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Earth Viewing Infrared Space System Sensor By Earth Viewing Systems (EVS)
Our Team Figure 1 – Company Organization EARTH VIEWING SYSTEM Program Manager Nafiseh Pishbin Chief Architect Mohammed Faissal Halim Chief  Scientist Ibrahim Siddo Sub-Contract Manager Lina Cordero Program Scheduler Erika Garofalo
Task ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Summary ,[object Object],[object Object],[object Object],Figure 2 – Area of Interest
Mission Concept Mission Operations Ground Element Launch Element Space Element Spacecraft Bus Payload Orbit and Constellation Subject Command, Control  and Communications Architecture Figure 3 – Mission Concept MISSION CONCEPT
Mission Requirements for EVIRS Table 1 – Mission Requirements Target Radiance or  Temperature Emissivity Radiance defined in Spectral Band (μm) Length × Width (Meters) Altitude Time Duration Mean Surrounding Background Radiance or Temperature Std Dev Background Radiance or Temperature Cloud Cover KTR Probability Of Detection Or Correct Classification (Percent) OTR Probability Of Detection Or Correct Classification (Percent) KTR/OTR Probability Of False Detection Or In-Correct Classification (Percent) Volcano 800K 0.8 400×400 Ground 2 Hours 400K N/C CFLOS 90 95 1 Volcanic Lava Flow 400K 0.8 -- 2000×2000 Ground Continuous 300K N/C CFLOS 95 97 1 Fire 500K 0.6 -- 10 Acres Ground 10 Minute (Flare-Up) 300K N/C CFLOS 90 95 0.1 Aircraft 1000 W/sr -- 2.7 – 3.0 Point Source 10kM 5 Minutes 1 µFlicks 0.0 μFlicks CFLOS 70 90 0.1 Oil Spillage 60F Variable: 0.5 to unity from 2 to 5 µm - 2000×2000 Sea Level Continuous 60F N/C CFLOS 90 99 0.01 Rocket 50,000 W/sr -- 2.7 – 3.0 Point Source Ground and 10kM 10 seconds 1 μFlicks 1 μFlicks CBLOS (10kM) 90 95 0.01 Missile 500,000 W/sr -- 2.7 – 3.0 Point Source see profile 100 seconds 1 μFlicks 1 μFlicks CBLOS (10kM) 97 98 0.001 High Energy Laser 10 W 10 μrad Beam Width -- 2.971365 Equiv Point Source Ground 100 millisec 1 μFlicks 0.0 µFlicks CFLOS 90 95 1 Oil Rig Burn Off 1000K See Oil Table 2.7 – 3.0 4.2 – 4.5 Equiv Point Source Ground 1 Hour 300K 0.0 μFlicks CFLOS 90 99 1 Industrial  Facilities 305K 0.75 --  100×100 Ground 24 Hours 287K N/C CFLOS 85 95 10 Special Event Unknown Unknown _ 50×50 Ground 1 second 1 µFlicks  0.0 µFlicks  CFLOS  90 100 0.1 All requirements shall be met simultaneously over the required surveillance area as defined in paragraph 1.0 of this RFP.  As an OTR only Probability of Stereo Coverage for any event shall be 0.90
Elevator Viewgraph Full Surveillance Coverage Mission Control Station Timely communication to the Users 24-7-365 Meets all target detection requirements Thorough Test Program Figure 4 – Elevator Viewgraph Sensors Targets Performance Volcano √ Volcanic Lava Flow √ Forest Fire √ Aircraft √ Oil Spillage √ Rocket √ Missile √ High Energy Laser √ Oil Rig Burn Off √ Industrial Facilities √ Special Events √
Targets Industrial Facilities Missile High Energy Laser Volcanic Lava Flow Aircraft Volcano Forest Fire Rocket Oil Rig Burn Off Oil Spillage
House of Quality Table 2 – House of  Quality Weight Meets Quality Cost 6 0.95 5.7 Dimensions 7 0.85 5.95 Weight 9 0.9 8.1 Software 8 0.8 6.4 Hardware 8 0.8 6.4 Staffing 4 0.9 3.6 Management Controls 8 0.9 7.2 Risk Management 9 0.78 7.02 Reviews 3 0.65 1.95 Technical Requirements 8 0.9 7.2 Timeline 5 0.75 3.75 Power 9 0.9 8.1 Expertise of Labor 8 0.95 7.6 Testing 9 0.9 8.1 Target Detection 9 0.8 7.2 TOTAL 110 94.27/110= 85%
Organizational Planning Figure 5 – Organizational Planning of System Design Preliminary Requirements Mission Objectives Mission CONOPS Mission  Architecture Trade Study Document Baseline for Further Study Proposal No Yes Evaluate Cost Performance Effectiveness
Organizational Planning Figure 6 – Organizational Planning of the System (V Model)
