Path: OpticalNavigation/Core
% Lunar mission planning Compute transfer delta-Vs and simulate a lunar landing starting from low Earth orbit. The entire spacecraft lands, there is no portion left in lunar orbit. The steps are: # Set the elements and date so that transfer orbit and lunar orbit match. # Compute the insertion delta-v # Circularize the lunar orbit # Do a Hohmann descent to the powered landing altitude # Do a powered landing using BilinearTangent --------------------------------------------------------------------------
Orbit: OrbitCoord/RARP2A Orbit: OrbitCoord/RPRA2AE Orbit: OrbitManeuver/DVHoh Orbit: OrbitMechanics/RVOrbGen Orbit: Visualization/EarthMoon Orbit: Visualization/TrajectoryPlot Propulsion: Rocket/RocketMass SC: BasicOrbit/Period SC: BasicOrbit/RV2El SC: BasicOrbit/VOrbit SC: Ephem/CEcl2Eq SC: Ephem/PlanetPosJPL SCPro: Landers/BilinearTangentLaw Common: Database/Constant Common: GUIs/Figui Common: General/CreateLatexTable Common: General/DisplayLatexTable Common: Graphics/PlotDoubleYAxis Common: Graphics/TimeLabl Common: Time/Date2JD Math: Integration/RK4 Math: Linear/Mag
Back to the OpticalNavigation Module page