Requirements
for the
Sentinel Small Sat (S^3) – Challenge
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Table of Contents
1
2
3
4
5
Introduction................................................................................................................4
Background ................................................................................................................4
Objective of the Sentinel Small Sat (S^3) Challenge...................................................4
Implementation ..........................................................................................................4
Requirements .............................................................................................................5
5.1 Mission Requirements.........................................................................................5
5.2 Launcher Interface Requirements .........................................................................5
5.3 Ground Segment Requirements ............................................................................5
5.4 Debris mitigation Requirements ...........................................................................6
5.5 Quality Assurance & Safety Requirements ...........................................................6
6
Planning .....................................................................................................................6
7
Financial & Contractual aspects .................................................................................6
8
Communication and Outreach ....................................................................................7
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1
Introduction
The purpose of this document is to provide the objectives, requirements and
implementation arrangements for the Sentinel Small Sat (S^3) Challenge.
2
Background
In recent years, a large number of private companies have started to develop and deploy
constellations with hundreds of satellites providing new infrastructure with innovative
Telecommunication and Earth Observation (EO) capabilities. These new systems are
designed to leverage the latest technological advancements and evolve quickly over time in
a more risk-taking approach and, hence, are likely to impact existing and planned
traditional space infrastructure.
Traditional development approaches have proven successful in generating high quality and
highly reliable products. Nevertheless, innovative satellite design, development and
operations approaches may facilitate the exploitation of the technological advancements
achieved by the earthbound consumer IT industry. Stimulating the adoption of such
approaches could foster growth and boost competitiveness of the European aerospace
industry. The main factor fuelling this revolution is the rapid development and high
integration of miniaturised technologies (electronics, sensors, MEMS, RF devices), and a
similar development in remote sensing technologies could lead to very light satellites with
higher capabilities and lower costs. Moving the space development cycle towards the IT
model, driven by a huge effort in terms of R&D and resources, may actually kick-start a
new era of innovation in space.
The Copernicus Programme supports the advent of the innovation wave in Europe by
ensuring a continuous supply of high quality data in an open and free manner for users for
decades to come.
3
Objective of the Sentinel Small Sat (S^3) Challenge
The S^3 Challenge goal is to stimulate innovative satellite design, testing and
manufacturing solutions leading to small missions complementary, or providing added
value, to current Sentinel family missions (see Annex I).
4
Implementation
The S^3 Challenge will be proposed as part of the 2017 ESA Challenge within the
Copernicus Master Prize. The Copernicus Master Prize is an ideas competition, aiming at
young and innovative entrepreneurs making use of Earth Observation Copernicus data. The
goal of the ESA Challenge within the Master prize is to obtain "out-of- the-box" ideas for
the benefit of the commercial use of EO data, by anticipating disruptive changes to current
market conditions and technologies.
The S^3 Challenge winner is planned to be launched on the Small Satellite Mission
Service (SSMS) proof-of-concept flight on Vega currently foreseen by end of 2018.
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The final aggregate configuration for the SSMS proof-of-concept flight will be taken into
account when selecting the S^3 Challenge winner.
The main milestones of the S^3 Challenge are illustrated in Annex II.
5
Requirements
5.1
Mission Requirements
Sentinel Small Sat missions shall be complementary or provide added value to current
Sentinel family missions.
The Sentinel Small Sat mission shall include both the space segment infrastructure and the
ground segment infrastructure (e.g. flight operations, payload data acquisition, product
description, processing and distribution).
Main parameters regarding the Sentinel missions are reported in Annex I to this document.
Further information is available at https://sentinels.copernicus.eu.
5.2
Launcher Interface Requirements
The proposed Sentinel Small Sat mission shall comply with the “Small Spacecraft Mission
Service, User Manual for SSMS Proof of Concept Flight on VEGA”, DC/BD/ST/CDU
N17-003 Issue 1, Rev. 0, Feb. 2017.
