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Algorithm resources“Update to Mars Coordinate Frame Definitions”, R. A. Mase, JPL IOM 312.B/015-99, 15 July 1999.“JPL Planetary Ephemeris DE421”, E. M. Standish, JPL IOM 312.N-03-009, 24 April 2003.“Report of the IAU/IAG Working Group on Cartographic Coordinates and Rotational Elements of thePlanets and Satellites: 2000”, Celestial Mechanics and Dynamical Astronomy, 82: 83-110, 2002.“IERS Conventions (2003)”, IERS Technical Note 32, November 2003.“Planetary Constants and Models”, R. Vaughan, JPL D-12947, December 1995.“Preliminary Mars Planetary Constants and Models for Mars Sample Return”, D. Lyons, JPL IOM312/99.DTL-1, 20 January 1999.“Interplanetary Mission Design Handbook, Volume 1, Part 2”, JPL Publication 82-43, September 15,1983.“Interplanetary Mission Analysis and Design”, Stephen Kemble, Praxis Publishing, 2006.page 22
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 itcm_ocs software.The simulation summary screen display contains the following information:calendar date = calendar date of trajectory eventTDB time = Barycentric Dynamical Time time of trajectory eventTDB julian date = Barycentric Dynamical Time julian date of trajectory eventsma (km) = semimajor axis in kilometers or astronomical unitseccentricity = 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 (days) = orbital period in hours or daysdelta-vx = x-component of the impulsive TCM velocity vector in meters/seconddelta-vy = y-component of the impulsive TCM velocity vector in meters/seconddelta-vz = z-component of the impulsive TCM velocity vector in meters/seconddeltav = scalar magnitude of the impulsive TCM delta-v in meters/secondstransfer time = elapsed time from TCM to entry interface in daysThe comma-separated-variable disk file is created by the odeprt subroutine and contains the followinginformation:time (days) = simulation time since launch in daysrs2sc-x (au) = x-component of spacecraft position vector in astronomical unitsrs2sc-y (au) = y-component of spacecraft position vector in astronomical unitsrs2sc-z (au) = z-component of spacecraft position vector in astronomical unitsrs2sc-mag (au) = heliocentric radius magnitude of spacecraft in astronomical unitsvs2sc-x (km/sec) = x-component of spacecraft velocity vector in kilometers per secondvs2sc-y (km/sec) = y-component of spacecraft velocity vector in kilometers per secondvs2sc-z (km/sec) = z-component of spacecraft velocity vector in kilometers per secondvs2sc-mag (km/sec) = heliocentric velocity of spacecraft in kilometers per secondpage 23
Page 4 and 5: upper bound for TCM delta-v compone
Page 6 and 7: The next input is an integer that d
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 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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