The spacecraft is placed into a near-circular, Sun-synchronous polar orbit at a nominal altitude of 450 nautical miles.
The spacecraft is 3-axis stabilized and Earth oriented. Sensing instruments are maintained in a continuous orientation toward Earth or space. The solar array rotates about the pitch axis to provide single-axis Sun orientation.
Receipt of commands, downlink telemetry, and mission sensor data is accomplished via the Communications Subsystem.
The Equipment Status Telemetry Subsystem provides health and welfare status, as well as command verification reporting to the ground system.
Using a combination of stellar reference and inertial measurements made by gyros, a Sun-sensor unit, and an Earth-sensing Assembly, attitude errors and satellite position are determined. Once determined, attitude corrections are made by Reaction Wheel Assemblies.
The Command and Control Subsystem accepts real-time and stored commands for routing and processing. These commands may perform stationkeeping for the spacecraft or direct data collection by the sensor suite.
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