ostm/jason2 - ostst hobart - march 12, 2007 1 ostm/jason2 mission status j. perbos/cnes, p....

OSTM/Jason2 - OSTST Hobart - March 12, 2007 1

OSTM/Jason2 Mission status

J. Perbos/CNES, P. Vaze/NASA, W. Bannoura/NOAA, F. Parisot/Eumetsat

OSTST meeting - Hobart

Presented by G. Zaouche - CNES


Summary

• Mission features and Responsibility sharing

• Science and Ops requirements, – OSTM/Jason-2 Products– System improvements

• Mission status– Station acquisition and keeping strategy– Satellite– Launcher– Ground System


Instruments

• Core Mission:• Poseidon-3 Altimeter• DORIS (Precise Orbit Determination

System)• Advanced Microwave Radiometer (AMR)• GPS Payload (GPSP)• Laser Retro-reflector Array (LRA)

• Passengers:• T2L2• JRE (Carmen2 + LPT)

• Core Mission:• Poseidon-3 Altimeter• DORIS (Precise Orbit Determination

System)• Advanced Microwave Radiometer (AMR)• GPS Payload (GPSP)• Laser Retro-reflector Array (LRA)

• Passengers:• T2L2• JRE (Carmen2 + LPT)

Science Measurements

Global sea surface height to an accuracy of < 4 cm every 10 days, for determining ocean circulation, climate change and sea level rise

Global sea surface height to an accuracy of < 4 cm every 10 days, for determining ocean circulation, climate change and sea level rise

Mission Objectives• Provide continuity of high precision ocean

topography measurements beyond TOPEX/Poseidon and Jason-1

• Provide a bridge to an operational mission to enable the continuation of multi-decadal ocean topography measurements

Mission Overview

• Launch Date: mid June 2008• Launch Vehicle: Delta II 7320• Proteus Spacecraft Bus provided by CNES• Mission life of 3 years (goal of 5 years)• 1335 km Orbit, 66º Inclination

• Launch Date: mid June 2008• Launch Vehicle: Delta II 7320• Proteus Spacecraft Bus provided by CNES• Mission life of 3 years (goal of 5 years)• 1335 km Orbit, 66º Inclination

Mission summary


NASA/JPL

NOAA

CNES

EUMETSAT

EUMETSAT – Usingen, Germany

NOAA - Wallops/ Fairbanks - USA

Jason 2

Dedicated Delta II Launch Vehicle

NASA Instrument Ops

Operational product processing and Science Data archive & Distribution

Operational product processing & Distribution

Science data processing, archive & Distribution

NASA ElementsNOAA ElementsEUMETSAT ElementsCNES Elements

S/C Operations (Suitland, MD)

S/C Operations (Toulouse, France)

Passengers Ops and mission centersCNES- JAXA

AMR Reflector

AMR Electronics

GPSP Antenna

LRA

Poseidon 3 Altimeter

DORIS

System elements


Mission Partnership

• CNES responsibilities:– Project Management– Satellite, Proteus bus– Payload

• Nadir Altimeter POS3• DORIS • T2L2 - CARMEN2 - LPT

– Ground System & Operations• Satellite Control Command Center (CCC)• OFL product processing and distribution• All archiving• Ground network• Satellite Operations before handover• Navigation, Guidance, Expertise for all mission

– System integration & test– Mission Operation support for CNES instruments– System Coordination for all mission phases– User interface

• CNES responsibilities:– Project Management– Satellite, Proteus bus– Payload

• Nadir Altimeter POS3• DORIS • T2L2 - CARMEN2 - LPT

– Ground System & Operations• Satellite Control Command Center (CCC)• OFL product processing and distribution• All archiving• Ground network• Satellite Operations before handover• Navigation, Guidance, Expertise for all mission

– System integration & test– Mission Operation support for CNES instruments– System Coordination for all mission phases– User interface

• NASA responsibilities:

– Project Management – Launch vehicle – Payload

• Advanced Microwave Radiometer (AMR)• GPS Receiver (GPSP)• Laser Retro-reflector Array (LRA)

– JPL Payload integration and test– Mission Operation support for JPL

instruments

• NASA responsibilities:

