Software Listing of Author : "Darin Koblick"

This is a GUI that I had developed to find the palindrome of any number. The underlying algorithm will take any positive 2+ digit number, reverse the sequence, and add the reversed sequence onto the original number. Example: 196 <--------- Starting Number Sequence +691 <--------- Reversed Number Sequence --------- 887 The algorithm will then check to see if the result is palindromic. Since 887 does not equal it's reversed counterpart, 788, this is not palindromic yet. The resulting number,887 is now reversed yet again following the processes until a palindrome is reached. 887 + 788 -------- 1675 + 5761 ---------- 7436 and so on ... The user will have to compile the palinsum.c function using the Matlab MEX compiler. Typing in 'mex palinsum.c' should accomplish this o a 32-bit Matlab environment with minimal...

  • Platform: Matlab, Scripts

The bulirsch-Stoer single-step ODE propagator has come to MATLAB in form of a MEX adaptation of Juergen Dietel's Numerical ODE solver. This may very well be the fastest single-step numerical propagator released on the Mathworks FileExchange. All functions are written in c++ and must be compiled to run on MATLAB. This code has been verified to compile correctly using MS Visual Studio 2010. Please Compile using the following command sequence: >> mex BulirschMex.cpp bulirsch.cpp basis_r.cpp t_dgls.cpp vmblock.cpp See testDriver.m for sample orbit propagation comparisons using Burlisch-Stoer vs ODE113.

  • Platform: Matlab, Scripts

Convert WGS 84 (CTS, ECEF) Coordinates to ECI (CIS, Epoch J2000.0) Coordinates. This function has been vectorized for speed. The associated error in converting between coordinate frames is on the order of 1.2*10^-11 km when compared to STK ephemeris output. To run this function type the following command in a MATLAB prompt: >> [r_ECI v_ECI] = ECEFtoECI(JD,r_ECEF,v_ECEF); Where JD is a Julian Date Vector [1 x N] r_ECEF is the position vector in ECEF coordinates [3 x N] v_ECEF is the velocity vector in ECEF coordinates [3 x N] r_ECI is the position vector in ECI coordinates [3 x N] v_ECI is the velocity vector in ECI coordinates [3 x N]

  • Platform: Matlab, Scripts

Convert ECI (CIS, Epoch J2000.0) Coordinates to WGS 84 (CTS, ECEF) Coordinates. This function has been vectorized for speed. Example Function Call: >> [r_ECEF v_ECEF] = ECItoECEF(JD,r_ECI,v_ECI); Where: JD is the Julian Date vector [1 x N] (units are in days) r_ECI is the position vector [3 x N] (any units are permitted) v_ECI is the velocity vector [3 x N] (any units are permitted)

  • Platform: Matlab, Scripts

Convert a specified Julian Date Vector to Greenwich Apparent Sidereal Time (GAST). The expected input matrix may contain multiple dimensions. The output matrix will be in the same size as the input matrix. Warning: Use caution when using GAST as a substitute for Greenwich Mean Sidereal Time (GMST). To run JD2GAST, use the following code sequence: GAST = JD2GAST(JD); Where: JD is the Julian Date input (days) GAST is the resulting Greenwich Apparent Sidereal Time output (0 to 360deg)

  • Platform: Matlab, Scripts

Convert orbital elements to a state vector, or a state vector back to orbital elements. Most readily available Keplerian orbital element conversion utilities do not address circular or parabolic orbits. This set of routines will address the complete spectrum of orbits from a circular equatorial orbit to a retrograde hyperbolic orbit without error. All functionality is vectorized for computational efficiency. Example Function Call One: >> [r_ECI v_ECEF] = orb2rv(p,e,i,O,o,nu); Where: p = semilatus rectum (km) [1 x N] e = Eccentricity [1 x N] i = Inclination (rad) [1 x N] O = Right Ascension of the Ascending Node (rad) [1 x N] o = Argument of Perigee (rad) [1 x N] nu = True Anomaly (rad) [1 x N] Example Function Call Two: >>[a,e,i,O,o,nu] = rv2orb(r_ECI,v_ECI) Where r = Position State Vector in km (ECI) [3 x N] v = Velocity State...

