Optical technologies in ESA programmes - Congrex

Optical technologies in 

ESA programmes 

Roland Meynart 

Earth Observation Directorate, Instrument Pre-Development Division 

With the cooperation of Nicolas Rando (Science and Exploration Directorate) 

and my colleagues of the Earth Observation and Technical Directorates 

International Conference on Space Optics, �ό�� 

ESA UNCLASSIFIED – For Official Use 

2010

What is space optics? 

1. 

2. 

3. 

What is optics? 

a. 

From �-rays to mm-wave 

– 

– 

What is it good for ? 

a. 

b. 

c. 

d. 

e. 

f. 

About �=100 GHz (quasi-optics !) 

Practically (here) � 

Earth Observation 

Space Science 

Exploration 

Microgravity research 

Communications 

Spacecraft avionics 

Focus of this talk on large systems 

Optics in ESA programmes | Roland Meynart | ICSO �ό�� 2010 | 05 October 2010 | Earth Observation | Slide 2 

≈ 

100-200 �m

Payload: What do we need ? 

Example: Planetary imaging spectrometer 

Satellite motion 

Re-imaging 

lens 

x 

2D array detector 

Dispersing element 

Collimator 

Telescope 

Ground swath 


� 

Slit 

Baffle

– 

Optics for Space (1) 

Not new of course, started with 

a. 

ground-based astronomy and astrometry 

Optics in ESA programmes | Roland Meynart | ICSO �ό�� 2010 | 05 October 2010 | Earth Observation | Slide 4

– 

Optics for Space (2) 

Not new of course, started with 

b. 

Accuracy ≈ 5-10 arcsec 

Astrometry for navigation 


© National Maritime 

Museum, Greenwich

A typical (almost) complete space system 

The ultimate astrometry mission: GAIA 

Final “catalogue” accuracy: 300 microarcsec 

It does astrometry, photometry and spectroscopy 


GAIA (2) 

1. 

High-stability structures – Advanced materials 


2. 

3. 

4. 

5. 

GAIA (3) 

Large detector array of arrays (106!), with 

advanced functionality 

Large high-accuracy mirrors 

Dispersive spectrometer 

Thermal control (shade!) 

What’s missing ? 


The ESA Science Programme 

“Cosmic Vision” 


The Cosmic vision themes (1) 








Cosmic Vision Implementation 

1. 

2. 

3. 

4. 

5. 

Space Science Programme 

a. 

b. 

c. 

Existing missions 

– 

includes 

Herschel, Planck lately 

Missions in development 

– 

LISA PF, Bepi 

Colombo, GAIA, JWST 

New MediumandLargecandidate missions in “Cosmic 

Vision 2015-2025” 

Space Sciences missions “enjoys” 

long preparation efforts 

ESA funds/develops space infrastructure (satellite, telescope) 

Instruments are generally provided by Institutes, funded by Member 

States, with few exceptions: 

a. 

GAIA (no instrument �) 

b. NIRSPEC (JWST) 

Cooperation with NASA traditional 


Cosmic Vision schedule 


Bepi Colombo (1) 

1. 

2. 

3. 

Just like a Earth Observation Mission, but a bit more difficult 

The problem is not just to get there but also to survive 

But we know much less on Mercury than on the Earth, so 

instruments are “easy” 


BepiColombo (2) 

Spacecraft 

Mercury 

Planetary 

Orbiter (MPO) 

Mercury 

Magnetospheric 

Orbiter (MMO) 

Stabilisation 3-axis stabilised 15-rpm spin-stabilised 

Orientation Nadir Spin axis at 90° to Sun 

Spacecraft Mass 520 kg 250 kg 

Payload Mass 60 kg 47 kg 

Power 600 W 325 W 

TM band X/Ka-band X-band 

Deployment 400 × 1508 km 400 × 11 824 km 

Operational lifetime > 1 year > 1 year 

Data volume 1550 Gb/year 160 Gb/year 

Equivalent average data rate 50 kb/s 5 kb/s 

Antenna High-temperature resistant 1.0 m 

X/Ka-band high-gain steerable 

antenna 

Thrusters Gridded ion thrusters 


0.8 m X-band phased array highgain 

antenna 

Other equipment high temperature resistant thermal protection, solar arrays

BepiColombo (3): some instruments 

BELA 

– 20 cm lightweight telescope 

– High sensitive (low noise) APD detector 

– 50mJ, 3ns diode pumped Nd:YAG laser, 10Hz 

nominal repetition 

MERTIS 

– 10 cm TMA telescope 

– Offner spectrometer (7-14 �m) Uncooled 

array 

– Thermoelectric array (7-40 �m) 


bolometer

JWST – NIRSPEC (1) 


Camera TMA 

JWST – NIRSPEC (2) 

Collimator TMA 

Coupling Optics (with 

Pick-off mirror 

underneath) 

Filter Wheel 

Micro Shutter 

Array 

Focal Plane 

Integral 

Assembly Fold Field Unit Calibration 

Mirror 

Assembly 

Re-focus 

Mechanism 

Calibration 

Mirror 2 

FORE Optics 

TMA 

Calibration 

Mirror 1 


JWST – NIRSPEC (3): detectors and 

micro-shutters 


COSMIC VISION 2015-2025 

Successive down-selection of Land M-class missions 


COSMIC VISION 2015-2025 


IXO – International X-ray Observatory 


- 

- 

� 

IXO summary 

New generation x-ray observatory (3.5 m2 at 1.5 keV, 0.65 m2 6.5 keV). 

at 

Agreement by ESA, JAXA and NASA as framework for all activities: 

• 

• 

• 

• 

A single large X-ray mirror assembly compatible with both 

pore optics and slumped glass technology. 

An extensible optical bench to reach F = 20 to 25m, plus 

ways to maximise Aeff above 6 keV. 