– Project Management – Launch vehicle – Payload

• Advanced Microwave Radiometer (AMR)• GPS Receiver (GPSP)• Laser Retro-reflector Array (LRA)

– JPL Payload integration and test– Mission Operation support for JPL

instruments

• NOAA responsibilities:– Project Management– Ground System & Operations

• Satellite Operations Control Center (SOCC)

• CDA Stations (2)• NRT product processing• All product distribution• All archiving• Ground network• Satellite operations after handover

– User interface

• NOAA responsibilities:– Project Management– Ground System & Operations

• Satellite Operations Control Center (SOCC)

• CDA Stations (2)• NRT product processing• All product distribution• All archiving• Ground network• Satellite operations after handover

– User interface

• EUMETSAT responsibilities:– Project Management– Ground System & Operations

• Earth Terminal (1)• NRT product processing, archiving and distribution• Ground network

– User interface

• EUMETSAT responsibilities:– Project Management– Ground System & Operations

• Earth Terminal (1)• NRT product processing, archiving and distribution• Ground network

– User interface


Summary





• Jason-2 shall pursue the scientific objectives of the T/P and Jason-1 missions and support the running operational services

• Jason-2 shall meet the better than 3.5 cm rms accuracy, at 1 Hz, on the fully validated sea surface height measurements and shall provide intermediate products with the required delay and accuracy

• In addition to wave height and wind speed, NRT products need to include SSH information, with the required accuracy, for monitoring and forecast ocean fast events

• Expectation of improving performances through off-line ground-processing updates

• Expectation of collecting a maximum of valid data near the coasts, over inland waters and sea-ice, in order to support emerging research in coastal dynamics, hydrology, sea-ice interactions…

Summary of science and Ops requirements


Products

• All O/I/GDR products will have the same format and very close scientific content.

– OGDR = IGDR but the following :• Orbit is computed using Doris Navigator files on OGDR• Meteorological fields are predicted• Pole Tide, Altimeter and radiometer calibration values (historical files)• Dynamic Atmospheric correction (derived from Mog2D) is not available • GIM ionospheric correction (derived from JPL maps) is not available • Platform derived off-nadir angle is not available

– IGDR = GDR but the following :• Orbit is computed using MOE ephemeris • Pole Tide, Altimeter and radiometer calibration values (historical files)• Dynamic Atmospheric correction (derived from Mog2D) is less accurate

• Taken into account Jason-1 heritage, products will be split into several files :

– One file close to current Jason-1 NRT-SSHA, limited to 1Hz sampling. – One file close to current Jason-1 I/GDR, containing 1hz and 20hz values. – One file close to current Jason-1 SGDR, containing 1hz, 20hz and waveforms values. This file will

not be generated in NRT.

• User Handbooks, reading tools, products samples will be defined and delivered to OSTST group in a few months


OGDR products (Near Real Time)

• Description : – NRT geophysical product, data latency of 3 hours.– DORIS/DIODE onboard orbit : 10 cm rms for the radial component– Ground retracking is performed and all environmental and geophysical corrections

computed. – Non fully validated product which contains data for both bands (Ku and C).– Two files :

• SSHA_OGDR : close to current Jason-1 NRT-SSHA, limited to 1Hz sampling.

• OGDR : close to current Jason-1 I/GDR, containing 1hz and 20hz values.

• Keys inputs : – Satellite telemetry– Auxiliary data

• Production requirement : – For the OGDR, 75% of the data taken shall be made available to the users within 3

hours from acquisition and 95% of the data within 5 hours.– No dynamical auxiliary data are mandatory input for OGDR processing. In case of lack

of dynamical auxiliary data, the corresponding OGDR field will be computed with the most recent data available (none field being set to default).


