| Mission type | Technology |
|---|---|
| Operator | AFRL |
| COSPAR ID | 2000-042A  |
| SATCAT no. | 26414 |
| Mission duration | 2 years, 4 months |
| Spacecraft properties | |
| Manufacturer | Spectrum Astro |
| Launch mass | 130 kilograms (290 lb) |
| Power | 330 watts |
| Start of mission | |
| Launch date | July 19, 2000 (2000-07-19) |
| Rocket | Minotaur I |
| Launch site | Vandenberg SLC-8 |
| Contractor | Orbital Sciences |
| End of mission | |
| Decay date | 12 November 2002 (2002-11-13) |
| Orbital parameters | |
| Reference system | Geocentric |
| Regime | Low Earth |
| Eccentricity | 0.00266 |
| Perigee altitude | 548.0 kilometers (340.5 mi) |
| Apogee altitude | 585.0 kilometers (363.5 mi) |
| Inclination | 97.8 degrees |
| Period | 96.0 minutes |
| Epoch | 19 September 2000, 16:09:00 UTC[1] |
| Instruments | |
| Fourier Transform Hyperspectral Imager | |
MightySat-2.1,[2] also known as P99-1orSindri was a small spacecraft developed by the Air Force Research Laboratory[3] to test advanced technologies in imaging, communications, and spacecraft bus components in space.
MightySat II.1 was manufactured by Spectrum Astro[2] 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 provided 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 pointing 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.[4]
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.[4]
|
U.S. Air Force Research Laboratory (AFRL) spacecraft and air vehicles
| |
|---|---|
| Launch/orbital vehicles |
|
| University Nanosat Program |
|
| Space weather satellites |
|
| Technology demonstrators |
|
| Tactical Satellite Program satellites |
|