Instruments include a wide field imager (WFI), Hard x-ray 

Camera (HXI), a non-dispersive imaging spectrometer 

(XMS), an X-ray grating spectrometer (XGS), High Time 

Resolution Spectrometer (HTRS), X-ray Polarimeter (XPOL). 

IXO concept compatible with Ariane 

5 and Atlas V 551 

IXO concept input to US decadal survey and ESA Cosmic Vision 

selection process 


- 

- 

- 

- 

Instruments assessment studies 

Request for Declaration of Intents (DOI) released by ESA in 2009. 

7 DOI’s were received from corresponding instrument consortia: 

• 

• 

• 

• 

• 

• 

• 

XMS – 

WFI – 

HTRS – 

HXI – 

XPOL – 

SRON 

MPE 

OP-XGS – 

CESR/CNES 

JAXA/ISAS/CEA 

INFN 

OU 

Si-μcalorimeters – 

CEA 

7 studies have been kicked-off (CAT-XGS under discussion with 

MIT/NASA). 

Assessment activities in parallel with system level studies. 


Critical areas (ESA and national) 


OPTICS: 

1. 

ESA has selected the Silicon Pore Optics as the 

baseline mirror technology in its IXO development plan 

for 2008-2012 (req. HEW < 5 arcsec at 1.25 keV). 

2. Encouraging results from Silicon Pore X-ray Optics: 

Single reflection HEW = 7 arcsec obtained from stack of 10 

plates (out of 45). 

CRYO-CHAIN: 

1. Maxi compressor (advanced linear compressor for e.g. 

10K cooler) TRP activity is running with Astrium & RAL 

since 2 years, 1 more year to go. 

2. 10K Stirling cooler (linked to previous activity) is running 

with Astrium & RAL since 2 years, 1 year to go. 

3. 

IXO technology - ESA funded 

The 50mK cooler development activity with CEA to 

develop sorption/ADR cooler combination is running since 

Jan 2008 for a 24 months duration. 


LISA – Laser Interferometer Space Antenna 


1. 

• 

• 

• 

• 

2. 

– 

LISA - Overview 

ESA/NASA collaboration. 

Measurement of gravitational wave using laser interferometry. 

Constellation of 3 spacecrafts separated by 5 million km. 

Interferometric measurements of variations in distance 

between couples of test masses at pico-metre level. 

LISA Pathfinder technology validation mission. 

Mission Formulation activities 

LISA recent activities dominated by support to the Astronomy and 

Astrophysics Decadal Survey (Astro2010) of the US National 

Academy of Sciences. 


1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

LISA – Critical areas 

Low-noise, high stability mechanisms (point-ahead and optical 

articulation). 

Highly stable materials for telescope assembly (CFRP, 

zerodur, inserts …). 

Low-noise electronic components for GRS front-end 

electronics (voltage references ..). 

Light sources for charge management discharge (LED’s, laser 

diodes …). 

Metrology system. 

High-power laser system (1-2 W EOL, redundant) 

Out-gassing & contamination issues. 

Micro-propulsion (lifetime characterization). 


LAPLACE 


LAPLACE 

1. 

2. 

3. 

4. 

5. 

Joint NASA-ESA outer planet mission to Jovian system 

Two spacecraft to perform coordinated observation of Jovian 

satellites (Callisto, Ganymede, Europa) and Jupiter’s magnetosphere, 

atmosphere and interior. 

Jupiter Ganymede Orbiter (JGO): ESA 

Jupiter Europa 

Oribiter 

(JEO): NASA 

Science instrumentation shared between NASA and ESA Member 

States 


LAPLACE (2) JGO Model Payload 


LAPLACE JGO: critical areas 


EUCLID 


Euclid - Mission overview 

‘Dark energy’ study via Weak Lensing and BAO techniques. 

VIS/NIR imaging survey, NIR spectroscopic survey. 

Observe 20.000 deg2 of extragalactic sky at galactic lat |b| ≥ 

1. 

2. 

3. 

4. 

5. 

~1.2m dia. Telesc. 


30 o 

Step & stare with instantaneous fields of about 0.5 × 1 deg2 . Wide 

survey requires about 4 yr. 

VIS and NIP with co aligned 1.0° x 0.5° field, 0.1 arcsec VIS pixel 

(36 CCDs, 4k x 4k). NIP (18 IR detectors). 

NIS channel – baseline as slit-less, 1.0° x 0.5° field, 0.5 as/px. 

Hawaii2RG IR detectors with 2.5 �m cut-off (US).

1. 

2. 

3. 

4. 

Euclid - Critical areas 

Large area focal planes (VIS & NIR) – state of art + radiation 

resistance. 

Exceptional requirements on PSF stability and low ellipticity 

(0.1 arcsec). 

Step and stare sky scanning strategy – duty cycle efficiency 

and Line of Sight Stability. 

Very high data rate – K band required. 

Existing development activities: 

1. CCD radiation testing – Euclid mission dose and test the impact 

on Euclid specific performance and ops mode. 

2. DMD – prequalification activity. 

3. Dichroics and feed for ground stations in K-band. 

4. FGS CCD – system issue for faster readout than the science 

sensors. A fast ADC and readout controller is to be developed 

for wide range generic applications 

5. Cryo-lens material –Manufacturing of refractive IR components 

(optical components and mounts), integration in an optical 

chain, and testing to demonstrate the opto-mechanical 

performances in representative environment (cryogenic 

temperatures and vibration levels). 

6. Mirror CVD & polishing – needed for high quality optical 

performance (15nm rms surface) 


Euclid Technology – Nationally 

funded 

Preliminary list 

1. 

2. 

3. 

4. 

Visible Wavelength CCD Pre-Development – optimisation based on baseline 

e2v-CCD-203 

Cryo-mechanisms -rotation accuracy, filter and optical element dimensions and 

masses, operational schedules for exchange speed and total lifetime cycles. 

