PULSED DETONATION ROCKET ENGINE Russian patent published in 2018 - IPC F02K7/02 

FIELD: rocket technics.

SUBSTANCE: pulse detonation rocket engine comprises a detonation burner unit, the input of which through the end wall serves for batch input of the detonation fuel and is hermetically connected through ballistic device with a magnetic cumulative impulse generator, a source of field flashing. Burner unit comprises an output blockage device in the form of a rotatory actuator operated valve, towing convergent-divergent channel, a lasing system of fuel’s spark ignition, a device for synchronous feeding of spark ignition, one output of which is electrically connected to the lasing system and the other connected with drive of rotatory flap, a gas dynamic resonator in the form of a cone circular deepening, formed between the inner surface of the burner can and the outer part of the conical shell. In the cage of the gas-dynamic resonator, a magnetic flux-cumulative magnetic generator is installed.

EFFECT: invention is aimed at increasing the power and towing performance of engine when operating in both pulsed and multi-rate modes, improving mass-dimensional and size parameters and operating factors.

10 cl, 9 dwg