NRT Products Quality Assessment System

• Quality Assessment System Developed by JPL under NOAA Contract has been installed &

tested at NOAA

• Presently running on Jason-1 IGDRs, until Jason-2 OGDR is fully defined

• QA Package has been made available to EUMETSAT via JPL licensing

Time Series (SSH) Asc/Des Maps (Iono) Histograms (Iono) Editing Time Series & Map (Wind)


OSTM Product Suite

Product: OGDR IGDR GDR

Latency: 3-5 Hours < 1.5 Days ~ 60 Days

1-Hz* OGDR-BUFR

1-Hz OGDR-SSHA IGDR-SSHA GDR-SSHA

20-Hz OGDR IGDR GDR

Waveforms S-IGDR S-GDR

* Compressed BUFR format; all other products in native netCDF format


OSS Nominal products

Major characteristics of the product

OGDR (NRT)

IGDR (OFL)

GDR (OFL)

Content Not fully validated geophysical level 2

product

Not fully validated geophysical level 2

product

fully validated geophysical level 2

product

Alt. ground retracking Applied Applied Applied

Orbit information source Better than 10 cm DORIS Navigator

2.5 cm preliminary orbit

1.5 cm Precise orbit

Structure segment pass pass

Packaging segment day cycle

Ground Processing mode systematic systematic systematic

Data latency /availability 3 hours / 75%5 hours / 95%

<1.5 calendar days / 95%

60 days / 95%

Format / Ground Processing

centers

Native and BUFR / NOAA and EUMETSAT

Native /CNES

Native /CNES

Ground Archiving centers NOAA and CNES and EUMETSAT

NOAA and CNES NOAA and CNES

Dissemination centers NOAA and EUMETSAT NOAA and CNES NOAA and CNES

Dissemination mode Systematic Electronic & Satellite

Systematic Electronic

Systematic Electronic - Media


Some system improvements

“Collecting a maximum of valid data near the coasts, over inland waters” Achieved through implementing new altimeter functional modes: “Median Tracker algorithm ” in addition to the current Poseidon 2 “Split Gate Tracker

algorithm” (adapted to ocean surfaces)• should improve significantly echo tracking capability over non ocean surfaces

Use of satellite altitude data provided in real time by DORIS/Diode :

2 new experimental modes :

Signal acquisition using Diode altitude data + usual on-board tracker :• should improve the delay to get echoes after a land-water transition (3 times better)

Range directly computed from : Diode altitude data + Digital Elevation Model data • DEM data stored on-board, representative of oceans, lakes and rivers, and flat land

areas• should improve data collection near the coasts and over inland waters

Final altimeter nominal mode will be selected after data evaluation during the assessment phase


Some system improvements

• New coastal & inland water product (demonstrative one) :

– ITT has been issued by CNES to develop a new product suitable for applications in coastal and inland areas.

– All current ground processing will be reviewed and analyzed.

– We foresee :• Dedicated retracking and radiometer algorithms

• Dedicated geophysical corrections (tides, ssb, …)

• Dedicated environmental corrections (wet tropo, iono, …)

– Prototype shall be ready for Jason-2 launch, operated during CalVal phase and products made available to OSTST community for review.

– Using OSTST feedbacks, this demonstrative product might become an official product during Jason-2 operation phase.


Summary





Jason-2 Orbit

target : 1 min

Jason-2is maintained in a control

box of ± 1 km

1 km

1 km

Jason-1 is maintained in a control

box of ± 1 km Each satellite remains in its control box

by controlling the equator crossing.The station keeping is made independently

Improvement wrt Jason-1 :for Jason-2 station keeping, maneuvers will be made with only one thrust above earth on any orbit (no more on the last orbit of the 10-day cycle)

• Tandem flight with Jason-1 planned for both altimeters cross-calibration purposes• Jason-2 final orbit characteristics :

- semi axis = 1336 km; inclination = 66° (same ground tracks as Jason-1)- Jason-2 : 1 minute ahead Jason-1


Station acquisition strategy

• Injection orbit (same as Jason-1)– 10 km below the nominal Jason-2 orbit : to avoid polluting the operational orbit

by pieces of launcher and to create a drift to reach the right time phase between Jason-2 and Jason-1.

• Maximal duration for station acquisition : 1 month• Number of rendezvous maneuvers and duration of the station acquisition depends

on the launch date (day number in the Jason cycle).

Test maneuver to check propulsion

system (DV< 15 cm/s)

4 daysInjection

Trim maneuver if needed

30 days max.Second rendez-vous

maneuver (DV ≤ 5 m/s)

First rendez-vous maneuver

(DV ≤ 5 m/s)

2 days

One or two inclination maneuvers

2 days min.


