Iridium Satellite Dannie Stamp Chief Officer of Operations

Iridium Satellite Dannie Stamp Chief Officer of Operations August 2, 2005 Iridium Status Overview 11 January 2005 Iridium Satellite LLC Confidential and Proprietary

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

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 3

Commercial Status Constellation and Gateway • One Commercial Gateway Provides Global Connectivity – Tempe, Arizona • Do. D 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 4

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

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 6

t in Drif Pro gres s 12 Spare Satellites 66 Operational Satellites Present Constellation Configuration (May 2006) 7

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

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 9

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 Battery & Radiator Solar Array Panels (2) L-Band MMA (3) Payload Electronics Ka-Band Feeder Link Antenna (4) Ka-Band Cross. Link Antenna (4) Launch Configuration 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. Ga. As Solar Arrays • One 60 A-hr SPV Ni. H 2 Battery • Three-Axis Momentum-Biased Attitude Control System • Redundant Orbit Adjust • Graphite Epoxy Structure • Active & Passive Thermal Control 10

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 11

Manufacturing Differences 12

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 13

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 14

Goals Obtained Quality Cost Cycle Time Traditional Aerospace Build, Test, Rebuild, Retest, …. Iridium Partnership Build, Verify, Ship, Shoot Savings $30 K/lb $9 K/lb 70% 18 Months 2 Months 16 Months 4 to 1 15

Iridium Assembly Process Station 0 Material Receipt Station 1 Heat-pipe Bonding Station 2 Nadir Panel Assy Station 3 Gateway Panel Assy Station 4 Comm Panel Assy Station 5 Comm Panel Test Station 6 Comm Equipment Test Station 7 Gateway Panel Integration Station 8 Comm Panel Assy Integration Station 9 SV Test Station 10 EMI Test/Shear Panel Station 11 MMA Integration Station 12 SV Test Station 13 Solar Array Integration Station 14 Launch Confidence Test Station 15 SV 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. 16

Stations 7 and 8 Gateway and Comm Panel Assy 17

Station 9 SV Factory Test 18

Station 11 Main Mission Antenna Attach 19

Station 12 Thermal Cycle Test 20

Management Team 21

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 22