Path: Orbit/OrbitControl
% Perform targeting in Earth orbit using the Lambert algorithm. Takes the states of two spacecraft at an epoch and a transfer time and performs Lambert targeting. Returns the delta-V and a flag for the long or short transfer. Propagation of the second state is performed with two-body dynamics using RVFromKepler. Checks if the transfer hits the Earth. Another radius may be input or input empty ([]) to skip the check. -------------------------------------------------------------------------- Form: [dV,tM,okFlag] = DVTarget(r1,v1,r2,v2,dT) % Earth [dV,tM,okFlag] = DVTarget(r1,v1,r2,v2,dT,mu,rPmin) % other planet(s) -------------------------------------------------------------------------- ------ Inputs ------ r1 (3,1) Position of spacecraft 1 (km) v1 (3,1) Velocity of spacecraft 1 (km/s) r2 (3,1) Position of spacecraft 2 v2 (3,1) Velocity of spacecraft 2 dT (1) Transfer time (s) mu (1) Gravitional parameter, default is Earth rPmin (1) Minimum periapsis allowed, default is Earth radius ------- Outputs ------- dV (:) Struct of delta-Vs .a (3,1) First delta-V (km/s) .b (3,1) Second delta-V (km/s) .total (1,1) Total delta-V tM (1) Flag: +/-1 for short/long transfer okFlag (1) Flag: 1 if maneuver is OK, 0 if hits the Earth elT (1,6) Transfer elements -------------------------------------------------------------------------- See also LambertTOF, RVFromKepler --------------------------------------------------------------------------
Orbit: OrbitMechanics/LambertTOF Orbit: Visualization/PlotLambertTransfer SC: BasicOrbit/RV2El SC: BasicOrbit/RVFromKepler Common: Database/Constant Math: Linear/Cross Math: Linear/Dot Math: Linear/Mag Math: Linear/Unit
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