I need help with MATLAB programmin. I am having a hard time with plotting in MATLAB. The following outputs a plot of the earth with a orbit inside it. The problem is that the calculations in the orbit do not include the radius of the earth. How do I increase the radius of the orbit by the radius of the earth to make the orbit outside of the earth.   % Given parameters omega_earth = rad2deg(7.2921151467e-5); period_of_repetition = 1 / 2; ecc = 0.74; inc = 63.4349; raan = -86.915798; argp = 270; f = linspace(0, 360, 100); mu = 398600.4418; t = 0:99; % Calculate semi-major axis a = ((omega_earth * period_of_repetition) / (360))^(-2/3); % Calculate periapsis and apoapsis distances periapsis_distance = a * (1 - ecc); apoapsis_distance = a * (1 + ecc); % Initialize arrays to store Cartesian coordinates and velocities x = zeros(1, 100); y = zeros(1, 100); z = zeros(1, 100); vx = zeros(1, 100); vy = zeros(1, 100); vz = zeros(1, 100); % Loop through each true anomaly for i = 1:length(f)     % Call kep2cart for each true anomaly     [x(i), y(i), z(i), vx(i), vy(i), vz(i)] = kep2cart(a, ecc, inc, raan, argp, f(i)); end % Plot 3D orbit figure; plot3(x, y, z, 'LineWidth', 2, 'Color', 'r'); hold on; % Plot the Earth as a simple sphere earth_radius = 6.371e3; % Earth's radius in meters [x_earth, y_earth, z_earth] = sphere; earth = surf(x_earth * earth_radius, y_earth * earth_radius, z_earth * earth_radius); colormap([0 0 1]); % Set the color to blue for Earth alpha(earth, 0.7); % Set transparency for Earth   % Set equal axis scale axis equal; % Set labels and title xlabel('X (meters)'); ylabel('Y (meters)'); zlabel('Z (meters)'); title('3D Representation of the Orbit around Earth'); % Add grid and legend grid on; legend('Orbit', 'Earth'); % Display the plot hold off;     function [x, y, z, vx, vy, vz] = kep2cart(a, ecc, inc, raan, argp, f)     %=========================================================================%     % FUNCTION: kep2cart     % DESCRIPTION: Converts kepler orbital elements to cartesian coordiantes     % INPUTS:     %   > a = semi-major axis [km]     %   > ecc = eccentricity     %   > inc = inclination angle [degs]     %   > raan = right ascension of the ascending node [degs]     %   > argp = arguement of periapsis [degs]     %   > f = true anomaly [degs]     %     % OUPUTS:     %   > x = 1x1 position value in the x-direction [km]      %   > y = 1x1 position value in the y-direction [km]     %   > z = 1x1 position value in the z-direction [km]     %   > vx = 1x1 velocity value in the x-direction [km/s]     %   > vy = 1x1 velocity value in the y-direction [km/s]     %   > vz = 1x1 velocity value in the z-direction [km/s]     %=========================================================================%          % Gravitational parameter      mu = 398600.4418;  % (km^3/s^2)          % Calculate angular momentum     h = sqrt(a * (1-ecc^2)*mu);    % (km^2/s)          % Calculate position and velocity in the periforcal frame     r_w = ((h^2 / mu) / (1 + ecc * cosd(f))) .* [cosd(f), sind(f), 0];     v_w = (mu / h) .* [-sind(f), ecc + cosd(f), 0];          % Calculate the Rotational Matrix     R1 = [cosd(-argp) -sind(-argp) 0;           sind(-argp) cosd(-argp)  0;                0           0       1];     R2 = [1      0          0;           0 cosd(-inc) -sind(-inc);           0 sind(-inc) cosd(-inc)];          R3 = [cosd(-raan) -sind(-raan) 0;           sind(-raan) cosd(-raan)  0;                0           0       1];          % Calculate position vector     r_rot = r_w * R1 * R2 * R3;          % Calculate velocity vector     v_rot = v_w * R1 * R2 * R3;          % Define the cartesian coordinates     x = r_rot(1);     y = r_rot(2);     z = r_rot(3);     vx = v_rot(1);     vy = v_rot(2);     vz = v_rot(3); end