Operator AFRL Mission duration 2 years, 4 months Rocket Minotaur I Period 1.6 hours Apogee 585,000 m Manufacturer Orbital ATK | COSPAR ID 2000-042A Power 330 watts Launch site Vandenberg SLC-8 Launch mass 130 kg Launch date 19 July 2000 Mission type Technology | |
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Similar MightySat‑1, TAOS, 3 Corner Satellite, PnPSat‑1, XSS 10 | ||
MightySat-2.1, also known as P99-1 or Sindri was a small spacecraft developed by the Air Force Research Laboratory to test advanced technologies in imaging, communications, and spacecraft bus components in space.
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Design
MightySat II.1 was manufactured by Orbital ATK in a modular approach, using, e.g., VME-based subsystems, and a planar payload deck for small experimental payloads. The satellite measured 0.67m x 0.83m x 0.86m (WxLxH) and had a launch weight of 123.7 kg (Bus Mass: 87.1 kg). Power was provied by 2-axis articulated Si solar arrays with a designed end-of-life power output of 330 W. The Attitude Determination and Control Subsystem featured a 3-axis zero-momentum-bias reaction wheel assembly with a Sun sensor, a star tracker and inertial measurement units, delivering an attitude jitter of 15.7 arcsec/sec, and poiting accuracy and knowledge of 648 and 540 arcsec, respectively. The communication was compatible with the US Air Force Space-Ground Link System with data rates of 1 Mbit/s for payload/experiments data downlink, 2.0 kbit/s for Command uplink, and 20 kbit/s for Telemetry downlink. Computing and data handling was done by a RAD6000 CPU @ 20 MIPS with an IEEE VME backplane 128 MByte CPU RAM, and a 21.6 MBytes/sec transfer rate, and a 2 Gbit Solid State Recorder for Science Data. Among its 10 experiments was a Fourier Transform Hyperspectral Imager.
Mission
MightSat II.1 was launched on July 19, 2000 with a Minotaur I. It deorbited in November 2002 due to natural decay of its orbit, exceeding more than twice its nominal lifetime.