Fusion multipath redundant tail cartridge type ignition device

Abstract

The utility model provides a gradual melting multi-path redundant tail explosive box type ignition device which is characterized in that at least two groups of ignition devices are mounted on a spray pipe and are respectively communicated with an electric ignition element; the ignition device comprises a box body, a box cover, ignition powder and a blocking film; the box body is communicated with the electric ignition element, and the box body and the box cover form a cavity for packaging ignition powder. The ignition powder is a middle hole grain, a through hole is formed in the middle of the box cover, and the blocking films are bonded to the box body and the box cover respectively to seal a fuel gas channel opening of the box body and the through hole in the box cover. The box body is made of an aluminum alloy material, the aluminum alloy box body can be slowly melted under high-temperature fuel gas of an engine, the box cover is made of a celluloid material, the celluloid material is a combustible material, the celluloid material can be rapidly burnt under flame of an ignition device and the high-temperature fuel gas of an engine propellant, and redundant materials cannot fly out. The problems of ignition reliability of the solid rocket engine tail ignition device and redundant flying objects of the ignition device are solved.

Description

Technical Field

[0001] The invention belongs to the technical field of ignition devices, and in particular relates to a gradual melting multi-path redundant tail cartridge type ignition device. Background Art

[0002] Solid rocket engines are generally composed of an engine casing, a combustion chamber, a nozzle and an ignition device. Among them, the ignition device is used to ignite the solid propellant in the combustion chamber. The high-temperature combustion gas generated by the combustion of the solid propellant is ejected through the nozzle and provides power for the engine. For engines with a fully loaded head, the ignition device generally chooses the tail ignition method. Unlike the head ignition method, the tail ignition opens the nozzle plug after ignition, and the flame and the remaining unburned excess inside the ignition device will be directly ejected from the nozzle, and there is no flame combustion process in a longer channel. Therefore, it is easy for excess matter to be ejected from the nozzle, which may cause the nozzle throat to be directly blocked and the excess matter to hit external parts such as aircraft airborne products that throw the engine away after being ejected, affecting the engine trajectory and the safety of airborne products outside the nozzle.

[0003] In addition, a solid rocket engine is usually equipped with an ignition device, which lacks a redundant design. Once the ignition device fails, the engine will fail to ignite. Moreover, for the tail ignition device, a large part of the ignition flame will fly out of the nozzle, resulting in a large ignition energy loss rate.

[0004] Therefore, it is necessary to design a suitable installation method for the tail ignition device to improve the ignition reliability and ensure that the ignition device will not have flying objects under high-temperature gas to block the nozzle and affect the safety of the products outside the nozzle. Summary of the invention

[0005] The present invention provides a gradual-melting multi-path redundant tail cartridge ignition device, which solves at least one technical problem of ignition reliability of a tail ignition device of a solid rocket engine and flying out of excess objects of the ignition device.

[0006] The technical solution provided by the present invention is as follows:

[0007] A gradual melting multi-way redundant tail cartridge type ignition device, wherein at least two groups of ignition devices are installed on the nozzle and are respectively connected to the electric ignition element;

[0008] The ignition device includes a box body, a box cover, ignition powder and a blocking film; the box body is connected to the electric ignition element and forms a cavity with the box cover to encapsulate the ignition powder; the ignition powder is a medium-porous powder column, a through hole is opened in the middle of the box cover, and the blocking film is respectively bonded to the box body and the box cover to seal the gas channel opening of the box body and the through hole on the box cover.

[0009] Furthermore, two groups of ignition devices are installed on the nozzle and are connected to the electric ignition elements respectively.

[0010] Furthermore, the inner cavity of the box body is a cylindrical cavity structure, and the ignition powder is a medium-hole cylindrical powder column.

[0011] Furthermore, the box body is made of aluminum alloy material.

[0012] Furthermore, the box cover is made of celluloid material.

[0013] Furthermore, the ignition powder, the box body and the box cover are bonded together by an adhesive.

