Sentinel-3: Current Status 1 year before Launch -...

Sentinel-3: Current Status 1 year before Launch

C. Donlon Sentinel-3 Mission Scientist

Overview

•  Sentinel-3 Satellite •  Sentinel-3 Ground

Segment •  Products

•  Summary

!Main satellite characteristics!•  1250 kg maximal mass •  Volume in 3.89 m x 2.202 m x 2.207 m •  Average power consumption of 1100 W •  Large cold face for optical instruments thermal control •  Modular accommodation for a simplified management of

industrial interfaces •  7.5 years lifetime (fuel for 5 add. Years)

•  Launch S3A 2015!•  Launch S3B 18 months later !

Observation: •  1 ground contact per orbit •  3h delivery timeliness (from satellite sensing)

Sea and Land Surface

Temperature Radiometer!

Ocean and Land Colour

Instrument!

Microwave !Radiometer!

SAR Radar Altimeter!

X-band Antenna

DORIS Antenna

S-band Antenna

Laser retro-

reflector

GPS

Sentinel-3: The Copernicus Medium Resolution Ocean and Land Mission!

Sentinel-3

GCOS ECV

5

S3 ECV Impact: Atmosphere Impact =6/11 (54%)

✔ T

✔  = S3 capability O = OLCI S = SLSTR T = Topography (MWR, SRAL, POD)

✔ S ✔ OS

✔ OST

✔ OS

✔ OS

6


✔ S GCOS ECV & S3:Ocean Impact =5/6 (83%)

✔ ST ✔ T

✔ OST

✔ O

S3 ECV Impact: Ocean

7

✔ OST ✔ OS ✔ OS ✔ OST ✔ OS ✔ OS ✔ O ✔ O

✔ OS ✔ T ✔ S

S3 ECV Impact: Terrestrial Impact =11/12 (92%)


Sentinel-3A Satellite Status

•  Platform readiness

•  Intermediate Satellite Qualification Review successfully completed => Environmental test campaign released •  Sentinel-3A AIT progressing: Full satellite and payload integrated since early July

•  Payload readiness •  SRAL PFM integrated on satellite, tests on-going. •  MWR PFM integrated on satellite, no open issues •  SLSTR PFM integrated on satellite, tests on-going.

•  SLSTR FM2 sub-system tests on-going (LOS, BB), instrument integration plan leads to calibration in Q1 2015. Integration (swap) of FM at satellite level in March 2015. •  OLCI PFM integrated on satellite; investigation of thermal issues affecting 1 camera on PFM detected during Tvac tests Camera will be swap for a camera allocated to FM2. •  Launch: Current launch window June-Sept 2015, depending on export license clearance from US State Department for launch from Russia •  Sentinel-3A predicted FAR Board date is 2nd half of July 2015, resulting in an earliest possible Launch Date 2 months later, 2nd half of September 2015 8

Sent ine l -3A in TAS Cannes test facilities in July 2015 (Credit: TAS)

Sentinel-3B Satellite Status

Sentinel-3B also in TAS Cannes ready for AIT (Credit: TAS)

–  Sentinel-3B satellite: Assembly Integration and

Testing (AIT) has started as well with mechanical integration of Topography Payload.

–  The platform units are mechanically and electrically integrated.

–  SMU recently re-delivered for completing the Platform IST.

–  DORIS and LRR are mechanically integrated. –  SRAL FM2: is now being integrated into the satellite. –  MWR FM2: delivered to TAS and awaiting integration –  OLCI-FM2: instrument ready in December 2014. –  SLSTR FM1: start of PFM refurbishment no earlier than

March 2015 –  Sentinel-3B Final Acceptance Review is predicted at the

end of 2016, corresponding to an earliest Launch date of end 1st quarter 2017.

POD Instruments - status

10

GNSS receiver/antenna integration

Doris receiver mounted on a satellite panel (right) and Doris antenna and LRR (top) mounted on the spacecraft

SRAL: Technical Status

The Sentinel-3A Satellite Thales Alenia Space in Cannes, France, with the Topography Payload installed

Instruments – SRAL status

12

!  SRAL PFM development is complete and the instrument is currently under mechanical integration into the spacecraft.

