RADARSAT Constellation Mission:

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RADARSAT Constellation Mission The Making of
Representation courtesy of MDA Systems Ltd
Alain Carrier, Director Earth Observation
Projects RCM Project Manager
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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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• Scalable Constellation of three small SAR1
  satellites
• Primary objective is to support the operational
  requirements of Canadian Government departments
• Canadian Government-owned and operated
• Prime contractor MDA Systems Ltd

(1) Synthetic Aperture Radar
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• Space Segment
• Three satellites (Bus, SAR payload, AIS)
• Ground support equipment (mechanical, electrical)
• Launch Segment
• Launch system
• Launch interface
• Supporting equipment

• Ground Segment
• Order Handling
• Mission Planning
• Spacecraft Control
• S-band/X-band Grd Terminal
• Reception and Archiving
• Product Generation
• Image Quality
• Spacecraft Simulator

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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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• Continuity of C-Band SAR for Operational Users
• Improved revisit over wide areas
• Responsive Ground Segment (Fast tasking and
  latency)
• Smaller, more cost efficient satellite
  development
• Improved reliability (i.e. redundancy and
  scalability)
• Evolution from RADARSAT-2 to wider Operational use

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Design Parameters Mission Requirements

• Three satellites with a potential of six
• Average daily coverage of Canadian waters and
  regular land coverage
• Average daily global access
• Data analyzed in near real time for operational
  applications
• 4-day Coherent Change Detection using SAR
  interferometry
• Gradual implementation with two launches
  separated by16 months
• Gradual replacement of aging satellites

RADARSAT Constellation daily coverage
RADARSAT-1 or 2 daily coverage
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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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• Phase 0/A Initiation and Planning
• Opportunity Assessment
• Advanced studies and concept design
• Industrial capability establishment
• Critical technology risk reduction
• Preliminary cost and schedule estimates
• Development confirmation of requirements

• Phase B Preliminary Definition
• Detailed requirements flowed down
• Risk reduction activities continued
• Preliminary design cycle completed
• Launch environment defined
• Mission Preliminary Design Review

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• Phase C Detailed Definition
• Completes design of all spacecraft elements
• Establishes implementation baseline
• Baseline launch vehicle selected
• LLI and associated NRE initiated
• Ground segment subsystem requirements established
• Ground segment Preliminary Design Review
• Mission Critical Design Review

• Phase D Implementation
• Manufacturing, AIT1, launch commissioning of
  each spacecraft
• Design, manufacturing, AIT of ground segment
• Operations development
• Training of operations maintenance personnel
• Constellation Commissioning Complete Review

(1) Assembly, Integration Test
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• Payload Critical Design Review
• SW CDR
• Power Distribution Unit CDR
• T/R module CDR
• Payload Electrical Model complete
• Antenna CDR
• Tile Controller CDR
• Payload Controller Unit CDR
• Central Electronic Unit CDR
• AIS PDR
• Mission AIT Planning
• AIT Dev Plan
• Ops Development
• Ops Dev Review
• Draft LEOP plan and Rehearsal plan

• Bus Critical Design Review
• Power CDR
• Attitude Determination Ctrl Syst. CDR
• Power Control Unit Qual. Status Review
• Propulsion CDR
• MGSE CDR
• SW CDR
• Command Data Handling QSR
• Thermal CDR
• Communication CDR
• Structural CDR
• Harness CDR
• Ground Segment Development
• GS PDR
• SIM PDR
• SCS PDR
• System Requirements Review for
• Restoration Archiving / Product Generation /
  Image Quality subsystems
• Order Handling / Mission Planning subsystem

Mission Critical Design Review
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• Ground Segment Final Acceptance Review
• Bus, Payload S/C Test Readiness Review
• Manufacturing Readiness Review
• Mission Preliminary Acceptance Review

• Operations Readiness Review
• Flight Readiness Review
• Commissioning Complete Review Proto-Flight
  Model
• Commissioning Complete Review (Flight Model 1,
  Flight Model 2)
• Constellation Commissioning Complete Review

