| Primary function | Near-Worldwide, secure, survivable satellite communications |
| Primary contractor | Lockheed Martin Space and Strategic Missiles, Sunnyvale, CA |
| Satellite Bus | A2100 Spacecraft Bus |
| Weight | Approximately 13,500 lbs at launch, 9,000 lbs on-orbit |
| Orbit-Altitude | 22, 000 + Miles (Geosynchronous) |
| Payload | Onboard signal processing, crossbanded EHF/SHF communications |
| Antennas |
2 SHF Downlink Phased Arrays,
2 Crosslinks,
2 Uplink/Downlink Nulling Antennas,
1 Uplink EHF Phased Array,
6 Uplink/Downlink gimballed Dish Antenna,
1 Each Uplink/Downlink earth coverage horns |
| Dimensions | Length - 32 ft (across payload axis), S/A Panels - 75.85 ft (across solar array axis) |
| First Launch | Apr 07 (planned) |
| Constellation | 3 Satellites |
| Design Life | 14 Years |
| Launch Vehicle: EELV |
| Unit Cost | Approximately $477 Million per satellite |
| Current as of | April 2004 |
