MATLAB: ODE45 to solve vector ode


I'm trying to solve the following differential equation
where I have and ,3×1 vectors, as intital conditions.
Here is my code:
clear all
mu = 400000; %km^3/s^2
r0 = [9000;1400;800];%km
v0 = [-1.3;6.3;3.7];%km/s
tspan = [0;30000];
ic = [r0;v0];
f = @(t,y)[y(2);-(mu*y(1))/(norm(y(1))^3)];
[ts,ys] = ode45(f,tspan,ic);
I'm getting the error of:
@(T,Y)[Y(2);-(MU*Y(1))/(NORM(Y(1))^3)] returns a vector of length 2, but the length of initial conditions vector is 6. The
vector returned by @(T,Y)[Y(2);-(MU*Y(1))/(NORM(Y(1))^3)] and the initial conditions vector must have the same number of
Error in ode45 (line 115)
odearguments(FcnHandlesUsed, solver_name, ode, tspan, y0, options, varargin);
Error in orbitplot (line 24)
[ts,ys] = ode45(f,tspan,ic);
How am I able to set up ode45 to be able to accept vectors as initial conditions?

Best Answer

  • You have a six element state vector. The y(1) and y(2) coming into your derivative function are not position and velocity vectors, they are the x and y position elements. It would probably be easier to write a short function for the derivative because of the calculations involved:
    function dy = gravity(y,mu)
    R = y(1:3);
    V = y(4:6);
    Rmag = norm(R);
    RDOT = V;
    VDOT = -mu * R / Rmag^3;
    dy = [RDOT;VDOT];
    Then call ode45 with a function handle that passes y and mu to the gravity function:
    [ts,ys] = ode45(@(t,y)gravity(y,mu),tspan,ic);
    ode45 isn't well suited for the orbit problem. You may have to use odeset( ) to create some tight tolerances to pass in to ode45 to get good results.