Path: Orbit/OrbitMechanics
% Low thrust delta v between two circular orbits.
The acceleration is aligned with the velocity vector. Computes the final apogee
Since version 2.
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Form:
[aF, dVRatio, t] = AFLTSpiral( a0, dV, accel, mu )
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Inputs
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a0 Initial semi-major axis
dV (:) Total delta-v
accel acceleration
mu Gravitational parameter
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Outputs
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aF (:) Final semi-major axis
dVRatio (:) Ratio of total delta-v to Hohmann Delta-V
t Maneuver duration (days)
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References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 89-90.
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Orbit: OrbitManeuver/DVHoh Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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