from
Circular Orbit Plane Change
by David Eagle
MATLAB script for solving the circular orbit plane change problem.
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| om_constants
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function om_constants
% astrodynamic and utility constants
% Orbital Mechanics with MATLAB
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global dtr rtd mu mmu smu omega req flat j2 aunit
dtr = pi / 180.0;
rtd = 180.0 / pi;
% earth gravitational constant (km**3/sec**2)
mu = 398600.436233;
% moon gravitational constant (km**3/sec**2)
mmu = 4902.800076;
% sun gravitational constant (km**3/sec**2)
smu = 132712440040.944;
% earth inertial rotation rate (radians/second)
omega = 7.292115486e-5;
% earth equatorial radius (kilometers)
req = 6378.1363;
% earth flattening factor (non-dimensional)
flat = 1.0 / 298.257;
% earth oblateness gravity coefficient (non-dimensional)
j2 = 0.00108263;
% astronomical unit (kilometers)
aunit = 149597870.691;
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