Sentinel Small Sat missions using CubeSats shall be compatible with the CubeSat standard
[CubeSat Design Specification, revision 13, California Polytechnic, 20 February 2014] and
foresee the provision of a deployer compliant with the CubeSat standard, for example
supplied by the following companies:
· ISIS
· ECM
· Astrofein
· TYVAK
· Toronto University Deployers
· D-Orbit
Mathematical models supporting Mission Analysis activities foreseen by the SSMS Proof
of Concept Flight shall be provided to launch service provider by March 2018.
5.3
Ground Segment Requirements
The implementation of the Data Processing function shall be compatible with a Cloud
type-computing environment and to the maximum extent based on open source software.
The proposed mission shall comply with the free and fully open Copernicus Data Policy.
As a baseline the proposal shall assume an autonomous ground segment including all
functions (flight operations, payload data acquisition, processing and distribution). ESA
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may provide support to the processing and distribution of the data of the proposed Sentinel
Small Sat mission.
For related descriptions, the ESA Copernicus Sentinels On-Line (technical web site)
provides the necessary information and is accessible through the following link
https://sentinels.copernicus.eu.
5.4
Debris mitigation Requirements
The Sentinel Small Sats shall fully comply with the ESA debris mitigation policies (ESAADMIN-IPOL(2014)2 - Space Debris Mitigation for Agency Projects).
5.5
Quality Assurance & Safety Requirements
The following documents may be used to support the Product and Quality Assurance
activities by the developers:
Tailored ECSS Engineering Standards for IOD CubeSat Projects, ref. TECSY/128/2013/SPD/RW, issue 1, revision 3, 24 November 2016.
Product and Quality Assurance Requirements for IOD CubeSat Projects, ref. TECSY/129/2013/SPD/RW, issue 1, revision 2, 05 October 2016.
6
Planning
The Sentinel Small Sat mission shall be designed, developed, tested and delivered for
launch within 12 months of the prize award date and in any case by the SSMS Proof of
Concept Flight on Vega required delivery date.
The mission shall be a hands-off programme for ESA. The proposers are free to engage the
support of other agencies or institutions to ensure the degree of project oversight they
consider useful. Under no circumstances ESA shall be held responsible for the completion
or accomplishments of the mission or any consequential situations or events.
7
Financial & Contractual aspects
The winner of the Sentinel Small Sat (S^3) challenge shall be awarded 1 MEuro and
provided with one launch service free of charge.
ESA shall decide on an incremental payment plan based on the procurement plan by the
bidder.
The team behind the winning proposal will be asked to sign a contract with ESA which
will serve to identify the rights and obligations of the team towards ESA, in particular the
way the funding is disbursed to the team. For this purpose ESA’s General Clauses and
Conditions
for
Contracts
shall
apply
[http://www.esa.int/About_Us/Law_at_ESA/Highlights_of_ESA_rules_and_regulations]
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8
Communication and Outreach
Proposals shall include a plan for innovative (including social media) communication and
outreach solutions to be implemented throughout the entire S^3 lifecycle (from design to
operation). The goal will be to inform through story telling and share the excitement and
innovative spirit leading to the birth of the first Sentinel Small Sat mission.
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Annex I
Sentinel Missions
Sentinel missions are part of the GMES/Copernicus Space Component (CSC).
The CSC includes a space segment and a ground segment. The space segment is
composed of the Sentinel-1,-2, -3, -5 Precursor, and -6 satellites, the Sentinel-4 and -5
payloads, and the Copernicus Contributing Missions (CCMs). The ground segment is
composed of the Sentinels Payload Data Ground Segments (PDGS), the Flight Operation
Segment (FOS), the Data Access System, and the Collaborative Ground Segment.
Space Segment
Mission fact sheets for each Sentinel are provided at the end of this Annex.
The Sentinel launch manifest is reported below.
Sentinel-1A
Sentinel-2A
Sentinel-3A
Sentinel-1B
Sentinel-2B
Sentinel-3B
Sentinel-4A
Sentinel-4B
Sentinel-5P
Sentinel-5A
Sentinel-5B
Sentinel-5C
Sentinel-6A
Sentinel-6B
Launch – 3 April 2014
Launch – 22 June 2015
Launch – 16 February 2016
Launch – 25 April 2016
Launch – 6 March 2017
FAR – October 2017
delivery to MTG – Nov 2019
delivery to MTG – Q3 2020
Launch – June 2017
AR – June 2019
delivery to MetOp-SG – Q3 2020
delivery to MetOp-SG – Q4 2021
FAR – Apr. 2020
FAR – Q2. 2025
Ground Segment
Payload Data Ground Segment
The Payload Data Ground Segment (PDGS) is a distributed ground segment that uses
existing facilities, infrastructure and expertise to support Sentinel missions and provide
access to CCMs.
