A satellite is in an elliptical orbit with eccentricity of 0.6 and perigee altitude 1000 Km. Determine: a) The semi major axis b) The period of revolution

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Given: eccentricity (e) = 0.6; perigee (Rp) = 1000 

Rp = a (1-e)1000 = a (1-0.6) => a (semi major axis) = 2500 Km.

By Kepler’s law; period of revolution T2= a3=> T = 125000 Sec.

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