the centrifugal force per unit mass acting on a satellite in a circular orbit around the sun satisfies `FltimesT^(-n)` where n is

For a satellite moving in a circular orbit around the earth, the ratio of its potential energy to kinetic energy is

A satellite of mass m is in an elliptical orbit around the earth of mass M(M gt gt m) the speed of the satellite at its nearest point ot the earth (perigee) is sqrt((6GM)/(5R)) where R= its closest distance to the earth it is desired to transfer this satellite into a circular orbit around the earth of radius equal its largest distance from the earth. Find the increase in its speed to be imparted at the apogee (farthest point on the elliptical orbit).

For a satellite moving in a circular orbit around the earth, the ratio of its total mechanical energy to kinetic energy

An artificial satellite moving in a circular orbit around the earth has a total energy E_(0) . Its potential energy is

An artificial satellite moving in a circular orbit around the earth has a total energy E_(0) . Its potential energy is

The time period of a satellite in a circular orbit around the earth is T . The kinetic energy of the satellite is proportional to T^(-n) . Then, n is equal to :

If the centripetal force acting on a body revolving along a circular path of radius 25 m is 200 N, its KE is

If the angular momentum of a planet of mass m, moving around the Sun in a circular orbit is L, about the center of the Sun, its areal velocity is :

A satellite moves round the earth in a circular orbit of radius R making one revolution per day. A second satellite moving in a circular orbit, moves round the earth one in 8 days. The radius of the orbit of the second satellite is

Suppose the gravitational force varies inversely as the n^(th) power of distance. Then the time period of a planet in circular orbit of radius R around the sun will be proportional to-