Repeatable igniter used for solid-liquid rocket engine

Abstract

The invention discloses a repeatable igniter used for a solid-liquid rocket engine. The repeatable igniter comprises a housing, wherein a connecting tube is arranged in the housing; a first interfaceof the connecting tube is connected to a methane gas inlet; a second interface of the connecting tube is connected to a spray tube; the connecting tube is of a hollow structure; a combustion cavity isarranged in the connecting tube; a rotational-flow spray tube and a spark plug hole are sequentially arranged on the connecting tube; the combustion cavity communicates with an accommodating cavity used for oxygen gas circulation through the rotational-flow spray tube; and an oxygen gas inlet which communicates with the accommodating cavity is further formed in the side wall of the housing. The rotational-flow spray tube is arranged on the connecting tube, so that oxygen gas can be sufficiently mixed with methane as rotational flow is generated, and therefore, a success rate of follow-up spark plug discharge ignition and reliability of the igniter are improved; and the spray tube adopts the structure of a laval spray tube, so that the outlet flame stability is improved, and an outlet flame divergence angle is effectively reduced. The igniter also can perform repeated ignition, and ignition delay of the igniter is smaller than 0.5 seconds.

Description

technical field [0001] Embodiments of the present invention relate to the field of ignition starting of rocket engines, in particular to a repeatable igniter for a solid-liquid hybrid rocket engine. Background technique [0002] Solid-liquid rocket motors generally use liquid oxidants and solid fuels. They have the common characteristics of liquid rocket motors and solid rocket motors in structure. They have the advantages of repeatable ignition, adjustable thrust, good environmental performance, safety and economy. Widely used in commercial or military fields. [0003] The ignition device is one of the key components of a rocket engine, and its function is to ignite the propellant accurately and reliably, so that it can establish and conduct stable combustion. Due to the different structural characteristics of solid-liquid rocket motors, there are both solid fuel grains and liquid oxidant injection. Therefore, in the ignition process, both the atomization of the oxidant an...

AI Technical Summary

Problems solved by technology

However, the pyrotechnic agent ignition method is not suitable for the requirements of multiple starts of some solid-liquid hybrid rocket engine models, and there will be some obstacles in the ground test of the engine: the ignition powder and the ignition head need to be reinstalled for each experiment, and the preparation time is too long. Long; the vibration at the moment of ignition will have an impact on the entire experimental system; in order to obtain repeatability, the ignition powder is generally designed as a powder column, and it is necessary to design a mold to cast the ignition powder column and perform mechanical processing, and the material cost and time cost are very high

The self-ignition method has the advantages of simple structure and good working performance, and can be used as an ignition method for solid-liquid rocket engines. However, many self-igniting liquid propellants have problems such as low calorific value, unstable chemical properties, and toxicity, which are highly dangerous and may cause injury to the operator

In addition, the self-ignition method is not suitable for propellant combinations that are not self-igniting

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