Design & manufacture of prototype grism- 1 to 2 micron range with constant 

resolving power 

Verify Teledyne Hawaii array image persistence and irradiation performance 

are consistent with EUCLID operational modes 


PLATO 


PLATO – Mission 

overview 

- To search for exo-planetary transits (occultations) in front of stars. 

- To characterize the parent stars via astero-seismology. 

- High time-resolution, high precision, and high duty-cycle visible photometry. 

- L2 - SF 2-1b LV (2146 kg) - Optics and detectors (CCD) at ~170K – 6yr. 

Concept 1 

• 

• 

• 

• 

• 

2-mirror optical design, 169 mm pupil / tel. 

12-telescopes with two simultaneously observed FoV (4 

groups of 3 tel.) 

Very large total FoV (~1800 deg² useful) allowing 

observing brighter stars. 

~0.15 m 2 collecting area per sub-field. 

Full FoV available with rotation every 6 months around the 

LoS. 

A group of 3 tel. 

Symmetry to 180 deg rotation 

every 6 months 


6 telescopes 

sighting FoV #1 

6 telescopes 

sighting FoV #2

Concept 2 

• 

• 

• 

• 

• 

PLATO – Mission overview (cont.) 

Dioptric system, 6 sph. lenses, 83 mm pupil 

54 refractive telescopes mounted individually on tilted base plate 

Total FoV ~625 deg 2 to see cool dwarfs at greater distance with 

required SNR 

0.3 m2 collecting area 

Circular FoV allows for monthly rotation around LoS with 

continuous observation 

concept3 


• 

• 

• 

• 

• 

Dioptric system with 6 lenses (2 aspherical), 115 mm 

pupil 

42 refractive telescopes mounted individually on stair 

case base plate 

Total FoV ~1800 deg2 in 4 groups of 10 tel. partially 

overlapping 

Needs quarterly rotation due to FPA configuration 

Grouping of telescopes gives access to large FoV

PLATO Technology – ESA funded 

Deployable Sunshield Demonstrator 

• 

• 

• 

Goal: Design and development of deployable sunshield 

demonstrator to be used on PLATO 

Requirement: Due to very large field-of-view of 

telescopes, Deployable Sunshield needed to avoid 

vignetting of telescope field-of-view 

Heritage: Based on GAIA deployable sunshield, Holddown 

and release mechanism (HDRM) is new 

development 

Strap 


PLATO TDP – Nationally funded 

Preliminary list 

CCD prototyping (All) 

• 

• 

Goal: Development of PLATO optimized high speed, high 

dynamic range CCD (specifications are concept dependant) 

Requirement: Due to multi-aperture approach, many CCDs 

need to be produced in short time frame 

Refractive telescope breadboard 

• 

• 

Goal: Bread-boarding of a 6 lens telescope, with large diameter 

lenses and operating at low working temperature 

Requirement: Due to 54 telescopes to be produced, heritage 

from a bread-board telescope is needed to validate lens 

mounting, barrel alignment and perform basic testing 


SPICA 


The SPICA mission 

SPICA = SPace IR telescope for Cosmology & Astrophysics. 

• 

• 

Formation of stars, galaxies, planets, exo-planet characterisation (5 - 210 um). 

Astronomical background limited performance, by means of a 5-6K, 3.5m diameter telescope. 

JAXA led mission: 

• Observatory at L2. Telescope at T=5-6K, �=3.5m M1, cryogens free. 

• Phase A study ongoing at JAXA – Launch by 2018, LV=H-IIB. 

• Model payload: 

• MIR (5-38µm) camera & spectrometer (JAXA). 

• MIR (5-27µm) coronograph (JAXA). 

• SAFARI (30-210µm) imaging spectrometer (Europe). 

• BLISS (sub-mm) spectrometer (US). 

Envisaged European contribution: 

• Mission of opportunity (large scientific return for < M class cost). 

• SPICA Telescope Assembly (STA) � 2x industrial study (ASF & TAS-F). 

• Ground station (4hr/day) � ESA assessment. 

• SpicA FAR-infrared Instrument (SAFARI). Nationally funded � consortium study. 


ASF 

TAS 

European contribution: STA 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

8. 

Diffraction limited performance at ��= 5 um. R-C designed. 

Total mass (including design margins) < 700 kg. 

Optical surfaces at T < 6K; heat load ~ 20 mW at 4.5K. 

All ceramic design (mirrors and support structure) selected by Astrium 

(SiC100) & TAS (HB-Cesic). 

M2 structure based on 4-leg design to meet COR req.ts. 

Need for dedicated Instrument Optical Bench confirmed. 

Focus and tip/tilt mechanism (at M2). 

STM + PFM. PFM delivery to JAXA by Q1-Q2/17. 

CRITICAL AREAS: 

1. 

2. 

Manufacturing and polishing of large size M1 (3.5m diameter). 

Focus, Tip & Tilt mechanism (M2 – operating at ~ 5K – environmental 

requirements). 


European contribution: SAFARI 

1. 

2. 

3. 

4. 

5. 

6. 

7. 

Cryogenic imaging spectrometer (FTS, 35 - 210 um). 

Herschel class instrument (c.f. SPIRE, PACS). 

Cold assembly < 50 kg (IOB). Warm electronics < 30 kg (SVM). 

Selection of detector technology impacts design (~ 6000 px: 

TES, KID, Si bolometers, Photo-cond.); planned by mid 2010). 

Phase A study conducted assuming adoption of TES. 

Additional internal cooler required by TES, KID and Si- 

Bolometer (Sorption Cooler + ADR � ~ 100 mK). 

PFM delivery to JAXA required by end 2015. 

CRITICAL AREAS: 

1. Detector array and read-out electronics development 

(competing: KID, TES, Si-Bolometers, Photoconductors � key 

decision by mid-2010). 

