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

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

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

RCM Description 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

RCM Description – Three Segments 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

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

Design Parameters – Key Drivers 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

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

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

Nomenclature and Outcome– Phases A and B 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

Nomenclature and Outcome– Phases C and D 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

Nomenclature and Outcome– Phase C Milestones 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

Nomenclature and Outcome– Phase D Milestones 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

Nomenclature and Deliverables – Sequencing Launch 1 Launch 2

Phase C Phase C Milestones

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

System Description – Specifications Bus Canadian Smallsat Bus Launcher Falcon 9 specifications (for design) can use PSLV, DNEPR Total Mass 1400 kg Antenna 9.45m2 Power <1600 W peak; <220 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

Bus Description – RCM Bus Pictures courtesy of Industrial team GPS Reaction Wheel Sun Sensor Magnetometer Battery SUN SENSOR Sun acquisition / Fail Safe Recovery / Qualified by heritage and design / Single Detector Cosine FOV / 10g / 500uA to 1300 uA MAGNETOMETER Provides attitude reference through 3 analogue signals proportional to 3 mutually normal projections of earth magnetic field / Measurement Range: +/- 70000 nT (Adjustable) / Accuracy: 150 Nt / Mass: LE 300g / Power consumption: < 1W / Qualification Status: Delta Qual Required MAGNETO TORQUE ROD To be qualified / Nominal Input Voltage: 28 V / Dipole Moment: 140 Am2 REACTION WHEEL Qualified / Momentum @ 6000 RPM: 18 NMS / Voltage: 22-34V / Mass: < 7kg / Power: Max :< 180W, Steady State: < 35W, Quiescent: < 11W. STAR TRACKER Configuration: 2 optical heads with 30 deg baffle, 2 Electronic Units with RS422 communication interface, Cross-strapping of optical heads and electronic units / Delta qualification required. BATTERY Cell level delta qualification (random vibrations) / Battery inherently fault tolerant / Mass for battery pack (2 modules): 33.6 kg / Vmax : 33.6 V, Vmin: 22V / Capacity: 66 A-Hr, Nominal / Operating Temperature: 0 degC to 25 degC. Star Tracker Power Control Unit Torque Rod N2 S-Band Antenna S-Band Transponder

System Description – RCM Payload Representations courtesy of Industrial team Power Distribution Unit Tx/Rx Module SAR Antenna Tile Controller Unit SYNTHIETIC APERTURE RADAR ANTENNA Two identical panels / Motorized deployment system / ncreased pointing accuracy: Direct connection between the antenna and the star tracker, Decoupled from the bus distortions and movements. TRANSMIT / RECEIVE MODULE High Temperature Cofired Ceramic (HTCC) package / Simplified assembly process and low recurring cost compare to Radarsat-2 TRM / Use of MMIC (Monolithic Microwave Integrated Circuit) designed by CSA. TILE CONTROLLER UNIT Power distribution to 4 TRMs / Digital Interface between the PLCU and the TRMs / nterconnection to the TRMs using flat flexible cable and solder less compression connectors. MASS MEMORY UNIT Internal Redundant / Large storage capacity of 700Gb at end of life / Output Data Rate of 300Mb/s (2 X 150Mb/s). CENTRAL ELECTRONIC UNIT Demodulation, modulation and filtering are performed by Digital Signal Processing for optimum performance and improve flexibility / 16 Resolution bandwidth from 14 to 100MHz / May store and generate up to 110 pre-defined pulse waveforms. PAYLOAD CONTROLLER UNIT Internal Redundant / Digital Interface between the Bus CDH (Command and Data Handling) and the Payload / Digital interfaces with all payload sub-systems. POWER DISTRIBUTION UNIT Internal Redundancy / Power Interface between the Bus Power Control Unit (PCU) and the SAR Antenna / Prime power switching for the TCUs and operational heaters. Payload Controller Unit AIS Mass Memory Unit Central Electronic Unit N2

System Description – Ground Segment Baseline St-Hubert (X+S), Svalbard (X+S), Masstown and Aldergrove (X)

