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===================program leo2geo_ocs===================transfer time algorithm-----------------------Edelbaum algorithm (non-coplanar orbits)initial guess type------------------linear guess with tangential thrustinggravity model type------------------j2 earth gravity model------------------------beginning of finite burn------------------------sma (km) eccentricity inclination (deg) argper (deg)0.700000000000D+04 0.615067684519D-16 0.285000000000D+02 0.000000000000D+00raan (deg) true anomaly (deg) arglat (deg) period (min)0.206748308333D-14 0.285866456178D+03 0.285866456178D+03 0.971419368695D+02rx (km) ry (km) rz (km) rmag (km)0.191377284137D+04 -.591734870255D+04 -.321285820480D+04 0.700000000000D+04vx (kps) vy (kps) vz (kps) vmag (kps)0.725856076669D+01 0.181305405204D+01 0.984408031306D+00 0.754605384101D+01------------------end of finite burn------------------sma (km) eccentricity inclination (deg) argper (deg)0.420000000000D+05 0.999999999999D-03 0.100000000000D+01 0.360000000000D+03raan (deg) true anomaly (deg) arglat (deg) period (min)0.000000000000D+00 0.423922295262D+02 0.423922295262D+02 0.142768906774D+04rx (km) ry (km) rz (km) rmag (km)0.309960418384D+05 0.282912582669D+05 0.493825749949D+03 0.419689619582D+05vx (kps) vy (kps) vz (kps) vmag (kps)-.207699129982D+01 0.227794898386D+01 0.397617474165D-01 0.308294103563D+01transfer time 15.0823889600487 hoursspacecraft mass 835.576420850925 kilogramspropellant mass 164.423579149075 kilogramsdelta-v 5813.28840908474 meters/secondThe following are typical transfer trajectory, optimal control <strong>and</strong> orbital element plots for this example.They were created with the Grapher plotting program (www.goldensoftware.com).The first plot is a view of the transfer trajectory from a north pole viewpoint looking down on theequatorial plane. The unit of each trajectory coordinate is Earth radii.page 8
This next plot illustrates the behavior of the pitch <strong>and</strong> yaw steering angles during the transfer.page 9
Page 1 and 2: Program leo2geo_ocsContinuous Low-T
Page 3 and 4: Dynamics, Vol. 22, No. 3, May-June
Page 5 and 6: ************************* initial g
Page 7: The level of output from the differ
Page 11 and 12: page 11
Page 13: The Edelbaum algorithm is described
Page 16 and 17: wheremsc iis the initial spacecraft
Page 18 and 19: dhh dt2p s 2wncos Ldkk dt2p s 2w
Page 20 and 21: sin 1uTr1tan uT,nThe pitch angle is
Page 22 and 23: 23JR122hsin L k cos LeJ 1242 22r2
Page 24 and 25: APPENDIX AContents of the Simulatio
Page 26 and 27: APPENDIX BTypical Sparse Optimizati

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