• Velocity for a circular orbit at a height 2R above the earth (R is radius of the earth) is
    A) $√{{GM}/R}$ B) $√{{2GM}/R}$ C) $√{{GM}/{2R}}$ D) $√{{GM}/{3R}}$
  • A satellite is in a circular orbit of radius 2R around the earth. At a certain point on its path a rocket fixed to the satellite is fired such that velocity of the satellite along the tangent increases. The resulting orbit of the satellite would be
    A) same as before
    B) circular orbit with radius greater than 2R
    C) elliptical orbit with minimum distance from the centre of earth equal to 2R
    D) elliptical orbit with maximum distance from the centre of earth equal to 2R
  • A satellite at a height R above the earth has a velocity $√{{2gR}\/5}$ directed at right angles to line joining it to the center of the earth. Its orbit is
    A) elliptical with closest distance of 2R
    B) circular orbit of radius 2.4R
    C) elliptical with farthest distance of 2R
    D) circular orbit of radius 2R
  • If a satellite in a circular orbit in the equatorial plane with a period of 24 hours were to rotate from east to west it would appear above a point on the equator at intervals of
    A) 24 hours B) 12 hours C) 8 hours D) 6 hours
  • A satellite in a circular orbit in the equatorial plane spinning from west to east appears above a certain point on the equator at intervals of 24 hours. If it were to spin in the opposite sense, this time interval would be
    A) 12 hours B) 8 hours C) 9 hours D) 6 hours