This block allows to input keplerian arguments and use them in other blocks.
This block allows to input keplerian arguments and use them in other blocks. For example it may be connected to propagation block and provide initial satellite position for the simulation. It also converts all the angle values from degrees (convinient for input) to radians (used by simulation blocks).
Output: 6x1 double (sma; eccentricity; inclination; periapsis; RAAN; mean_anomaly)
Semi-major axis - Semi major axis of the orbit elipse. It should have value greater than 0 given in meters.
Eccentricity - Parameter describing shape of the orbit. For eliptical orbits it shoul be betwen 0 and 1.
Inclination - Angle between orbit plane and equatorial plane. It should be between 0 and 180 degrees.
Periapsis argument - Periapsis argument given in meters.
Right ascension of ascending node - RAAN of the orbit. Value in degrees.
Mean anomaly - Mean anomaly given in degrees.
Semi-major axis [m] = 7070000
Eccentricity = 0.001
Inclination [deg] = 97.97
Periapsis argument [deg] = 0
Right ascension of ascending node [deg] = 0
Mean anomaly [deg] = 0
macros/KEPLERIAN_INPUT.sci
macros/AB_keplerian_input.sci