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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.

rv2bp2(mu, r, v)
function [bplane, ibperr] = rv2bp2(mu, r, v)

% convert body-centered cartesian position 
% and velocity vectors to b-plane elements

% input

%  mu = gravitational constant (km**3/sec**2)
%  r  = position vector (kilometers)
%  v  = velocity vector (kilometers/second)

% output

%  bplane(1)  = hyperbolic speed (kilometers/second)
%  bplane(2)  = declination of asymptote (radians)
%  bplane(3)  = right ascension of asymptote (radians)
%  bplane(4)  = radius magnitude (kilometers)
%  bplane(5)  = periapsis radius (kilometers)
%  bplane(6)  = b-plane angle (radians)
%  bplane(7)  = b dot t
%  bplane(8)  = b dot r 
%  bplane(9)  = b magnitude (kilometers)
%  bplane(10) = b-plane vector x-component
%  bplane(11) = b-plane vector y-component
%  bplane(12) = b-plane vector z-component
%  ibperr     = error flag (1 ==> not hyperbola)

% Orbital Mechanics with MATLAB

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

ibperr = 0;

% angular momentum vector

wv = cross(r, v);

c1 = norm(wv);

rrd = dot(r, v);

% position magnitude

rm = norm(r);

% velocity magnitude

vx = norm(v);

% hyperbolic speed

vhe2 = vx * vx - 2.0d0 * mu / rm;

if (vhe2 < 0.0d0)
    
   % orbit is not hyperbolic; set error flag
   
   ibperr = 1;
   
   tv = zeros(3);
   
   rv = zeros(3);
   
   bplane = zeros(12);
   
   return
   
end

vhem = sqrt(vhe2);

bplane(1) = vhem;

rdot = rrd / rm;

p = c1 * c1 / mu;

% semimajor axis

a = rm / (2.0d0 - rm * vx^2 / mu);

% orbital eccentricity

e = sqrt(1.0d0 - p / a);

% cosine and sine of true anomaly

cta = (p - rm) / (e * rm);

sta = rdot * c1 / (e * mu);

b = sqrt(p * abs(a));

ab = sqrt(a * a + b * b);

z = rm / c1 * v - rdot / c1 * r;

pv = cta * r / rm - sta * z;

qv = sta * r / rm + cta * z;
    
sv = -a / ab * pv + b / ab * qv;
    
bv = b * b / ab * pv + a * b / ab * qv;

sv = sv / norm(sv);

% declination of asymptote

bplane(2) = asin(sv(3));

% right ascension of asymptote

bplane(3) = atan3(sv(2), sv(1));

bplane(4) = rm;

% perapsis radius of hyperbola

rp = (e - 1.0d0) * mu / vhe2;

bplane(5) = rp;

ab = sqrt(sv(1) * sv(1) + sv(2) * sv(2));

% t vector

tv(1) = sv(2) / ab;

tv(2) = -sv(1) / ab;

tv(3) = 0.0d0;

rv = cross(sv, tv);

rv = rv / norm(rv);

% b dot t

bdott = dot(bv, tv);

bplane(7) = bdott;

% b dot r

bdotr = dot(bv, rv);

bplane(8) = bdotr;

% b-plane angle (radians)

theta = atan3(bdotr, bdott);

bplane(6) = theta;

% b magnitude (kilometers)

bplane(9) = rp * sqrt(1.0d0 + 2.0d0 * mu / (rp * vhe2));

% b-plane vector

bplane(10:12) = bv;


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