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

Project Status – Schedule and Cost Distribution Y1 Y2 Y3 Y4 Y5 Y6 Y7 Y8 Y9 Y10 Y11 Y12 Y13 Y14 Y15 Phase A Phase B Phase D Based on MCP minus E1 Phase A: 1.4% (State between 1 – 2%) Phase B: 4.4% (State between 4 – 5%) Phase C: 21.3% (State between 15 – 25%) Phase D: 72.8% (State between 70 – 75%) Phase E1 is 3% of the total MCP cost. Now Ops Phase N

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

Industrial Team

Industrial Team – Contract Arrangement & Control Typical contract structures: Cost reimbursable (Progress payments) Firm Fix Price (Milestone payments) Canadian content Regional distribution Earned Value Management 10% of total value of Canadian contracts to Atlantic Canada’s firms; 10% of total value of Canadian contracts to Prairie Province firms; 10% of total value of Canadian contracts to BC’s firms; 35% of total value of Canadian contracts to Ontario firms and; 35% of total value of Canadian contracts to Quebec firms. N

Back Up

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 1) Maritime surveillance - ice - wind - ship monitoring 2) Ecosystem monitoring - forestry - agriculture - wetlands - coastal changes - permafrost) 3) Disaster management - mitigation - warning - response - recovery -Natural Resources Canada, Environment Canada, Department of Fisheries and Oceans, Department of National Defence, Transport Canada, Agriculture and Agri-foods Canada, Parks Canada, Industry Canada. -Atlantic Canada Opportunities Agency, Western Economic Diversification Canada, Canada Economic Development-Quebec, Department of Foreign Affairs and International Trade, Public Works and Government Services Canada, Communications Security Establishment Canada. N

System Description – Spacecraft SOLAR ARRAY SUBSYSTEM Solar Cell type: BTJ, 2nd generation triple junction Two Arrays: Main array with deployment angle = 33 deg relative to axial axis, Safe hold array fixed to opposite side panel (used during LEOP and in safe hold spin configuration) Maximum Power output of main array at End of Life: 917W Orbit Average Power output of main array at End of Life, Maximum Eclipse: 580W. PROPULSION SUBSYSTEM Qualification Status: Modified Development. All components have flight heritage / Propellant: High Purity Hydrazine / Mass: 90 kg (with propellant). BUS STRUCTURE Qualification Status: New Development / Honecomb panels: 13, including mid-deck and + Z (end) panels, Bus stiffener panel and payload stiffener panel / Edges of exterior panels equipped with threaded inserts / PFM level Modal Tests to be conducted to seek out natural frequencies using analogue payloads units. N

System Description – Spacecraft Exterior Layout

System Description – Security Level 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

Payload Description – Automatic Identification of Ship (AIS) 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.

Payload Description – Model Philosophy of Main Units

Bus Description – Model Philosophy of Bus Ssyst/Unit POWER CONTROL UNIT New Development / Internally Redundant: Controller Cards / Highly radiation tolerant components / 30 kg / Controller Card (2), Switch Card (5), Pyro Card (2) Propulsion Card (1), Battery Card (1), Solar Array Card (1) . GPS Redundant GPS Receiver Systems / Qualified / Extensive flight heritage / High accuracy solution: 10m along track, 10m cross track and 15m radial, 3 sigma / On-orbit SW updatable . S-BAND ANTENNA Omni directional / To be qualified / 2200-2400 MHz / 50 deg to 90 deg half cone angle coverage / Power Handling: 5W / Temperature Range: -115 degC to 120 degC / Mechanical Load: 40g / Natural Frequency: > 100 Hz / Mass: 225g. S-BAND TRANSPONDER Requires delta Qualification / Frequencies (same as Radarsat-2): Uplink: 2053.458333MHz, Downlink: 2230 MHz / Bandwidth: Downlink: 500kbps nominal, 40 kbps emergency, Uplink: 4 kbps BPSK/PM demodulator / Power: 5W / Discrete unit commanding and telemetry: RS422 / Dual redundant.

RCM Description – System Diagram 1 NRTD: Near Real Time Ship Detection. (1) SXGT: S/X Band Ground Terminal

Roles & Responsibilities – PMO Level Integration 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) 35

Project Status – Requirements Evolution

[SYS2010] Imaging Time Per Orbit [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.

[SYS3100] AIS Operating Time Per Orbit [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.