Closest Approach Between the Earth and Heliocentric Objects: cae2oprt(jdate) - File Exchange

Code covered by the BSD License

Highlights from
Closest Approach Between the Earth and Heliocentric Objects

atan3 (a, b) four quadrant inverse tangent
cae2o(x) Earth-to-object closest approach objective function
cae2oprt(jdate) print Earth-to-object closest approach conditions
caeqm (time, y) heliocentric equations of motion
caevent(objfunc, prtfunc, ti,... predict close approach events
eci2orb1 (mu, r, v) convert eci state vector to six classical orbital
gdate (jdate) convert Julian date to Gregorian (calendar) date
hel_eqm (t, y) heliocentric equations of motion
heqms (t, y) first order form of the heliocentric equations of motion
jd2str(jdate) convert Julian date to string equivalent
jplephem (et, ntarg, ncent) reads the jpl planetary ephemeris and gives
julian (month, day, year) Julian date
kepler1 (manom, ecc) solve Kepler's equation for circular,
keycheck pause and request user input
minima (f, a, b, tolm) one-dimensional minimization
oeprint(mu, oev) print six classical orbital elements
orb2eci(mu, oev) convert classical orbital elements to eci state vector
readoe2(filename) read orbital elements 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
uvector(x) unit vector
cae2ho.m
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from Closest Approach Between the Earth and Heliocentric Objects by David Eagle
MATLAB script that predicts closest approach between the Earth and heliocentric objects.

cae2oprt(jdate)

function cae2oprt(jdate)

% print Earth-to-object closest approach conditions 

% required by cae2ho.m

% Orbital Mechanics with MATLAB

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

global aunit drsaved

% convert julian day to calendar date and time strings

[cdstr, utstr] = jd2str(jdate);

fprintf('\n\ntime and conditions at closest approach');
fprintf('\n=======================================\n\n');

fprintf('calendar date        ');

disp(cdstr);

fprintf('\nTDB time             ');

disp(utstr);

fprintf('\nTDB Julian date      %16.8f \n\n', jdate);

% display slant range

fprintf('geocentric distance  %16.8f  AU \n\n', drsaved);

fprintf('geocentric distance  %16.8f  km \n\n', aunit * drsaved);

Highlights from Closest Approach Between the Earth and Heliocentric Objects

Highlights from
Closest Approach Between the Earth and Heliocentric Objects