Final functional tests in Toulouse, with antenna provisionally connected in front of

the “RF wall EGSE”

SRAL PFM mechanical integration in the satellite

At SWH = 2m, the altimeter range noise is estimated to 0.7 cm rms. Better than LRM mode since the number of averaged pulses is greater in SAR mode (256 instead of 84 within a tracking cycle)

SRAL calibration and characterisation

•  Key parameters to characterize the SRAL altimeter instrument performances are:

•  Range Impulse response: •  Low Pass Filter: •  Range noise

•  Some other parameters will require in-flight validation, this will be done during commissioning:

•  Antenna pointing accuracy, antenna pattern •  Range Absolute bias

14

SRAL Impulse Response

−1000 −500 0 500 1000−50

−45

−40

−35

−30

−25

−20

−15

−10

−5

0

Frequency (kHz)

Nor

mal

ized

leve

l (dB

)

Impulse Response ( Ku−Band ) | mode : SAR I,Q

Side lobe thresholdIdeal side lobesIRIdeal IR

−150 −100 −50 0 50 100 150 200−40

−35

−30

−25

−20

−15

−10

−5

0

Frequency (kHz)

Nor

mal

ized

leve

l (dB

)

Impulse Response ( Ku−Band ) | mode : SAR I,Q

Side lobe thresholdIdeal side lobesIRIdeal IR

Impulse Response function (CAL-1) Ku-band/SAR-mode/Nominal chain

very close to theoretical “sinc” function

C-band Range Impulse Response

SRAL PFM Instrument Azimuth Impulse Response

->First Side Lobe is at -13.2 dB below the IR peak ->3dB resolution is 298 meters

16

SRAL PFM performance

Receive chain amplitude response (CAL-2)

• No spurious “spikes”

• Ripple within specifications and as expected

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

−1000 −500 0 500 1000−3.5

−3

−2.5

−2

−1.5

−1

−0.5

0

0.5

1

1.5

Ave

rage

(dB

)

Average, Ku−Band

−1000 −800 −600 −400 −200 0 200 400 600 800 10001

1.05

1.1

1.15

1.2

1.25

1.3

1.35

1.4

1.45

1.5

Zoom

(dB

)

Frequency (kHz)

Average, Ku−Band

SRAL Tracking performance

green: altitude variation of the test scenario red: SRAL PFM tracking window position blue: altitude difference Tracking performance (noise/lag) as expected

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 10

0.1

0.2

0.3

0.4

0.5

0.6

0.7

0.8

0.9

1

0 5 10 15 20 25 30

−250

−200

−150

−100

−50

0

50

100

150

200

m

Time (s)

Altitude variation (Initial altitude : 815042.357 m)

Scenario altitudeAltimeter altitude command

0 5 10 15 20 25 30−16

−15

−14

−13

−12

−11

−10

−9

−8Altitude difference

Time (s)

m

Altitude difference

Instruments – MWR status

18

!  MWR PFM test campaign in IABG completed end of August, including mechanical vibrations, thermal vacuum (TB/TV), Instrument performance calibration in vacuum

MWR PFM being prepared for calibration with the installation of

cold loads

MWR PFM & cold loads entering the vacuum chamber

MWR vibration tests

19

MWR Performance

20

Sensitivity/Accuracy

100 200 300 400 500 600 700 800

115.5

116

116.5

117

Earth observation (I) samples

K

Ta @ 23.8 GHz (Earth observation)

NO BLK

100 200 300 400 500 600 700 800

-1-0.5

00.5

11.5


K

Accuracy: Ta - Temp Target (Earth observation)

100 200 300 400 500 600 700 800116.5

117

117.5

118


K

Ta @ 36.5 GHz (Earth observation)

NO BLK

23.8 GHz36.5 GHz

100 101 102

10-2

10-1

Allan STD - 23.8 GHz

Time (s)

K

100 101 102

10-2

10-1

Allan STD - 36.5 GHz

Time (s)

K

Typical test conditions/results: •  Receiver temperature: 25 C •  Target temp. (uncorrected): 76.9 / 116.4 C •  Allan variance is decreasing for the complete

measurement period showing an extremely high stability of the MWR electronics and the target temperature.

