A MATLAB Script for Interplanetary Gravity-Assist Trajectory Design

-plane coordinates of incoming hyperbola(Earth mean ecliptic and equinox of J2000)------------------------------------------b-magnitudeb dot rb dot tb-plane anglev-infinityr-periapsisdecl-asymptoterasc-asymptote10926.123827 kilometers-5624.826686 kilometers9367.043644 kilometers329.015557 degrees7461.895071 meters/second6551.899868 kilometers69.561615 degrees359.934069 degreesheliocentric orbital elements and state vector of the flyby planet(Earth mean ecliptic and equinox of J2000)------------------------------------------sma (km) eccentricity inclination (deg) argper (deg)1.0820914211e+008 6.7937075123e-003 3.3945145412e+000 5.4791266699e+001raan (deg) true anomaly (deg) arglat (deg) period (days)7.6652480729e+001 1.6186109023e+002 2.1665235693e+002 2.2470163874e+002rx (km) ry (km) rz (km) rmag (km)+4.29752391622680e+007 -9.99955112678054e+007 -3.84947712346467e+006 +1.08907262975836e+008vx (kps) vy (kps) vz (kps) vmag (kps)+3.19380548390697e+001 +1.37091300934537e+001 -1.65550710959099e+000 +3.47954062860684e+001ARRIVAL CONDITIONS==================arrival calendar date14-Jan-2010arrival TDB time 03:40:25.798arrival TDB julian date 2455210.653076flyby-to-arrival time225.807368 daysheliocentric arrival delta-v vector and magnitude(Earth mean ecliptic and equinox of J2000)------------------------------------------arrival delta-vxarrival delta-vyarrival delta-vzarrival delta-v-3467.202912 meters/second-2289.213745 meters/second755.119148 meters/second4222.819026 meters/secondpre-impulse heliocentric orbital elements and state vector of the spacecraft(Earth mean ecliptic and equinox of J2000)------------------------------------------sma (km) eccentricity inclination (deg) argper (deg)1.7688276799e+008 3.9074776462e-001 2.4685986487e+000 3.2054753420e+002raan (deg) true anomaly (deg) arglat (deg) period (days)3.4838038539e+002 1.7366712574e+002 1.3421465994e+002 4.6961136376e+002rx (km) ry (km) rz (km) rmag (km)-1.32035535104875e+008 +2.06286564188419e+008 +7.56463416445357e+006 +2.45040308490532e+008vx (kps) vy (kps) vz (kps) vmag (kps)-1.60226359485842e+001 -8.71331877377552e+000 -5.07078284513825e-001 +1.82456546931295e+001post-impulse heliocentric orbital elements and state vector of the spacecraft(Earth mean ecliptic and equinox of J2000)------------------------------------------page 5