[0014] Furthermore, the ignition powder in the ignition device is a combination of multiple ring-shaped ignition powders.

[0015] Furthermore, the plurality of annular ignition charges are bonded together by adhesive.

[0016] Furthermore, the adhesive is DG-4 adhesive.

[0017] Furthermore, the ignition powder is boron potassium nitrate ignition powder.

[0018] A gradual melting multi-path redundant tail cartridge type ignition device provided by the present invention has the following beneficial effects:

[0019] (1) The present invention provides a gradual melting multi-path redundant tail cartridge ignition device, wherein at least two groups of ignition devices are installed on the nozzle and are respectively connected to the electric ignition element; the ignition device comprises a box body, a box cover, ignition powder and a blocking film; the box body is connected to the electric ignition element and forms a cavity with the box cover to encapsulate the ignition powder; the ignition powder is a medium-porous powder column, a through hole is opened in the middle of the box cover, and the blocking film is respectively bonded to the box body and the box cover to seal the gas channel opening of the box body and the through hole on the box cover, thereby solving the ignition reliability problem caused by ignition energy loss and ignition device failure of the tail ignition device of the solid rocket engine.

[0020] (2) The present invention provides a gradual melting multi-path redundant tail medicine box type ignition device, wherein the box body is made of aluminum alloy material, and the aluminum alloy box body can slowly melt under the high temperature combustion gas of the engine, and the box cover is made of celluloid material, and the celluloid material is a combustible material, which will burn rapidly under the flame of the ignition device and the high temperature combustion gas of the engine propellant, and will not produce any excess matter flying out, thereby solving the problem of excess matter flying out of the ignition device. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a schematic diagram of the installation structure of the ignition device at the nozzle;

[0022] Figure 2 It is a schematic diagram of the appearance and structure of the ignition device;

[0023] Figure 3 Schematic diagram of the internal structure of the ignition device.

[0024] Description of Figure Numbers

[0025] 1- ignition device, 2- electric ignition element, 3- nozzle, 11- box body, 12- box cover, 13- ignition powder, 14- blocking film. DETAILED DESCRIPTION

[0026] The following detailed description of the present invention will make the features and advantages of the present invention more clear and explicit.

[0027] The word “exemplary” is used exclusively herein to mean “serving as an example, example, or illustration.” Any embodiment described herein as “exemplary” is not necessarily to be construed as preferred or advantageous over other embodiments.

[0028] like Figure 1 As shown, the present invention provides a gradual melting multi-way redundant tail cartridge type ignition device, wherein at least two groups of ignition devices are threadedly mounted on the nozzle 3 and are connected to the electric ignition element 2 respectively.

[0029] like Figure 2 and Figure 3 As shown, the ignition device includes a box body 11, a box cover 12, ignition powder 13 and a blocking film 14; the box body 11 is connected to the electric ignition element 2, and forms a cavity with the box cover 12 to encapsulate the ignition powder 13; the ignition powder 13 is a mesoporous powder column, a through hole is opened in the middle of the box cover 12, and the blocking film 14 is bonded to the box body and the box cover respectively, and the gas channel opening of the box body 11 and the through hole on the box cover 12 are sealed. The box cover 12 and the ignition powder 13 have a hole in the middle to facilitate the flame output of the ignition device.

[0030] The inner cavity of the box body 11 is a cylindrical cavity structure, and the ignition powder 13 is a middle-hole cylindrical powder column.

[0031] The solid rocket engine is equipped with a plurality of, for example, two, ignition devices 1 and a plurality of, for example, two, electric ignition elements 3, having a multi-path, for example, dual-path redundancy function.

