Path: Orbit/OrbitManeuver

% Computes the delta-V to insert into a planetary or lunar orbit.
 The maneuver is done instantaneously. The default mu is for the
 Earth's moon.

 Type OrbMnvrInsertion for a lunar insertion demo.
    deltaV = OrbMnvrInsertion( r, v, rT, vT, rP, i, mu, qCToP )

   r           (3,1)  Spacecraft position in central body frame
   v           (3,1)  Spacecraft velocity in the central body frame
   rT          (3,1)  Planet position in the central body frame
   vT          (3,1)  Planet velocity in the central body frame
   rP          (1,1)  Perigee altitude (km)
   i           (1,1)  Planet orbit inclination (rad)
   mu          (1,1)  Gravitational parameter (Moon is the default)
   qCToP       (4,1)  Quaternion from central body to planet fixed frame

   deltaV      (3,1)  Vector velocity change in the central body frame



Common: Database/Constant
Common: Graphics/Plot3D
Common: Quaternion/QForm
Math: Linear/Cross
Math: Linear/Mag
Math: Linear/Unit
Orbit: OrbitCoord/RPRA2AE
Orbit: OrbitMechanics/RVOrbGen
SC: BasicOrbit/Period
SC: BasicOrbit/RV2El
SC: BasicOrbit/VOrbit

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