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Dynamics, Vol. 22, No. 3, May-June 1999. For this example the initial true longitude is free. However,the optimal control solution includes the effect of propellant mass depletion due to thrusting while theexample in Dr. Kechichian’s technical paper assumes constant mass and therefore constant thrustacceleration. This example also includes the effect of the Earth’s J2gravity term.The first six lines of any input file are reserved for user comments. These lines are ignored by thesoftware. However the input file must begin with six and only six initial text lines.***************************************************** leo-to-geo low-thrust trajectory optimization** single phase continous-thrust maneuver** program leo2geo_ocs - leo-to-geo orbit transfer** J. Kechichian example - leo2geo_jk.in**************************************************The first three program inputs are the initial spacecraft mass, thrust magnitude and specific impulse.Please note the proper units for each data item.initial spacecraft mass (kilograms)1000.0thrust magnitude (newtons)98.0specific impulse (seconds)3300.0The next six numerical inputs are the classical orbital elements of the initial orbit.****************** INITIAL ORBIT ******************semimajor axis (kilometers)7000.0orbital eccentricity (non-dimensional)0.0orbital inclination (degrees)28.5argument of perigee (degrees)0.0right ascension of the ascending node (degrees)0.0true anomaly (degrees)0.0The following input determines if the software will constrain or free the initial true longitude.constrain initial true longitude (1 = yes, 2 = no)2The following five inputs are the user-defined classical orbital elements of the final mission orbit.**************** FINAL ORBIT ****************page 3