CN111365145B - A reusable igniter for a rocket engine - Google Patents

Abstract

The invention discloses a reusable igniter for a rocket engine, comprising: an outer electrode and an inner electrode, a combustion chamber for accommodating an electronically controlled solid propellant is arranged between the outer electrode and the inner electrode; The electrode surrounds the combustion chamber, and the inner electrode is inserted into the electrically controlled solid propellant; the conductive assembly includes an outer electrode conductive assembly and an inner electrode conductive assembly electrically connected with the outer electrode and the inner electrode ; the outer electrode is provided with a nozzle communicating with the combustion chamber; the combustion chamber is provided with a communication chamber near the nozzle end, and the electronically controlled solid propellant is not filled in the communication chamber for electronic control The gas produced when the solid propellant is ignited flows towards the nozzle. The igniter provided by the invention can realize multiple ignition, can be used repeatedly, and the ignition intensity is controllable.

Description

A reusable igniter for a rocket engine

technical field

The invention relates to the technical field of ignition starting of engines, in particular to a reusable igniter for rocket engines.

Background technique

The liquid ramjet engine uses liquid fuel and has the advantages of high speed, high maneuvering trajectory, and long range. Electronically controlled solid propellants generally use oxidants and binders with high oxygen content, which have the advantages of repeatable ignition, controllable burning rate, good environmental performance, safety and economy, and can be widely used in commercial or military fields.

The ignition device is one of the key components of the liquid ramjet engine, and its function is to ignite the fuel accurately and reliably, so that it can establish and conduct stable combustion. However, organizing stable combustion in high-speed airflow requires that fuel injection, atomization, fuel-air mixing and combustion reactions are completed in a short time, so sufficient ignition energy must be available to ignite the combustible mixture. For a liquid ramjet rocket engine fueled by liquid hydrocarbons, it needs to undergo droplet breakup, atomization, evaporation, and mixing, resulting in the total ignition delay time of the fuel is much higher than its residence time in the combustion chamber, so it is necessary to achieve a limited length of , It is very difficult to ignite the fuel in the combustion chamber, spread the flame, maintain the flame and stabilize the combustion under the high-speed airflow.

At present, the more commonly used ignition methods for liquid ramjet engines mainly include: jet ignition, which is achieved by injecting high-energy airflow into the combustion chamber, the ignition system is relatively independent from the combustion chamber structure, the strength of ignition energy, ignition position, mode of action, etc. It is easy to control and adjust, but it cannot be ignited many times, and the large flow of liquid fuel can easily quench the igniter and make the combustion unstable. In addition, the more commonly used ignition methods include pyrotechnic ignition, self-ignition, torch ignition and laser ignition. Among them, the pyrotechnic ignition method is relatively mature and has the advantages of simple structure and high temperature of combustion products, but it cannot be ignited multiple times. The high ignition risk and the long preparation time for the installation of the ignition device will affect the ignition reliability and stability of the liquid ramjet rocket engine.

SUMMARY OF THE INVENTION

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, unstable combustion, and inability to repeat the ignition many times.

To achieve the above object, the present invention proposes a reusable igniter for a rocket engine, comprising:

an outer electrode and an inner electrode, a combustion chamber for accommodating the electronically controlled solid propellant is arranged between the outer electrode and the inner electrode;

The outer electrode surrounds the combustion chamber, and the inner electrode is inserted into the electronically controlled solid propellant;

A conductive component, including an outer electrode conductive component and an inner electrode conductive component electrically connected with the outer electrode and the inner electrode;

The outer electrode is provided with a nozzle communicating with the combustion chamber;

The combustion chamber is provided with a communication cavity near the nozzle end, and the electronically controlled solid propellant is not filled in the communication cavity, so that the gas generated after the electronically controlled solid propellant is ignited flows to the nozzle.

Compared with the prior art, the beneficial effects of the present invention are:

1. The reusable igniter for a rocket engine provided by the present invention energizes the outer electrode and the inner electrode at the same time through the conductive component, so as to realize the ignition of the electronically controlled solid propellant, thereby realizing the ignition of the rocket engine. Ignition, the time required for ignition is short; and the igniter stops working after the power is turned off. Therefore, the igniter provided by the present invention can realize multiple ignition and can be used repeatedly.

