Final answer:
To find the time for one orbit of a satellite placed in Earth orbit at a certain height, we can use Kepler's third law and the formula T = 2π√(r^3/(GM)). By plugging in the given values and solving the equation, we can determine the time it takes for the satellite to complete one orbit.
Step-by-step explanation:
To find the time it takes for the satellite to complete one orbit, we can use Kepler's third law which states that the period of an orbit is related to the radius of the orbit. The formula for the period is given by:
T = 2π√(r3/GM)
where T is the period, r is the radius of the orbit, G is the gravitational constant, and M is the mass of the Earth.
First, we need to convert the height of the satellite above the surface of the Earth to the radius of the orbit by adding the radius of the Earth (6370 km).
r = 600 km + 6370 km = 6970 km
Next, we can substitute the values into the formula and solve for T:
T = 2π√((6970 km)3/(6.67 x 10-11 N m2/kg2) x (5.97 x 1024 kg))
Calculating this expression will give us the time for one orbit of the satellite.