The multi-mission PDGS provides the generic elements (archives, interfaces, catalogues,
networks, user services, etc.) for the Sentinels and through the Data Access Integration
Layer, overall data delivery monitoring, multi-mission order handling, etc. The PDGS also
includes Sentinel-1, -2 and -3 specific elements such as algorithms and processors,
modules related to the customisation/adaptation of mission planning, user services and
facilities for acquisition, archiving, and dissemination and calibration/validation functions.
Annex I Page 1
These mission-specific elements are integrated into the configured multi-mission
infrastructure which will be deployed in the operational centres.
Flight Operations Segment
The Flight Operations Segment (FOS) of the CSC is the collection of software and
hardware needed to monitor and, if required, modify flight operations of the Sentinels.
All commands to the Sentinels originate from the FOS, and all telemetry from the
Sentinels flow through the FOS. The FOS provides commanding of the Sentinels for
communications and, as needed for commissioning and contingency operations, uplink
observation plans, scripts and command sequences that are used to execute most
operations. The FOS also uplinks flight software when changes are required.
The FOS controls the execution of the observation plan and coordinates commands and
data needed to maintain the spacecraft in its orbit. The FOS receives all telemetry data
from the Sentinels, real-time engineering telemetry and analyzes recorded engineering
telemetry to ensure health, safety, and performance of the spacecraft.
CSC Collaborative Ground Segment
The CSC Collaborative Ground Segment, with non CSC-funded functions and elements,
provides supplementary access to Sentinel Missions data either through specific data
acquisition services (e.g. Quasi-Real-Time), or specific data products.
Mission Management and Operations
Sentinel operations are performed in accordance with the Sentinels High-Level Operations
Plan (HLOP) document available on-line at:
https://sentinels.copernicus.eu/documents/247904/351367/Sentinel+High+Level+Operatio
ns+Plan
Routine operations start after the commissioning and ramp-up phase of the Sentinels.
Sentinel-1A & -1B and Sentinel-2A, have started Routine Operations.
The up-to-date Sentinel-1 observation scenario is available online at:
https://sentinels.copernicus.eu/web/sentinel/missions/sentinel-1/observation-scenario
The detailed Sentinel-1 observation plan in the form of acquisition segments is published
at:
https://sentinels.copernicus.eu/web/sentinel/missions/sentinel-1/observationscenario/acquisition-segments
The detailed Sentinel-2A observation plan in the form of acquisition segments is published
at:
https://sentinels.copernicus.eu/web/sentinel/missions/sentinel-2/acquisition-plans
Annex I Page 7
Regular Sentinel-1, -2A, 3A mission status reports are released weekly on Sentinel Online
(available at sentinels.copernicus.eu).
Sentinel Data Dissemination
The data access system through which ESA disseminates Copernicus Sentinel products is
constantly evolving to remain in step with the growing user demand and data volumes. In
its current configuration, the data access system consists of 4 logical data hub instances
through which users can access Copernicus data (i.e. Sentinel core products):
•
•
•
•
the Open Access Data Hub (SciHub) - open to everybody, on the basis of selfregistration;
the Copernicus Services Data Hub (CopHub) – open to the Copernicus Services
and EU institutions;
Collaborative Data Hub (ColHub) - open to GSC and Copernicus Participating
States, following signature of a CollGS agreement with ESA;
the International Access Hub (IntHub) – open to international partners, following
signature of a technical arrangement with ESA.
The underlying data hub software (DHuS) is managed within an open source framework in
order to respond efficiently to new user requirements and allow re-use of the software by
various stakeholders. The latest version of the DHuS open source is available online at
https://github.com/SentinelDataHub/DataHubSystem. The DHuS software is being
progressively adopted by several stakeholders, e.g. Member States, International partners
and Industry.