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Launch 1
Launch 2
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Phase C
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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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Bus Canadian Smallsat Bus
Launcher Falcon 9 specifications (for design) can use PSLV, DNEPR
Total Mass 1400 kg
Antenna 9.45m2
Power lt1600 W peak lt220 W average
Orbit 600 km, 100m radius orbital tube
Polarisation Single Pol / Dual cross selectable pol Compact polarimetry available on all modes One fully polarimetric mode
Imaging Time 12 minutes/orbit (peak 20 minutes every three orbits) 10 minutes continuous imaging
Lifetime 7 years (each satellite)
Drawing courtesy of MDA Systems Ltd
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Pictures courtesy of Industrial team
GPS
Reaction Wheel
Sun Sensor
Magnetometer
Battery
Star Tracker
Power Control Unit
Torque Rod
S-Band Transponder
S-Band Antenna
N2
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Representations courtesy of Industrial team
Power Distribution Unit
Tx/Rx Module
SAR Antenna
Tile Controller Unit
AIS
Mass Memory Unit
N2
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St-Hubert (XS), Svalbard (XS), Masstown and
Aldergrove (X)
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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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Y1
Y3
Y2
Y9
Y4
Y7
Y5
Y8
Y6
Y10
Y13
Y15
Y14
Y12
Y11
Phase A
Phase B
Phase D
Now
Ops Phase
N
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Outline

• Project Description
• Design Parameters
• Nomenclature and Outcome
• System Description
• Project Status
• Industrial Team

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• Typical contract structures
• Cost reimbursable (Progress payments)
• Firm Fix Price (Milestone payments)
• Canadian content
• Regional distribution
• Earned Value Management

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Back Up
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RCM Description Primary Objective

• Support the operational requirements of Canadian
  Government departments in the delivery of
  services to Canadians in areas of
• Maritime surveillance
• Ecosystem monitoring
• Disaster management

N
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N
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Representations courtesy of Industrial team

• High-grade crypto on-board the satellites (Crypto
  Flight Unit) and on the ground (Crypto Ground
  Unit) to encrypt all commands and telemetry as
  well as classified science data (as needed)
• RCM will be capable of handling both classified
  and unclassified Orders and Products
• Unclassified science data will be encrypted to a
  lesser level (commercial grade)
• Crypto Ground Units will encrypt commands
  originating from the CSA operations center as
  well as decrypt classified and unclassified
  telemetry and science data

Crypto Flight Unit
Crypto Ground Unit
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• An additional payload is being considered to
  receive AIS signal
• Would allow real time coherent acquisition of AIS
  signal with SAR image to identify vessels of
  interest.

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(1) SXGT S/X Band Ground Terminal
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• Project Management
• Schedule, Cost, Risks
• Technical progress integration (Space Ground)
• Implementation analysis
• Intellectual Property
• Mission Management
• Data Policy
• Data Utilization
• Application Development
• Commercialization License
• Governance (Approval and Reporting)

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SYS2010 Imaging Time Per Orbit. Each spacecraft
in the system shall be capable of imaging at any
time when all of the following constraints are
satisfied 1.No more than 36 minutes of imaging
in any moving window time period of duration
equal to three orbital periods. 2.No more than
20 minutes of imaging in any moving window time
period of duration equal to one orbital period.
3.No more than 10 minutes of imaging in any
moving window time period of duration 20 minutes.
4.The spacecraft is not in eclipse.
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SYS3100 AIS Operating Time Per Orbit. Each
spacecraft in the system shall be capable of
collecting AIS at any time when all of the
following constraints are satisfied 1.No more
than 51 minutes of AIS collection in any moving
window time period of duration equal to three
orbital periods. 2.No more than 25 minutes of
AIS collection in any moving window time period
of duration equal to one orbital period. 3.No
more than 15 minutes of AIS collection in any
moving window time period of duration 25 minutes.