MightySat-2.1

MightySat-2.1
Mission type Technology
Operator AFRL
COSPAR ID 2000-042A
Mission duration 2 years, 4 months
Spacecraft properties
Manufacturer Orbital ATK
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 0.0026639786
Perigee 548.0 kilometers (340.5 mi)
Apogee 585.0 kilometers (363.5 mi)
Inclination 97.8& degrees
Period 96.0 minutes
Instruments
Fourier Transform Hyperspectral Imager

MightySat-2.1,[1] also known as P99-1 or Sindri was a small spacecraft developed by the Air Force Research Laboratory[2] to test advanced technologies in imaging, communications, and spacecraft bus components in space.

Design

MightySat II in orbit (artist's impression)

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 provied 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 poiting 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.[3]

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.[3]

Payload and experimental instruments[3]

Stand-Alone Experiments/Sensors

Engineering/Experimental Bus Components

References

  1. Krebs, Gunter. "Mightysat-2 (P99-1)". Gunter's Space Page. Retrieved 10 July 2013.
  2. "MightySat II.1 Datasheet" (PDF). General Dynamics. Retrieved 2008-08-01.
  3. 1 2 3 "MightySat II.1: a standard-interface demonstration smallsat" (PDF). General Dynamics. 2005-11-05. Retrieved 2010-12-22.
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