Clark was selected in the NASA SSTI (Small Spacecraft Technology Initiative) program, along with Lewis, to demonstrate advanced spacecraft technologies. Contract start was July 11, 1994. Contract was cancelled by NASA in March 1998 when overruns had reached 20% of original contract price and no end to development was in site. NASA took possession of the hardware and instruments built which may be flown on a later sattelite. Spacecraft: 3-Axis stabilised, zero momentum biased control system with 0.05 deg control and 0.03 deg knowledge. Two solar arrays generate 289W orbit average power. Two 15-Ahr NiH2 CPV batteries. Hydrazine propulsion system with 12.5 kg propellant.2 Gbit solid state storage. UHF command and telemetry links.25 Mbps X-band image data downlink. Graphite composite structure. Payload: Worldview Imaging Corp's panchromatic 3-m resolution, 15-m multispectral resolution with cloud editing capability. Micro-Measuring Air Pollution from Satellites (µMAPS). X-Ray Spectrometer (soft and gamma). Atmospheric Tomography (3D pollution mapping).

Design Life: 3 years (required life is 1 year). Total Length: 1.8 m. Maximum Diameter: 0.9 m. Total Propellants: 13 kg. Electric system: 0.29 total average kW. Electrical System: Two solar arrays.

Clark was selected in the NASA SSTI (Small Spacecraft Technology Initiative) program, along with Lewis, to demonstrate advanced spacecraft technologies.

Clark was to have demonstrated advanced spacecraft technologies. Contract was cancelled by NASA in March 1998 when overruns had reached 20% of original contract price and no end to development was in site.

• 6 - JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. HTML when accessed: http://msl.jpl.nasa.gov/home.html