calculating an eci state vector from classical orbital elements

08032016, 09:10 PM
Post: #1




calculating an eci state vector from classical orbital elements
This HP Prime program demonstrates how to calculate an Earthcenteredinertial state vector (position and velocity vectors) from classical orbital elements.
The following is the output from this program. demo_orb2eci classical orbital elements semimajor axis = 223705.147138 km eccentricity = 0.971280418487 inclination = 51.9434659014 degrees argument of perigee = 347.329965384 degrees raan = 212.885279071 degrees true anomaly = 347.74343648 degrees eci position vector (km) r_x = −5864.79273588 r_y = −1781.73078924 r_z = −2156.29990967 eci velocity vector (km/sec) v_x = 0.492973713027 v_y = −7.31828662239 v_z = 8.19193017132 

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