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Semi-major axis from cartesian co-ordinates

  1. Nov 23, 2009 #1
    Can anyone suggest how to calculate the semi major axis of a body in an elliptical orbit when all I've got is x,y,z,vx,vy and vz?

    I'm guessing I need to calculate the eccentricity too. I really suck at conversions like this. :(
     
  2. jcsd
  3. Nov 23, 2009 #2

    ideasrule

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    Keplerian orbits are all two-dimensional, so you don't need to worry about z or vz; they can be defined as 0.

    Take a look at http://en.wikipedia.org/wiki/Orbit#Analysis_of_orbital_motion, especially the equation at the very end. Provided you know the mass & position of the body being orbited, the semi-major axis (a) can easily be calculated.
     
  4. Nov 23, 2009 #3

    D H

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    You better have at least one other thing. You need to know the body's gravitational constant, G*M, which are often combined as a single parameter μ.

    Hint: How is the specific angular momentum related to the semi-major axis?
    Hint: You need to calculate the eccentricity.

    No, they can't. He is given non-zero values. Ignoring them *will* yield the wrong answer.
     
  5. Nov 23, 2009 #4

    ideasrule

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    Yes, if you're actually given a set of positions and velocities in all dimensions, you can't ignore one of them. Ignoring z and Vz only works if you get to arbitrarily define your coordinate system, in which case you can set both to 0.
     
  6. Nov 24, 2009 #5
    aha, so I can use:

    [tex]\textbf{h}=\textbf{r}\times\textbf{v}[/tex]

    to find the specific angular momentum and then

    [tex]a\left(1-e\right)=\frac{h^{2}}{GM}[/tex]

    But then how can I separate the eccentricity and semi-major axis?
     
  7. Nov 24, 2009 #6

    D H

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    Simple: Compute the eccentricity vector and take its magnitude. So what's this eccentricity vector thing?

    [tex]\vec e = \frac{\vec v \times \vec h}{GM} - \frac{\vec r}{||\vec r||}[/tex]
     
  8. Nov 24, 2009 #7
    Ok, I've done that now.

    One thing though, I also found the following equations which I found http://microsat.sm.bmstu.ru/e-library/Ballistics/kepler.pdf [Broken]:

    [tex]a=\frac{GMr}{2GM-rv^{2}}[/tex]

    and

    [tex]e=\sqrt{1-\frac{h^{2}}{GMa}}[/tex]

    I've tested both sets of equations and I get the same numbers for the eccentricity, which is good. However, I'm getting different results for the semi major axis. :(
     
    Last edited by a moderator: May 4, 2017
  9. Nov 24, 2009 #8

    D H

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    http://photos-d.ak.fbcdn.net/hphotos-ak-snc1/hs017.snc1/4224_95107990559_95107705559_3010885_4034015_s.jpg [Broken]

    The vis-viva equation, doh!

    [tex]v^2=GM\left(\frac 2 r - \frac 1 a\right)[/tex]

    I was thinking to much of your problem in term of converting cartesian position and velocity to orbital elements (six of them). The specific angular momentum and the eccentricity vector are the keys to unlocking that puzzle. However, all you wanted was the semi-major axis. The vis-viva is the key to answering that particular problem.

    That's because you have the relation between angular momentum wrong, here:
    That should be

    [tex]a(1-e^2) = \frac {h^2}{GM}[/tex]
     
    Last edited by a moderator: May 4, 2017
  10. Nov 26, 2009 #9
    DH, you are an absolute star and a lifesaver!! Thanks so much for the help!!
     
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