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The next input is an integer that defines the maximum number of algorithm iterations.maximum number of algorithm iterations10000The level of output from the NLP algorithm is controlled with the following integer input.***************************sparse NLP iteration output---------------------------1 = none2 = terse3 = standard4 = interpretive5 = diagnostic---------------2The level of output from the optimal control algorithm is controlled with the following integer input.Please note that option 4 will create lots of information.**********************optimal control output----------------------1 = none2 = terse3 = standard4 = interpretive-----------------1The level of output from the Sparse Optimization Suite differential equations algorithm is controlledwith the following integer input. Please note that option 5 will create lots of information.****************************differential equation output----------------------------1 = none2 = terse3 = standard4 = interpretive5 = diagnostic---------------1The level of output can be further controlled by the user with this final text input. This program optionsets the value of the SOCOUT character variable described in the Sparse Optimization Suite user’smanual. To ignore this special output control, input the simple character string no.*******************user-defined output-------------------input no to ignore------------------a0b0c0d0e0f0g0h0i0j2k0l0m0n0o0p0q0r0page 6
Optimal control solutionThe following is the program output created by the itcm_ocs simulation for this example. Please seeAppendix A for additional details about this information.program itcm_ocs================input data file ==> e2m_tcm.inuser-defined fpa, radius and orbital inclinationTCM delta-v vector and magnitude(heliocentric EME2000)----------------------delta-vx 2.86350904748275 meters/seconddelta-vy 19.7001824350835 meters/seconddelta-vz -2.66101349730156 meters/seconddeltav 20.0842690898477 meters/secondTCM delta-v inertial pointing angles(heliocentric EME2000)----------------------right ascension 81.7297238627486 degreesdeclination -7.61364380952683 degreesTCM delta-v orbit-plane pointing anglespitch -59.1104234734653 degreesyaw 265.879855271489 degreestime and conditions prior to TCM maneuver(heliocentric EME2000)----------------------calendar date June 8, 2003TDB time 18:20:44.077TDB Julian date 2452799.26439903sma (km) eccentricity inclination (deg) argper (deg)0.190725765750D+09 0.204056802425D+00 0.234926769446D+02 0.253488459798D+03raan (deg) true anomaly (deg) arglat (deg) period (hrs)0.463121032996D+00 0.394861259377D+01 0.257437072392D+03 0.126193097746D+05rx (km) ry (km) rz (km) rmag (km)-.319331575699D+08 -.136207676243D+09 -.590899587841D+08 0.151867971768D+09vx (kps) vy (kps) vz (kps) vmag (kps)0.316260605833D+02 -.655290816096D+01 -.295930903551D+01 0.324330976528D+02time and conditions after TCM maneuver(heliocentric EME2000)----------------------page 7
Page 4 and 5: upper bound for TCM delta-v compone
Page 8 and 9: calendar date June 8, 2003TDB time
Page 10 and 11: sma (au) eccentricity inclination (
Page 12 and 13: B-plane coordinates at Mars sphere-
Page 14 and 15: (3) Point functions - SOI distance
Page 16 and 17: Heliocentric equations of motionFig
Page 18 and 19: In these equations, and r eqare th
Page 20 and 21: Geocentric-to-areocentric coordinat
Page 22 and 23: Algorithm resources“Update to Mar
Page 24 and 25: s2e-x (au) = x-component of Earth p
Page 26 and 27: time and conditions after TCM maneu
Page 28 and 29: calendar date December 24, 2003TDB
Page 30 and 31: ----------------------calendar date
Page 32 and 33: time and conditions at Mars SOI(Mar
Page 34 and 35: time and conditions at Mars sphere-

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