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Path: Orbit/ThreeBody
% Simulate the Earth orbit to L2 point low thrust transfer.
Consists of the sequence: spiral out / coast / reverse thrust / halo orbit
Type L2OrbitSim for a demo.
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Form:
[t,y,dv] = L2OrbitSim( x, d, times )
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Inputs
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x (4,1) Decision variables [phase, T1, T2, dT]
- phase Initial phase angle of Earth orbit in xy plane
- T1 Time to stop spiral thrust arc
- T2 Time to start insertion thrust arc
- dT Duration of reverse thrust arc
d (.) Data structure describing spacecraft model and CRTBP
system
times (1,:) Vector of times over which to evaluate dynamic system.
Optional. Default is to use d.times.
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Outputs
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t (N,1) Time vector
y (N,7) State vector: [x, y, z, vx, vy, vz, mass]
dv (1,1) Total delta-v over trajectory
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References:
Online course notes, Prof. J.D. Mireles James, Rutgers University.
http://www.math.rutgers.edu/~jmireles/notes.html
M. T. Ozimek and K. C. Howell, "Low-Thrust Transfers in the Earth?Moon
System, Including Applications to Libration Point Orbits",
JOURNAL OF GUIDANCE, CONTROL, AND DYNAMICS Vol. 33, No. 2,
March/April 2010, DOI: 10.2514/1.43179
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Common: Graphics/Plot2D Common: Graphics/Plot3D Math: Linear/Cross Math: Linear/Unit Orbit: OrbitData/SEML2OrbitData Orbit: OrbitData/SunEarthMoonSystemConstants Orbit: ThreeBody/FCRTBPRHS
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