENUS (Vegetation and Environment New µ-Spacecraft) A demonstration space mission dedicated to land surface environment (Vegetation and Environment New.
CAPACITY Final Presentation, 2 June 2005, ESTEC Operational Atmospheric Chemistry Monitoring Missions (“CAPACITY”) Final Presentation ESA-ESTEC, Noordwijk.

CAPACITY Final Presentation, 2 June 2005, ESTEC Operational Atmospheric Chemistry Monitoring Missions (“CAPACITY”) Final Presentation ESA-ESTEC, Noordwijk.
The Pursuit for Efficient S/C Design The Stanford Small Sat Challenge: –Learn system engineering processes –Design, build, test, and fly a CubeSat project.

The Pursuit for Efficient S/C Design The Stanford Small Sat Challenge: –Learn system engineering processes –Design, build, test, and fly a CubeSat project.

Similar presentations

Ads by Google