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A reusable igniter for a rocket engine

A rocket engine and igniter technology, which is applied to rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of repeated ignition, unstable combustion, etc., and achieve short ignition time, simple structure, and easy ignition. The effect of convenient location

Active Publication Date: 2020-12-18
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The invention provides a reusable igniter for a rocket engine, which is used to overcome the defects of the liquid ramjet rocket engine in the prior art, such as ignition and combustion instability, and the inability to repeatedly ignite

Method used

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  • A reusable igniter for a rocket engine
  • A reusable igniter for a rocket engine
  • A reusable igniter for a rocket engine

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0069] This embodiment provides a reusable igniter for rocket motors, such as figure 1 shown, including:

[0070] An external electrode 3 and an internal electrode 4, and a combustion chamber for accommodating an electronically controlled solid propellant is arranged between the external electrode 3 and the internal electrode 4; in this embodiment, the components of the electronically controlled solid propellant include lithium perchlorate , polyvinyl alcohol, metal aluminum powder, water and plasticizers, etc.

[0071] The outer electrode 3 surrounds the combustion chamber, and the inner electrode 4 is inserted in the electronically controlled solid propellant;

[0072] A conductive component, including an external electrode conductive component and an internal electrode conductive component electrically connected to the external electrode 3 and the internal electrode 4;

[0073] The conductive components such as figure 1 , Figure 2a with Figure 2b As shown, it include...

Embodiment 2

[0092] In this embodiment, the igniter 16 provided by Embodiment 1 is applied to liquid rocket motors, such as Figure 4 As shown, it includes: an igniter 16, a power supply unit 15, an insulating and heat-insulating protective cover 17, a tail base 18, and an external threaded interface 19 of the engine.

[0093] The tail base 18 is made of stainless steel, and is a sealed cylinder with an internal thread opening at one end and a round hole at the other end.

[0094] The housing and the engine of the igniter 16 are all cylindrical configurations; wherein, the external threaded interface 19 of stainless steel material is welded at the combustion chamber of the liquid rocket engine, and one end of the tail base 18 is provided with a joint that cooperates with the external threaded interface 19 of the engine. Internal thread structure. The casing of the igniter 16 is wrapped by an insulating and heat-insulating protective sheath 17 , and nested in the tail base 18 . The power ...

Embodiment 3

[0097] In this embodiment, the igniter 16 provided in Embodiment 1 is applied to a liquid ramjet rocket engine, such as Figure 5 As shown, it includes: two igniters 16, which are symmetrically installed on both sides of the liquid ramjet engine, a power supply unit 15, an insulating and heat-insulating protective sleeve 17, a fixing sleeve 20, and an inner threaded interface 21 in the engine cavity.

[0098] The fixing sleeve 20 is made of a stainless steel tube and is installed in the cavity of the liquid ramjet. One end of the fixing sleeve 20 is provided with an external thread that is compatible with the internal thread interface 21 of the cavity of the liquid ramjet. The central line of the nozzle 1 of the igniter coincides with a round hole with a diameter slightly larger than that of the nozzle 1; the other end is provided with an annular concave platform, and the concave platform is provided with a circular hole slightly larger than the diameter of the power supply uni...

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PUM

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Abstract

The invention discloses a reusable igniter for the rocket engine. The rocket engine comprises an outer electrode, an inner electrode and a conductive assembly; a combustion cavity used for containingan electric control solid propellant is formed between the outer electrode and the inner electrode; the outer electrode surrounds the periphery of the combustion cavity, and the inner electrode is inserted into the electric control solid propellant; the conductive assembly comprises an outer electrode conductive assembly and an inner electrode conductive assembly which are electrically connected with the outer electrode and the inner electrode; the outer electrode is provided with a nozzle communicated with the combustion chamber; the end, close to the nozzle, of the combustion cavity is provided with a communicating cavity, and the communicating cavity is not filled with the electric control solid propellant and used for enabling gas generated after the electric control solid propellant is ignited to flow towards the nozzle. The igniter provided can realize multi-time ignition, can be repeatedly used, and is controllable in ignition intensity.

Description

technical field [0001] The invention relates to the technical field of engine ignition, in particular to a reusable igniter for a rocket engine. Background technique [0002] The liquid ramjet rocket engine uses liquid fuel, which has the advantages of fast speed, high maneuverability trajectory, and long range. Electronically controlled solid propellants generally use oxidizers and binders with high oxygen content, which have the advantages of repeatable ignition, controllable burning rate, good environmental performance, safety and good economy, and can be widely used in commercial or military fields. [0003] The ignition device is one of the key components of the liquid ramjet rocket engine, and its function is to ignite the fuel accurately and reliably so that it can be established and burn stably. However, organizing stable combustion in a high-speed airflow requires the completion of fuel injection, atomization, fuel-air mixing and combustion reactions in a short tim...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/95
CPCF02K9/95
Inventor 李洋夏智勋马立坤胡建新冯运超何志成段炼
Owner NAT UNIV OF DEFENSE TECH
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