Calculation of Keplerian and Hill's orbital elements for GEO and Molniya satellites from position and velocity vectors.
This project calculates the complete set of orbital elements for two communication satellites:
- INTELSAT-20 (Geostationary Earth Orbit - GEO)
- MONILIYA3-50 (Molniya-type highly elliptical orbit)
Given position (r) and velocity (v) vectors in an inertial coordinate system, the program computes:
- 6 classical Keplerian elements
- True anomaly and Mean anomaly
- Hill's elements (r, ṙ, u, Ω, G, H) for the GEO satellite
- Orbital period verification using Kepler's 3rd law
- 2D orbit visualization in perifocal coordinates
Given position and velocity vectors for INTELSAT-20 and MONILIYA3-50 satellites:
INTELSAT-20:
- r = (16575.5879, -38775.5254, 5.3421) km
- v = (2.8271, 1.2079, -0.0008) km/s
MONILIYA3-50:
- r = (-495.4135, 8636.4268, -3136.0422) km
- v = (-4.0917, 5.5089, 4.9534) km/s
Earth's gravitational constant (GM) = 398600.4418 km³/s² (WGS84)