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calculating an eci state vector from classical orbital elements
08-03-2016, 09:10 PM
Post: #1
calculating an eci state vector from classical orbital elements
This HP Prime program demonstrates how to calculate an Earth-centered-inertial 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


Attached File(s)
.zip  demo_orb2eci.zip (Size: 453.44 KB / Downloads: 4)
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