Chemical thrusters convert chemical energy predominantly into thermal energy and further into kinetic energy. These conversions are lossy and typically limit the usable thrust to 40-70% of the chemical energy (rockets). The exit velocity is maximized by increasing the temperature. However, temperature cannot be increased at will and can increase losses. Thrusters also have limited controllability under changing external conditions. The options for isochoric or detonative combustion are limited. This concept is intended to increase efficiency and controllability.
Through changes in catalytic loads and electromagnetic dose, combustion is increased and can be selectively regulated. Pressure/temperature are influenced and can be adapted e.g. to the changing external pressure. The achievable thrust increases due to the higher exit velocity. Further advantages exist. The geometry of combustion chambers can be optimized (e.g. smaller, more efficient). The concept is particularly promising for detonation engines or novel supersonic combustors.