MightySat-2
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MightySat-2
| Operator | AFRL |
|---|---|
| Major contractors | General Dynamics |
| Mission type | Technology demonstrator |
| Satellite of | Earth |
| Launch date | July 19, 2000 |
| Launch vehicle | Minotaur I |
| Launch site | Vandenberg AFB |
| Mission duration | 2 years 4 month |
| Orbital decay | November 2002 |
| COSPAR ID | 2000-042A |
| Mass | 130 kg |
| Power | 330 W |
| Orbital elements | |
| Regime | Low Earth orbit |
| Eccentricity | 0.0026639786 |
| Inclination | 97.8° |
| Apoapsis | 585.0 km |
| Periapsis | 548.0 km |
| Orbital period | 96.0 min |
| Instruments | |
| Main instruments | Fourier Transform Hyperspectral Imager |
MightySat-2 (or Sindri) was a small spacecraft developed by the Air Force Research Laboratory[1] to test advanced technologies in imaging, communications, and spacecraft bus components in space.
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Contents
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Design
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 a 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.[2]
Mission
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.[2]
Payload and experimental instruments[2]
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
- 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
- ^ "MightySat II.1 Datasheet" (PDF). General Dynamics. http://www.gd-ais.com/capabilities/offerings/marketing/MightySatdatasheet.pdf. Retrieved 2008-08-01.
- ^ a b c "MightySat II.1: a standard-interface demonstration smallsat" (PDF). General Dynamics. 2005-11-05. http://www.gd-space.com/documents/Mightysat%20051105A%20(SS).pdf. Retrieved 2010-12-22.
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