Reusable Second Stage Rocket with Substages

I would like to propose a reusable second stage rocket based on the design I proposed for the first stage. The second stage will have the same design layout compared to the first stage. The first major difference will be, the vacuum optimized nozzle. The second difference will be, the ejected tanks will not be recoverable. They will be made of a special plastic which would decompose into gas while falling towards the earth.

There will be three different versions of these rockets. The first version will have maximum payload bay for LEO missions. The second version will have more stacked tanks and smaller payload bay for high energy missions. The third version will only have propellent tanks and a disposable aerodynamic cone to be used for interplanetary missions and second stage refueller. The additional tanks carried by the second stage would be transferred to an orbiting second stage to extend its range.

Once the second stage completes its mission, it would rotate around and direct its engines towards earth with a slight angle. As it orbits the earth, the ions at that altitude will decelerate the rocket and reduce its altitude slowly. The objective is to use the thin atmosphere to slow down the rocket with no fuel consumption. Additionally, it will allow the rocket to approach its launch location by circulating the earth. After certain altitude, the rocket will fire its engines to decelerate the rocket actively. The air filling the Lincoln hat like void of the rocket will be ejected in a controlled manner from the top of the rocket, like the first stage, to maneuver the rocket. The descending trajectory of the rocket will be planned to make it land on the launch platform.