2. Internal cooler (~100 mK, SC+ADR, unless PC’s selected). 

3. FTS scanning mechanism (operating in cryo conditions). 

4. Constrained mass and cooling power resources. 

5. Compressed development schedule (FM by 2015). 


Back To The Earth 


ESA’s living Planet Programme 

ESA's Living Planet Programme 

comprises two main components: 

-a science and research element 

including Earth Explorer missions, 

-the Earth Watch element, 

delivering Earth observation data for 

operational services. It includes 

– meteorological missions with 

Eumetsat, 

– missions focusing on the 

environment and civil security 

under the GMES initiative. 


Since 

1977 

ESA EO development 

Earthnet: 

1990 2000 2010 2030 

METEOSAT 

M-1, 2, 3, 4, 5, 6, 7 

Access for European users to non-European missions: 

Landsat, SeaWifs, NOAA, JERS, MODIS, ALOS, Proba, Bird, Scisat... 

ERS-1, -2 

METEOSAT Second Generation 

MSG-1, -2, -3 

Earth 

Explorers 

ENVISAT 

Earth Watch 

METOP-1, -2, -3 

GOCE 

SMOS 

(Gravity and Ocean 

Circulation Explorer) 

(Gravity and Ocean Circulation Explorer) 

EE 7 

EE 8 

Sentinel 1 


Applications 

Services 


to initiate long term 

Sentinel 4/5 monitoring systems and 

Sentinel 5PC 

GMES in cooperation with EC 

services 


Meteo 

MTG 

in cooperation 

with EUMETSAT 

Science 

(Soil Moisture and 

Ocean Salinity) 

(Polar Ice 

Monitoring) 

ADM/Aeolus (Atmospheric 

Dynamics Mission) 

SWARM (Magnetic Mission) 

(Clouds, Aerosols & 

EarthCare Radiation Mission) 

CryoSat2 

to better understand 

the Earth 

System

In orbit: ESA Earth Observation 

missions 


� 

� 

� 

� 

Six missions in space 

More than 3000 projects 

worldwide use their data – 

increasing further 

More than 100 Terabyte of data 

per year 

30 partner missions

Earth data: thousands of scientific 

projects 

2002 

First images 

Prestige tanker 

oil slick 

Bam earthquake 

Ozone hole 2003 

Tectonic uplift 

(Andaman) 

B-15A 

iceberg 

Hurricane 

Katrina 

Chlorophyll 

concentration 

Arctic 2007 

L’Aquila 2009 

CO2 map 


Serving 3000 

scientific 

projects 

and 

many 

operational 

users (including 

GMES Services) 

2010

The Earth Explorer Missions 

SMOS 

2 Nov. 2009 

GOCE 

17 March 2009 

Cryosat 

8 April 2010 

SWARM 

ADM 

AEOLUS 


EE 8 

EE 7 

EARTH 

CARE

GOCE – the ESA Gravity Mission 

� In space since March 2009 

� Four measurement cycles of 

the Earth’s gravity field so far 

A unique mission: 

� First gradiometer in space 

� Very low orbit (255 km) 

� Active air drag control (ion engine) 


GOCE before launch 


SMOS – The ESA Water Mission 

In space since 2 November 2009 

Applications: 

First global observations of two key 

variables of the Earth’s water cycle 

� Improve models of global water 

cycle and global ocean currents 

� Improved management of water 

resources 


SMOS 


Light pollution on Earth 

Source: US DoD 


SMOS Radio-Frequency Interference 

1. 

2. 

3. 

March 2010 

Strong RFI sources can contaminate large areas of SMOS 

swath (several deg in latitude) 

Not only on land! 

Not only for SMOS 

August 2010 


CryoSat-2 – the ESA Ice Mission 

� monitoring precise changes in the 

thickness of the polar ice sheets and 

floating sea ice, up to latitudes of 

88° 

� Launch 8 April 2010 


SWARM: The ESA Magnetic Field Mission 


�� 

� 

Primary objectives 

– 

– 

– 

– 

Core dynamics, geodynamo processes, and 

core-mantle interaction 

lithospheric magnetisation 

3-D electrical conductivity of the mantle 

electric currents in magnetosphere and 

ionosphere 

Secondary objectives 

– Magnetic forcing of upper atmosphere 

– Magnetic signature related to ocean circulation 

• 

• 

• 

• 

• 

SWARM Constellation: 3 small satellites 

distributed in two orbits: 

1 satellite in 530-300 km altitude, 

2 satellites in 450-300 km altitude, 

Polar orbit Drifting local time 

Mass: 500 kg, Power: 220 W 

Launch Mid 2012

ADM (Atmospheric Dynamics Mission)-Aeolus 

The ESA Wind Mission 

• 

• 

• 

• 

• 

• 

�� 

to provide global observations of 

wind profiles from space 

�� to improve the quality of weather 

forecasting 

�� to enhance our understanding of 

atmospheric dynamics and climate 

processes 

Doppler wind lidar @ 355 nm 

Incoherent detection, molecular + 

aerosol scattering 

Single LOS, 35 deg roll 

Orbit 405 km, SSO dawn-dusk 

Mass: 1500 kg, 2300 W 

Launch (Vega): 2013 


Aeolus receiver 


Aeolus laser transmitter 


1. 

2. 

3. 

4. 

5. 

Highest power space laser developed 

so far 

Single-frequency, tunable 

Laser-induced damage improved 

with coating optimisation and partial 

pressurization (most critical in UV) 

Alignment stability is a challenge 

Continuous mode instead of burst 

mode ?