2. The reusable igniter for a rocket engine provided by the present invention can effectively avoid the large flow of liquid fuel in the prior art by setting a combustion chamber in the igniter and filling the combustion chamber with an electronically controlled solid propellant. It is easy to quench the igniter.

3. The reusable igniter for a rocket engine provided by the present invention can control the burning rate of the electronically controlled solid propellant by changing the input voltage, thereby controlling the ignition intensity.

4. The reusable igniter for the rocket engine provided by the present invention has a simple structure and is relatively independent from the combustion chamber structure, and the ignition position is easy to control and adjust.

Description of drawings

In order to explain the embodiments of the present invention or the technical solutions in the prior art more clearly, the following briefly introduces the accompanying drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are only These are some embodiments of the present invention, and for those of ordinary skill in the art, other drawings can also be obtained according to the structures shown in these drawings without creative efforts.

1 is a structural diagram of a reusable igniter for a rocket engine provided by Embodiment 1;

2a is a structural diagram of a conductive assembly in the reusable igniter for a rocket motor provided by Embodiment 1;

2b is a cross-sectional view of the conductive assembly in the reusable igniter for a rocket engine provided in Example 1;

3a is a structural diagram of an inner electrode in the reusable igniter for a rocket engine provided in Example 1;

Figure 3b is a cross-sectional view of a ceramic insulator in the reusable igniter for a rocket engine provided in Example 1;

Fig. 4 is the structure diagram of the liquid rocket engine ground test bench in Embodiment 2;

FIG. 5 is a structural diagram of a scramjet ground test bench in Example 3. FIG.

Description of reference numerals: 1-spout, 2-combustion chamber, 3-outer electrode, 4-inner electrode, 5-ceramic insulator, 6-connection terminal, 7-electrode column, 8-insulation layer, 9-conductive disc, 10-Conductive rod, 11-Conductive elastic insert, 12-Inner ring, 13-External thread interface, 14-Elastic insulating sealing ring, 15-Power supply unit, 16-Igniter, 17-Insulation heat insulation protective cover, 18-Tail Base, 19-engine external thread interface, 20-fixing sleeve, 21-engine cavity internal thread interface.

The realization, functional characteristics and advantages of the present invention will be further described with reference to the accompanying drawings in conjunction with the embodiments.

Detailed ways

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but must be based on the realization by those of ordinary skill in the art. When the combination of technical solutions is contradictory or cannot be realized, it should be considered that the combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

The present invention provides a reusable igniter for a rocket engine, comprising:

an outer electrode and an inner electrode, a combustion chamber for accommodating the electronically controlled solid propellant is arranged between the outer electrode and the inner electrode;

The outer electrode surrounds the combustion chamber, and the inner electrode is inserted into the electronically controlled solid propellant;

A conductive component, including an outer electrode conductive component and an inner electrode conductive component electrically connected with the outer electrode and the inner electrode;

The outer electrode is provided with a nozzle communicating with the combustion chamber;

The combustion chamber is provided with a communication cavity near the nozzle end, and the electronically controlled solid propellant is not filled in the communication cavity, so that the gas generated after the electronically controlled solid propellant is ignited flows to the nozzle.

The outer electrode conductive component is used for electrically connecting with the outer electrode, so that the outer electrode is positively charged;

The inner electrode conductive assembly is used to electrically communicate with the inner electrode to negatively charge the inner electrode.

Preferably, the electrically controlled solid propellant is a new type of energetic material that can release a large amount of gas after being electrified. After the igniter is electrified, the electronically controlled solid propellant can be ignited immediately, so that the electronically controlled solid propellant releases a large amount of gas, thereby realizing ignition. Select the appropriate electronically controlled solid propellant to ensure ignition stability.

Preferably, the conductive component includes a terminal, and one end of the terminal is set as a coaxial ring structure, including an inner ring and an outer ring;

The outer electrode conductive component is an external thread interface disposed on the outer ring, and is used for threaded connection with the outer electrode; the external thread interface on the outer ring is made of conductive material, and the other parts are of insulating material;

The inner electrode conductive component is a conductive elastic insert disposed in the inner ring, which is used for inserting with the inner electrode; the inner ring is made of insulating material.

The structure design of the inner and outer rings of the terminal is to isolate the positive and negative electrodes of the circuit to avoid short circuits in the circuit.

