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The additional kinetic energy to be provided to a satellite of mass m revolving around a planet of mass M , to transfer it forms a circular orbit of radius R_(1) to another of radius R_(2)(R_(2)gtR_(1)) is

The additional kinetic energy to be provided to a satellite of mass m revolving around a planet of mass M , to transfer it forms a circular orbit of radius R_(1) to another of radius R_(2)(R_(2)gtR_(1)) is

The additional kinetic energy to be provided to a satellite of mass m revolving around a planet of mass M , to transfer it forms a circular orbit of radius R_(1) to another of radius R_(2)(R_(2)gtR_(1)) is

The work done to increases the radius of orbit of a satellite of mass 'm' revolving around a planet of mass M from orbit of radius R into another orbit of radius 3R is

A satellite revolving around a planet has orbit velocity 10km/s . The additional velocity required for the satellite to escape from the gravitational field of the planet is

Two satellites of masses 80 kg and 120 kg revolve round a planet in circular orbits of radii 16 R and 9 R respectively, where R is radius of the planet. The ratio of the speeds of satellites will be

For a satellite at a distance 11R from the surface of a planet P of radius R. Its time period is 24hrs. Evaluate time period of another satellite at a distance 2R from surface of P

An artificial satellite is revolving around a planet of mass M and radius R, in a circular orbit of radius r. From Kelper's Third law about the period of a satellite around a common central body, square of the period of revolution T is proportional to the cube of the radius of the orbit r. Show usnig dimensional analysis, that T = (k)/(R ) sqrt((r^3)/(g)), Where k is a dimensionless constant and g is acceleration due to gravity.

An artificial satellite is revolving around a planet of mass M and radius R in a circular orbit of radius r. From Kepler's third law about the period of a satellite around a common central body, square of the period of revolution T is proportional to the cube of the radius of the orbit r. Show using dimensional analysis that T=(k)/(R) sqrt((r^(3))/(g)) where k is dimensionless RV g constant and g is acceleration due to gravity.