EarthCARE: The ESA-JAXA Cloud, 

Aerosols and Radiation Mission 

Main Objective 

Quantify impact of clouds and aerosols on radiation 

Payload 

• Lidar at 355nm 

• W-Band Doppler Radar 

• Multi-spectral imager 

• Broad-band radiometer 


Satellite 

• Polar sun-sync. orbit 

• 13:45-14:00 desc. node 

• 393 km mean altitude 

• 2 tons, 2.5 kW 

• Launch: Sep 2013 +

EarthCARE Overview 

Four instruments employed in synergy: 

2 active: ATLID lidar + CPR radar � vertical cloud/aerosol profiles 

2 passive: MSI imager + BBR radiometer � horizontal radiance fields 

BBR 


EarthCARE Satellite 

EarthCARE key mission parameters 

Launch date September 2013 

(under review) 

Lifetime 3 years (+1 yr 

consumables) 

Orbit type Sun synchronous 

Inclination 97� 

Attitude control 3 axis stabilized 

yaw steered 

Dry mass 1795 kg 

Fuel load 231 kg 

Solar array power (EOL) 5200 W 

Nominal power demand < 2700 W 


Cloud Profiling Radar 


Atmospheric Lidar (ATLID) 


Broad-Band Radiometer 


1. 

2. 

3. 

4. 

Optical Head has three fixed single mirror 

telescopes pointing forward, nadir and aft 

Black-coated Microbolometer arrays in the 

focal plane of each image 

A four aperture chopper drum (two empty 

and two with quartz filters) rotates 

continuously to provide alternate total and 

short wave signals 

A calibration drum carrying four black 

bodies and a viscal arrangement surrounds 

the chopper drum

– 

– 

Multi-Spectral Imager (MSI) 

Two cameras: Visible, Near and Short-wave 

infra-red and Thermal Infra-Red modules 

VNS and TIR parts share a common 

baseplate mounted on iso-static mounts 


7 th EARTH EXPLORER MISSION 

SELECTION PROCESS 

Step 1: 

Call and selection 

Step 2: 

Mission 

Assessment 

(Phase 0) 

Step 3: 

Mission Feasibility 

(Phase A) 

Step 4: 

Implementation 

(Phases B, C/D, E1) 

Call for Ideas 

ESAC Recommendation / PB-EO Selection 

Mission Assessment Groups / Phase 0 

Reports for Assessment 

User Consultation Meeting 


Mission Advisory Groups / Phase A 

Reports for Mission Selection 

User Consultation Meeting 


Implementation 

� March - July 2005 

� May 2006 

� Spring 2007 - 2008 

� Autumn 2008 

� 20-21 January 2009 

� February 2009 

� 2010-2011 

� 2012 


24 

6 

BIOMASS 

CoReH2 O 

PREMIER 

�2012-2017 ? 

3 

1

BIOMASS measurement concept 

Observation Concept: 

• Repeat-pass polarimetric interferometry 

using a p-band SAR 

• Measurement of changes in biomass with 2 x global coverage per 

year 

Duration: 

Revisit Time: 

Coverage 

Spatial Res: 

5 years 

25-45 days 

Global (swathwidth of 60-100km) 

50 x 50m (multilook) 

Orbit: Dawn-Dusk 

Instrument: P-Band polarimetric SAR 

(435 MHz, BW: 6 MHz) 

Instrument mode baseline: Full polarimetric mode 

Incidence 

Noise equivalent 

� 0 

option: compact pol mode (TX: circular,Rx: duallinear) 

> 23 degrees 

Threshold: < -27 dB, Goal: < -30 dB 

Candidate ESA Earth Explorer 7 Missions | 27 June, 2010 | M. Drinkwater Pag. 74 

Polarimetric 

Interferometric 

Phase 


Orbit cycle 

n+1 

Polarimetric 

radar 

intensity

BIOMASS Satellite Concepts 

Concept 1 

Concept 2 

Mass 

Data storage 

1200-2600 kg 

400-700 Gb 

Power 

Data Downlink 


Concept 3 

800-1200 W 

260-290 Mb/s

CoReH 2 O Mission Objectives 

Primary Objectives 

Retrieval of snow extent, thickness and snow water equivalent to 

improve 

- snow and ice processes in NWP and climate models, 

- understanding of land-cryosphere-atmosphere exchange 

processes, e.g. 

- Glacier mass balance 

- Snowmelt and glacier run-off 


CoReH 2 O Satellite Concepts 

Concept 1 

Single antenna concept 

(4.5 m � 2 m) 

Flight Direction 

Solar 

Array 

Mass 

Data storage 

Feed 

Cluster 

Deployed 

Reflector 

960-1200 kg 

1200-1400 Gb 

X-band 

Reflector 

Feed 

Arrays 

Flight Direction 

Power 


Concept 2 

Dual-antenna concept 

(3.3 m � 2.1 m, 3.3 m � 1.2 m) 

Solar 

Array 


1500-1700 W 

460 Mb/s 

Ku-band 

Reflector

Primary Objective 

- 

PREMIER Mission Objectives 

To quantify the dynamical, radiative and chemical processes controlling global 

atmospheric composition in the mid-Upper Troposphere and Lower 

Stratosphere (UT/LS, 5 – 25 km altitudes) to which surface climate is 

particularly sensitive. 

Secondary Objective 

- To explore processes controlling the composition of the lower 

troposphere/boundary layer and links to higher layers. 


Orbit 

PREMIER Measurement Concept 

Sun-synchronous, flying in tandem with 

MetOp at an altitude of 817 km with 09:30 

local time at the descending node. 

Payload 

– 

– 

– 

817 km 

Limb imaging FTIR for trace gases and particles (IRLS) 

• Spectral coverage 770-980 cm-1 and 1070-1650 cm-1 • Spectral sampling 0.2 cm-1 / 1.25 cm-1 • Spatial sampling 2 km / 500 m 

• High spectral resolution mode for atmospheric chemistry 

• High spatial resolution mode for fine scale dynamics 

Infrared Limb Cloud Imager (IRCI) 

mm-wave limb-sounder (MLWS-STEAM-R) 

• Spectral coverage in the ranges of 310-360 GHz 

• Covering an altitude range of 22 km with 14 beams 

• Vertical spatial sampling of 1.5 km 

• Along-track spatial sampling is 50 km 

MetOp 


3327 km 

Data products 

H2O, O3, T, HNO3, NO2 , 

C2H6, N2O, CH4, CFC- 

11, CFC-12, HCFC-22, 

ClO, CO, SF6, HDO, 

N2O5, ClONO2, CH2O, NH3, HO2NO2, … 

Aerosol extinction, 

Cirrus IWC, Cirrus size 

information, PSC 

parameters 

8 min ahead 

PREMIER

PREMIER Satellite Concepts 

Mass 

Data storage 

Concept 1 

Limb 

Nadir 

~1000 kg 

512 Gb 

Flight direction 

Limb 

Power 


Concept 2 

Flight direction 

1500 W 

520 Mb/s 


The new scientific priorities 


1. 

