IGNITION DEVICE FOR LOW-THRUST ROCKET ENGINES ON NON-SELF-IGNITING GASEOUS (LIQUID) FUEL AND GASEOUS OXIDIZER Russian patent published in 2022 - IPC F02K9/00 

FIELD: rocket and space technology.

SUBSTANCE: invention relates to the rocket and space technology, namely to low-thrust rocket engines operating in continuous and pulse modes on non-self-igniting gaseous (liquid) fuel and gaseous oxidizer. An ignition device for low-thrust rocket engines consists of an ignition unit and an electric spark plug of surface discharge, an ignition device case with nozzle elements of supplying fuel and gaseous oxidizer, a fuel electric valve, an oxidizer electric pneumatic valve. There are two coaxial channels in the device case, sequentially located along its axis: the first of them, closer to the spark plug, with smaller equal diameter and length, and the second one – with twice greater a diameter and five times greater a length. Fuel is tangentially supplied to the channel with smaller geometric dimensions through two jet nozzles. Gaseous oxidizer is tangentially supplied to the channel with larger diameter and length through six jet nozzles. A discharge cavity with a height h=0.75 mm is located in the case from the side of the spark plug, limited, from one side, with the end surface of the plug, and from the other side – with a diaphragm with a central hole with a diameter two times smaller the diameter of the channel, to which fuel is supplied. A peripheral area of the oxidizer channel is connected to the discharge cavity by means of two longitudinal channels located in diametrically opposite directions relatively to the axis of the device.

EFFECT: organization of effective and reliable ignition in a low-thrust rocket engine on non-self-igniting gaseous (liquid) fuel and gaseous oxidizer.

3 cl, 1 dwg