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Elliptic orbit proofs

  1. Oct 29, 2009 #1
    1. The problem statement, all variables and given/known data
    Prove that:
    r=a(cos E-e)(ihat,xi)+(sqrt(a*p)) *sin E (ihat,eta)


    2. Relevant equations

    E=eccentric anomaly
    e=eccentricity


    3. The attempt at a solution

    Rotational matrices come into play here, but I'm not sure to what extent. alpha=beta*gamma*delta, with their respective matrices.

    This appears to have no 3rd component on it (only xi and eta).

    I have all of the equations for E, e, p, a, theta, and so on to substitute in for the proof.

    How is the rotational matrix involved?
     
  2. jcsd
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