Official name USA 11
Alternative name USA 11 (DSCS III F2, DSCS 3-2, DSCS III B-4)
Cospar ID 1985-092B
Norad ID 16116
Launch date 1985-10-03
Launch site AFETR
Launch vehicle Shuttle IUS
Country/Organization USA
Type application Communication
Operator US Air Force (USAF)
RCS size UNKNOWN
Decay date ON ORBIT
Period (min) 1449.81
Inclination (deg) 14.71
Perigee (km) 36038
Apogee (km) 36071
Eccentricity 0.000457640516440389
Mean motion (revs. per day) 0.993233596126389
Semi-Major axis (km) 42432.635
Raan (deg) 353.127
Arg of perigee (deg) 143.3997
Shape Hex Poly + 2 Pan
Mass (kg) 1159.56
Height (m) 2.1
Width (m) 1.93
Depth (m) 1.93
Span (m^2) 9.5
Lifetime 10 years
Contractors Lockheed Martin
Equipment 6 SHF transponders, 1 special purpose transponder (SHF and UHF)
Propulsion ?
Configuration DSCS-3 Bus, 3-Axis stabilization
Power 2 deployable solar arrays, batteries

DSCS-3 (Defense Satellite Communications System 3) are geostationary communications satellites, which provide a robust anti-jam, nuclear hardened capability that supports Department of Defense (DoD) worldwide requirements, White House and Diplomatic communications. They are the follow-on generation of the DSCS-2 satellites.

The system is used for high priority communications such as the exchange of wartime information between defense officials and battlefield commanders. The system provides uninterrupted secure voice and high-data rate communications to globally fixed and mobile DoD users, NATO, the United Kingdom, the Diplomatic Telecommunications Service, and the White House Communications Agency.

DSCS-3 carries:

  • six independent Super High Frequency (SHF) transponders and one special purpose single channel transponder operating on both SHF and Ultra High Frequency
  • Three receive antennas (two Earth coverage horns, one steerable 61-beam nulling lens)
  • Five transmit antennas (two Earth coverage horns, two steerable 19-beam wave guide lens, one high gain parabolic gimbaled dish)

DSCS-3 B7 also carried the CHARGECON-GEO (Charge Control at Geosynchronous Altitude, S90-3) experiment for the Space Test Program.

Two solar wings produce 1700 Watts of onboard power at the beginning of life and 1230 watts at the end of life.

DSCS-3 satellites were designed to be injected directly into GEO by the launch vehicle (Titan-34D IUS, Titan-34D Transtage or Shuttle IUS) without the need to incorporate an apogee kick engine. Switching to Atlas-2, Atlas-2A and Delta-4M launch vehicles made it necessary to include a dedicated apogee kick stage (IABS) with the satelite for injecting the DSCS-3 into GEO orbit.

Another DSCS-3 satellite was constructed under the name STARSAT to be used as a test object in the "Huron King" nuclear weapons test for the effects of system generated electromagnetic pulse (SGEMP) on a full-scale operating DSCS-3 military communications satellite. The spacecraft was contained in a large above-ground tank.

The DSCS-3 is succeeded by the WGS series of satellites.

DSCS-3 B12 was retired in 2015 and was moved into a graveyard orbit above the geostationary belt.

Satellite COSPAR Date LS Launch Vehicle Remarks
DSCS 3-1 1982-106B 1982-10-30 AFETR Titan-34D IUS with DSCS-2 16
USA 11 1985-092B 1985-10-03 AFETR Shuttle IUS with Atlantis F-1 (STS-51-J), DSCS-3 B5
USA 12 1985-092C 1985-10-03 AFETR Shuttle IUS with Atlantis F-1 (STS-51-J), DSCS-3 B4
USA 44 1989-069B 1989-09-04 AFETR Titan-34D Transtage with DSCS-2 15
USA 78 1992-006A 1992-02-11 AFETR Atlas-2 IABS
USA 82 1992-037A 1992-07-02 AFETR Atlas-2 IABS
USA 93 1993-046A 1993-07-19 AFETR Atlas-2 IABS
USA 97 1993-074A 1993-11-28 AFETR Atlas-2 IABS
USA 113 1995-038A 1995-07-31 AFETR Atlas-2A IABS
USA 134 1997-065A 1997-10-25 AFETR Atlas-2A IABS with Falcon Gold
USA 148 2000-001A 2000-01-21 AFETR Atlas-2A IABS
USA 153 2000-065A 2000-10-20 AFETR Atlas-2A IABS
USA 167 2003-008A 2003-03-11 AFETR Delta-4M IABS
USA 170 2003-040A 2003-08-29 AFETR Delta-4M IABS