Question

a) What linear speed must an Earth satellite have to be in a circular orbit at an altitude of 141 km above Earth's surface? (b) What is the period of revolution?

Answer #1

**IN an orbit**

**Fc = Fg**

**m*v^2/r = G*M*m/r^**

**v = sqrt(GM/r)**

**M = Mass of earth = 5.98*10^24**

**G = gravitational constant = 6.67*10^-11
Nm^2/kg^2**

**r = orbital radis = (R+h)**

**R = radius of earth = 6.4*10^6 m**

**h = altitude = 141000 m**

**V =
sqrt(6.67*10^-11*5.98*10^24/(6.4*10^6+141000))**

**v = 7809 m/s
<<<<======ANSWER**

**+++++++++++++++++++++++++**

**time period T = 2*pi*r/V**

**T = 2*pi*r^(3/2)/sqrt(GM)**

**T =
2*pi*(6.4*10^6+141000)^(3/2)/sqrt(6.67*10^-11*5.98*10^24)**

**T = 5263 s <<<<<=======ANSWER**

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