1. Not finding help here? Sign up for a free 30min tutor trial with Chegg Tutors
    Dismiss Notice
Dismiss Notice
Join Physics Forums Today!
The friendliest, high quality science and math community on the planet! Everyone who loves science is here!

Orbit of satellite 2nd order ODE using Matlab

  1. Sep 11, 2012 #1
    Hi,

    I am completely stuck on this problem that has been given to us.

    I must solve a set of 2nd order differential equations using Euler's method. It is for a geosychronous orbit of a satellite, meaning the orbit is circular and the velocity vector is perpendicular to the radius vector (r.V=0). The equations are:

    d2x/dt2=-k2x/r3

    and

    d2y/dt2=-k2y/r3

    k^2,r and V are all given.

    My first step was to set up sets of ode's to solve.

    for the first equation we have,

    let y1=x and y2=dy1/dt

    hence, dy2/dt= -k2y1/r3

    and for the second,

    let y3=y and y4=dy3/dt

    hence, dy4/dt= -k2y3/r3

    which I think is correct.

    Now I have to pass this into a matlab function which uses eulers method. But I have no idea how to implement it. my main problem at the moment is that I do not know what to use as my initial y1,2,3,4 values in the function vector.

    Can any one help?
     
  2. jcsd
  3. Sep 11, 2012 #2
    I am not sure why anyone would want to solve and ODE for motion which is completely known, but still.

    You can take any initial position as long as it is on the orbit (circle). The velocity, as you say, is perpendicular to it and must be equal to the length of the orbit divided by one sidereal day.
     
Know someone interested in this topic? Share this thread via Reddit, Google+, Twitter, or Facebook




Similar Discussions: Orbit of satellite 2nd order ODE using Matlab
  1. 2nd order ODE (Replies: 20)

  2. 2nd ORDER ODE MIRROR (Replies: 4)

Loading...