Height of the satellite's orbit: \( h = 35780 \) km
Radius of Earth: \( R = 6400 \) km
Tangential velocity: \( v = 3.08 \) km/s
Step 2: Finding the orbital radius The satellite moves in a circular orbit around Earth. The total orbital radius \( r \) is: \[ r = R + h \] \[ r = 6400 + 35780 = 42180 \text{ km} \] Step 3: Finding the circumference of the orbit The satellite travels along a circular path. The circumference (\( C \)) of the orbit is given by: \[ C = 2\pi r \] \[ C = 2 \times 3.1416 \times 42180 \] \[ C \approx 264983.3 \text{ km} \] Step 4: Calculating the time period The time period \( T \) is the total distance traveled divided by the velocity: \[ T = \frac{\text{Circumference}}{\text{Velocity}} \] \[ T = \frac{264983.3}{3.08} \] \[ T \approx 86000 \text{ seconds} \] Converting to hours: \[ T = \frac{86000}{3600} \approx 23.89 \text{ hours} \] Thus, the time taken by the satellite to complete one revolution is approximately 24 hours.