DVTarget:

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
   ------
   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

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 See also LambertTOF, RVFromKepler
--------------------------------------------------------------------------

Children:

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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