Post a New Question


posted by .

A satellite is launched into orbit 200 kilometers above the Earth.The orbital velocity of a satellite is given by the formula v=√GmE/r, where v is the velocity in meters per second, G is a given constant, mE is the mass of Earth, and r is the radius of the satellite"s orbit. The radius of Earth is 6,380,000 meters. What is the radius of the satellite's orbit in meters?

  • Math -

    From your given information,
    r = 6,380,000 + 200,000 = 6,580,000 m or
    ....6,380 + 200 = 6,580 km.

    The velocity required to maintain a circular orbit around the Earth may be computed from the following:

    Vc = sqrt(µ/r)

    where Vc is the circular orbital velocity in feet per second, µ (pronounced meuw as opposed to meow) is the gravitational constant of the earth, ~1.40766x10^16 ft.^3/sec.^2, and r is the distance from the center of the earth to the altitude in question in feet. Using 3963 miles for the radius of the earth, the orbital velocity required for a 250 miles high circular orbit would be Vc = 1.40766x10^16/[(3963+250)x5280] = 1.40766x10^16/22,244,640 = 25,155 fps. (17,147 mph.) Since velocity is inversely proportional to r, the higher you go, the smaller the required orbital velocity.

    Insert your data to derive your orbital velocity.

Answer This Question

First Name
School Subject
Your Answer

Related Questions

More Related Questions

Post a New Question