  • Platform: Matlab, Scripts

RaDec2AzEl will take the Right Ascension and Declination in the topocentric reference frame, site latitude and longitude as well as a time in GMT and output the Azimuth and Elevation in the local horizon reference frame. List of Inputs: Topocentric Right Ascension (Degrees) Topocentric Declination Angle (Degrees) Lat (Site Latitude in degrees -90:90 -> S(-) N(+)) Lon (Site Longitude in degrees -180:180 W(-) E(+)) UTC (Coordinated Universal Time YYYY/MM/DD hh:mm:ss) List of Outputs: Local Azimuth Angle (degrees) Local Elevation Angle (degrees) Sample Function Call: [Az El] = RaDec2AzEl(294.9891115,-20.8235624,39.007,-104.883,'1994/05/14 13:11:20.59856')

  • Platform: Matlab, Scripts

Convert a time given in UTC to Solar Apparent or Solar Mean Time. External Function Call Sequence: >> [SAT,SMT] = UTC2SolarApparentTime('2000/03/20 15:00:00',-1.416667); >> [SAT,SMT] = UTC2SolarApparentTime('2000/09/23 15:00:00',-1.416667); UTC (Coordinated Universal Time YYYY/MM/DD hh:mm:ss) [N x 19] char Lon (Site Longitude in degrees -180:180 W(-) E(+)) [N x 1] SAT (Solar Apparent Time YYYY/MM/DD hh:mm:ss) [N x 19] char SMT (Solar Mean Time YYYY/MM/DD hh:mm:ss) [N x 19] char

  • Platform: Matlab, Scripts

Compute the equation of time with accuracy on the order of seconds. This routine can handle multiple millenniums. Function Call With Time String: >> EQtime = EquationOfTime('2000/01/01 00:00:00'); Function Call With Julian Date: >> EQtime = EquationOfTime(2451544.5); Input List: UTCjd (Coordinated Universal Time YYYY/MM/DD hh:mm:ss or Julian Date (Fractional Days)) [N x M] (double or char) Output List: EQtime (Equation of Time Solution for a specified date in fractional minutes) [N x 1] (double)

  • Platform: Matlab, Scripts

Convert a specified Julian Date Vector to Greenwich Mean Sidereal Time (GMST). The expected input matrix may contain multiple dimensions. The output matrix will be in the same size as the input matrix. Warning: Use caution when using GMST as a substitute for Greenwich Apparent Sidereal Time (GAST). To run JD2GMST, use the following code sequence: GMST = JD2GMST(JD); Where: JD is the Julian Date input (days) GMST is the resulting Greenwich Mean Sidereal Time output (0 to 360deg)

  • Platform: Matlab, Scripts

This algorithm will accept a Latitude, Longitude and Altitude location as well as a specific universal coordinated time. It will use this information and calculate the position of the moon in a local coordinate frame (az and alt aka az and el). Example Function Call: [Az El] = LunarAzEl('1991/05/19 13:00:00',50,10,0) Input List: UTC Date and Time - Use format YYYY/MM/DD hh:mm:ss Latitude - Site Latitude in degrees -90:90 -> S(-) N(+) Longitude - Site Longitude in degrees -180:180 W(-) E(+) Altitude - Site Altitude in km Output List: Az - Lunar Azimuth angle in degrees El - Lunar Elevation/Altitude Angle in degrees

  • Platform: Matlab, Scripts

Predict the azimuth and elevation of the Sun within +/- 1 degree at any geodetic latitude, longitude and altitude. Function Call: [Az El] = SolarAzEl('2008/02/18 13:10:00',60,15,0) Input List: UTC Date and Time - Use format YYYY/MM/DD hh:mm:ss Latitude - Site Latitude in degrees -90:90 -> S(-) N(+) Longitude - Site Longitude in degrees -180:180 W(-) E(+) Altitude - Site Altitude in km Output List: Az - Solar Azimuth angle in degrees El - Solar Elevation/Altitude Angle in degrees

  • Platform: Matlab, Scripts
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