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APPENDIX AContents of the Simulation Summary and CSV FilesThis appendix is a brief summary of the information contained in the simulation summary screendisplays and the CSV data files produced by the leo2geo_ocs software.The simulation summary screen display contains the following information:sma (km) = semimajor axis in kilometerseccentricity = orbital eccentricity (non-dimensional)inclination (deg) = orbital inclination in degreesargper (deg) = argument of perigee in degreesraan (deg) = right ascension of the ascending node in degreestrue anomaly (deg) = true anomaly in degreesarglat (deg) = argument of latitude in degrees. The argument of latitude is the sum oftrue anomaly and argument of perigee.period (min) = orbital period in minutesrx (km) = x-component of the spacecraft’s position vector in kilometersry (km) = y-component of the spacecraft’s position vector in kilometersrz (km) = z-component of the spacecraft’s position vector in kilometersrmag (km) = scalar magnitude of the spacecraft’s position vector in kilometersvx (km/sec) = x-component of the spacecraft’s velocity vector in kilometers per secondvy (km/sec) = y-component of the spacecraft’s velocity vector in kilometers per secondvz (km/sec) = z-component of the spacecraft’s velocity vector in kilometers per secondvmag (km/sec) = scalar magnitude of the spacecraft’s velocity vector in kilometers persecondtransfer time = total thrust duration in hoursfinal mass = final spacecraft mass in kilogramspropellant mass = expended propellant mass in kilogramsthrust duration = maneuver duration in secondsdelta-v = scalar magnitude of the accumulated delta-v in meters/secondsThe delta-v is determined using a cubic spline integration of the thrust acceleration data at eachcollocation node.The comma-separated-variable disk file is created by the odeprt subroutine and contains the followinginformation:time (hrs) = simulation time since ignition in hourspage 24