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.
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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)
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Inputs
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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
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Outputs
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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
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See also LambertTOF, RVFromKepler
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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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