Cowell's Method - MICE Version: om_constants - File Exchange

Code covered by the BSD License

Highlights from
Cowell's Method - MICE Version

atan3 (a, b) four quadrant inverse tangent
ceqm_mice (t, y) first order form of Cowell's
cspice_furnsh(file) -Abstract
cspice_pxform(from, to, et) -Abstract
cspice_str2et(str) -Abstract
cspice_sxform(from, to, et) -Abstract
cspice_unload(file) -Abstract
eci2orb1 (mu, r, v) convert eci state vector to six classical orbital
gravity_mice (t, y) N degree and M order
mice_spkezr(targ, et, ref, ab... -Abstract
mice_spkpos(targ, et, ref, ab... -Abstract
oeprint1(mu, oev) print six classical orbital elements
om_constants astrodynamic and utility constants
readegm(fname) read gravity model data file
rkf78 (deq, neq, ti, tf, h, t... solve first order system of differential equations
svprint(r, v) print position and velocity vectors and magnitudes
tperiod (sma, ecc, inc, argpe... orbital periods
zzmice_dp(x) -Abstract
zzmice_str(x) -Abstract
cowell_mice.m
View all files

from Cowell's Method - MICE Version by David Eagle
PDF document and MATLAB script that demonstrates using Cowell’s method to predict orbital motion.

om_constants

function om_constants

% astrodynamic and utility constants

% Orbital Mechanics with Matlab

%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

global dtr rtd emu mmu smu omega req flat j2 aunit

dtr = pi / 180.0;

rtd = 180.0 / pi;

% earth gravitational constant (km**3/sec**2)

emu = 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;

Highlights from Cowell's Method - MICE Version

Highlights from
Cowell's Method - MICE Version