||This article contains orbital elements but does not include an epoch, or date when those elements, which typically vary over time, were correct.|
|Mission duration||2 years, 4 months|
|Launch mass||130 kilograms (290 lb)|
|Start of mission|
|Launch date||July 19, 2000|
|Launch site||Vandenberg SLC-8|
|End of mission|
|Decay date||12 November 2002|
|Perigee||548.0 kilometers (340.5 mi)|
|Apogee||585.0 kilometers (363.5 mi)|
|Fourier Transform Hyperspectral Imager|
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.
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 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.
- Kestrel Fourier transform (visible) hyperspectral imager
- Quad TMS320C40 (QC40) floating point digital signal processor
- DARPA-Aerospace sponsored PicoSat launcher assembly
- Shape memory alloy thermoelastic tailoring experiment
- Starfire optical reflectors for use with Kirtland’s Starfire Optical Range
Engineering/experimental bus components
- NRL miniature SGLS transponder (known as the NSX)
- Multi-functional composite bus structure
- Solar array concentrator
- Advanced composite solar array substrate
- Solar array flexible interconnect
- Krebs, Gunter. "Mightysat-2 (P99-1)". Gunter's Space Page. Retrieved 10 July 2013.
- "MightySat II.1 Datasheet" (PDF). General Dynamics. Archived from the original (PDF) on 2007-10-20. Retrieved 2008-08-01.
- "MightySat II.1: a standard-interface demonstration smallsat" (PDF). General Dynamics. 2005-11-05. Retrieved 2010-12-22.