Stability

Sentinel-3A E1 Commissioning Phase planning

Estimated no earlier than Sept 2015

Estimated no earlier than March 2016

Archive and Offline Processing Centre

Mission Performance Centre (MC)

CDB

CDB

CDB

CDB

CDB

Infoterra UK Farnborough

Indra Madrid

CLS Toulouse

Eumetsat Darmstadt

DLR Oberpfaffenhofen

ACRI Nice

CDB

CLS Brest

CDB

Sentinel-3 ground segment

ALL FACILITIES SUPPORTING S-3 GROUND SEGMENT ACTIVITIES ARE ESTABLISHED Stations: Data Acquisition and Near Real Time Product Generation: Data downlink, data processing (NRT and offline) For Sentinel-3: Svalbard

Processing and Archiving Centres (PAC): perform the Sentinels’ systematic non-time-critical data processing, on-the-fly processing for specific cases and reprocessing following algorithm/calibration parameters upgrades.

For Sentinel-3: Archiving and offline processing centres

–  DLR for OLCI processing and archiving –  CLS for SRAL processing and archiving –  ACRI for SLSTR and S-3 synergy products

processing and archiving –  EUMETSAT’s marine centre acts as PAC for

marine products. Missions Performance Centres (MPC): Operational Quality Control, Expert Support Laboratories (ESL), Calibration and Validation For Sentinel-3: consortium led by ACRI

T0 Sensing time

time 3 h 2-3 d ~30 d ~every 1-2 y

NRT products

STC products

NTC products

(only NTC products) Reprocessing Campaign NRT: Near Real time STC: Slow Time Critical NTC: Non time Critical

Ocean forecasting, Meteorology, Oceanography

Operational Ocean, Ocean forecasting, Oceanography

Climatology, Oceanography, Data exploitation

Sentinel-3 Product Timeliness (Example for SRAL)

L 1 FR OL _ 1 _ EFR

L 1 RR

OL _ 1 _ ERR

L 2 FR Land

OL _ 2 _ LFR L 2 FR Water

OL _ 2 _ WFR L 2 RR Land

OL _ 2 _ LRR L 2 RR Water

OL _ 2 _ WRR

L 1 SL _ 1 _ RBT

L 2 Land SL _ 2 _ LST

L 2 Water SL _ 2 _ WST

L 2 VGT _ P

SY _ 2 _ VGP L 2

SYN SY _ 2 _ SYN

L 2 VGT _ S 10 SY _ 2 _ V 10

L 2 VGT _ S 1

SY _ 2 _ VG 1

OLCI PRODUCTS

OLCI & SLSTR SYNERGY PRODUCTS

SLSTR PRODUCTS

VEGETATION - LIKE PRODUCTS

L 2 Marine Products L 2 Land

products L 1 Products

Op#cal'Sensors'Sen#nel.3'User'Products''

Op#cal'Sensor:'Level'2'Products'–'High'Level'''

Original operational baseline: split between LRM and SAR mode Late 2012: Request by the Copernicus user community to extend usage of

SAR mode for the S-3 SRAL instrument up to 100% of Earth coverage.

Low Resolution Mode (LRM) over open ocean

SAR mode over land, sea ice and coastal areas

100% SAR mode

SRAL: Changed observation scenario to 100% SAR

Note: LRM shall be kept as a back-up to reduce operational risks and to allow a possible switch to the LRM scenario if necessary

ESA Presentation | DD/MM/YYYY | Slide 26

ESA UNCLASSIFIED – For Official Use

•  BUT: SAR technology is new and complex " Further work required to understand all in-orbit conditions and emerging processing approaches.

•  NEW S3 SAR L1A products will be produced and made available to users.

