![]() Illustration of IABS carrying its payload, a DSCS III satellite, to geostationary orbit. | |
Manufacturer | GE Astro Space |
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Country of origin | United States |
Used on | Atlas II, Atlas IIA, Delta IV Medium |
General characteristics | |
Height | 0.68 m |
Diameter | 2.9 m |
Gross mass | 1578 kg |
Propellant mass | 1303 kg |
Empty mass | 275 kg |
Launch history | |
Status | Retired |
Total launches | 10 |
Successes (stage only) | 9 |
Failed | 1 (payload reached final orbit on its own) |
First flight | Feb 11, 1992 |
Last flight | Aug 29, 2003 |
Integrated Apogee Boost Stage | |
Powered by | 2 R-4D |
Maximum thrust | 980 N |
Specific impulse | 312 s |
Propellant | NTO/MMH |
The Integrated Apogee Boost Stage (IABS - alternately, Integrated Apogee Boost Subsystem) was an American rocket stage used for the launch of Defense Satellite Communications System III satellites to geostationary orbit when using a launch vehicle without an upper stage capable of delivering them there directly.[1] Earlier DSCS III satellites had launched on the Titan 34D (using the Transtage or Inertial Upper Stage) and Space Shuttle Atlantis (using the Inertial Upper Stage), which were capable of delivering them directly to geostationary orbit - as such, the satellites were not capable of moving from geostationary transfer orbit to geostationary orbit themselves. Because of this, launch of these satellites on the Atlas II and Delta IV families required an apogee kick stage - the IABS - to be added to the satellite. The IABS was developed by GE Astro Space, who also manufactured the DSCS III satellites it was designed for.[2]