Blade Hexagonal Structure

I named my rocket as Blade. Now on I will reference it as Blade. In this article, I would like to clarify my Patented monolithic gradient hexagonal structure. The load bearing and support of this high aspect ratio rocket was made possible by two things: gradient honeycomb design and pressurized propellent. Gradient honeycomb distributes the load over a larger volume which is a good thing for a lifting body, to have more surface area for lift. The gradual increase of diameter of the hexagons allows well balanced load and pressure distribution. These small voids allow smooth pressure difference transition between the 600 psi fuel tanks and the ambient atmosphere down to vacuum. The void sections facing the belly of the rocket are filled with pressurized methane gas (not up to 600 psi but lower). They soak heat from the belly of the rocket during Mach speeds and used as cold gas thrusters to maneuver the rocket in vacuum and steer it during its return flight. Each hexagonal structure that is filled with liquid methane and liquid oxygen is directly go to the aft engines. They feed the relevant unified engine directly. No piping required. The fuel distribution between the hexagonal reserves is also managed at the aft section of the rocket. Minimizing the piping and complexity.

The hexagonal structures double as structural support, fuel tank and pipe. The pressure of the propellent coupled with this structure strengthens the whole body. Weight induced to keep propellent under pressure allowed the rocket to be shaped as a wing (which requires much more structural support than a pencil shaped rocket). The solution to use honeycomb design allowed pressurized inner structure which added strength without additional weight. This self-supporting architecture allowed a lighter solution for the problem and turned the rocket into a reusable space ship. By allocating some of these hexagonal structures for the by pass air added almost no additional weight penalty but tremendously improved the fuel economy. Additionally, the bypass ducks at the nose reduced the shock waves on the nose to acceptable level.

Finally, and most importantly, such a high aspect ratio structure traveling at very high supersonic speeds could only stay in one piece if the thrust was distributed evenly on its structure. Pressure fed small unified engines allowed very precise throttling with minimal leg time. Only, fast and precise response of the engines could achieve that, not the classical turbopump engines.