The idea is to come up with a liquid rocket design that can be implemented with limited engineering resources. Building complex turbopumps, combustion chambers and nozzles maybe outside the reach of some countries. Even though at a lower efficiency, the rocket may still launch a satellite into orbit.
The idea is to burn a lot of fuel at a moderate pressure. The stages of the rocket will be strapped side by side. The first stage will be a giant tank that is separated into two sections. The larger section for liquid oxygen and the smaller one for the liquified methane. Gaseous fuel is preferred due to its better dispersion after the injector compared to the liquid fuels. These two cryogenic liquids have close boiling points. Therefore, they can be stored next to each other without thick separators. The idea is to increase the height of the tank to increase the pressure on bottom. Also, the piping from the tanks to the engine is shortened. The engine of the rocket will be a triangular graphite block. On the sides, the liquid propellent will flow and heat up before ignition. Additionally, the nozzle will be cooled. Graphite has high temperature resistance and is very good heat conductor and comparably cheaper than the alternatives. The fuel and the oxidizer will meet on the top of the pyramid and there they will be ignited. Opposite ejection will slow down the oxidizer and the fuel for a better combustion. Finally, the exhaust gas will be ejected straight downward like in aerospike engines.
The propellent tanks will be pressurized using the external air compressed by the nose wind turbine. The turbine will be carefully designed for an optimal drag to compression ratio. The upper sections of the propellent tanks will have special sponges that will stop the sloshing, equalize the pressure on the propellent surface and isolate the contact between the ambient compressed air and the propellent.
Four of these rockets will be strapped together to form the first stage of the rocket. The middle section will have ailerons to direct the rocket. The air intake from the middle void will be circled by the hot nozzle gasses. As a result, the air will be heated and accelerated to contribute to the thrust of the rocket.
The rocket will carry two separate second stages. Therefore, two separate missions will be conducted with one launch.
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