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MightySat-2.1

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MightySat-2.1
Mission typeTechnology
OperatorAFRL
COSPAR ID2000-042A Edit this at Wikidata
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

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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

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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]

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Stand-alone experiments/sensors

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  • 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

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  • 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

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  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. Archived from the original (PDF) on 2010-02-15. Retrieved 2010-12-22.