MightySat-2.1

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MightySat-2.1
Mission type Technology
Operator AFRL
COSPAR ID 2000-042A
Mission duration 2 years, 4 months
Spacecraft properties
Manufacturer General Dynamics
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[edit]

MightySat II in orbit (artist's impression)

MightySat II.1 was manufactured by General Dynamics 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[edit]

MightSat II.1 ws 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][edit]

Stand-Alone Experiments/Sensors[edit]

  • 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[edit]

  • The NRL miniature SGLS Transponder (known as the NSX)
  • The Multi-functional Composite Bus Structure
  • Solar Array Concentrator
  • Advanced Composite Solar Array Substrate
  • Solar Array Flexible Interconnect

References[edit]

  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. ^ a b c "MightySat II.1: a standard-interface demonstration smallsat" (PDF). General Dynamics. 2005-11-05. Retrieved 2010-12-22.