Data Access Copernicus Contributing Missions
The data offer and information for data access are presented on the CSCDA web portal
(http://spacedata.copernicus.eu). The status of CORE datasets implementation and data
delivery as well as the quota consumption per project within additional datasets is
published
at
https://spacedata.copernicus.eu/web/cscda/data-provision-status.
Annex I Page 3
Copernicus Sentinel-1 Project Data Sheet
Mission Profile:
C-Band SAR Payload:
·
·
·
·
·
·
·
·
·
·
·
·
·
·
·
·
·
Sentinel-1 Mission Objectives:
European polar orbiting radar observatory
providing continuity of SAR data for operational
applications.
These services include applications such as:
·
·
·
·
·
Monitoring sea ice zones and the arctic
environment
Surveillance of marine environment
Monitoring land surface motion risks
Mapping of land surfaces: forest, water
and soil, agriculture
Mapping in support of humanitarian aid
in crisis situations
Annex I Page 4
Sentinel-1A Launch: 3 April 2014
With a Soyuz launcher from CSG (Kourou)
Sentinel-1B Launch: Early 2016
With a Soyuz launcher from CSG (Kourou)
7 years lifetime (consumables for 12)
Sun-Synchronous orbit @ 693km
Inclination: 98.18 deg.
Mean LST: 18:00 at Ascending Node
12-days repeat cycle, 175 orbits/cycle
96 hrs operative autonomy
Maximum eclipse duration:19 minutes
Spacecraft Platform:
· 3 axis stabilized, yaw/pitch/roll steering (zero Doppler)
· 0.01 deg attitude accuracy (each axis)
· Right looking flight attitude
· 10 m orbit knowledge (each axis, 3s) using GPS
· Spacecraft Availability: 0.998
· S/C Launch Mass: 2300kg (incl. 130 kg fuel)
· Solar Array Power: 5900W (End-of-Life)
· Battery Capacity: 324 Ah
· Science Data Storage Capacity: 1410 Gb (End-of-Life)
· Communication Links:
· S-Band TT&C Link: TC at 64kbps, and TM at 128kbps/2Mbps
· X-Band Payload Data Downlink at 520Mbps
· Optical Downlink for Payload Data Relay through EDRS at
520Mbps
Centre frequency: 5.405 GHz
Polarisation: HH, HV, VH, VV
Incidence angle: 20º – 45º
Radiometric accuracy: 1 dB (3σ)
NESZ: -22 dB
PTAR: -25 dB
DTAR: -22 dB
Four nominal operational modes designed
for inter-operability with other systems:
·
·
·
·
Strip map Mode with 80 km swath and
5x5 metre (range x azimuth) spatial
resolution
Interferometric Wide Swath Mode with
250 km swath, 5x20 metre (range x
azimuth) spatial resolution and burst
synchronisation for interferometry
Extra-wide Swath Mode with 400 km
swath and 20x40 metre (range x
azimuth) spatial resolution
Wave Mode with 5x5 metre (range x
azimuth) spatial resolution leap-frog
sampled images of 20x20 km at 100 km
along the orbit, with alternating 23° and
36.5° incidence angles.
COPERNICUS Sentinel-2 Project Data Sheet
System:
·
Senti
nel-2 Mission Objectives:
The Sentinel-2 twin satellite system will
systematically acquire high resolution images
from Land with unprecedented revisit between 56deg and +84deg. Its fields of application are
vegetation (agriculture and forestry), human
inhabitancy, and their interactions.
User products:
· Level1c ortho-rectified Top Of Atmosphere
reflectance,
archived
systematically,
provided as 100km x 100km tiles. This
product includes the parameters for
reflectance to radiance conversion.
· Prototype Level2a ortho-rectified Bottom Of
Atmosphere
reflectance
“tool
box”,
including cloud screening and atmospheric
corrections.
Annex I Page 7
7.25 years nominal in orbit lifetime
(consumables for 12years)
· Sun-Synchronous orbit @ 786km
· Mean LST: 10:30 at Descending Node
· 5 days global geometric revisit (2 satellites)
· 15 days of operative autonomy.
