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Orbit that does not need maneuvering

  1. Oct 16, 2016 #1
    Hi!

    This is a textbook problem that I need help with (I want to practice as much as I can before the exams) and I hope that there is someone who can guide me. The question is:
    You’re doing a first-order analysis on a new satellite in an elliptical (e = 0.2) orbit at 700 km altitude. Can you design the orbit so no maneuvers are necessary to maintain it? Hint: consider secular J2 perturbations only – can the effects of Ω counteract with ω? If it can’t be done at 700 km, is another altitude feasible?

    2. Relevant equations
    See below

    3. The attempt at a solution
    I used the following equations (for J2 perturbations) :
    upload_2016-10-16_21-36-42.png

    And for p and n:
    upload_2016-10-16_21-36-36.png

    I inserted n and p into the first two equations and got:

    upload_2016-10-16_21-37-26.png

    I assumed that they were all constant, so I ended up with:
    upload_2016-10-16_21-39-17.pngupload_2016-10-16_21-39-31.png

    And this gave me of i1 = 90° and i2=63°. If we have these inclinations then there is no need for maneuvering. And now for the next question:

    The next question to answer is can the effects of Ω counteract with ω? If it can’t be done at 700 km, is another altitude feasible? I have no idea how to answer this question.

    As you can see I may be completely lost. I don't see my solution feasible since it doesn't actually answer the question about the no maneuvering bit. Anyone that can help me? Thanks!
     
    Last edited by a moderator: Oct 16, 2016
  2. jcsd
  3. Oct 17, 2016 #2
    Anyone that can help? : (
     
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