2. 

3. 

Updated Science Strategy for ESA’s 

LPP, after broad user consultation 

SP-1304 identifies key scientific 

challenges for: hydrosphere, 

atmosphere, cryosphere, biosphere 

and geosphere 

Emphasis on the Earth system 

approach, where interactions and 

interfaces between different parts of 

the Earth system are fundamental

Call for EE 8 

1. Call for proposals was issued in October 2009 

2. 

Proposals 

could 

non-ESA mission 

be 

made for a full satellite or a guest 

payload 


on a 

3. Budget ceiling of 100 MEURO industrial cost for the space segment and 

mission specific ground segment (i.e. excluding launcher, operations, 

generic ground segment, level 2 processor) 

4.EE-8 

mission 

to 

be 

launched 

in 2018 

Number of proposals 

Passive optical 19 

Passive microwave 5 

Active microwave 9 

Active optical 7 

Synthetic aperture radar 6 

Constellations 5

Weather, climate, environment & 

human life 

� The environment and human 

activities influence each other 

� The value of Earth Observation 

from space: not only science, but 

politics, economy and daily life of 

citizens profit from data 


Meteorological programmes: MTG 

1977 2002 

2017 

1 observation mission: 

-MVIRI: 3 channels 

-Spinning satellite 2 observation missions: 

- SEVIRI: 12 channels 

- GERB 

- Spinning satellite 

5 observation missions: 

- HRFI: 4 channels 

- FDHSI: 16 channels 

- Lightning Imager 

- Infra-Red Sounder 

-3-axis stabilised satellites 

GMES Sentinel 4 


Meteorological programmes: MTG 

1. 

Five observation missions implemented with 4 instruments on 2 

spacecraft 

a. 

b. 

c. 

d. 

Flexible Combined Imager (FCI) 

– 

– 

– 

16 channels between 0.4 and 13.3 �m 

Spatial sampling between 0.5 and 2 km 

Full disk coverage in 10 min 

Infra-Red-Sounder (IRS) 

– 

– 

– 

hyperspectral soundings at 0.625 cm-1 sampling in 

two bands (700 – 1210 cm-1 ; 1600 – 2175 cm-1) 

Spatial sampling : 4 km 

Full disk coverage in 30 min 

Lightning imager 

– 

global scales detection of optical events at 10 km scale 

UV-Visible Near-infared 

– 

Spectrometer (UVN) 

GMES Sentinel-4 missions (see later) 


Critical Pre-developments 

1. 

2. 

3. 

Scan Mechanisms (2x) 

Cryocoolers 

a. 

b. 

VLWIR (� c 

(2W at 55K) 

Pulse-Tube 

Stirling 

~ 15 �m)HgCdTe detector arrays 


Meteorological programmes: post-EPS 

EPS/MetOp 

2006 

Post-EPS/MetOp-SG 

2018 


The Changing Arctic 

� 

� 

Arctic sea-ice extent 

(September) has shrunk by 

12% per decade since 1978 

The Arctic increasingly 

becomes an arena of high 

geopolitical relevance 


The changing oceans 

� 

� 

Sea Level Rise: Thermal 

expansion of the oceans 

and melting ice 

Problems for countries 

with low reliefs like 

Bangladesh (food 

security, etc.) 


The changing 

� 

air quality 

Air quality measurements from 

space highlight the direct, 

often dramatic influence of 

human activities on the 

environment 

SCIAMACHY NO2 concentration, 2008 mean 


Global Monitoring for Environment and 

Security 

GMES aims at developing operational services, following the 

example of meteorology, but for other domains such as: 

• emergency management 

• air quality monitoring 

• land monitoring 

• ocean & sea ice monitoring etc… 

In addition, science is needed to 

create and continuously 

improve operational services 


We care for a safer world

GMES Components 

GMES is a user-driven EU led initiative 

� 

� 

� 

Services Component – coordinated by EC 

• 

• 

Produces information services in response to European 

policy priorities in environment and security 

Relies on data from in-situ and space component 

In-situ component – coordinated by EEA 

• 

• 

Observations mostly within national responsibility, 

with coordination at European level 

Space Component – coordinated by ESA 

• 

Sentinels - EO missions developed specifically for GMES 

Contributing Missions - EO missions built for purposes other than 

GMES but offering part of their capacity to GMES 

(EU/ESA MSs, EUMETSAT, commercial, international) 

GMES is a perfect example of a system of systems 


We care for a safer world

GMES Services 

� 

� 

Monitoring Earth sub-systems: 

•Land: land use and land cover changes 

•Ocean: sustainable ocean resources and impact of 

environmental hazards 

• Atmosphere: effect of greenhouse gases and aerosols 

on climate change, air quality, and ultraviolet radiation 

• 

Other Services: 

Emergency: rapid mapping services in case of 

humanitarian crises, and natural or man-made disasters 

•Security: maritime surveillance, conflict prevention and 

mitigation outside Europe 

• Climate change is cutting across the above domains 


~600 M 

Euro since 

2002 

(EC+ESA)

Earth Observation: 

headlines 2009 / 2010 


GMES dedicated missions: Sentinels 

Sentinel 1 – SAR imaging 

All weather, day/night applications, interferometry 

2012 A / 2015 B 

Sentinel 2 – Multi-spectral imaging 

Land applications: urban, forest, agriculture,.. 

