Non-tubular rocket stage landing apparatus

A method of using a non-tubular rocket stage landing apparatus for receiving a landing non-tubular rocket stage having a vertical perspective having at least one horizontal non-circular cross section along the vertical length and a downward view showing all non-circular circumference sections within a pass-through non-circular circumference, hereafter called a non-circular pass through circumference and having a point most distant from the center axis of the platform, the method comprising the steps of providing a non-tubular rocket stage landing apparatus comprising

• a platform, an area, a perimeter, a top, a bottom, and a center,
• a dampening cushioning device comprising a base not attached to but in rotational communication with the center of the platform, a dampening cushioning region above the base, and a protruding top with a base element attached to the dampening cushioning region and configured to participate in diffusing hot gas from ignited fuel away from the dampening cushioning device and the landing site of the landing non-tubular rocket stage and avoid having the hot gas blowing back to the landing non-tubular rocket stage,
• an exhaust diffuser device comprising a base having a first diameter, a first inside surface, a first edge in communication with the platform to form multiple openings configured to direct hot gases from ignited fuel from the landing non-tubular rocket stage away from the dampening cushioning device on the platform, the landing site of the landing non-tubular rocket stage, and avoid having the hot gas blowing back to the landing non-tubular rocket stage, a mid-region with a second inside surface and a second diameter attached to the dampening cushioning device and the second inside surface, and an upper section with a third diameter, a third inside surface, and a third edge configured to releasably attach to a base of a landing non-tubular rocket stage, the exhaust diffuser device having, a truncated cone shape with an outer surface and the first diameter is larger than the second diameter that is larger than the third diameter;
• a hollow shell configured to vertically pass a non-tubular rocket stage with a noncircular pass-through circumference comprising an overall first shape configured to receive the non-tubular rocket stage, an outer surface, an inner surface, an upper end having an upper opening with a fourth edge with a first noncircular circumference having a second shape at least as large as the non-circular pass through circumference, a lower region with a second circumference having a third shape at least as large as the non-circular pass through circumference and less than the first circumference and configured to expose the third edge of the exhaust diffuser device and a flared bottom with a third circumference and an inside surface between the second circumference and the third circumference that is configured to enclose and be in communication with the outer surface of the exhaust diffuser device to direct ignited fuel to the diffuser top and outward away from the dampening cushioning device and from the landing site of the landing non-tubular stage to avoid blow back and damage to the landing non-tubular stage, and
• a rotational device configured to be in communication with the hollow shell and the landing non-tubular rocket with the noncircular pass-through circumference and to rotate the hollow shell to align the hollow shell with the landing noncircular rocket with the noncircular pass-through circumference of the rocket,
• providing a landing nontubular stage a pre-determined target area on earth containing the rocket non-tubular stage landing apparatus,
• refining the position of the center of the rocket non-tubular stage landing apparatus to be the target of the descending landing non-tubular stage to receive the landing non-tubular stage;
• rotating the hollow shell until the first non-circular circumference having a second shape at least as large as the non-circular pass-through circumference aligns with the non-circular pass-through circumference of the descending non-tubular rocket stage, and
• retrieving the rocket nontubular stage intact to form a retrieved non-tubular rocket stage.