1. Iridium Satellite Dannie Stamp Chief Officer of Operations August 2, 2005

2. 2 Historical Timeline 1991 1992 1993 1994 1995 1996 1997 1998 1999 System Telephony Engineering Satellite Requirements Design Launch Vehicle Design Deployment & Launch PROGRAM FUNDING Satellite & LV R&D Qualification June 97 Satellite Mfg. First Satellite Jan 97 Nov 98 FOC Ground System Design 1991 1992 1993 1994 1995 1996 1997 1998 1999

3. 3 System Status Summary System Acquired from Bankruptcy by Iridium Satellite LLC 12/2000 –Committed Multinational Investment Partnership Anchor Customer: U.S. Department of Defense Commercial Service Re-introduced 03/2001 –Maintainable Cost Structure Vertical Market Distribution Strategy for Solution-Based Voice, Messaging and Data Services Subcontract with Boeing for Satellite Operations and Maintenance 2014 Constellation Lifespan Projected –66 Operational Satellites –12 Spare Satellites

4. 4 Commercial Status Constellation and Gateway One Commercial Gateway Provides Global Connectivity –Tempe, Arizona DoD Gateway in Hawaii Supports US Government Traffic Satellite Constellation –66 Fully Operational Satellites –12 In-Orbit Spares –Constellation Life to 2013/2014 Satellite Operations –Main Facility in Leesburg, VA –Back-up Facility in Chandler, AZ All Gateways Support Voice and Data Services –Dial-up –Direct Internet Access –Short Message Service –Short Burst Messaging –Paging –RUDICS

5. 5 Aero Maritime Government / Security Military ReliefFishing Oil/Gas aero Counterinsurgency / Interdiction Boating Shipping Forestry/Land Mgmt Remote Industry Mining General Private/Corporate Commercial Aeronautical Primary Customer Segments

6. 6 Marketing & Distribution Iridium Sells its Services Through a Network of World Leaders in Satellite Telecommunications These Partners Offer Value-Added Products and Services that are Proven Across the Mobile Communications Industry

7. 7 Present Constellation Configuration 66 Operational Satellites 12 Spare Satellites (May 2006) Drift in Progress

8. 8 Multiple Launch Vehicles Used DELTA II PROTON LONG MARCH 2C EUROCKOT 12 launches 5 SVs / LV 3 launches 7 SVs / LV 6 launches 2 SVs / LV 1 launch 2 SVs / LV

9. 9 Iridium Satellite Constellation Each Satellite Footprint is Approximately 2800 Miles in Diameter All Satellite Footprints Overlap Each Satellite has 48 Spot Beams Size of Each Spot Beam is Approximately 250 Miles in Diameter All Spot Beams on a Satellite Overlap

10. 10 Solar Array Panels (2) Battery & Radiator Ka-Band Cross- Link Antenna (4) Ka-Band Feeder Link Antenna (4) L-Band MMA (3) Payload Electronics Dry Mass………………..1159 lbs Wet Mass………………..1412 lbs Instant. Peak Power…...>4000 W Avg. Power Load…………620 W Vehicle Length……………160 in Vehicle “Wingspan”..........330 in Seven Power PC Processors Four Gimbaled K-Band Feederlinks Four K-Band Crosslinks (2 Fixed & 2 Gimbaled) Three L-Band Phased Arrays Two 42.5 sq. ft. GaAs Solar Arrays One 60A-hr SPV NiH 2 Battery Three-Axis Momentum-Biased Attitude Control System Redundant Orbit Adjust Graphite Epoxy Structure Active & Passive Thermal Control Iridium Satellite Vehicle (SV) Three Principal Elements Of SV: –Payload – Provides All Command, Control and Communications Functions –Main Mission Antennas (MMAs) – Provide L-Band Telephony Functions –Bus – Platform For SV Operations, Provides Power, Pointing, Propulsion Launch Configuration

11. 11 SV Constellation Life Assessment Extended Full Constellation Outlook to 2014 –Hardware Loss Trend has Decreased Since Constellation Deployment (Infant Mortality) –SV Subsystem Performance is Well Characterized and Understood with Over 4 Years of Operational Data –Successful Launches in 2002 and Strategy to Drift Satellites Between Planes Improves Replenishment Flexibility –Aerospace GAP Run Validates Conservative Ten Year Lifetime Prediction –Updated Battery Reliability Data Significantly Improved Constellation Outlook –Successful Life Extending Initiatives Implemented On-Orbit –Single Commercial Gateway Configuration and Lower Than Designed Traffic Loads Implies Reduces Stress, Thereby Increasing Reliability

12. 12 Manufacturing Differences

13. 13 Iridium Parts Program General Philosophy –Manage Parts & Materials Via Parts, Materials, and Processes Control Plan Consideration of Quality Level and Package Selection Diversity of Methods Allowed as Long as All Program Requirements Are Met Key Requirement is Engineering Analysis and Justification for Part & Supplier Selection –Select Parts Based On Lowest Total Cost to the Program, Not Just Part Costs Knowledge of the Part and Its Potential Problems –Select Suppliers Based on Their Knowledge of: Their Products Their Process Variability Their Reliability and Reliability Drivers –Optimize the Opportunity to Identify Problems in Advance –Implement a Program that Takes Advantage of Lessons Learned

14. 14 Iridium Parts Program (Cont’d) What the Parts Program was Not –A Program Which Blindly Used Commercial Parts, Based Upon Reduced Recurring Cost Extensive Nonrecurring Engineering was Done to Determine the Correct Part for Every Application Industrial and Military Parts were Also Used –The Program Discourages the Conclusion that All Commercial Parts Are Acceptable for All Space Applications Only Specific Suppliers and Specific Parts Were Used The Parts Used are Considered to Be Appropriate Only for this Specific System’s Parameters

15. 15 Goals Obtained Traditional Aerospace Iridium Partnership Savings QualityBuild, Test, Rebuild, Retest, …. Build, Verify, Ship, Shoot 4 to 1 Cost$30K/lb$9K/lb70% Cycle Time18 Months2 Months16 Months

16. 16 Iridium Assembly Process Station 0Material Receipt Station 1Heat-pipe Bonding Station 2Nadir Panel Assy Station 3Gateway Panel Assy Station 4Comm Panel Assy Station 5Comm Panel Test Station 6Comm Equipment Test Station 7Gateway Panel Integration Station 8Comm Panel Assy Integration Station 9SV Test Station 10EMI Test/Shear Panel Station 11MMA Integration Station 12SV Test Station 13Solar Array Integration Station 14Launch Confidence Test Station 15SV Pack and Ship Note: Additional detail of Iridium Manufacturing can be found in “Designing Space Systems for Manufacturability” can be found in Chapter 19 of Space Mission Analysis and Design, Third Edition.

17. 17 Stations 7 and 8 Gateway and Comm Panel Assy

18. 18 Station 9 SV Factory Test

19. 19 Station 11 Main Mission Antenna Attach

20. 20 Station 12 Thermal Cycle Test

21. Management Team

22. 22 Iridium Network Performance Voice/Data –Tempe Gateway Measured Performance: 8,590 Weekly Test Calls 99.2% Call Success Rate 0.6% Call Drop Rate Short Burst Data Services –Tempe Measured Performance: 99.64% First Attempt Message Success Rate Highly Reliable Satellite Communication Solutions