Continuity of Landsat, SPOT 

2013 A/ 2016 B 

Sentinel 3 – Ocean and global land monitoring 

Wide-swath ocean color, vegetation, sea/land 

surface temperature, altimetry 

2013 A/ 2017 B 

Sentinel 4 – Geostationary atmospheric 

Atmospheric composition monitoring, transboundary 

pollution – flown on MTG 

2018+ 

Sentinel 5 – Low-orbit atmospheric 

Atmospheric composition monitoring – flown on MetOp-SG 

(S5 Precursor launch in 2014) 

2018+ 


Sentinel–1: C-band SAR mission 

� Applications: 

• 

• 

ice and marine/land monitoring 

mapping in support of 

humanitarian aid in crisis situations 

� 4 operation modes 

� 2300 Kg spacecraft mass 

� Sun synchronous orbit at 693 km mean altitude 

� 12 days repeat cycle 

� 7 years design life time, consumables for 12 

years 


Sentinel–2: Superspectral imaging 

mission 


• generic land cover maps 

• 

risk mapping and fast images 

for disaster relief 

� 13 spectral bands (VIS, NIR & SWIR) 

� Spatial resolution: 10, 20 and 60 m and 290 km swath 

� 1200 kg spacecraft mass 

� 5 days repeat cycle (cloud free) with 2 satellites 

� Sun synchronous orbit at 786 km mean altitude 

� 7 years design life time, consumables for 12 years 


Sentinel-2 services 

General services: Global carbon, Crop monitoring, Spatial planning 

(vegetation, urban), Forest monitoring, Water services, Soil erosion, 

large scale natural or man made disasters, surveillance of infrastructures 

Thematic services: Sustainable management of developing countries, 

Nature protection services, support to humanitarian aid, Food security 


Sentinel-2 Satellite & Payload 

Satellite MultiSpectral instrument 

• Satellite mass: 1200KG 

• Satellite power consumption: 1400W (1700W at Solar 

Array level, GaAs triple junction), 87Ah battery 

• Hydrazine propulsion system (117Kg) 

• TT&C using S band (64Kb/s up – 2018Kb/s down), with 

authenticated/encrypted commands 

• X band mission data distribution (520 Mbits/sec) 

• Mission data onboard storage: > 2.4 Tbits 

• Optical Communication Payload 

• Wheels, magnetometers, magnetorquers, star 

trackers, coarse sun and earth sensors, accurate 

Inertial Measurement Unit and 2f GPS 

• Filter based push broom imager (280KG, 1m 3 ) 

• Three mirrors silicon carbide telescope, with dichroic 

beam splitter 

• Focal plane arrays: Si CMOS VNIR detectors, HgCdTe 

SWIR detectors passively cooled (190K) 

• Onboard wavelet compression (~1/3) 

• Integrated video & compression electronics (state of 

the art wavelet compression) 

• Radiometric resolution 12bits 

• Radiometric accuracy < 5% 


60 m 

20 m 

10 m 

400 

nm 

B1 

600 

nm 

VNIR 

Sentinel-2 spectral bands 

800 

nm 

1000 

nm 

1200 

nm 

Spectral bands versus spatial resolution 


1400 

nm 

SWIR 

VIS NIR SWIR 

Visible 

B5 

B6 

B7 B8a 

B2 B3 B4 B8 

B9 B10 

Aerosols Water-vapour Cirrus 

Vegetation 

Red-edge 

Continuity with SPOT5 multispectral 

1600 

nm 

Snow / ice / cloud discrimination 

B11 B12 

1800 

nm 

2000 

nm 

2200 

nm 

2400 

nm

S2 instrument 

SIC Three Mirror 

Anastigmat 

Telescope 

Pushbroom sensor 

optical FOV 20.6° 

15 cm effective pupil 

diameter 

video electronics and wavelet 

compression electronics 

Spectral range 0.4 – 2.4 �m 

raw data rate 1.4 Gbit/s 

mass 289 kg 

power 250 W 

optical stripe filters 


Monolithic Si and hybrid 

HgCdTe cooled detectors 

Full Field 

of View 

Sun 

Diffuser

Sentinel–3: Ocean & global land mission 


• 

• 

Sea/land colour data and 

surface temperature 

sea surface and land ice 

topography 

� 1250 kg spacecraft mass 

� Sun synchronous orbit at 814.5 km mean 

altitude over geoid 

� 27 days repeat cycle 

� 7 years design life time, consumables for 12 

years 


Marine & Land Services 

Marine Land 

GMES Initial 

Service GMES 

Marine & Coastal 

Environment 

Polar 

Environment 

monitoring 

Maritime 

Security 

Global 

Change 

Ocean 

Sentinel–3 

Requirement 

sea-surface topography. 

mesoscale circulation. 

water quality. 

sea-surface temperature. 

wave height and wind. 

sediment load and 

Transport eutrophication. 

sea-ice thickness ice. 

surface temperature. 

ocean-current forecasting 

water transparency. 

wind and wave height. 

global sea-level rise. 

global ocean warming. 

ocean CO2 flux. 

GMES Initial 

Service GMES 

Global Change 

Land 

Land Cover & 

Land Use Change 

Forest 

Monitoring 

Flood 

Security 

Early Warning 

Humanitarian 

Aid 

Air Pollution 

(Local to 

Regional Scales) 

Risk 

Management 

(flood & Fires) 

Sentinel–3 

Requirement 

forest cover 

Change mapping. 

soil degradation 

Mapping. 

land use mapping 

Vegetation indices. 

forest cover 

mapping. 

regional land- 

Cover mapping. 

drought monitoring. 

land use mapping. 

aerosol 

concentration. 

burned scar mapping. 

fire detection. 


