The motion of low orbit satellites can be approximated by saying that the needed

Question

The motion of low orbit satellites can be approximated by saying that the needed centripetal on the for the circular or is equal 9 (the gravitational acceleration as observed a) surface of Earth). bit assumption sm/sec any problem due to the atmosphere What Using this and neglecting is the orbital speed of the satellite? b) Setting the radius of the orbit equal to the radius of the Earth R-640okm. How long does it take for one orbit? c) What is the weight of the astronauts on board of that satellite? Explain why?

Explanation / Answer

Solution:

a) Given that centripetal acceleration = v^2/R = g= 9.8 m/s^2

=> v= orbital speed = sqrt [(9.8)(R)] where R is the radius of the satellite's orbit.

                               = sqrt ( 9.8 * 6.4 *10^6) = 7919.6 m/s

b) Time = distance /speed

= circumference of the orbit / speed = 2 * pi * (6.4 e6) / 7919.6 = 5077.58 s

                                                          = 1.41 hours

c) Weight of the astronauts on board is zero since they float when on board. They are accelerating at the same rate as the earth they feel weightless.

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