Earth Viewing Systems Satellite Sensor Project, for Professor DiNardo's Course. The presentation was given on 14th May, 2009. ______________________________________ I realize that some of the graphics do not have their sources cited, but I did not make those slides, and the group members who made them did not remember their sources. So, please forgive this oversight, since I consider it important enough to students of the earth surveillance class at The City College of New York (and elsewhere) that old presentations be available to them. If, however, you can give me the sources of the graphics that you see, then I will be grateful, and I will be happy to cite them.

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

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

14. Technical Plan

15. Viewing Area 9 Degrees 15 Degrees Figure 9 – Viewing Area

16. Bore-sight with 16° FOV Figure 10 – Bore-sight with 16° FOV

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

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

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

32. Management Plan

42. TIMELINE SCHEDULE

44. Vendors - Telescope Corning will provide the mirrors. L3 Communications SSG – Tinsley will polish the mirrors for our telescopes.

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”