System Architecture Detection Power:  Solar Panel Processing Electronics Cooling System Optics & Detector Telescope Beam Splitter Reflector Refractor FPA and nTDI  FOV PSF Figure 7 – Flow-down Graph
Geostationary Orbit Definition: A geosynchronous orbit that is fixed with respect to a position on the Earth. Figure 8 – Geostationary orbit
Technical  Plan
Viewing Area 9 Degrees 15 Degrees Figure 9 – Viewing Area
Bore-sight with 16° FOV Figure 10 – Bore-sight with 16° FOV
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Bore-sight with 16° FOV
Telescope: Scanner Figure 11 – Scanner Three Mirror Anastigmatic  Figure 12 – Scanner 2D Design ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Scanning System
Telescope: Scanner Figure 13 – Scanner Signature
Focal Plane Table 3 – Scanner Technical Specifications SCANNER Array Size 12x512 Raw Charge Capacity N/A Me Detector size (Pixel Pitch) 15 µm Integration Time 100 to 20000 µs Mux Part Number N/A Integration Mode Spectral Band 2-5 µm Operational Mode Detector Cut-off >5 µm Frame Rate 1 to 50 Hz Operating Temperature 90 to 150 K Frame Time ms Nominal Irradiance (measured on FP) cm -2 s -1 Number of Signal Output Channels N/A NEI or NEDT at nominal background cm -2 s -1 Max Data Rate per Video Tap N/A MHz Max Irradiance cm -2 s -1 Cross Talk 1 % Min Irradiance cm -2 s -1 Power Dissipation N/A mW
Telescope: Starer Figure 14 – Starers Figure 15 – Starer 2D Design ,[object Object],[object Object],[object Object],[object Object],[object Object],8.96 Degrees 8.96 Degrees
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Telescope: Starer
Telescope: Starer Figure 16 – Starer Signature
Focal Plane Table 4 – Starer Technical Specifications STARER Array Size 1024×1024 Raw Charge Capacity N/A Me Detector size (Pixel Pitch) 18 µm Integration Time 100 to 20000 µs Mux Part Number N/A Integration Mode Spectral Band 2-5 µm Operational Mode Detector Cut-off >5 µm Frame Rate 1 to 50 Hz Operating Temperature 90 to 150 K Frame Time ms Nominal Irradiance (measured on FP) cm -2 s -1 Number of Signal Output Channels N/A NEI or NEDT at nominal background cm -2 s -1 Max Data Rate per Video Tap N/A MHz Max Irradiance cm -2 s -1 Cross Talk 1 % Min Irradiance cm -2 s -1 Power Dissipation N/A mW
Processor ,[object Object],[object Object],[object Object],[object Object],Figure  17 - SIDECAR™ ASIC
Cooler ,[object Object],[object Object],[object Object],[object Object],[object Object],Figure  18– Panel Internal Surface Figure  19 – Panel External Surface
Communication Systems ,[object Object],[object Object],[object Object],Figure  20 – Communication Systems
Other Peripherals ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Figure  21 – Gimbal System
Confusion Matrix Target Detection False Alarm Background Missing a Target TARGET: Volcano Sensoreality Target No target Target 100 4 No target 0 96
Confusion Matrix Volcano Sensoreality Target No target Target 100 4 No target 0 96 Forest Fire Sensoreality Target No target Target 90 30 No target 10 70 High Energy Laser Sensoreality Target No target Target 100 0 No target 0 100
Management Plan
Kick Off Meeting ,[object Object],[object Object],[object Object],[object Object]
System Requirements Review Mtg. ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Program Management Review Mtg. ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Preliminary Design Review Meeting
In Process Review Meeting ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Critical Design Review Meeting ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Test Readiness Review Meeting
Consent to Ship Review Meeting ,[object Object],[object Object],[object Object],[object Object],[object Object]
[object Object],[object Object],[object Object],[object Object],[object Object],Requirements Verification Review Mtg.
