Path: Orbit/OrbitMechanics
% Approximate time for an orbit to decay based on an exponential atmosphere.
Default units are km.
Type OrbDecay for a demo in earth orbit
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Form:
t = OrbDecay( h, cD, A, m, mu, R, rho0, hScale )
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Inputs
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h Altitudes [km]
cD Drag coefficient (2 to 4)
A Effective satellite area [m2]
m Satellite mass [kg]
mu Gravitational parameter [km3/sec2]
R Planet radius [km]
rho0 Base density (at zero altitude) [kg/m3]
hScale Atmospheric scale height (default is 6 km) [km]
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Outputs
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t Decay time
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References: Wiesel, W. E., Spaceflight Dynamics, McGraw-Hill, 1988,
pp. 83-86.
Hughes, P. C., Spacecraft Attitude Dynamics, John Wiley
1986, p. 259.
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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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