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Path: Orbit/ThreeBody
% Simulate an escape trajectory from Earth using CRTBPRHS.
Since version 2014.1
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Form:
s = EarthEscape( el0, jD, days, gRatio )
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Inputs
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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
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Outputs
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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
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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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