A controllable ablation interlayer multi-pulse engine

Abstract

The present invention relates to the technical field of multi-pulse solid rocket engines, specifically a controllable ablation barrier type multi-pulse engine, in which multiple pulse units are assembled in the engine outer shell, and each pulse unit is provided with an electrically heated ablation barrier assembly. When the previous pulse is completed, the hard barrier is converted into a soft barrier by means of electrical heating, and the material strength decreases. After the next pulse charge is ignited, the pulse engine barrier can be opened safely and controllably. After the gas channel is opened, the isolation material is made of a low-melting-point thermoplastic material, which can be directly ablated under the action of the high-temperature gas in the combustion chamber, reducing the impact on the subsequent working process of the engine. The barrier structure of the present invention has no prefabricated defects, which reduces the risk of failure of the multi-pulse engine barrier. The entire barrier opening action does not produce destructive debris, which greatly improves the working stability and reliability of the multi-pulse engine.

Description

Technical Field

[0001] The present invention relates to the technical field of multi-pulse solid rocket engines, in particular to a controllable ablation barrier type multi-pulse engine. Background Art

[0002] Traditional solid rocket motors provide only a single burst of thrust, making it difficult to perform large maneuvers during a missile's terminal phase. Multi-pulse engines offer a method for managing and distributing energy in solid rocket motors. This allows for efficient energy management, multiple shutdowns and restarts, and multiple thrust control, improving a missile's terminal phase penetration maneuverability.

[0003] Using an isolator to structurally separate the grains of each pulse, allowing each to ignite independently, is an effective solution for implementing a pulse engine. The structural design and operating mode of the isolator significantly influence the performance of the pulse engine and are key technologies for its engineering application.

[0004] Currently, isolation devices are made of two main materials: hard materials such as ceramics and metals, and soft materials such as rubber. These isolation devices are typically opened by creating a prefabricated defect in the structure. After the subsequent pulse ignition, the positive pressure of the gas causes the isolation device to break along the prefabricated defect, rapidly opening the gas passage. However, this method requires very high quality control of the prefabricated defect, reducing the reliability of the pulse engine and generating destructive debris that can adversely affect the operation of the engine's combustion chamber and nozzle. Summary of the Invention

[0005] In order to overcome the defects of the above-mentioned prior art, the purpose of the present invention is to provide a controllable ablation barrier type multi-pulse engine to solve the technical problem in the prior art that when the isolation device in the engine is damaged along the prefabricated defects under the action of the positive pressure of the gas, the isolation device is prone to produce destructive fragments, which has an adverse effect on the engine and reduces the working reliability of the pulse engine.

[0006] The present invention is achieved through the following technical solutions:

[0007] A controllable ablation barrier type multi-pulse engine comprises an engine outer shell and a plurality of pulse units; the plurality of pulse units are coaxially assembled in sequence in the engine outer shell, the pulse units comprising an electrically heated ablation barrier assembly, a charge and an igniter; the electrically heated ablation barrier assembly is a cylindrical structure, wherein an ablation side is provided at one end of the electrically heated ablation barrier assembly, the charge is assembled in the ablation barrier assembly, and the igniter penetrates the ablation side of the electrically heated ablation barrier assembly and contacts the charge.

[0008] Preferably, the outer diameter of the ablation side of the electric heating ablation spacer assembly corresponds to the inner diameter of the engine outer shell.

[0009] Preferably, the electric heating ablation barrier assembly includes a heating ring, an ablation layer, a supporting insulating assembly and a plurality of electrode pins; wherein the supporting insulating assembly is a cylindrical structure, the ablation layer is attached to one end of the supporting insulating assembly to form an ablation side, the heating ring is assembled on the ablation layer, and a plurality of electrode pins are vertically arranged in the outer side walls of the supporting insulating assembly, and all of them pass through the ablation layer and the heating ring in sequence and are connected to an external power supply to form a heating circuit, the drug column is assembled in the supporting insulating assembly, and the igniter passes through the heating ring, the ablation layer and the end of the ablation barrier assembly in sequence to contact the drug column.

[0010] Furthermore, the heating ring is an open thin-walled circular ring structure, wherein electrode positioning holes are respectively provided at both ends of the opening of the heating ring, and the electrode pins are connected to the external power supply through the electrode positioning holes; a number of centripetal heating plates are arranged along the circumference on the inner side of the heating ring, wherein a number of centripetal heating plates have through holes reserved at the center of the heating ring to form a first igniter mounting hole for assembling the igniter; a number of centripetal plates are assembled on the ablation layer through the heating ring.

[0011] Furthermore, the thickness of the plurality of centripetal heating plates is greater than the thickness of the heating ring.

[0012] Furthermore, the ablation layer has a circular boss structure, wherein several pairs of ablation layer guide holes are distributed on the outer circular ring of the ablation layer, and each pair of ablation layer guide holes corresponds to the two electrode positioning holes of the heating ring, which are used to pass through the electrode pins. The middle boss part of the ablation layer is provided with several centripetal grooves along the circumference, and several centripetal heating plates are correspondingly assembled in the several centripetal grooves. Several centripetal heating plates have reserved through holes at the center of the middle boss part to form a second igniter mounting hole for assembling the igniter.

[0013] Furthermore, the outer diameter of the outer ring of the ablation layer corresponds to the inner diameter of the engine outer shell.

[0014] Furthermore, the depth of the centripetal groove corresponds to the thickness of the centripetal heating plate.