TIMELINE SCHEDULE
Risk Management ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
Vendors - Telescope Corning will provide the mirrors. L3 Communications  SSG – Tinsley will polish the mirrors  for our telescopes.
Vendors - Detectors ,[object Object],[object Object],Figure  22 – IR sensors
Vendors - Software ,[object Object],[object Object],Figure  22 – Software Capabilities Sample Figure  23 – Software Capabilities Sample
Vendors Telescope Cost and Design Information Space Programs Cooling System Sensors Space Programs Space Programs Gimbal System Processor
Table 5 – Budget Breakdown Budget Breakdown Category Item Quantity Price $ FPA Subsystem Starer 1 3.7M Scanner 1 4.0M Telescope Subsystem Starer 5 5.0M Scanner 1 1.0M Communication Systems Compress and Communications 1 3.0M First Level Threshold Algorithm 1 12.0M Target Detection and Report Generation 1 20.0M Signal Processor SIDECAR™ ASIC  1 0.052M Gimbaled Subsystem MODEL-25 PAN & TILT GIMBAL 6 36.0M Thermal Control Carbon-Carbon Radiator (Passive Cooler) 2 4.0M Human Resources Program Management Office 6 1.5M System, Integration and Test Engineering 15 3.0M Quality Engineering 4 1.0M Documentation and Specification Config. Manag. 10 2.0M Software Engineering 300K SLOC 60.0M TOTAL ~160.0M
Additional Specifications Table 6 – Additional Specifications Item Weight Power  Dimensions Length Width Height Gimbal System 180.0 lb 750 W 48.0” 34.5” 56.0” Cooling System 11.0 lb 0 0.022” 28.25” 57.24” FPA Scanner N/A 11 mW 0 0.0071” 0.3024” FPA Starer N/A 11 mW 0 0.72” 0.72” Processing System 16.0 lb 300 mW 17.5” 5.3” 13.4” Telescope Starer 354.2 lb N/A 78.0” 45.0” 47.76” Telescope Scanner 190.0 lb N/A 5.886” 3.0” 3.071” TOTAL 751.2 lb  < 1000 lb 750.322 W  < 1000 W 92” < 96”   48” < 48” 57.24” < 72”
Thanks & Acknowledgements ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
References ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
References ,[object Object],[object Object],[object Object],[object Object],[object Object],[object Object]
[object Object],[object Object],Follow Up Technical Errata 1 Professor DiNardo’s responses are in  red .
[object Object],[object Object],Follow Up Technical Errata 2
[object Object],Follow Up Technical Errata 3
[object Object],Follow Up Technical Errata 4
[object Object],[object Object],[object Object],[object Object],[object Object],Follow Up: Architect’s Personal Notes 1
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Follow Up: Architect’s Personal Notes 2
[object Object],[object Object],[object Object],[object Object],Follow Up: Architect’s Personal Notes 3
[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],[object Object],Follow Up: Architect’s Personal Notes 4

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Earth Viewing Infrared Space System Sensor

  • 1. Earth Viewing Infrared Space System Sensor By Earth Viewing Systems (EVS)
  • 2. Our Team Figure 1 – Company Organization EARTH VIEWING SYSTEM Program Manager Nafiseh Pishbin Chief Architect Mohammed Faissal Halim Chief Scientist Ibrahim Siddo Sub-Contract Manager Lina Cordero Program Scheduler Erika Garofalo
  • 3.
  • 4.
