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
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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]
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Outputs
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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
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AC: ACData/ACTConstants Orbit: OrbitCoord/RPRA2AE SC: BasicOrbit/CP2I SC: BasicOrbit/E2Nu SC: BasicOrbit/El2RV SC: BasicOrbit/M2E SC: BasicOrbit/M2EApp SC: BasicOrbit/M2EEl SC: BasicOrbit/M2EHy SC: BasicOrbit/M2Nu SC: BasicOrbit/M2NuPb SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeBlankLT Common: General/DeleteCell Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/AssignColors Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle Common: Graphics/TimeLabl Common: Graphics/TitleS Math: Linear/DupVect Math: Linear/Mag
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