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A MATLAB Script for Propagating Interplanetary Trajectories from Earth to Mars

A MATLAB Script for Propagating Interplanetary Trajectories from Earth to Mars

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Numerically integrate the orbital equations of motion of an Earth to Mars interplanetary trajectory.

atan3 (a, b)
function y = atan3 (a, b)

% four quadrant inverse tangent

% input

%  a = sine of angle
%  b = cosine of angle

% output

%  y = angle (radians; 0 =< c <= 2 * pi)

% Orbital Mechanics with Matlab

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

epsilon = 0.0000000001;

pidiv2 = 0.5 * pi;

if (abs(a) < epsilon)
    y = (1 - sign(b)) * pidiv2;
    return;
else
    c = (2 - sign(a)) * pidiv2;
end

if (abs(b) < epsilon)
    y = c;
    return;
else
    y = c + sign(a) * sign(b) * (abs(atan(a / b)) - pidiv2);
end

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