earth to mars transfer in matlab

To calculate a transfer from Earth to Mars in Matlab, one can use the interplanetary equations of motion and numerical integration techniques such as the Runge-Kutta algorithm.

Here's an example of a transfer calculation:

```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)
```910 chars17 lines```

This code defines initial conditions such as the gravitational parameters, semimajor axes, eccentricities, inclination, and node angles of Earth and Mars. Using these parameters and the Hohmann transfer equation, the code calculates the delta-v required to transfer from Earth's orbit to Mars' orbit.

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