APlanet:

Path: Orbit/OrbitMechanics

% Perturbing acceleration due to a planet on a spacecraft.
 The spacecraft is within the sphere of influence of another body. 
 The equations become
  2 
 d r       mu r
  --    +   ---- = a
 	2          3
 dt        |r|

 This function is valid when r << rho. Multiple planets can be input at once.

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   Form:
   [a, aP] = APlanet( r, mu, rho )
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   ------
   Inputs
   ------
   r           (3,1)   Vector of the spacecraft from the central body
   mu          (:)     Planet gravitational parameter(s)
   rho         (3,:)   Vector of the perturbing planet(s) from the central body

   -------
   Outputs
   -------
   a           (3,1)   Total acceleration
   aP          (3,:)   Accelerations of individual planets

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   Reference: Bond, V.R., M.C. Allman, Modern Astrodynamics
              Princeton University Press, 1996, pp. 203-204.
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Children:

Math: Linear/Mag

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