Preferably, the conductive component further includes a power supply unit, and the power supply unit is disposed at the other end of the connection terminal;

The power supply unit includes two layers of power supply layers and two layers of insulating layers for wrapping the power supply layers respectively;

The power supply unit is connected to an external power supply, and the external power supply supplies power to the external thread interface and the conductive elastic insert respectively through the two power supply layers.

The external power source can be DC, AC, or pulsed electricity to rapidly ignite the electronically controlled solid propellant.

The power supply unit has a simple structure and is distributed at one end of the conductive component to avoid wiring on the outer wall of the engine, reducing the complexity of the engine design and increasing the safety performance of the engine. In addition, the four-layer design of the power supply unit can effectively avoid the short circuit of the two-layer power supply layer.

Preferably, an elastic insulating sealing ring is provided at the connection between the external thread interface and the external electrode to prevent air leakage and at the same time prevent the connection terminal from being damaged due to the temperature rise of the external thread interface due to electrification.

Preferably, the outer electrode and the inner electrode are fixedly connected through a ceramic insulating member;

the ceramic insulator is located in the combustion chamber, and the two ends are respectively embedded in the inner wall of the outer electrode;

At least one through hole is formed on the ceramic insulating member, and the inner electrode is inserted into the electrically controlled solid propellant through the through hole.

The outer electrode is isolated from the inner electrode by a ceramic insulator. Preferably, the ceramic insulating member is made of alumina high temperature resistant ceramic material to enhance its high temperature resistance performance.

Preferably, the inner electrode comprises at least one electrode post, a conductive disc and a conductive rod;

One end of the electrode column is fixedly connected to one side of the conductive plate, and one end of the conductive rod is fixedly connected to the other side of the conductive plate;

The other end of the electrode column is inserted into the electrically controlled solid propellant through the through hole;

The other end of the conductive rod is inserted into the inner ring, and is inserted into the conductive elastic insert.

After being energized, the conductive elastic inserts conduct electricity to the conductive rods, and the conductive rods conduct electricity to the conductive discs, and the conductive discs finally conduct electricity to the electrode posts.

The number of electrode columns can be designed according to the actual ignition needs to enhance the application range of the igniter.

The electrode column, the conductive disk and the conductive rod can all conduct electricity, the conductive rod is plugged with the inner electrode conductive component, and the conductive rod can quickly make the whole inner electrode negatively charged through the electric conduction of the inner electrode conductive component.

Preferably, the side of the electrode column is coated with an insulating layer. When the filling amount of the electrically controlled solid propellant in the combustion chamber can completely cover the entire electrode column, the sides of the electrode column are all coated with an insulating layer, and the far conductive disc end of the electrode column is in contact with the electrically controlled solid propellant. The igniter is ignited for the first time; when the electrically controlled solid propellant filling in the combustion chamber only completely covers the side of the electrode column, the side of the electrode column is coated with an insulating layer near the end of the conductive disc, and the end of the far conductive disc is not coated The insulating layer, the part of the electrode column that is not coated with the insulating layer is in contact with the electrically controlled solid propellant, which can realize the first ignition of the igniter.

Preferably, the insulating layer is made of high-temperature resistant insulating material and covers the side of the inner electrode, in order to isolate the electrically controlled solid propellant from the side of the inner electrode and prevent the electrically controlled solid propellant from being separated from the igniter device when the whole of the electrically controlled solid propellant is energized and burned. , and the insulating layer will gradually ablate from the contact end of the electronically controlled solid propellant and the inner electrode during the multiple ignition process to ensure that the electronically controlled solid propellant is ignited and burned multiple times.

Preferably, the number of the electrode posts is the same as the number of the through holes; an assembly gap of 0.1-0.2 mm is set between the electrode posts and the through holes.

The assembly gap, that is, the diameter of the through hole is 0.1-0.2 mm larger than the diameter of the electrode post.

An assembly gap is left between the electrode post and the through hole to prevent the electrode post from being heated and expanded after being energized and damaging the structure of the igniter.

If the assembly gap is too large, it may cause air leakage. If it is too small, the gap may not be enough. After the electrode column is energized, the heat expansion will still damage the igniter structure.

Preferably, the assembly gap is sealed by ceramic-metal bonding glue to prevent air leakage, and has the function of thermal expansion and contraction.

