Head injector of low-thrust engine for electric discharge and ignition by utilizing nozzle clearance

Abstract

The invention discloses a head injector of a low-thrust engine for electric discharge and ignition by utilizing nozzle clearance. The head injector provided by the invention comprises a high voltage positive electrode copper rod, a positive electrode wiring nut, a positive electrode insulating spacer, a seal locking nut, a seal extruding ring, a sealing pad, a casing, a sealing ring, an oxidizingagent swirler, a positive electrode insulating sleeve, an electric discharge circumferential seam adjusting block, an oxidizer nozzle outlet end cover and a fuel centrifugal nozzle. The size miniaturization of the head injector of the low-thrust engine can be realized, and because the electric discharge area of the nozzle ring seam is large and the interval can be adjusted, the spark plug single-point electric discharge fault caused by pollution can be avoided effectively.

Description

technical field [0001] The invention belongs to the technical field of liquid rocket engine propulsion, and in particular relates to a small-thrust liquid rocket engine head injector which utilizes nozzle gap discharge to ignite. Background technique [0002] Small-thrust liquid rocket engines are important auxiliary power systems for spacecraft. They are mainly used for spacecraft orbit change control, orbit transfer, orbit maintenance, rendezvous and docking, and attitude control. They usually meet the requirements of multiple starts and pulse work. Among them, the two-component small engine uses separately stored oxidant and fuel as propellants, and is the most widely used. [0003] The bicomponent engine using self-igniting propellants does not require additional ignition devices. The engine starts quickly and ignites reliably, has a simple structure, and can be started many times. However, its disadvantages are that the self-igniting fuel is toxic, flammable, explosive,...

AI Technical Summary

Problems solved by technology

However, spark plug igniters also have certain disadvantages

First of all, the injector at the head of the engine needs to reserve space for the installation of the spark plug and the ignition system, resulting in an increase in the size and weight of the structure, as shown in the reference (Rollbuhler R.J. "Experiment performance of a water electrolysis rocket", numbered NASA TM X- 1737, 1968.) records that in order to ensure the ignition reliability of the main engine of the space shuttle, usually two spark discharge igniters are used as a safety backup at the head of each ignition chamber, which increases the structure and weight of the engine

Secondly, the electric spark plug releases the electric spark between the two tip points of the positive and negative electrodes. The discharge area is small, and it may be polluted by the coverage and deposition of combustion products, resulting in discharge ignition failure, etc.

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