design later became known as the LM-900 satellite bus and was optimized to carry remote sensing payloads. Four reaction wheels stabilized the spacecraft's altitude, which was measured by two star trackers and a sun sensor. Orbital position information was provided by a GPS receiver. The spacecraft body was a hexagonal design of and , with 1.5 kilowatts of power provided by three solar panels. Its design life was seven years. IKONOS operated in a Sun-synchronous, near-polar, circular orbit at approximately . Optical Sensor Assembly IKONOS primary instrument was the Optical Sensor Assembly (OSA), designed and built by Kodak. It had a primary mirror aperture of , and a folded optical focal length of using 5 mirrors. The main mirror featured a honeycomb design to reduce mass. The detectors at the focal plane included a panchromatic sensor with 13,500 pixels cross-track, and four multispectral sensors (blue, green, red, and near-infrared) each with 3,375 pixels along-track. Its nadir image swath was . Total instrument mass was and it consumed 350 watts. See also GeoEye-1 References External links IKONOS data sheet by DigitalGlobe Commercial imaging satellites of the United States Lockheed Martin satellites and probes Spacecraft launched in 1999 2015 disestablishments in the United States Derelict satellites orbiting Earth