  • 5. Mission Concept Mission Operations Ground Element Launch Element Space Element Spacecraft Bus Payload Orbit and Constellation Subject Command, Control and Communications Architecture Figure 3 – Mission Concept MISSION CONCEPT
  • 6. Mission Requirements for EVIRS Table 1 – Mission Requirements Target Radiance or Temperature Emissivity Radiance defined in Spectral Band (μm) Length × Width (Meters) Altitude Time Duration Mean Surrounding Background Radiance or Temperature Std Dev Background Radiance or Temperature Cloud Cover KTR Probability Of Detection Or Correct Classification (Percent) OTR Probability Of Detection Or Correct Classification (Percent) KTR/OTR Probability Of False Detection Or In-Correct Classification (Percent) Volcano 800K 0.8 400×400 Ground 2 Hours 400K N/C CFLOS 90 95 1 Volcanic Lava Flow 400K 0.8 -- 2000×2000 Ground Continuous 300K N/C CFLOS 95 97 1 Fire 500K 0.6 -- 10 Acres Ground 10 Minute (Flare-Up) 300K N/C CFLOS 90 95 0.1 Aircraft 1000 W/sr -- 2.7 – 3.0 Point Source 10kM 5 Minutes 1 µFlicks 0.0 μFlicks CFLOS 70 90 0.1 Oil Spillage 60F Variable: 0.5 to unity from 2 to 5 µm - 2000×2000 Sea Level Continuous 60F N/C CFLOS 90 99 0.01 Rocket 50,000 W/sr -- 2.7 – 3.0 Point Source Ground and 10kM 10 seconds 1 μFlicks 1 μFlicks CBLOS (10kM) 90 95 0.01 Missile 500,000 W/sr -- 2.7 – 3.0 Point Source see profile 100 seconds 1 μFlicks 1 μFlicks CBLOS (10kM) 97 98 0.001 High Energy Laser 10 W 10 μrad Beam Width -- 2.971365 Equiv Point Source Ground 100 millisec 1 μFlicks 0.0 µFlicks CFLOS 90 95 1 Oil Rig Burn Off 1000K See Oil Table 2.7 – 3.0 4.2 – 4.5 Equiv Point Source Ground 1 Hour 300K 0.0 μFlicks CFLOS 90 99 1 Industrial Facilities 305K 0.75 -- 100×100 Ground 24 Hours 287K N/C CFLOS 85 95 10 Special Event Unknown Unknown _ 50×50 Ground 1 second 1 µFlicks 0.0 µFlicks CFLOS 90 100 0.1 All requirements shall be met simultaneously over the required surveillance area as defined in paragraph 1.0 of this RFP. As an OTR only Probability of Stereo Coverage for any event shall be 0.90
  • 7. Elevator Viewgraph Full Surveillance Coverage Mission Control Station Timely communication to the Users 24-7-365 Meets all target detection requirements Thorough Test Program Figure 4 – Elevator Viewgraph Sensors Targets Performance Volcano √ Volcanic Lava Flow √ Forest Fire √ Aircraft √ Oil Spillage √ Rocket √ Missile √ High Energy Laser √ Oil Rig Burn Off √ Industrial Facilities √ Special Events √
  • 8. Targets Industrial Facilities Missile High Energy Laser Volcanic Lava Flow Aircraft Volcano Forest Fire Rocket Oil Rig Burn Off Oil Spillage
  • 9. House of Quality Table 2 – House of Quality Weight Meets Quality Cost 6 0.95 5.7 Dimensions 7 0.85 5.95 Weight 9 0.9 8.1 Software 8 0.8 6.4 Hardware 8 0.8 6.4 Staffing 4 0.9 3.6 Management Controls 8 0.9 7.2 Risk Management 9 0.78 7.02 Reviews 3 0.65 1.95 Technical Requirements 8 0.9 7.2 Timeline 5 0.75 3.75 Power 9 0.9 8.1 Expertise of Labor 8 0.95 7.6 Testing 9 0.9 8.1 Target Detection 9 0.8 7.2 TOTAL 110 94.27/110= 85%
  • 10. Organizational Planning Figure 5 – Organizational Planning of System Design Preliminary Requirements Mission Objectives Mission CONOPS Mission Architecture Trade Study Document Baseline for Further Study Proposal No Yes Evaluate Cost Performance Effectiveness
  • 11. Organizational Planning Figure 6 – Organizational Planning of the System (V Model)
  • 12. System Architecture Detection Power: Solar Panel Processing Electronics Cooling System Optics & Detector Telescope Beam Splitter Reflector Refractor FPA and nTDI FOV PSF Figure 7 – Flow-down Graph
  • 13. Geostationary Orbit Definition: A geosynchronous orbit that is fixed with respect to a position on the Earth. Figure 8 – Geostationary orbit
  • 15. Viewing Area 9 Degrees 15 Degrees Figure 9 – Viewing Area
  • 16. Bore-sight with 16° FOV Figure 10 – Bore-sight with 16° FOV
  • 17.
  • 18.
  • 19.
