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All the obtained simulation results have been
processed using Monte-Carlo technique.
Below one can see dependencies, which characterize
influence of antenna system base length, observation
conditions, GLONASS and GPS constellation
RMS values of Euler angles, deg.
1.00
0.90
0.80
0.70
0.60
0.50
0.40
0.30
0.20
0.10
0.00
1 2 3 4
Antenna base length, m.
Fig. 5 Incomplete GLONASS+GPS
RMS values of Euler angles, deg.
0.90
0.80
0.70
0.60
0.50
0.40
0.30
0.20
0.10
0.00
Incomplete GLONASS + GPS;
r.m.s value
of sys. error is 0.005 m.
completeness and systematic errors level on the
accuracy of the TUD satellite attitude determination.
Main attention was paid to the influence of the
antenna system base length. These results are
demonstrated in Fig. 4 – 8. Each symbol on these
figures corresponds to 30 samples of Monte-Carlo
simulation. The magnitude of r.m.s. attitude for any
fixed base length depends also on the observation
condition and magnitude of systematic error, which is
fixed and is equal to 0.005m.
Pitch
1 2 3 4 5
Antenna base length, m.
Fig. 6 Complete GLONASS+GPS
Yaw
Roll
Complete GLONASS + GPS;
r.m.s value
of sys. error is 0.005 m.
Pitch
Yaw
Roll
5
RMS values of Euler angles, deg.
2.00
1.90
1.80
1.70
1.60
1.50
1.40
1.30
1.20
1.10
1.00
0.90
0.80
0.70
0.60
0.50
0.40
0.30
0.20
0.10
0.00
Complete GLONASS;
r.m.s value
of sys. error is 0.005 m.
Pitch
1 2 3 4 5
Antenna base length, m.
Fig. 7 Complete GLONASS
RMS values of Euler angles, deg.
5.00
4.50
4.00
3.50
3.00
2.50
2.00
1.50
1.00
0.50
0.00
1 2 3 4
Antenna base length, m.
Fig. 8 Incomplete GLONASS
RMS values of Euler angles, deg.
1.00
0.90
0.80
0.70
0.60
0.50
0.40
0.30
0.20
0.10
0.00
Fig. 9 GPS only
Yaw
Roll
Incomplete GLONASS;
r.m.s value
of sys. error is 0.005 m.
Pitch
1 2 3 4 5
Antenna base length, m.
Yaw
Roll
GPS;
r.m.s value
of sys. error is 0.005 m.
Pitch
Yaw
Roll
5