Sentinel–3 Payload Complement 

Optical Mission Payload : 

• Ocean and Land Color 

Instrument (OLCI) 

• Sea and Land Surface 

Temperature 

Radiometer (SLSTR) 

Topography Mission Payload : 

• Ku-/C-band Synthetic Aperture 

Radar Altimeter (SRAL) 

• MicroWave Radiometer 

(Bi-frequency) 

• Precise Orbit Determination 

(POD) including” 

• GNSS Receiver 

• DORIS 

• Laser Retro-Reflector 


Sentinel–3 Payload 

Sea and Land 

Surface 

Temperature 

Radiometer 

Laser Retro- 

Reflector 

Microwave 

Radiometer 

S-band 

Antenna 

SAR Radar 

Altimeter 

Ocean and 

Land Colour 

Instrument 

X-band 

Antenna 

DORIS 

Antenna 


- 

OLCI: the MERIS heritage 

Geometry 

FOV: 68.4º nadir w/ OZA < 

55º 

- swath: 1100km 

Grating spectrometer 

- 5 cameras covering 400-1020 

nm, binned to 15 (MERIS) & 6 

new bands 

- depolarized 

- solar diffuser for frequent 

- calibration over south pole 

Radiometric Accuracy: 

- absolute < 2% 

- Inter-channel < 1% 

- Stability: < 0.1% (day time) 

Major Improvements over 

MERIS: 

- CCD, optical bench design 

- SNR/s, video electronics 


SLSTR: the (A)ATSR heritage 

Radiometric performance: 

- 7 AATSR & 2 additional bands: 1.375, 2.2 µm 

- 

- 

- 

-NEDT < 0.08K (TIR) 

SNR > 20 (solar @ Lmin) 

Absolute accuracy < 2-5%, 0.2K 

Radiom. Stability < 0.1%, 0.08K 

- 

Polarisation sensitivity < 0.07 

Innovation (compared to AATSR): 

- 3 instead of 1 mechanism, due to wider swath 

(2 scanners and one flip mechanism) 

- More complex front-end & electronics (more channels) 

- New detector technology, multiple pixels (higher resol.) 


Sentinel-4, -5: Atmospheric composition 

Observation Requirements 

Carbon monoxide (methane) 

Methane 

Water vapour 

Cloud 

Cloud 

Glyoxal 

Nitrogen dioxide 

Rayleigh scattering 

Bromine monoxide 

Formaldehyde 

Aerosol 

Aerosol 

Aerosol 

Aerosol 

Total ozone 

Sulphur dioxide 

Ozone vertical profile 

Sentinel-4 

Sentinel-5 Sentinel-5p 

250 500 750 1000 1250 1500 1750 2000 2250 2500 

Wavelength [nm] 


� 

� 

Implementation of S-4/-5/-5p 

Sentinel 4 will be a realised as 

- addition of a UVN spectrometer on the MTG-S platforms; 

- utilisation of TIR data from the IR sounder onboard the 

- 

same platforms; and 

utilisation of imager data from the MTG-I platforms. 

Sentinel 5 will consist of 

- a UVNS spectrometer embarked on the post-EPS 

- 

platforms; 

implementation of the Sentinel 5 IR sounding 

requirements in addition to meteorological requirements 

- 

for the post-EPS IR sounder; and 

utilisation of post-EPS imager and of 3MI aerosol data. 

� Sentinel 5-p will consist of a UVNS spectrometer embarked on 

a dedicated platform and utilisation of the JPSS imager 


Sentinel–4: GEO atmospheric mission 

Applications: 

• air quality, climate forcing and 

tropspheric composition 

Instrumentation: 

• UV-VIS-NIR spectrometer 

• Use of thermal IR sounder 

and cloud imager 

UVN 

IRS 

Yaw-flip at equinox 

� UV-VIS-NIR with spectral bands 305 – 500 nm and 750 – 

775 nm 

� Spatial sampling of 8 km at 45°N and spectral resolution 

0.5 nm or better, repeat cycle: 1 hour 

� Geostationary orbit, at about 0o longitude 

� Embarked on MTG-Sounder Satellite and operated by 

EUMETSAT 


Sentinel–5: 

LEO atmospheric mission 

Applications: 


stratospheric ozone 


• UV-VIS-NIR-SWIR spectrometer 

• Use of thermal IR sounder 

and cloud imager 

� UV-Visible (270-500nm), 

� NIR (685-775nm) and 

SWIR (1590–1675nm; 2305-2385nm) push-broom grating 

spectrometer with spectral resolution between 0.4 nm and 1.0 nm 

� Spatial sampling with 50 (T)/15 (G) km < 300nm and 15 (T)/5(G) 

km > 300 nm 

� Global daily coverage 

� sun-synchronous Low Earth Orbit platform at 824 km mean altitude 

� Sentinel-5 embarked on post-EPS, operated by EUMETSAT, launch in 

2018+ 


Sentinel–5 precursor: 

LEO atmospheric mission 

Applications: 


stratospheric ozone 


• UV-VIS-NIR-SWIR spectrometer 

(UVN = NL, SWIR = ESA) 

� UV-Visible (270-500nm), 

NIR (675-775nm) and 

SWIR (2305-2385nm) push-broom grating spectrometer 

� Global daily coverage with 7 km sampling [TBC] 

� Sun-synchronous Low Earth Orbit platform at 824 km mean altitude 

� Guarantees data delivery for GMES Atmospheric Services between 

2015-2020 


ESA EO missions – 

launch schedule 

Update at www.esa.int 


And all the rest 

Sorry for not mentioning 

- 

- 

- 

- 

- 

Exploration: Exomars 

Atomic clocks 

Laser communications 

Avionics (Fibre-optics sensing, gyros,…) 

The next step in EO: high-res from Geo-stationary orbit 

- …….. 


Σας 

Thank you for your attention 

ευχαριστούμε 

για 

τη 

συμμετοχή 

σας!

Optical technologies in ESA programmes - Congrex

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