Preferably, the outer electrode and the inner electrode are made of metal or alloy with high temperature resistance and strong electrical conductivity, so as to increase the electrical conductivity of the inner and outer motors, thereby effectively shortening the ignition time.

The igniter provided by the invention can be used for rocket engines such as liquid rocket engines, liquid ramjets and scramjets, and has a wide application range.

Example 1

The present embodiment provides a reusable igniter for a rocket engine, as shown in FIG. 1 , comprising:

The outer electrode 3 and the inner electrode 4 are provided with a combustion chamber for accommodating the electrically controlled solid propellant between the outer electrode 3 and the inner electrode 4; in this embodiment, the components of the electrically controlled solid propellant include lithium perchlorate , polyvinyl alcohol, metal aluminum powder, water and plasticizer, etc.

The outer electrode 3 surrounds the combustion chamber, and the inner electrode 4 is inserted into the electrically controlled solid propellant;

Conductive components, including the outer electrode conductive components and the inner electrode conductive components electrically connected with the outer electrodes 3 and the inner electrodes 4;

As shown in FIG. 1 , FIG. 2 a and FIG. 2 b , the conductive component includes a terminal 6 , one end of the terminal 6 is set as a coaxial annular structure, including an inner ring 12 and an outer ring; wherein, the inner ring 12 and A welding point for an external power supply line is arranged between the outer rings.

The outer electrode conductive component is an external thread interface 13 arranged on the outer ring, which is used for threaded connection with the outer electrode 3; the external thread interface 13 on the outer ring is made of conductive material, and the other parts are of insulating material. ;

The inner electrode conductive component is a conductive elastic insert 11 disposed in the inner ring 12 for plugging with the inner electrode 4; the inner ring 12 is made of insulating material.

The conductive assembly further includes a power supply unit 15, and the power supply unit 15 is arranged at the other end of the connection terminal 6;

The power supply unit 15 includes two power supply layers and two insulating layers for wrapping the power supply layers respectively;

The power supply unit 15 is connected to an external power supply, and the external power supply supplies power to the external thread interface 13 and the conductive elastic insert 11 respectively through the two power supply layers.

An elastic insulating sealing ring 14 is provided at the connection between the external thread interface 13 and the external electrode 3 .

The outer electrode 3 and the inner electrode 4 are fixedly connected through a ceramic insulating member 5;

The ceramic insulating member 5 is located in the combustion chamber 2, and the two ends are respectively embedded in the inner wall of the outer electrode 3;

The ceramic insulating member 5 is provided with three through holes, and the inner electrode 4 is inserted into the electrically controlled solid propellant through the through holes. A cross-sectional view of the ceramic insulator 5 is shown in Figure 3b.

The inner electrode 4, as shown in FIG. 3a, includes three electrode columns 7, conductive discs 9 and conductive rods 10;

One end of the electrode column 7 is fixedly connected to one side of the conductive plate 9, and one end of the conductive rod 10 is fixedly connected to the other side of the conductive plate 9;

The other end of the electrode column 7 is inserted into the electrically controlled solid propellant through the through hole; an assembly gap of 0.15 mm is set between the electrode column and the through hole, and the assembly gap passes through the ceramic - Metal bonding glue sealing;

The other end of the conductive rod 10 is inserted into the inner ring 12, and is inserted into the conductive elastic insert 11;

After power-on, the conductive elastic insert 11 conducts electricity to the conductive rod 10, the conductive rod 10 conducts electricity to the conductive disc 9, and the conductive disc 9 finally conducts electricity to the electrode column 7.

The outer electrode 3 is provided with a nozzle 1 communicating with the combustion chamber;

The combustion chamber is provided with a communication cavity near the first end of the nozzle, and the communication cavity is not filled with the electronically controlled solid propellant, for the gas generated after the electronically controlled solid propellant is ignited to flow to the nozzle.

In this embodiment, as shown in FIG. 1 , a communication cavity is provided between the other end of the electrode column 7 and the nozzle 1 ; the electrically controlled solid propellant is filled in the non-communication cavity part of the combustion cavity, and the three electrodes of the inner electrode 4 The electrode column 7 is inserted into the electrically controlled solid propellant; the three electrode columns 7 are coated with an insulating layer 8 on the side near the end of the conductive disk 9, and the side (about 1mm in length) of the far conductive disk 9 is not coated with an insulating layer. 8 and directly contact with the electronically controlled solid propellant to achieve the first ignition.

