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first park orbit coast anglerange anglerasc of launch site at 0 hrrasc of launch site at launcharglat of launch site at launchgreenwich sidereal time at 0 hrasymptote true anomalyasymptote argument of latitudeascending node to launch siteascending node to asymptotelocal circular velocityinjection velocityinjection delta-v249.509236 degrees79.672900 degrees166.529456 degrees273.099821 degrees95.554950 degrees247.094755 degrees150.163663 degrees175.227849 degrees96.311041 degrees175.801220 degrees7793.033366 meters/second11434.279080 meters/second3641.245714 meters/secondIn the launch1 solution display screens,rasc = right ascensionarglat = argument of latitude = sum of argument of perigee and true anomalyraan = right ascension of the ascending nodeThe output shown for ascending node to launch site and ascending node to asymptoteare the angles measured from the ascending node along the equator to the launch site at the launch timeand launch hyperbola asymptote, respectively. Also, since the calculations assume an initial circularpark orbit, the true anomaly on the hyperbola at injection is identically zero (injection occurs at perigee)and the argument of latitude of the maneuver is equal to the argument of perigee.Technical discussionThis section is a brief summary of the geometry and orbital mechanics involved in the design andanalysis of interplanetary injection trajectories.The following diagram, extracted from “JPL Publication 82-43, Interplanetary Mission DesignHandbook”, illustrates the basic geometry of the interplanetary launch problem. In this figure, represents inertial right ascension measured relative to the Vernal Equinox, represents geocentricdeclination measured relative to the Earth’s equator, is the launch azimuth measured positiveclockwise from true north, is the right ascension of the ascending node (RAAN), and Lis thegeocentric latitude of the launch site. Items with an “infinity” subscript refer to the hyperbolicasymptote of the outgoing or departure trajectory.Lpage 6