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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Orbit: OrbitCoord/CEcl2SER Orbit: OrbitData/SunEarthMoonSystemConstants Orbit: OrbitMechanics/VEscape Orbit: ThreeBody/CRTBPRHS SC: BasicOrbit/CP2I SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: Ephem/CEcl2Eq Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit
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