Multispectral Instrument Payload:
Push broom Multi Spectral Imager, using a three
mirrors anastigmatic SiC telescope concept:
· Separate VNIR and SWIR detection chains
· 13 multispectral channels: between 400 nm
and 2300 nm
· Spatial resolution: 10m, 20m, 60m
· Spectral resolution: 1nm – 180 nm
· Observation mode: ~40 min/orbit, nadir
pointing
· Radiometric accuracy: < 5 %
· Radiometric resolution: 12 bits
· Geo-location: < 20m (3)
· Swath: 290Km
· Mass: 290kg
· Power consumption: 250W
· Data rate: 490Mbits after on-board
compression
Spacecraft:
· AOCS: 3 axis stabilised (on-board attitude
knowledge <10rad (2 )
· Launch mass: 1200 kg (117kg of N2H4
included, 60kg of margin)
· Power: 7.2m2 solar array, 1700W EOL
· 2.4 Tbits of on-board mission data storage
· 2Gbits TM/TC storage
· Authenticated TT&C at S band: 64kb/s up
with authenticated/encrypted commands,
2018Kb/s down
· X-band Data transmission at 520Mb/s (8psk)
Launch Vehicle:
· VEGA and Rockot: launch capability of
1225Kg at 786km
Optical Communication Payload:
· Optical Communication Payload for mission
data relay through EDRS: 600Mb/s
transmission capability for Sentinel-2.
COPERNICUS Sentinel-3 Project Data Sheet
Mission Orbit:
Type:
Frozen, sun-synchronous low earth orbit
Repeat cycle:
27 days (14+7/27 orbits per day)
Average altitude:
814.5km over geoid
Mean solar time:
10h00 at descending node
Inclination:
98.65o
S Launcher:
Rockot/Plesetzk (S3B)
entinel-3 Mission Objectives:
Spacecraft Configuration:
Sentinel-3 is dedicated to operational oceanography & Launch mass:
1250kg
global land applications, providing 2 days global coverage Stowed dimensions: (H)3710 mm (W)2202 mm (L)2207mm
Earth observation data (with 2 Satellites) for sea and land Attitude control: Gyroless, 3 axis stabilised platform with 3
applications with real-time products delivery in less than 3
star tracker heads, 4 reaction wheels and
hours.
magnetic off-loading.
Acquire data to feed ocean/atmosphere models and to derive
Geodetic pointing and yaw stearing
global land products and services.
Orbit control:
8x1N hydrazine thrusters for in-plane and
• Sea/land colour data, in continuation of Envisat/MERIS.
out-out plane manoeuvres.
• Sea/land surface temperature, in continuation of
130kg hydrazine tank capacity
Envisat/AATSR.
3 meter accuracy real-time onboard orbit
• Sea surface and land ice topography, in continuation of
determination based on GPS and Kalman
Envisat altimetry.
filtering
• Along-track SAR for coastal zones, in-land water and
Power: 2.1 kW rotary wing with 10 m2 triple junction
sea ice topography.
GaAs European solar cells.
• Vegetation products by synergy between optical
Ion battery, 160Ah
instruments.
Communications:
64kbps uplink, 1Mbps downlink
Mission Duration:
S-band command and control link (with
A series of satellites, each designed for a lifetime of 7 years,
ranging).
shall be launched to provide an operational service over 15
2x280Mbps X-band science data downlink
to 20 years. Furthermore, two satellites shall operate at any
384 Gbit solid state mass memory
time to fulfil the mission requirements.
Autonomy: Position timeline and on-board sun ephemeris for
>2 weeks nominal autonomous operations.
