Path: Orbit/OrbitManeuver
% Low thrust delta v between two circular orbits.
The acceleration is aligned with the velocity vector. This equation is
an approximation assuming the orbit is nearly circular throughout the
spiral. See also LowThrustEscape.
The acceleration must be in the same units as a0 and mu.
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Form:
[dV, dVRatio, t] = LTSpiral( a0, af, accel, mu )
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Inputs
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a0 (1,:) Initial semi-major axis (km)
af (1,:) Final semi-major axis (km)
accel (1,1) Acceleration (km/s)
mu (1,1) Gravitational parameter (km^3/sec^2)
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Outputs
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dV (1,:) Total delta-v
dVRatio (1,:) Ratio of total delta-v to Hohmann Delta-V
t (1,:) Maneuver duration (days)
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References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 89-90.
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AC: ACData/ACTConstants Orbit: OrbitManeuver/DVHoh SC: SCData/sCTConstants Common: CommonData/Constants Common: CommonData/SwooshWatermark Common: CommonData/xSplashSmall Common: Database/Constant Common: General/CellToMat Common: General/DeleteCell Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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