  • 20. Telescope: Scanner Figure 13 – Scanner Signature
  • 21. Focal Plane Table 3 – Scanner Technical Specifications SCANNER Array Size 12x512 Raw Charge Capacity N/A Me Detector size (Pixel Pitch) 15 µm Integration Time 100 to 20000 µs Mux Part Number N/A Integration Mode Spectral Band 2-5 µm Operational Mode Detector Cut-off >5 µm Frame Rate 1 to 50 Hz Operating Temperature 90 to 150 K Frame Time ms Nominal Irradiance (measured on FP) cm -2 s -1 Number of Signal Output Channels N/A NEI or NEDT at nominal background cm -2 s -1 Max Data Rate per Video Tap N/A MHz Max Irradiance cm -2 s -1 Cross Talk 1 % Min Irradiance cm -2 s -1 Power Dissipation N/A mW
  • 22.
  • 23.
  • 24. Telescope: Starer Figure 16 – Starer Signature
  • 25. Focal Plane Table 4 – Starer Technical Specifications STARER Array Size 1024×1024 Raw Charge Capacity N/A Me Detector size (Pixel Pitch) 18 µm Integration Time 100 to 20000 µs Mux Part Number N/A Integration Mode Spectral Band 2-5 µm Operational Mode Detector Cut-off >5 µm Frame Rate 1 to 50 Hz Operating Temperature 90 to 150 K Frame Time ms Nominal Irradiance (measured on FP) cm -2 s -1 Number of Signal Output Channels N/A NEI or NEDT at nominal background cm -2 s -1 Max Data Rate per Video Tap N/A MHz Max Irradiance cm -2 s -1 Cross Talk 1 % Min Irradiance cm -2 s -1 Power Dissipation N/A mW
  • 26.
  • 27.
  • 28.
  • 29.
  • 30. Confusion Matrix Target Detection False Alarm Background Missing a Target TARGET: Volcano Sensoreality Target No target Target 100 4 No target 0 96
  • 31. Confusion Matrix Volcano Sensoreality Target No target Target 100 4 No target 0 96 Forest Fire Sensoreality Target No target Target 90 30 No target 10 70 High Energy Laser Sensoreality Target No target Target 100 0 No target 0 100
  • 33.
  • 34.
  • 35.
  • 36.
  • 37.
  • 38.
  • 39.
  • 40.
  • 41.
  • 43.
  • 44. Vendors - Telescope Corning will provide the mirrors. L3 Communications SSG – Tinsley will polish the mirrors for our telescopes.
  • 45.
  • 46.
  • 47. Vendors Telescope Cost and Design Information Space Programs Cooling System Sensors Space Programs Space Programs Gimbal System Processor
  • 48. Table 5 – Budget Breakdown Budget Breakdown Category Item Quantity Price $ FPA Subsystem Starer 1 3.7M Scanner 1 4.0M Telescope Subsystem Starer 5 5.0M Scanner 1 1.0M Communication Systems Compress and Communications 1 3.0M First Level Threshold Algorithm 1 12.0M Target Detection and Report Generation 1 20.0M Signal Processor SIDECAR™ ASIC 1 0.052M Gimbaled Subsystem MODEL-25 PAN & TILT GIMBAL 6 36.0M Thermal Control Carbon-Carbon Radiator (Passive Cooler) 2 4.0M Human Resources Program Management Office 6 1.5M System, Integration and Test Engineering 15 3.0M Quality Engineering 4 1.0M Documentation and Specification Config. Manag. 10 2.0M Software Engineering 300K SLOC 60.0M TOTAL ~160.0M
  • 49. Additional Specifications Table 6 – Additional Specifications Item Weight Power Dimensions Length Width Height Gimbal System 180.0 lb 750 W 48.0” 34.5” 56.0” Cooling System 11.0 lb 0 0.022” 28.25” 57.24” FPA Scanner N/A 11 mW 0 0.0071” 0.3024” FPA Starer N/A 11 mW 0 0.72” 0.72” Processing System 16.0 lb 300 mW 17.5” 5.3” 13.4” Telescope Starer 354.2 lb N/A 78.0” 45.0” 47.76” Telescope Scanner 190.0 lb N/A 5.886” 3.0” 3.071” TOTAL 751.2 lb < 1000 lb 750.322 W < 1000 W 92” < 96” 48” < 48” 57.24” < 72”
  • 50.
  • 51.
  • 52.
  • 53.
  • 54.
  • 55.
  • 56.
  • 57.
  • 58.
  • 59.
  • 60.