MightySat-2.1


MightySat-2.1, also known as P99-1 or Sindri was a small spacecraft developed by the United States [Air Force Research Laboratory|Air Force Research Laboratory] to test advanced technologies in imaging, communications, and spacecraft bus components in space.

Design

[Image:Mightysat2.jpg|thumb|left|250px|MightySat II in orbit (artist's impression)]
MightySat II.1 was manufactured by Spectrum Astro 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 and had a launch weight of 123.7 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.

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.

Payload and experimental instruments

Source:

Stand-alone experiments/sensors

Engineering/experimental bus components

  • NRL miniature SGLS transponder
  • Multi-functional composite bus structure
  • Solar array concentrator
  • Advanced composite solar array substrate
  • Solar array flexible interconnect