[0032] When the engine is working, the electric ignition element 3 receives the current on the aircraft to ignite. The flame passes through the ignition channel, burns the blocking film 14, and then is transferred to the ignition device, igniting the ignition powder 13 in the ignition device. After the ignition powder 13 burns, it breaks through the blocking film 14 on the box cover, further igniting the solid propellant in the solid rocket engine. After the solid propellant is ignited, high-temperature combustion gas is generated and the pressure in the engine is increased. When the pressure is greater than the opening pressure of the nozzle plug cap, the nozzle plug cap is opened, and the high-temperature combustion gas is ejected through the nozzle, providing propulsion for the solid rocket engine.

[0033] The box body 11 used in the ignition device is made of aluminum alloy material. The aluminum alloy box body can be slowly melted under the high temperature combustion gas of the engine, so that no excess material will fly out.

[0034] The box cover 12 used in the ignition device is made of celluloid material, which is a combustible material and can burn rapidly under the flame of the ignition device and the high-temperature combustion gas of the engine propellant without generating any excess material flying out.

[0035] The ignition powder 13, the box body 11 and the box cover 12 in the ignition device can be bonded and fixedly connected by an adhesive.

[0036] When the ignition powder 13 in the ignition device is used in combination of multiple ring-shaped ignition powders, the ignition powders 13 can be bonded together by an adhesive, and the number of ignition powder blocks to be bonded can be adjusted according to the amount of ignition powder required for reliable ignition of the engine.

[0037] The adhesive used is DG-4 adhesive, which has a good ignition powder bonding effect. Of course, other adhesives with similar effects can be selected according to specific circumstances.

[0038] Ignition powder 13 is selected from boron potassium nitrate ignition powder, which has good ignition performance.

[0039] The above-mentioned gradual-melt dual-path redundant tail cartridge ignition device solves the problems of installation method of the tail ignition device of the solid rocket engine, excess flying objects of the ignition device, design margin of the ignition device and ignition reliability.

[0040] The present invention has been described in detail above in conjunction with specific implementations and exemplary examples, but these descriptions cannot be understood as limiting the present invention. Those skilled in the art understand that, without departing from the spirit and scope of the present invention, a variety of equivalent substitutions, modifications or improvements may be made to the technical solution of the present invention and its implementation methods, all of which fall within the scope of the present invention. The scope of protection of the present invention shall be subject to the attached claims.

[0041] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A gradual melting multi-way redundant tail cartridge ignition device, characterized in that: The at least two groups of ignition devices are mounted on the nozzle (3) and are respectively connected to the electric ignition element (2); The ignition device comprises a box body (11), a box cover (12), ignition powder (13) and a blocking film (14); the box body (11) is connected to the electric ignition element (2) and forms a cavity with the box cover (12) for encapsulating the ignition powder (13); the ignition powder (13) is a medium-porous powder column, a through hole is provided in the middle of the box cover (12), and the blocking film (14) is respectively bonded to the box body and the box cover to seal the gas channel opening of the box body (11) and the through hole on the box cover (12).

2. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1 is characterized in that: Two groups of ignition devices are installed on the nozzle (3) and are respectively connected to the electric ignition element (2).

3. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1 is characterized in that: The inner cavity of the box body (11) is a cylindrical cavity structure, and the ignition powder (13) is a medium-hole cylindrical powder column.

4. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1 is characterized in that: The box body (11) is made of aluminum alloy material.

5. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1 is characterized in that: The box cover (12) is made of celluloid material.

6. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1, characterized in that: The ignition powder (13), the box body (11) and the box cover (12) are bonded together by an adhesive.

7. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1 is characterized in that: The ignition powder (13) in the ignition device is a combination of multiple ring-shaped ignition powders.

8. The gradual melting multi-way redundant tail cartridge ignition device according to claim 7 is characterized in that: A plurality of annular ignition powders are bonded together by adhesive.

9. The gradual melting multi-way redundant tail cartridge ignition device according to claim 6 or 8, characterized in that: The adhesive is DG-4 adhesive.

10. The gradual melting multi-way redundant tail cartridge ignition device according to claim 1, characterized in that: The ignition powder (13) is selected from boron potassium nitrate ignition powder.

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