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Hybrid-Rocket Propulsion

What is a hybrid rocket engine?

Like all chemical rocket engines, hybrid propulsion uses an oxidizer and a fuel. The term hybrid is derived from the respective aggregate state of the two components. While oxidizer and fuel are used in liquid form in liquid propulsion systems, they are present in solid form in solid propellants. Hybrid systems combine the states of aggregation, whereby the oxidizer is usually found in liquid form and the fuel in solid form.

Why a hybrid rocket engine?

By combining the drive concepts, the following advantages of liquid and solid drives are combined:

Areas of responsibility



The tank must not only withstand the oxidizer's working pressure of approx. 70 bar, but must also be made as light as possible by skilful selection of materials and manufacturing technologies. Thermodynamic simulations are used to determine the load situation, which serves as input parameter for a necessary FEM simulation of the tank structure.

Fluid System

Security plays a major role here. The oxidizer must be fed into the combustion chamber in a controlled manner and encounter as little resistance as possible. The main task is the thermodynamic calculation and selection of fluid line components.


Important for efficient combustion is the dispersion of the oxidizer, which is achieved with the help of the injector. With different geometries and drillings the flow can be influenced in various ways and the oxidizer can be atomized.

Combustion chamber

A calculation model provides the thermal and mechanical loads that must later be absorbed by the housing, insulation, seals and other machine elements. At a pressure of up to 35 bar and a gas temperature of more than 3000 K, this application requires special materials to meet the lightweight construction requirements.

Fuel Grain

There are different fuels, mostly kerosene wax, HTPB, ABS or other plastics are used. Especially with ABS, the shear profile of the drive can be significantly influenced with additive manufacturing processes. The exact chemical composition finally influences the thrust and the burn-up rate of the fuel and is optimized with additives to our requirements.


An optimally designed laval nozzle provides the necessary thrust with maximum efficiency of the drive. Here too, high-temperature-resistant materials such as graphite are used to withstand the thermal loads over the entire combustion period.

combustion chamber
Combustion Chamber