|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
Path: Orbit/ThreeBody
% Compute a stable initial state for a HALO orbit
Type HALOInit for a demo.
Since version 11.
--------------------------------------------------------------------------
Form:
d = HALOInit( Ax,Az, system, point, d0, doPlot );
--------------------------------------------------------------------------
------
Inputs
------
Ax (1,1) Amplitude of oscillation in the x direction (AU)
Az (1,1) Amplitude of oscillation in the z direction (AU)
system (:) String name of system: 'SEM' or 'EM'
point (1,1) Which libration point: L1 (1) or L2 (2)
d0 (.) Data structure output from previous call. Optional.
doPlot (1,1) Flag to plot (1) or not (0)
-------
Outputs
-------
d (.) Data structure output with system constants and fields:
.point
.x0
.x0f
.tf
.x0Hist
.t
.xSTM
.x
--------------------------------------------------------------------------
References:
Online course notes, Prof. J.D. Mireles James, Rutgers University.
http://www.math.rutgers.edu/~jmireles/notes.html
--------------------------------------------------------------------------
Common: Graphics/NewFig Orbit: OrbitData/EarthMoonSystemConstants Orbit: OrbitData/SunEarthMoonSystemConstants Orbit: ThreeBody/CRTBPLinearSystem Orbit: ThreeBody/HALOState
Back to the Orbit Module page