PropagateNBody:

Path: Orbit/OrbitSim

% Propagate n-bodies in an n-body problem.
 Inputs are the initial state vector, the time vector and the
 gravitational parameters.

 The demo is earth orbit and another for Alpha-Centauri
 including A and B and a hypothetical planet
 at 1 AU from Alpha-Centauri A.
  
 This function includes the right-hand-side and uses ode113 for
 propagation.
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   Form:
   x = PropagateNBody( x0, t, mass, name, tol, eps )
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   ------
   Inputs
   ------
   x0             (6*n,1)  State vector [r;v;r;v;r;v...]
   t              (1,:)    Time vector 
                  (1,:)    Masses
   name           {:}      Name of body
   tol            (1,2)    [abs rel]
   
   -------
   Outputs
   -------
   x              (6*n,:) 	State vector
  
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   References: http://www.physics.buffalo.edu/phy302/topic1/index.html
               http://www.scholarpedia.org/article/N-body_simulations             
--------------------------------------------------------------------------

Children:

Common: Database/Constant
Common: Graphics/AssignColors
Common: Graphics/NewFig
Common: Graphics/Plot2D
Common: Graphics/TimeLabl
Common: Graphics/TitleS
Math: Linear/Mag
Orbit: OrbitCoord/RPRA2AE
SC: BasicOrbit/El2RV

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