S-3A: First mission to provide 100% SAR altimetry coverage

Product Level

Product Description

Relevance for

L1A Unpacked L0 data processed to engineering parameters with geo-location information

Fundamental studies on SAR processing such as Doppler beam formation and calibration studies using ground-based Transponders

L1B-S Geo-located, Calibrated gathered azimuth formed complex (I and Q) power echoes after slant/Doppler range correction

Geophysical retrieval algorithm developers (over ocean, land and ice surfaces), surface characterisations studies (e.g. impact of sea state bias, wave directional effects etc) and QC systems

L1B Geo-located, Calibrated Multi-looked power waveforms

geophysical retrieval algorithm developers and QC systems

•  Expected advantages of L1A: •  Foster a new generation of SAR altimetry

specialists maintaining Europe at the competitive edge

•  Enhance maintenance and development of existing and new products over the Earth surface (ocean, ice and land) within Copernicus

•  Enhance uptake, application, and quality control (e.g. transponder calibration) of SRAL SAR data products by the Copernicus user community

•  Reduce large-scale reprocessing efforts (because starting from intermediate L1 products rather than from L0)

SRAL: Changed observation scenario to 100% SAR

Request from EC for two “new” operational products

#  Fire Radiative Power –  FRP in core product list –  FRP at 1 km (pixel level) –  Accuracy: goal 10%, threshold 30% –  Threshold Detection: Goal 5MW, threshold 50 MW –  NRT (< 3 h)

#  Aerosol (Global) –  Global Aerosol in core product list –  Aerosol at pixel level (goal) –  Accuracy: goal AOD 0.1 over land, AOD 0.05 over ocean –  NRT (< 3 h) –  AOD 550 nm over ocean and land (goal) –  Include uncertainties at pixel level (goal)

SENTINEL-3: NEW PRODUCTS UNDER DEVELOPMENT FRP and AOD

The Sentinel-3 Mission Performance Centre: Operational Quality Control

Mission Performance Framework

Coordination

External/ complementary

Sentinel-3 Validation

Teams

Expert Support Labora-tories (ESL)

ESA/EUM expertise

Quality Working Groups (QWG)

International Cooperation

ESA/EUM Op. QC

Validation& Analysis

Payload Data

Ground Segment

DB

Potential Sentinel-3 user involvement

October(2014(

CSC'Data'Access:'Interac#on'with'Users'

29(

Collabora#ve'Access'Hub'

Copernicus'Services''Access'

Scien#fic'/'Other'Access'Hub'

Interna#onal'Agreements'Access'Hub'

Copernicus'Space'Component'Data'Access'Portal'

'www.sen&nel.esa.int+

Opening'of'dissemina.on'of'all'S1A'products'to'all'users'on'the'3rd'October'2014'

Data'Access'–'An'Engineering'View'

30(

MSs'Collabora#ve'

Access'

Copernicus'Services''Access''

CSC(GS

(Da

ta(Access(

Scien#fic'/'Other'Access'

Interna#onal'Agreements'

Access'

ESA(funded(R&D(projects(

Scien@fic/(Other((users(

e.g.(scien@fic,(commercial((outreach,(general(public(

Copernicus(Services(

MSs(CollGS(Users(e.g.(public,(scien@fic,(

commercial(

Interna@onal(users(

Funded+and+Operated+by+MSs+

Na@onal(Mirrors(((Inc(local(sta@on)(Na@onal(Mirrors(((Inc(local(sta@on)(

Na#onal'Access''

Interna@onal(Mirrors(Interna@onal(

Mirrors(((Inc(local(sta@on)(

Funded+and+Operated+by++int.+partners++

Int’l Access

Summary

–  Sentinel-3A is a mission well-tuned to make a significant contribution to the GCOS ECV

–  The S3A Satellite Assembly Integration and Testing (AIT) is proceeding well.

–  Launch of the S3A-unit is anticipated in late 2015 –  Sentinel-3B satellite is starting integration with a launch

anticipated in 2016/17. –  Ground segment development in full development –  New L1 products for Altimetry and optical sensors are in

preparation. –  The ESA CCI programme is well poised to take full advantage

of early Sentinel-3 data.

Thank you - any questions? For more information http://www.esa.int

See Donlon et al (2012) The GMES Sentinel-3 Mission, Remote Sensing of Environment, http://dx.doi.org/10.1016/j.rse.2011.07.024,

and the Mission Requirements Traceability Document (MRTD) at

http://download.esa.int/docs/EarthObservation/GMES_Sentinel-3_MRTD_Iss-1_Rev-0-issued-signed.pdf

Contact: [email protected]

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