9 to 10 months

Start of cycle 1

Start of OFL pdts delivery + data reprocessing

Verification Phase5 months

First Verification WorkshopNRT Verif Phase Near RT products delivery by NOAA

and EUM

Nominal satellite and instruments modesLEOP3 days

In-Flight Assessment Meeting

Orbit Acquisition 4 weeks Orbit Acquisition key point

Assessment Phase2 months

Resp : CNES with support of EUMETSAT, NASA, NOAA

Resp : CNES with support of EUMETSAT, NASA, NOAA

Resp : CNES , NASA with support of PIs

Resp : CNES , NASA with support of PIs

Resp : CNES(generation and distribution), NOAA (distribution)

Resp : EUMETSAT, NOAA (generation and distribution)NRT Operational Phase

OFL Operational Phase

Start of Satellite & Ground nominal operations

Sat Op Handover Review

Flight operations Hand over to NOAA

Final Verification workshop OFL Verif Phase

Resp :CNES (Sat Operations) Resp : NOAA (Sat Operations)

Resp : CNES for System coordination

Operational Phase

Sat Operational Phase2 months

CNES

Mission Phases


Jason-2 satellite

• 8-instrument Payload

– AMR (NASA/JPL)– GPSP (NASA/JPL)– LRA (NASA/JPL)– DORIS receiver (CNES)– POSEIDON 3 altimeter (CNES)– 3 passengers : Carmen 2 (CNES), T2L2 (CNES), LPT

(JAXA)

• 505kg/ 472W satellite


DORIS

• Provides accurate time-tagged Doppler measurements to meet Jason2 POD requirements

– MOE/IGDR required accuracy : 2.5 cm on radial component– POE/GDR required accuracy : 1.5 cm (1cm goal) with Laser

measurement

• Delivers on-board, in real time, an estimation of satellite position with an accuracy better than 10 cm RMS on the radial component

• Provides accurate TAI time-tagging of satellite PPS and payload measurements with an accuracy better than 7 microseconds

• Provides to both altimeter chains and to T2L2 equipment the 10 MHZ USO signal

• DGxx BDR corresponds to a new design of DORIS receivers– USO NG design (different from JASON1 USO design) but with a 5

MHz resonator (instead of 10 MHz) to improve short-term stability– Improvement of resonator selection and process method to reduce

USO sensitivity to radiation in SAA area (DORIS/JASON1 lessons learned)

• Flight Model 4 delivered and assembled on the satellite

• Flight Model 3 will be delivered mid April and will replace FM4

DORIS 2 frequency antenna

Doris DGxx BDR (including USO)


Altimeter (Poseidon3)

• Provides accurate range measurement between the satellite and the mean sea surface

– measurement in Ku-band

– C-band range data used to correct for ionosphere path delay

• Additional parameters :

– Significant Wave Height (SWH) in Ku-band

– Backscatter coefficient 0 related to the wind speed

– Antenna mispointing

• Poseidon 3 design derived from both Poseidon 2 and SIRAL altimeters (CRYOSAT mission)

• 2 frequency antenna : copy of Jason-1 antenna

• Processing Units : built and testing completed

• Radiofrequency Units : built and testing completed

• Flight Software is validated

• Altimeter assembly and performance tests in progress

• Delivery for assembling on satellite : May 07

Poseidon3 two frequency antenna

Poseidon3 FM on the payload module panel


• The instrument is comprised of a 23.8 GHz water vapor sensing channel, an 18.7 GHz channel to estimate ocean surface contributions, and a 34.0 GHz channel to estimate cloud liquid content

• Measures single polarization, radiometric brightness temperatures in a nadir beam co-aligned with that of the CNES supplied Poseidon-3 altimeter, i.e. it provides “wet” tropospheric path delay correction for nadir altimeter range measurement. Critical to meeting OSTM science requirements.

• Same functional requirements as the JMR but different implementation which lead to a new generation design : less mass and power

• New antenna design with larger reflector (1m) and inherited JMR feed, significantly reduces calibration uncertainties and improves coastal resolution

• Instrument has completed testing and has been delivered to CNES/Alcatel (Feb ’07) and is integrated on the S/C

• Closure of one open point: Rework of Noise Source units and swap with existing flight HW is planned for April ‘07

Electronics Support Assembly

Complete AMR Instrument

Advanced Microwave Radiometer (AMR)


Choke-Ring Antenna ( 1 of 2)

GPSP Electronics Unit (1 of 2)

• High performance GPS receiver designed to provide precise orbit determination as a validation to the primary DORIS system and to enhance the accuracy during nominal operations.