Example 2

In this embodiment, the igniter 16 provided in Embodiment 1 is applied to a liquid rocket engine, as shown in FIG. 4 , including: an igniter 16 , a power supply unit 15 , an insulating and heat-insulating protective cover 17 , a tail base 18 , and an engine external thread interface 19.

The tail base 18 is made of stainless steel, and is a sealed cylinder with an open inner thread at one end and a concave circular hole at the other end.

The casing of the igniter 16 and the engine are both cylindrical structures; wherein, the external threaded interface 19 of stainless steel is welded at the combustion chamber of the liquid rocket engine, and one end of the tail base 18 is provided with an external threaded interface 19 that cooperates with the engine. Internal thread structure. The housing of the igniter 16 is wrapped by an insulating and thermally insulating protective sleeve 17 and is nested in the tail base 18 . The power supply unit 15 is positioned in cooperation with the other end of the tail base 18, and is sealed with a sealing ring at the contact point, so as to realize the fixation and sealing of the igniter and the liquid rocket motor.

In this embodiment, the igniter 16 is energized and ignited, so that the electronically controlled solid propellant in the igniter 16 is rapidly ignited and burned to generate high-temperature flame and energy for igniting the liquid rocket motor. One end of the power supply unit 15 is connected to the inner and outer electrodes of the igniter, and the other end is connected to the liquid rocket motor control system, which is used to transmit the ignition signal of the liquid rocket motor control system to the inner and outer electrodes, and the electronically controlled solid propellant is ignited and continuously stabilized by electric energy. The burning speed is several seconds to generate a high-temperature combustion flame, which ensures that the liquid rocket engine can be ignited quickly and reliably. At the same time, the igniter 16 can be re-ignited by activating the ignition signal again in the event of a flameout that may be caused by uneven mixing of the gas. In addition, the ignition energy can be controlled by adjusting the voltage according to the different fuel flow of the liquid rocket engine.

Example 3

In this embodiment, the igniter 16 provided in Embodiment 1 is applied to the liquid ramjet rocket engine, as shown in FIG. 5 , including: two igniters 16 symmetrically installed on both sides of the liquid ramjet engine, a power supply unit 15 , insulation and heat insulation protection Sleeve 17, fixed sleeve 20, threaded interface 21 in the engine cavity.

The fixing sleeve 20 is made of stainless pipe and is installed in the cavity of the liquid ramjet. One end of the fixing sleeve 20 is provided with an external thread which is adapted to the inner threaded interface 21 of the cavity of the liquid ramjet, and this end is also provided with The center line of the nozzle 1 of the igniter coincides with a circular hole with a diameter slightly larger than the diameter 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 unit 15 for sealing the igniter.

In this embodiment, the igniter 16 is entirely wrapped in a layer of insulating and heat-insulating protective sleeve 17 , and then installed in the fixing sleeve 20 . One end of the fixing sleeve 20 is connected with the threaded interface 21 in the cavity of the liquid ramjet. The power supply unit 15 is positioned in cooperation with the other end of the fixing sleeve 20, and a sealing ring is sealed on the concave platform, which can realize the fixing and sealing of the igniter and the liquid ramjet.

In this embodiment, the igniter 16 is energized and ignited, so that the electronically controlled solid propellant in the igniter 16 is rapidly ignited and burned to generate high temperature flame and energy for igniting the liquid ramjet. One end of the power supply unit 15 is connected to the inner and outer electrodes of the igniter, and the other end is connected to the liquid ramjet control system, which is used to transmit the ignition signal of the liquid ramjet control system to the inner and outer electrodes, and the electronically controlled solid propellant is ignited and continuously stabilized by electric energy. The burning speed is several seconds to generate a high-temperature combustion flame, which ensures rapid and reliable combustion when the liquid ramjet gas and air are mixed. At the same time, in the event of a flameout that may be caused by difficulty in ignition when the air-fuel ratio is large, the igniter can be re-ignited by restarting the ignition signal. In addition, the ignition energy can be controlled by adjusting the voltage according to the different fuel flow of the liquid ramjet.

Example 4

In this embodiment, the igniter 16 provided in Embodiment 1 is applied to a scramjet engine, including: an igniter, a power supply unit, an insulating and heat-insulating protective cover, an igniter base, an insulating flange, and an engine cavity opening.

