Path: Orbit/ThreeBody

% Simulate an escape trajectory from Earth using CRTBPRHS. 

   Since version 2014.1
   s = EarthEscape( el0, jD, days, gRatio )

   el0     (1,6)   Earth orbit elements
   jD      (1,1)   Reference Julian date
   days    (1,1)   Number of days to run simulation
   gRatio  (1,1)   Ratio of Earth/Sun gravity at which to stop sim

   s        (.)    Data structure with fields:
                     s.crtbp   CRTBP system data
                     s.time    Time vector (sec)
                     s.rECI    ECI position
                     s.vECI    ECI velocity
                     s.rHE     Helio centric position (xy=ecliptic)
                     s.vHE     Helio centric velocity
                     s.gEarth  Gravitational acceleration from Earth
                     s.gSun    Gravitational acceleration from Sun
                     s.vEsc    Theoretical escape velocity magnitude
                     s.dVEscape Delta-v vector for escape from init orbit


Common: Time/Date2JD
Math: Linear/Mag
Math: Linear/Unit
Orbit: OrbitCoord/CEcl2SER
Orbit: OrbitData/SunEarthMoonSystemConstants
Orbit: OrbitMechanics/VEscape
Orbit: ThreeBody/CRTBPRHS
SC: BasicOrbit/El2RV
SC: Ephem/CEcl2Eq

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