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Navigation - Small Satellites carrying GPS receivers
Global Positioning System receivers provide highly accurate time and
position information, and use a constellation of 24 navigation satellites
maintained by the US DOD in order to accurately determine their own position.
Although designed for Terrestrial geolocation and navigation, the system can be employed in the highly
dynamic environment in Low Earth Orbit. Landsat was the first civil spacecraft to carry a
GPS receiver into orbit, but the receiver technology has advanced to a stage where GPS
receivers can now routinely be carried on smaller platforms. Since Selective
Availability has been switched off, accuracies in the order of 10m in all axis
are achievable for simple position fixes.
A space borne GPS receiver is different from a terrestrial receiver, as it
travels at great velocity relative to the GPS constellation, and satellites
tracked change constantly. As a consequence it has to cope
with higher Doppler shifts and Doppler shift rates. In LEO this can be of the order of
±60kHz. Consequently, the receiver only has a short time available to perform a
frequency/code search in order to lock onto the spread spectrum GPS signals. In order to
predict GPS satellite visibility, the antenna geometry and orbital dynamics of the host
satellite must be well known. For more precise applications, differential and
double-differential filtering of GPS is proposed for formations of
satellites. For greater precision, kinematic GPS employs the basic understanding
of the dynamics to further improve accuracy.
Orbit determination using GPS receivers on small satellites is now well demonstrated,
and the next challenge now is to perform attitude determination on a small platform.
Several small missions have recently been launched in order to demonstrate this. GPS can
also be used in ionospheric research, and this is achieved by monitoring GPS signals as
the satellite-to-satellite path skims the upper atmosphere.
GPS can only be effectively used near the Earth's surface, but various
experiments have demonstrated that sidelobe signals can be picked up above the
GPS constellation at 20,000; e.g. from Geostationary heights.
| Satellite |
Launch |
Receiver |
Channels |
Antennas |
Status |
| ORBComm-X |
1991 |
Trimble Tans II |
6 |
1 |
Spacecraft not operational |
| Radcal |
1993 |
2x Trimble Tans Quadrex |
6+6, L1 C/A |
4 |
To demonstrate post processing attitude
determination |
| PoSat-1 |
1993 |
Trimble Tans II with LEO firmware |
6 |
1 |
Operational, orbit determination |
| DarpaSat |
1994 |
Rockwell AST-5 |
6, L1, L2 |
2 |
Operational, orbit determination |
| Step-0 (TAOS) |
1994 |
Rockwell AST-5 |
6, L1, L2 |
? |
- |
| APEX |
1994 |
Trimble TANS II |
6 |
1 |
- |
| MICROLAB |
1995 |
JPL/AOA Turbo Rogue(GPS-MET) + Trimble Tans |
8+6 |
1+4 |
Operational, atmospheric measurements |
| ORBCOMM-FM1 |
1995 |
Trimble Tans II |
6 |
4 |
To demonstrate real time orbit determination |
| ORBCOMM-FM2 |
1995 |
Trimble Tans II |
6 |
4 |
To demonstrate real time orbit determination |
| FASat-alfa |
1995 |
Trimble Tans II with LEO firmware |
6 |
1 |
Spacecraft not operational |
| GEMStar |
1995 |
Trimble Tans Vector |
|
|
Launch failure |
| REX-II |
1996 |
2xTrimble Tans Vector |
6 |
4 |
Operational, demonstrated orbit and attitude
fixes
420-600mm baslines, aligned better than 0.1 degreeReported 0.3-0.5 degree accuracy |
| Zeya |
1997 |
GPS and Glonass |
|
|
Launched |
| Lewis |
1997 |
SS Loral Tensor |
? |
4 |
Satellite malfunctioned |
| Clark |
1997 |
Trimble Tans Vector |
|
|
Programme abandoned. There were plans for real
time attitude determination |
| ØRSTED |
1998 |
Trimble Tans II + modified JPL Turbo Rogue |
6+8 |
2 |
Launched |
| SunSat |
1998 |
JPL Turbo Rogue |
8 |
1 |
Launched |
| FASat-Bravo |
1998 |
Trimble Tans II with LEO firmware |
6 |
1 |
Launched |
| SNOE |
1998 |
JPL MicroGPS |
no correlator |
1 |
Launched |
| Phase-3D |
|
AMSAT GPS receiver |
? |
8 |
Launched |
| TMSat-1 |
1998 |
SSTL SGR-10 |
12 |
2 |
Launched |
| UoSAT-12 |
1999 |
SSTL SGR-20 |
24 |
5 |
Demonstrated simultaneous tracking of 12
satellites and "lost in space" solution within 4 minutes. |
| SeaStar |
1997 |
Motorola Viceroy |
? |
2 |
|
| STRV-1c |
2000 |
JPL MicroGPS |
no correlator, L1, L2 |
1 |
Launched, but can not be
operated |
| Teamsat (/Yes) |
1997 |
Trimble TANS II |
|
2 |
Launched. Aimed to show GPS use above the GPS
constellation. |
| Equator-S |
1998 |
|
|
|
Aim to show GPS use above the GPS constellation. |
| SAC-A |
1998 |
|
|
4? |
Differential GPS, aim to measure position to
sub-10cm accuracy |
| Tsinghua-1 |
2000 |
SSTL SGR-10 |
12 |
2 |
Operational |
| SNAP-1 |
2000 |
SSTL SGR-05 |
12 |
1 |
Operational |
| HETE-II |
2000 |
CNES |
|
|
|
| SAC-C |
2000 |
Blackbeard |
|
|
|
| CHAMP |
|
JPL BlackJack |
|
|
|
| SimpleSAT |
2001 |
Trimble Vector |
|
|
Never operated |
| PICOSat |
2001 |
JPL Turbo-Rogue |
|
|
Receiver part of ionospheric
occultation experiment |
| PCSAT |
2001 |
|
|
|
Operational |
| PROBA |
2001 |
SSTL SGR-20 |
24 |
|
Operational |
| GRACE
1&2 |
2002 |
|
|
|
|
| ALSAT-1 |
2002 |
SSTL SGR-20 |
24 |
|
Operational |
| Mozhayets |
2002 |
|
|
|
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| FedSat |
2002 |
dual frequency |
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The Trimble series 6 channel receivers are equipped with LEO firmware, to allow them to
operate in the highly dynamic environment of space, with high velocity and high velocity
derivatives. The Trimble Tans II employs a 68000 processor. The Quadrex employs antenna
switching to commutate between four antennas. The Vector is a Quadrex which includes a
coprocessor to permit basic attitude determination.
Further information on
space-borne GPS can be found at the Department of Geodesy and Geomatics Engineering,
University of New Brunswick.
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References
[1] Precise platform
positioning with a single GPS receiver, S.B.Bisnath et al, GPS World, April
2002, [http://www.gpsworld.com]
[2] JPL Press release for BlackJack [http://www.jpl.nasa.gov/releases/2000/blackjackgps.html]
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