• HW is build to print of the Jason-1 GPS receiver• As on Jason-1, the instrument is block-redundant with 2 identical single-

string receivers and antennas• Each redundant side of the GPSP subsystem consists of a dual-frequency

L1/L2 patch antenna/choke-ring assembly, an electronics unit, and a coaxial RF cable

• Complete instrument was successfully delivered for S/C integration and fully integrated on S/C in Dec ‘07

Payload GPS

receiver (primary)

Ant. #1

Ant. #2

coax

GPSP Instrument

Spacecraft chassisSkin

connectors

1553

RS-422

DHU Internal Bus

Power A

Power B

Telemetry Interface

B

Telemetry Interface

AProcessor Module A

Processor Module BPayload

GPS receiver

(redundant)

Global PositioningSystem Payload (GPSP)


• Consists of several quartz corner cubes arrayed as a truncated cone with one in the center and the others distributed azimuthally around the cone.

• The LRA supports determination of the Poseidon-3 altimeter bias through direct comparison of altimeter measurements with laser measured "altitude" corrected to sea level from local tide gauges

• Totally passive reflector designed to reflect laser pulses back to their point of origin on earth. The assembly contains no electronics or software.

• The LRA allows the OSTM/Jason-2 spacecraft to be tracked with centimeter accuracy by approximately 40 satellite laser ranging stations

• The LRA is an exact copy of the Jason LRA and has been delivered to CNES/Alcatel for S/C integration (March ’07)

NASA SLR Stations at GSFC

Laser RetroreflectorAssembly (LRA)


Passengers : T2L2

• Main mission objectives :– Compare distant clocks with an accuracy of a few picoseconds

– Contribute to better characterize the Doris USO noise

• Environment testing completed• Delivered to CNES, performance tests in progress• Delivery for assembling on satellite : mid April 07

Electronics Optical Unit


Passengers :Carmen2, LPT

Carmen2 • mission objectives : to study the influence of space

radiation on advanced components ; to measure the deposit dose into the DORIS USO ( South Atlantic Anomaly)

• Environment testing completed• Delivery for assembling on satellite : mid March 07

LPT• mission objective : to measure the radiation environment at

the Jason2 orbit• Environment testing nearly completed• Delivery for assembling on satellite : April 07

LPT Electronics

Carmen2

LPT Sensors


Satellite Status

• Proteus Bus equipment fully qualified• Proteus Platform has been integrated and delivered• Platform integrated with Launch Vehicle Interface (LVA). • Platform Safe to Mate (missionisation) completed.


Satellite Status

• All functional validation tests performed. • Flight Software Validation completed• Spacecraft Data Base available

•Payload Assembly and Integration Tests (AIT) has started Dec 06

• Payload Instrument Module assembly completed


December 2006 :

DORIS AIT

Satellite Status


Satellite Status

December 2006 :

GPSP AIT


End January 2006

AMR AIT

Satellite Status


February 2007

Altimeter antenna integration test

Satellite Status


• Boeing Delta II-7320 manifested as single payload launch

• Payload integration and launch from VAFB (Vandenberg Air Force Base), CA

• Implementation timetable based upon ATP (Authority To Proceed) at L-27 months (Mar 06)

• NASA Flight Planning Board has identified a launch date of 15 Jun 08

• Single payload configuration will require a system that reduces vibration loads to the spacecraft

• Softride isolation system selected for implementation by Boeing

• Completed PDR in Feb ’07 with full delivery expected by end of 2007.

• Restarted Loads and Structures Working Group to ensure successful implementation

• Overall LV development is on schedule with no significant issues.

