satellite orbit in matlab

main.m
% Constants
G = 6.67430e-11;     % Gravitational constant
M = 5.972e24;        % Earth mass
R = 6.371e6;         % Earth radius

% Initial conditions
r0 = R + 500e3;      % Initial distance from Earth's center
v0 = 7000;           % Initial velocity

% Time span
tspan = [0 2*pi*sqrt((r0^3)/(G*M))]; % One orbit period

% Differential equation for satellite motion
f = @(t, y) [y(3); y(4); -G*M*y(1)/(sqrt(y(1)^2 + y(2)^2))^3; -G*M*y(2)/(sqrt(y(1)^2 + y(2)^2))^3];

% Solve differential equation
[t, y] = ode45(f, tspan, [r0; 0; 0; v0]);

% Plot satellite orbit
figure;
plot(y(:,1), y(:,2));
axis equal;
xlabel('x (m)');
ylabel('y (m)');
title('Satellite Orbit Simulation');
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