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1)What must be the orbital speed of a satellite in a circular orbit 740 above the surface of the earth?

2)What is the period of revolution of a satellite with mass that orbits the earth in a circular path of radius 8000 (about 1630 above the surface of the earth)?

  • PHYSIC -

    You must provide units with your numbers. You should have learned that by now

  • PHYSIC -

    Since 8000 - 1630 = 6370, the radius of the earth in km, I believe I am on safe ground assuming that you mean "740km" above the earth in your first question.

    The velocity required to maintain a circular orbit derives from Vc = sqrt(µ/r) where Vc = the velocity in m/s, µ = the earth's gravitational constant, 3.9863x10^14 m^3/sc^2 and r = the orbital radius in meters.

    Vc = sqrt[3.9863x10^14/(6370+740)1000]

    The period of a particular orbit derives from
    T = 2(Pi)sqrt(r^3/µ)

    I'll let you complete this one.

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