This problem concerns the properties of circular orbits for a satellite of mass m orbiting a planet of mass M in an almost circular orbit of radius r. In doing this problem, you are to assume that the planet has an atmosphere that causes a small drag due to air resistance. "Small" means that there is little change during each orbit so that the orbit remains nearly circular, but the radius can change slowly with time. The following questions will ask about the net effects of drag and gravity on the satellite's motion, under the assumption that the satellite's orbit stays nearly circular. Use G if necessary for the universal gravitational constant. What is the potential energy U of the satellite?Express your answer in terms ofm, M, G, and r. What is the kinetic energy K of the satellite?Express the kinetic energy in termsof m, M, G, and r.

A) U = - GMm/r

B) K = 0.5 mGM/r

Explanation:

A) The potential energy U of the satellite

U = - GMm/r

G = universal gravitational constant which is ( 6.67e-11 Nm^2/c^2 )

M = mass of the planet

m = mass

r = distance ( radius )

B) Kinetic energy

kinetic energy expressed as K = 0.5 m Vo^2

NOTE : Vo^2 = GM / r

hence kinetic energy will be expressed as

K = 0.5 mGM/r

the box does not move because you need to use a force greater than 300 n. you are only using 50 n. it needs to at least be 301 n for the box to move because then it is an unbalanced force and it will move the way that the greater force is pushing it. if you use only 300 n it will be a balanced force and will not move because the force you are exerting on the   box is the same as its force.

hope this !

im sorry if i went too in depth, i am going to include a link to a video on khan academy that will explain this.   hope that you like the video and that it explains more in detail to you.

that is the link.