Code covered by the BSD License

### Highlights from A MATLAB Script for Time and Coordinate Calculations

• brentsolve for a single real root of a nonlinear equation
• coe2eqoe(coe)convert classical orbital elements to
• coe2mee(mu, coe)convert classical orbital elements to modified equinoctial orbital elements
• ecf2eciecf-to-eci transformation
• eci2ecfeci-to-ecf transformation
• eci2fpc1(gast, reci, veci)convert inertial state vector to flight path coordinates
• eci2mee(mu, reci, veci)convert eci state vector to
• eci2orb1convert eci state vector to six classical orbital
• eci2orb2convert eci state vector to complete set of classical orbital elements
• 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
• findleap(jdate)find number of leap seconds for utc julian date
• fpc2ecftransform relative flight path coordinates
• fpc2eci(gst, fpc)convert relative flight path coordinates to inertial state vector
• funargthis function computes fundamental arguments (mean elements)
• gast2this function computes the greenwich sidereal time
• gast4this function computes the greenwich sidereal time
• gdateconvert Julian date to Gregorian (calendar) date
• geodet1geodetic latitude and altitude
• geodet4geodetic to geocentric coordinates
• get_tdb_timeinteractive request and input of Barycentric Dynamical 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
• getsvinteractive request of state vector
• gettimeinteractive request and input of universal time
• hrs2hmsconvert decimal hours to hours,
• jd2str(jdate)convert Julian date to string equivalent
• jdfunctionobjective function for tdb2utc
• julianJulian date
• kepler1solve Kepler's equation for circular,
• lla2eciconvert geodetic altitude, latitude and longitude to eci position vector
• mee2coe(mee)convert modified equinoctial elements to classical orbit elements
• nod(jdate)this function evaluates the nutation series and returns the
• nut2000bnutation based on iau 2000b theory
• obliq(t)function to compute mean obliquity of the ecliptic in arcseconds
• oeprint1(mu, oev, ittype)print six classical orbital elements
• oeprint3(mu, oev, ittype)print complete set of orbital elements
• om_constantsastrodynamic and utility constants
• orb2eci(mu, oev)convert classical orbital elements to eci state vector
• orb2hyper(oev)this function converts classical orbital elements
• osc2meanconvert osculating classical orbital elements
• rv2fpctransform from cartesian coordinates
• rv2hyperconvert position and velocity vectors to
• rv2tle(reci, veci)convert osculating position and velocity vectors
• svprint(r, v)print position and velocity vectors and magnitudes
• tdb2utcconvert TDB julian date to UTC julian date
• times_novasthis function computes the terrestrial time (tt) julian date
• utc2tdbconvert UTC julian date to TDB julian date
• utc2ttconvert UTC julian date to TT julian date
• csystems.m
• elong2ra.m
• View all files
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# A MATLAB Script for Time and Coordinate Calculations

### David Eagle (view profile)

Interactive MATLAB script that can be used to perform time and coordinate calculations.

File Information
Description

PDF document and interactive MATLAB script called csystems.m which can be used to perform a variety of time and coordinate calculations. This script performs the following types of time calculations;

convert UTC calendar date and time to UTC Julian date, convert UTC Julian date to UTC calendar date and time, Greenwich apparent sidereal time, convert Universal Coordinated Time (UTC) to Terrestrial Time (TT), convert Universal Coordinated Time (UTC) to Barycentric Dynamical Time (TDB), convert Barycentric Dynamical Time (TDB) to Universal Coordinated Time (UTC)

The csystems script can also be used to perform the following types of coordinate calculations;

convert geodetic coordinates to eci position vector, convert eci state vector to ecf state vector, convert eci state vector to classical orbital elements, convert classical orbital elements to eci state vector, convert flight path coordinates to eci state vector, convert eci state vector to relative flight path coordinates, convert classical orbital elements to modified equinoctial elements, convert modified equinoctial elements to classical orbital elements, convert osculating orbital elements to mean elements, convert eci state vector to Two Line Elements (TLE)

MATLAB release MATLAB 7.12 (R2011a)