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Minimum velocity for GEO orbit transfer

  1. Oct 11, 2009 #1
    1. The problem statement, all variables and given/known data
    A GEO spacecraft crosses the earth’s equatorial
    plane when its true anomaly is 30 deg. The
    eccentricity of the orbit is 0.1 and its initial
    inclination is 5 deg with respect to the equator.
    What minimum velocity increment is required to
    transfer this GEO to an equatorial orbit?


    2. Relevant equations
    e=.1
    theta=30 degrees
    i=5 degrees
    cos E=e+cos(theta)/1+e*cos(theta)
    deltav=2*v*sin(i/2)


    3. The attempt at a solution
    Not sure where to start. I am thinking I begin with the equations above. I think it is a plane transfer but not sure how to do it.
     
  2. jcsd
  3. Oct 12, 2009 #2

    gabbagabbahey

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    Homework Helper
    Gold Member

    Use conservation of energy.

    What is the energy of the spacecraft in is original (tilted) orbit? What would be its energy if it were in an equatorial orbit?
     
  4. Oct 12, 2009 #3

    D H

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    Staff Emeritus
    Science Advisor

    Conservation of energy is not going to help here. Even a small plane change maneuver can be fairly expensive delta-v wise, and ideally there will be no change in orbital energy. For example, the International Space Station's orbit has a 51.6 degree inclination because plane change maneuvers are expensive. A 51.6 degree inclination is the lowest inclination orbit into which vehicles launched from Baikonur can be placed. (Baikonur is at 45.6 degrees latitude, so vehicles could launch into a 45.6 degree orbit from there. However, that would result in spent first stages dropping on China. A 45.6 degree inclination is the lower limit imposed by physics. Politics adds a 6 degree surtax.)


    When can you perform a plane change? For an elliptical orbit, which of the choices requires the least delta-v?

    From the last of the relevant equations, you obviously you need to compute the velocity. How do you compute that?

    BTW, that last equation is not quite right. That is the equation for a pure plane change from a circular orbit. What is the equation for a pure plane change from an elliptical orbit?


    Note: I am assuming you are to do a pure plane change in this problem -- that is, you are to keep the satellite in geosynchronous orbit. It is a tad cheaper to simply cancel the z component of velocity at the right time, but that will result in a non-geosynchronous orbit.


    These lecture slides might be of use. Start at slide 34.
    http://web.nps.navy.mil/~ssweb/AA4362/week8/wk8_lecture2.htm [Broken]
     
    Last edited by a moderator: May 4, 2017
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