Annex I Page 10
Payload:
OLCI: Ocean and Land Colour instrument
Swath:
1270km, with 5 tilted cameras
Spatial sampling:
300m @ SSP
Spectrum:
21 bands [0.4-1.02] μm
Radiometric accuracy:
2% absolute, 0.1% relative
SLSTR: Sea and Land Surface Temperature Radiometer
Swath: 180rpm dual view scan, 750km (backwards) and
1420km (nadir)
Spatial sampling: 500m (VIS, SWIR), 1km (MWIR, TIR)
Spectrum:
9 bands [0.55-12]μm
Noise equivalent dT:
50mK (TIR) at 270K
SRAL: SAR Radar Altimeter
Operation frequency:
dual C and Ku bands
Radar measurement modes:
LRM and SAR
Pulse Repetition Frequency (PRF): 1923.87 Hz and 17.8
kHz
Tracking modes: Closed-loop and Open-loop
Total range error: 3cm
MWR: MicroWave Radiometer (SRAL wet troposphere
correction by co-located measurements)
Operation frequency:
dual 23.8GHz 36.5GHz
Radiometric accuracy:
3K absolute, 0.6K relative
POD: Precise Orbit Determination
Ground processing of GPS data with enhancement through
Laser Retro-Reflector and DORIS (CFI)
Final accuracy:
3cm (after processing)
Annex I Page 7
Sentinel5 Mission Objectives:
The Sentinel-5 mission covers the needs for
continuous monitoring of the atmospheric
chemistry at high temporal and spatial resolution
from a low-Earth orbit. The main data products
will be O3, NO2, SO2, HCHO, CO, CH4 and
aerosol optical depth, enabling services
addressing global air quality monitoring and
composition-climate interaction.
Mission Profile:
The Sentinel-5 UVNS instrument will be
embarked on the MetOp-SG satellite A. Global
coverage is achieved with a daily revisit time.
Annex I Page 10
Sentinel-5 Project Data Sheet
Instrument Coverage:
The Sentinel-5 UVNS instrument is a high
resolution spectrometer, covering the following
wavelengths bands:
· ultraviolet (270-370 nm),
· visible (370-500 nm)
· near-infrared (685-773 nm)
· short-wave infrared (1590-1675 & 23052385nm)
The instrument consists of 5 spectrometers, in a
push-broom
configuration
with
a
108°
instantaneous Field-of-View.
The spatial resolution is about 7 km at Nadir and
the spectral resolution ranges between 0.25 nm for
the longest wavelengths and 1.0 nm at the shortest
wavelengths.
Instrument Elements:
The instrument is composed of the following units:
· the Instrument Optical Module which
contains the optical and detection part
· the Detection Support Electronics
· the Instrument Control Subsystem.
Instrument Characteristics:
· Allocated Mass = 292.5 kg
· Allocated Mean Power = 250 W
· Data Rate during acquisition = < 20
Mbps
· Mission reliability = > 0.75 @ 7.5
years
Flight Acceptance Review:
Sentinel-5 PFM shall be ready for launch
with MetOp-SG A1 in 2021
Sentinel-5 FM2 shall be ready for launch
with MetOp-SG A2 in 2028
Sentinel-5 FM3 shall be ready for launch
with MetOp-SG A3 in 2035
Flight Operations & Payload Data
Processing (and Dissemination):
EUMETSAT (Darmstadt, Germany)
COPERNICUS Sentinel-5 Precursor Project Data Sheet
Mission Profile:
Spacecraft Platform:
·
·
·
·
·
·
Sentinel-5p Mission Objectives:
European polar orbiting UV-VIS-NIR-SWIR
spectrometer payload providing continuity of
atmospheric chemistry data at high temporal and
spatial resolution with increased frequency of
cloud-free observations for the study of
tropospheric variability.
Provides measurements of:
UVN:
· Ozone
· NO2
· SO2
· Formaldehyde
· Aerosol
SWIR:
· CO
· CH4
NIR:
· Clouds and surface albedo.
Annex I Page 7
7 years lifetime
Sun-Synchronous orbit @ 824km
Inclination: 98.730 deg.
Mean LST: 13:30 at Ascending Node
16-days, 227 orbits repeat cycle
72 hrs operative autonomy.
TROPOMI Payload:
Astrobus L 250 M from ASTRIUM
3-axis stabilised with yaw steering
Mono-propellant hydrazine propulsion.
Spacecraft Launch Mass:
~ 900 kg.
