Answer:
Explanation:
Let the radius of orbit of geostationary satellite be R .
Time period of satellite = 2πR / V₀ where V₀ is orbital velocity
T = 2πR / √gR
T= 2πR / √(GM / R )
T = 2πR¹°⁵ / √GM
R¹°⁵ = T x √GM / 2π
T = 23.934 h = 23.934 x 60 x 60 s = 86126.4 s
R¹°⁵ = 86126.4 x √ ( 6.67 x 10⁻¹¹ x 5.972 x 10²⁴ ) / 2π
= 86126.4 x √ ( 398.33 x 10¹² ) / 2π
= 86126.4 x 19.95 x 10⁶ / 2π
= 273.428 x 10⁹
R = 42.92 x 10⁶ m
= 42920 km
Radius of orbit = 42920 km
radius of earth = 6370 km
Altitude of satellite = 42920 - 6370 = 36550 km .
In US customary unit = 36550 x 10³ /.9144 yards
= 36550 x 10³ /(.9144 x 1760 ) miles
= 22771 miles .
