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Highlights from
Repeating Ground Track Orbit Design

  • atan3four quadrant inverse tangent
  • brentsolve for a single real root of a nonlinear equation
  • eqxrathis function computes the intermediate right ascension
  • erotthis function returns the value of the earth rotation angle
  • etilt1this function computes quantities related to the orientation
  • funargthis function computes fundamental arguments (mean elements)
  • gast4this function computes the greenwich sidereal time
  • get_utc_timeinteractive request and input of universal coordinated time
  • getdateinteractive request and input of calendar date
  • getoe(ioev)interactive request of classical orbital elements
  • gravityfirst order equations of orbital motion
  • julianJulian date
  • kepler1solve Kepler's equation for circular,
  • kozai1analytic orbit propagation
  • nut2000_lplow precison nutation based on iau 2000a
  • obliq(t)function to compute mean obliquity of the ecliptic in arcseconds
  • orb2eci(mu, oev)convert classical orbital elements to eci state vector
  • readgm(fname)read gravity model data file
  • repeat_eqmfirst order equations of orbital motion
  • rkf78solve first order system of differential equations
  • rpt2func(x)rz objective function
  • rpt4fun1delta-fundamental interval objective function
  • sun2precision ephemeris of the Sun
  • times_novasthis function computes the terrestrial time (tt) julian date
  • repeat3.m
  • repeat2.m
  • repeat1.m
  • repeat4.m
  • View all files

Repeating Ground Track Orbit Design

by

David Eagle (view profile)

 

19 Nov 2012 (Updated )

Four MATLAB scripts for designing and analyzing repeating ground track orbits.

repeat.zip
atan3.m
brent.m
egm96.dat
eqxra.m
erot.m
etilt1.m
funarg.m
gast4.m
getdate.m
getoe.m
get_utc_time.m
gravity.m
julian.m
kepler1.m
kozai1.m
license.txt
nut2000_lp.m
obliq.m
orb2eci.m
readgm.m
repeat.pdf
repeat1.m
repeat2.m
repeat3.m
repeat4.m
repeat_eqm.m
rkf78.m
rpt2func.m
rpt4fun1.m
sun2.m
times_novas.m

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