Q. 38

# A satellite is in

Given

Radius of earth = R = 6400 km

Aphelion earth - satellite distance ra = 6R

Perihelion earth - satellite distance rp = 2R

We know for an ellipse  Where e is the eccentricity of the ellipse, and the semi major axis.  Now, the angular momentum of the satellite is conserved we then, we have Where m is the mass of satellite and vp and va are the velocities at the perigee and apogee respectively Now from conservation of energy at the apogee and perigee Where K and U are the kinetic and gravitational potential energy of the satellite Where M is the mass of earth. Using the relation between vp and va above we have Putting the values of rp and ra we have  To transfer the satellite to a circular orbit of radius 6R the satellite’s velocity has to be maintained at a value of Rate this question :

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