earth to mars transfer in matlab

main.m
% Define initial conditions
mu_earth = 3.986004418e5; % Earth's gravitational parameter (km^3/s^2)
mu_mars = 4.282837e4; % Mars' gravitational parameter (km^3/s^2)
a_earth = 149.6e6; % Earth's semimajor axis (km)
a_mars = 227.9e6; % Mars' semimajor axis (km)
e_earth = 0.0167; % Earth's eccentricity
e_mars = 0.0934; % Mars' eccentricity
inc = 1; % Inclination (deg)
RAAN = 0; % Right ascending node (deg)
w = 0; % Argument of periapsis (deg)

% Calculate delta-v for transfer using Hohmann transfer
a_transfer = (a_earth + a_mars)/2; % Semimajor axis of transfer orbit (km)
delta_v1 = sqrt(mu_earth/a_earth) * (sqrt((2*a_transfer)/(a_earth + a_transfer)) - 1); % Delta-v from Earth to transfer orbit (km/s)
delta_v2 = sqrt(mu_mars/a_mars) * (1 - sqrt((2*a_transfer)/(a_mars + a_transfer))); % Delta-v from transfer orbit to Mars (km/s)
delta_v_total = delta_v1 + delta_v2; % Total delta-v for transfer (km/s)
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