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From Wikipedia, the free encyclopedia

MightySat-2.1
Mission typeTechnology
OperatorAFRL
COSPAR ID2000-042A
SATCAT no.26414Edit this on Wikidata
Mission duration2 years, 4 months
Spacecraft properties
ManufacturerSpectrum Astro
Launch mass130 kilograms (290 lb)
Power330 watts
Start of mission
Launch dateJuly 19, 2000 (2000-07-19)
RocketMinotaur I
Launch siteVandenberg SLC-8
ContractorOrbital Sciences
End of mission
Decay date12 November 2002 (2002-11-13)
Orbital parameters
Reference systemGeocentric
RegimeLow Earth
Eccentricity0.00266
Perigee altitude548.0 kilometers (340.5 mi)
Apogee altitude585.0 kilometers (363.5 mi)
Inclination97.8 degrees
Period96.0 minutes
Epoch19 September 2000, 16:09:00 UTC[1]
Instruments
Fourier Transform Hyperspectral Imager
 

MightySat-2.1,[2] also known as P99-1 or Sindri 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.

Design

MightySat II in orbit (artist's impression)
MightySat II in orbit (artist's impression)

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]

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.[4]

Payload and experimental instruments[4]

Stand-alone experiments/sensors

  • 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

References

  1. ^ "NASA - NSSDCA - Spacecraft - Trajectory Details". nssdc.gsfc.nasa.gov. Retrieved 2018-05-02.
  2. ^ a b Krebs, Gunter. "Mightysat-2 (P99-1)". Gunter's Space Page. Retrieved 10 July 2013.
  3. ^ "MightySat II.1 Datasheet" (PDF). General Dynamics. Archived from the original (PDF) on 2007-10-20. Retrieved 2008-08-01.
  4. ^ a b c "MightySat II.1: a standard-interface demonstration smallsat" (PDF). General Dynamics. 2005-11-05. Retrieved 2010-12-22.
This page was last edited on 26 September 2019, at 10:10
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