Launch Vehicle


Jason2 Ground System : Earth stations

HBK

TM/TC SBAND Earth Terminal

Hartebeesthoek, South Africa

Resp : CNES - Phase : LEOP and Assessment, contingency in routine phase

USG

TM/TC Earth Station

Usingen, Germany

Resp : EUMETSAT - Phase : all

FBK

WPS

Command and Data Acquisition Stations

Fairbanks, Alaska, USA

Wallops, Virginia, USA

Resp : NOAA - Phases : all

EUMETSAT Earth Station :• built and accepted in 2006• integrated into Jason2

Ground System • currently involved into

System Tests

NOAA stations :• already existing• adaptation to Jason2 :

in progress• to be integrated into

Jason2 Ground System in summer 2007


FBK

WPSUSG

HBK

CNES J2CCC

Jason-2 Command Control Center (J2CCC)

Localisation : Toulouse, France

Resp : CNES

Phase : active control center for LEOP and assessment (-> handover), contingency in routine phase

NOAA SOCC

Satellite Operation Control Center (SOCC)

Localisation : Suitland, USA

Resp : NOAA

Phase : active control center for routine phase (handover ->)

EUMETSAT processing centre

EUMETSAT processing center (EUMPC)

Localisation : Darmstadt, Germany

Resp : EUMETSAT

Phase : all

Role : routing non real-time exchanges between CNES and NOAA

PRESTOSatellite simulator (PRESTO)


Resp : CNES

Phase : all

Jason2 Ground System :Satellite command/control


Jason2 Ground System :CNES command/control center

CNES Control Center :

• for LEOP & Assessment phases

• adaptation and integration to Jason2 Ground System: completed

• currently involved in the compatibility tests

• will participate to Operational System qualification from Summer 2007


Jason2 Ground System :NOAA command/control center

NOAA Control Center :

• for satellite operational phase

• adaptation to Jason2 Ground System : in progress

• first compatibility tests : April 2007

• to be integrated into Jason2 Ground System in summer 2007

• will participate to Operational System qualification from Fall 2007


FBK

WPSUSG

HBK

CNES J2CCC

NOAA SOCC

EUMETSAT processing centre

JPL instrument experts(Pasadena)

CNES Mission CentreSSALTO (Toulouse)

NOAA Mission Centre

CNES Mission Centre : SSALTO (Segment Sol Multi-mission Altimétrie et Orbitographie)


Resp : CNES

EUMETSAT Processing Center (EUMPC)

Localisation : Darmstadt (Germany)

Resp : EUMETSAT

NOAA Mission Center

Localisation : Suitland (USA)

Resp : NOAA

JPL Payload command/control center

Localisation : Pasadena, USA

Resp : JPL

Jason2 Ground System : Products Processing centers

Users


EUMETSAT Near Real TimeProduct Center

EUMETSAT Near Real Time Product Center :

• development in progress• integration to Jason2 Ground System: summer 2007• will participate to Operational System qualification end

2007• for operational phases


NOAA Near Real TimeProduct Center

NOAA Near Real Time Product Center :

• development in progress• integration to Jason2

Ground System: summer 2007

• will participate to Operational System qualification end 2007

• for operational phases


CNES Off lineProduct Center

CNES Off line Product Center (SSALTO) :

• adaptation to Jason2 ground system in progress

• new development in progress

• integration to Jason2 Ground System: summer 2007

• will participate to Operational System qualification end 2007

• for verification and operational phases


Users Products and Data access

NOAA CLASShttp://www.class.

noaa.gov/nsaa/products/welcome

EUMETCASThttp://www.eumetsat.int/

Home/Main/Access_to_Data/Delivery_Mechanisms

CNES AVISOhttp://www.jason.

oceanobs.com


Project Summary

• Successfully completed all mission reviews– Satellite Critical design Review October ’06– System Interface Review December ’06– Instruments level reviews

• Build and test of all instruments is nearly complete• Current measured payload and satellite performance meets all

requirements• Several key risk items for System Safety and LV have been addressed

with clear mitigation paths established.• Payload instruments integration has started Dec ‘06• Satellite Assembly, Integration and Test: from June ‘07 to January

2008• Ground System qualification tests and End to End (Satellite-Ground)

tests : from April ’07 to May ’08

• Launch: mid June 2008– 2 months schedule margin for satellite and system development

ostm/jason2 - ostst hobart - march 12, 2007 1 ostm/jason2 mission status j. perbos/cnes, p....

Documents