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. u = -(gmm) / (r)k = (gmm) / (2r)part athe total mechanical energy of the satellite will the samevary in a more complex way than is listed herepart bas the force of the air resistance acts on the satellite, the radius r of the satellite's orbit will the samevary in a more complex way than is listed herepart cas the force of the air resistance acts on the satellite, the kinetic energy of the satellite will the samevary in a more complex way than is listed herepart das the force of the air resistance acts on the satellite, the magnitude of the angular momentum of the satellite with respect to the center of the planet will the samevary in a more complex way than is listed here