Spacecraft Power:
UV-VIS-NIR-SWIR
push-broom
grating
spectrometer. UVN module provided as a 1500 W (EOL)
430W average power consumption.
national contribution by the Netherlands:
·
·
·
·
·
·
·
·
Number of channels: 4
Spectral range: 270-500 nm, 675-775 nm,
2305-2385 nm
Spectral resolution: 0.25-1.1 nm
Observation mode: nadir pointing, global
daily coverage, 7*7 km2 ground pixel
Radiometric accuracy: ~ 2 %
Mass: 200kg
Power consumption: 120 W average
Data Volume: 140 Gbits/orbit.
Science Data Storage Capacity:
480 Gbit (EOL) using flash-memory technology.
Communication Links:
S-Band TT&C, 64 kbit/s uplink, 128 kbit/s-1
Mbit/s downlink with ranging and coherency
X-Band Science Data, 310 Mbit/s downlink
OQPSK.
Launch Vehicle:
ROCKOT.
Indicative FAR date:
April 2016
COPERNICUS – Jason-CS/Sentinel-6
Project Data Sheet
AMR-C (Climate-quality microwave radiometer – NOAA/JPL contribution):
3 channels.
GNSS POD Receiver (heritage from Sentinel-3b) provides GNSS measurements for Precise Orbit
Determination.
DORIS enables precise orbit determination, as well as providing on-orbit position to the satellite
attitude control.
Laser Retroreflector Array (NOAA/JPL contribution) enables tracking by ground-based lasers.
TriG Receiver for Radio Occultation (NOAA/JPL contribution) uses GNSS measurements for RO.
Spacecraft
Based on CryoSat with deployable solar-array extension flaps; most electronics mounted on nadir
plate acting as radiator; GaAs solar arrays, with 850 W minimum (end of life); 2x108 Ah Li-ion
batteries. Attitude: 3-axis stabilised local-normal pointing; mono-propellant propulsion system for
deorbiting and orbit maintenance.
Jason-CS/Sentinel-6 Mission
To provide continuity of the reference, high-precision ocean topography service after Jason-3.
Mission Duration
·
6 months commissioning
·
5 year operational mission.
Mission Orbit
·
Type:
·
Repeat cycle:
·
Mean altitude:
·
Inclination:
LEO, non sun-synchronous
10 days
1336 km
66°
Spacecraft and Payload
Spacecraft design based on CryoSat-2, with necessary adaptations for the higher, mid-inclination
orbit, harsher radiation environment, increased payload and space debris mitigation.
Instruments
Poseidon-4 (SAR Radar Altimeter):
·
Interleaved mode providing conventional pulse-width limited and SAR altimetry
simultaneously (only the pulse-width limited data recorded over land)
·
Possibility of following a built-in digital elevation model for improved tracking over land;
·
Separate SAR and pulse-width limited modes possible as fall-back.
Annex I Page 10
- Dimensions (flight configuration) 5.13 m x 4.17 m x 2.35 m
- Dimensions (stowed configuration) 5.13 m x 2.47 m x 2.35 m
- Mass
1440 kg (wet)
- Power
891 W average consumption
- Data volume:
order of magnitude 1200 Gbit/day
- on-board storage by SSR 496 Gbits (beginning of life)
Launch Vehicle
US launcher baseline (Falcon-9, Atlas-4 or Antares) procured by NASA-JPL/KSC.
Flight Operations
Mission control for LEOP and IOV from ESOC. Commissioning and routine operations from
EUMETSAT. Two operational ground stations, at Fairbanks and Kiruna (to be confirmed)
RF Links
- X-band data downlink:
150 Mbps at 8.090 GHz
- S-band TTC link:
16 kbps uplink,32 kbps downlink
Payload Data Processing
Data processing and dissemination at EUMETSAT and NOAA.
Annex II
S^3 Main Milestones
1 April 2017 => Sentinel Small Sat (S^3) Challenge call opens
30 June 2017 => S^3 Proposal Submission Deadline
21 July 2017 => S^3 best proposals short-list
26 July 2017 => S^3 final evaluation team meeting
October 2017 => Master Prize Awards ceremony
March 2018 => S^3 Math Models delivered to launcher
End 2018 => Launch
Annex II Page 1