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A satellite is in an elliptic orbit arou...

A satellite is in an elliptic orbit around the earth with aphelion of 6R and perihelion of 2R where `R = 6400 km` is the radius of the earth. Find eccentricity of the orbit. Find the velocity of the satellite at apogee and periagee. What should be done if this satellite has to be transferred to a circular orbit of radius 6R ?
`[G = 6.67 xx 10^(-11) " SI unit and " M = 6 xx 10^(24) kg]`

Text Solution

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We know that Perigee `(r_p) = a(1-e) = 2R...(1)`, Apogee `(r_a) = a(1 +e) = 6R ` ..... (2)
Solving (1) and (2)` rArr ` we get eccentricity (e) ` =1/2`
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