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A Simplified–Modified Algorithm for Glonass Broadcast Orbits Computation

Medjahed SID AHMED

Medjahed SID AHMED

Algerian Space Agency (ASAL), Centre of Space Techniques (CTS), Department of Space GeodesyOran, Algeria
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AHMED, Medjahed SID
  
19 abr 2025
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Publicado en línea: 19 abr 2025
Páginas: 1 - 13
Recibido: 01 oct 2024
Aceptado: 23 ene 2025
DOI: https://doi.org/10.2478/arsa-2025-0001
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© 2025 Medjahed SID AHMED, published by Sciendo
This work is licensed under the Creative Commons Attribution 4.0 International License.

Figure 1.

Moon and sun perturbations
Moon and sun perturbations

Figure 2.

Orbits of GLONASS satellite number 01 (March 8, 2024)
Orbits of GLONASS satellite number 01 (March 8, 2024)

Figure 3.

Difference (Δ2) in X, Y, and Z (positions)
Difference (Δ2) in X, Y, and Z (positions)

Figure 4.

Difference (Δ2) in Vx, Vy, and Vz (velocities)
Difference (Δ2) in Vx, Vy, and Vz (velocities)

Figure 5.

Difference between (Δ1) and (Δ2) of integrate orbits
Difference between (Δ1) and (Δ2) of integrate orbits
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Statistics of differences (position, velocity, and L–S acceleration)

Axis Units Δ Min Max Mean RMS
X m Δ1Δ2 0.0000.000 22.73321.912 1.1161.084 1.4221.379
Y m Δ1Δ2 0.0000.000 8.1788.361 0.9070.874 1.1701.124
Z m Δ1Δ2 0.0000.000 8.0727.330 1.0210.946 1.2661.174
Vx m/s Δ1Δ2 0.00000.0000 0.01140.0126 0.00120.0011 0.00150.0014
Vy m/s Δ1Δ2 0.00000.0000 0.00970.0097 0.00090.0008 0.00120.0010
Vz m/s Δ1Δ2 0.00000.0000 0.00900.0085 0.00090.0009 0.00120.0011
γx m/s2 Δ1Δ2 Constant 0 Constant 1.02 × 10−6 Constant 1.97 × 10−7 Constant 2.92 × 10−7
γy m/s2 Δ1Δ2 Constant 0 Constant 1.02 × 10−6 Constant 1.96 × 10−7 Constant 2.91 × 10−7
γz m/s2 Δ1Δ2 Constant 0 Constant 1.02 × 10−6 Constant 1.57 × 10−7 Constant 2.35 × 10−7

Maximum difference in X, Y, and Z axes between Δ1 and Δ2

Axes Position (m) Velocity (m/s) L–S acceleration (m/s2)
X 1.228 0.00192 7.4506 × 10-9
Y 1.240 0.00193 7.4506 × 10-9
Z 1.207 0.00188 3.7253 × 10-9
(3D) 1.760 0.00270 8.0115 × 10-9
Mean 0.4546 0.00067 3.0185 × 10-9
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