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Path: Orbit/OrbitMechanics
% Computes the parking orbit plane for a heliocentric injection. The parking orbit is defined in the ECI frame. The injection velocity is defined in the ecliptic frame. Type EclipticInjectionPlane for a demo. Since version 11. -------------------------------------------------------------------------- Form: [rAAN, inc] = EclipticInjectionPlane( jD, v ) -------------------------------------------------------------------------- ------ Inputs ------ jD (1,1) Julian date of injection vEcl (3,1) Velocity vector in the ecliptic frame (xy ecliptic plane) ------- Outputs ------- rAAN (1,1) Right ascension of the ascending node (rad) inc (1,1) Orbit inclination (rad) dVEq (3,1) Earth-relative velocity in ECI (km/s) nEq (3,1) Orbit-normal vector for parking orbit --------------------------------------------------------------------------
Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DeBlankLT Common: General/MatToCell Common: General/Watermark Common: Graphics/Axis3D Common: Graphics/Mesh2 Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/XLabelS Common: Graphics/YLabelS Common: Graphics/ZLabelS Common: Time/DTSToDTA Common: Time/Date2JD Math: Linear/Cross Math: Linear/Dot Math: Linear/DupVect Math: Linear/Mag Math: Linear/Unit Math: Trigonometry/CosD Math: Trigonometry/SinD Orbit: Interplanetary/EarthHelioState Orbit: OrbitCoord/OrbNEl Orbit: OrbitCoord/SLR Orbit: OrbitMechanics/RVOrbGen SC: BasicOrbit/CP2I SC: BasicOrbit/E2M SC: BasicOrbit/E2Nu SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/Nu2E SC: BasicOrbit/Nu2M SC: Ephem/CEcl2Eq SC: Ephem/SunV1
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