A Novel Rocket First Stage

A rocket engine generates high thrust by burning high amounts of fuel with oxidizer. This is achieved by pumping the propellant into the combustion chamber at a very high rate. I propose a large drainage for the propellant tanks to allow large mass flow. Therefore, negating the need for turbopumps and combustion chambers. Using liquid methane as fuel allows the tanks to be placed inside one another. LOX and liquid methane have similar liquifying temperatures negating the need for heavy shielding between the tanks. This approach also increases the tanks height and therefore the bottom pressure.

My proposal would only work for the first stage of a rocket. It also requires solid boosters for takeoff.

The design is as follows: The large drainage from the fuel and the oxidizer would be mixed inside a helical pipe before they are ejected from atomizer nozzles. In order to increase the surface area for efficient burning, the nozzles would be mounted on a curved form. As a result, high amounts of propellant would be ejected and burned efficiently. The ignition will be achieved by heated copper alloy mesh placed close to the nozzle exit. Just before the launch, this mesh would be heated on the ground and the propellant valves would be opened slightly to initiate the burn as a pilot light.

There would be a duct around the bottom of the rocket used as an air intake and double as a propelling nozzle like in a fighter jet. The air intake provides bypass air to contribute to the thrust to improve the efficiency of the rocket. More importantly, the flowing air guides the burned gases. There would be thrust vectoring nozzle at the end of the duct. This nozzle opening would be adjusted depending on the ambient pressure to improve efficiency. Additionally, thrust vectoring would allow the maneuvering of the rocket.

This rocket stage would only generate thrust after reaching a certain speed which would be attained by strapped solid boosters. As the rocket accelerates the propellant drainage would be opened to contribute to the thrust. When the solid boosters are ejected, the first stage should be able to generate enough thrust to continue accelerating the rocket.

Depending on the size of the duct, it would also generate lift like a ring wing. This would be handy when the stage separates from the upper one. The stage separation would also reveal an aerodynamic nose for the first stage. Coupled with the ring wing and parachutes, the stage would decelerate to water with lower speed. The duct section of the rocket would absorb the impact on water and break. As a result, the stage would be refurbished with minimal damage to the main fuselage.