In this embodiment, the igniter 16 is energized and ignited, so that the electronically controlled solid propellant in the igniter 16 is rapidly ignited and burned to generate high temperature flame and energy for igniting the liquid ramjet. One end of the power supply unit 15 is connected with the inner and outer electrodes of the igniter, and the other end is connected with the scramjet engine control system, which is used to transmit the ignition signal of the scramjet engine control system to the inner and outer electrodes, and the electronically controlled solid propellant is ignited and ignited by electric energy. Continue to stabilize the burning rate for several seconds to generate a high-temperature combustion flame, which ensures that the scramjet can ignite quickly and reliably. At the same time, when the flameout may be easily caused by the supersonic airflow, the igniter can be ignited again by starting the ignition signal again. In addition, the ignition energy can be controlled by adjusting the voltage according to the different fuel flow of the scramjet.

The above descriptions are only the preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Under the inventive concept of the present invention, the equivalent structural transformations made by the contents of the description and drawings of the present invention, or the direct/indirect application Other related technical fields are included in the scope of patent protection of the present invention.

Claims (9)

1. A reusable igniter for a rocket engine, comprising:

the electric control solid propellant powder burning device comprises an outer electrode and an inner electrode, wherein a burning cavity for containing the electric control solid propellant is arranged 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 conductive assembly comprises a wiring terminal, one end of the wiring terminal is arranged to be of a coaxial annular structure and comprises an inner ring and an outer ring;

the outer electrode conductive component is an external thread interface arranged on the outer ring and is used for being in threaded connection with the outer electrode; the external thread interface on the outer ring is made of a conductive material, and the other parts of the external thread interface are made of an insulating material;

the inner electrode conductive component is a conductive elastic insertion piece arranged in the inner ring and used for being inserted with the inner electrode; the inner ring is made of insulating materials;

the outer electrode is provided with a nozzle communicated with the combustion cavity;

the combustion cavity is provided with a communicating cavity near the nozzle end, the communicating cavity is not filled with the electric control solid propellant, and the gas generated after the electric control solid propellant is ignited flows to the nozzle.

2. A reusable igniter for a rocket engine as recited in claim 1, wherein said electrical conducting assembly further comprises a power supply unit, said power supply unit being disposed at the other end of said electrical terminals;

the power supply unit comprises two power supply layers and two insulating layers which are used for wrapping the power supply layers respectively;

the power supply unit is connected with an external power supply, and the external power supply supplies power to the external thread interface and the conductive elastic insertion piece respectively through two layers of power supply layers.

3. A reusable igniter for a rocket engine as recited in claim 1, wherein a resilient insulating gasket is disposed at a junction of said male threaded interface and said outer electrode.

4. A reusable igniter for a rocket engine as recited in claim 1, wherein said outer electrode and said inner electrode are fixedly attached by a ceramic insulator;

the ceramic insulating part is positioned in the combustion cavity, and two ends of the ceramic insulating part are respectively embedded into the inner wall of the outer electrode;

the ceramic insulating part is provided with at least one through hole, and the inner electrode penetrates through the through hole and is inserted into the electric control solid propellant.

5. A reusable igniter for a rocket engine as recited in claim 4, wherein said inner electrode comprises at least one electrode post, a conductive disk and a conductive rod;

one end of the electrode column is fixedly connected to one side of the conductive disc, and one end of the conductive rod is fixedly connected to the other side of the conductive disc;

the other end of the electrode column penetrates through the through hole and is inserted into the electric control solid propellant;

the other end of the conducting rod is inserted into the inner ring and is connected with the conductive elastic insertion piece in an inserting mode.

6. A reusable igniter for a rocket engine as recited in claim 5, wherein said electrode post side edges are coated with an insulating layer.

7. A reusable igniter for a rocket engine as recited in claim 5, wherein said number of electrode posts corresponds to said number of through holes; and an assembly gap of 0.1-0.2 mm is arranged between the electrode column and the through hole.

8. A reusable igniter for a rocket engine as recited in claim 7, wherein said assembly gap is sealed by a ceramic-to-metal adhesive glue.

9. A reusable igniter for a rocket engine as recited in claim 1, wherein said outer and inner electrodes are fabricated from a metal or alloy.

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