Compute subsatellite position from practical orbital parameters. Review period, longitude shift, coverage span, and speed. Use structured results for missions, analysis, testing, and planning.
| Altitude (km) | Inclination (°) | RAAN (°) | Argument of Perigee (°) | True Anomaly (°) | Time Step (s) | Points |
|---|---|---|---|---|---|---|
| 500 | 51.6 | 25 | 10 | 0 | 300 | 24 |
| 700 | 98.2 | 15 | 5 | 20 | 240 | 30 |
| 35786 | 0.1 | 75 | 0 | 180 | 600 | 18 |
The calculator models a simplified orbital ground track using classical orbital relationships. First, semi major axis is estimated as a = RE + h. Mean motion is then n = √(μ / a³). Orbital period is T = 2π / n.
The instantaneous subsatellite point comes from the orbit frame projected into Earth fixed coordinates. Using inclination i, right ascension of ascending node Ω, argument of perigee ω, and true anomaly ν, the argument of latitude becomes u = ω + ν.
Position components in the inertial frame are rotated by Earth rotation angle θ = ωE t. Latitude is obtained from φ = atan2(z, √(x²+y²)) and longitude from λ = atan2(y, x). Longitude shift per orbit is approximated from the ratio of orbital period to sidereal day.
This engineering calculator is ideal for quick planning, screening, and educational analysis. It does not replace high precision perturbation models, drag models, or full propagator software.
A ground track shows the subsatellite path across Earth’s surface as the spacecraft moves in orbit and Earth rotates beneath it.
The track shifts because Earth rotates during each orbit. The amount of shift depends mainly on orbital period and Earth’s sidereal rotation rate.
Yes. It is especially useful for quick low Earth orbit planning, visibility studies, coverage checks, and conceptual mission screening.
It accepts eccentricity, but the propagation is simplified for engineering speed. For high fidelity eccentric orbit studies, use a full orbital propagator.
Repeat orbits estimate how many revolutions are needed before the ground track roughly aligns again with earlier longitudes.
For most cases, the highest absolute latitude reached by the subsatellite point is close to the orbital inclination, assuming a prograde or retrograde orbit.
Yes. The page includes CSV export for table data and PDF export for a printable summary of the calculated output section.
No. It is best for preliminary engineering analysis. Certified mission work should use validated dynamics tools and perturbation aware propagation methods.
Important Note: All the Calculators listed in this site are for educational purpose only and we do not guarentee the accuracy of results. Please do consult with other sources as well.