[0015] Furthermore, the supporting insulating assembly includes a porous material layer and an insulating ring, the porous material layer is assembled at the end of the insulating ring to form a cylindrical structure, a plurality of insulating ring guide holes are provided in the insulating ring, the electrode pins pass through the ablation layer and the heating ring in sequence along the insulating ring guide holes and are connected to an external power supply to form a heating circuit, the charge is assembled in the insulating ring, and a third ignition mounting hole is opened on the porous material layer for assembling an igniter.

[0016] Furthermore, the material of the ablation layer is ABS thermoplastic material.

[0017] Compared with the prior art, the present invention has the following beneficial technical effects:

[0018] The present invention provides a controllable ablation barrier-type multi-pulse engine. Multiple pulse units are assembled in the engine outer shell. Each pulse unit is equipped with an electrically heated ablation barrier assembly. After the previous pulse is completed, the hard barrier is converted into a soft barrier by electrical heating, reducing the material strength. After the next pulse charge is ignited, the pulse engine barrier can be opened safely and controllably. After the gas channel is opened, the insulation material is made of a low-melting-point thermoplastic material, which can be directly ablated under the action of the high-temperature gas in the combustion chamber, reducing the impact on the subsequent operation of the engine. The barrier structure of the present invention has no prefabricated defects, reducing the risk of barrier failure in the multi-pulse engine. The entire barrier opening action does not produce destructive debris, greatly improving the operating stability and reliability of the multi-pulse engine.

[0019] Furthermore, the outer diameter of the ablation side of the electric heating ablation barrier assembly corresponds to the inner diameter of the engine outer shell. When the previous pulse is working, the embodiment of the present invention is in a hardened state. Compared with traditional prefabricated defect hard barriers and soft barriers, it has stronger pressure-bearing capacity and reliability, can improve the stability and safety of the pulse engine barrier operation, and reduce the risk of accidental ignition caused by prefabricated defects.

[0020] Furthermore, the electric heating ablation interlayer assembly consists of a heating ring, an ablation layer, a supporting insulating assembly and a number of electrode pins. The ablation layer is attached to one end of the supporting insulating assembly to form an ablation side. The heating ring is assembled on the ablation layer. The several electrode pins are vertically arranged in the outer side walls of the supporting insulating assembly, and all of them pass through the ablation layer and the heating ring in sequence and are connected to an external power supply to form a heating circuit. By heating the heating ring, the interlayer is softened and locally ablated before the pulse charge is ignited. Combined with the action of high-temperature combustion gas after the pulse charge is ignited, the ablation layer can be directly ablated, reducing the impact on the subsequent working process of the engine.

[0021] Furthermore, the heating ring has an open thin-walled circular ring structure, which is convenient for forming an electric heating circuit, wherein electrode positioning holes are respectively provided at both ends of the opening of the heating ring to facilitate the insertion of positive and negative electrodes, and a number of centripetal heating plates are arranged along the circumference of the inner side of the heating ring. The several centripetal plates are assembled on the ablation layer through the heating ring, which is convenient for heating the ablation layer, causing it to ablate quickly and reducing the impact on the subsequent working process of the engine.

[0022] Furthermore, the thickness of the plurality of centripetal heating plates is greater than the thickness of the heating ring, so that the plurality of centripetal heating plates can be directly assembled on the ablation layer, thereby facilitating ablation work on the ablation layer.

[0023] Furthermore, the ablation layer has a circular boss structure, in which several pairs of ablation layer guide holes are distributed on the outer circular ring of the ablation layer, and a heating circuit can be realized in series. The number of ablation layer guide holes corresponds to the number of pulse units in the engine casing, so that they can be staggered and penetrate the electrode pins to realize a series heating circuit of multi-stage pulse units.

[0024] Furthermore, the supporting insulation component includes a porous material layer and an insulating ring. The porous material is a circular thin sheet. The use of porous material processing can facilitate the entry of high-temperature fuel gas into the combustion chamber and can also effectively support the insulating ring. When the lower-level unit is needed to work, the igniter works to ignite the end face of the charge column. The high-pressure fuel gas generated can smoothly open the softened ablation layer and the porous material layer, thereby realizing the operation of the lower-level pulse unit. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 This is a schematic diagram of the structure of the controllable ablation barrier type multi-pulse engine of the present invention;

[0026] Figure 2 Schematic diagram of the structure of the pulse unit in the present invention;

[0027] Figure 3 This is a schematic diagram of the structure of the ablation barrier component in the pulse unit of the present invention;

[0028] Figure 4 Schematic diagram of the structure of the heating ring in the present invention;

[0029] Figure 5 Schematic diagram of the three-dimensional structure of the heating ring in the present invention;

[0030] Figure 6 Schematic diagram of the structure of the ablation layer in the present invention;

[0031] Figure 7 Schematic diagram of the three-dimensional structure of the ablation layer in the present invention.

[0032] In the figure: 1-heating ring; 2-ablation layer; 3-porous material layer; 4-insulating ring; 5-electrode pin; 6-charge; 7-igniter; 8-pulse unit; 9-engine outer shell; 11-electrode positioning hole; 12-centripetal heating plate; 13-first igniter mounting hole; 21-ablation layer guide hole; 22-centripetal groove; 23-second igniter mounting hole; 31-third igniter mounting hole; 41-insulating ring guide hole. DETAILED DESCRIPTION

[0033] In order to enable those skilled in the art to better understand the solutions of the present invention, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the embodiments described are only 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 ordinary technicians in this field without making creative efforts should fall within the scope of protection of the present invention.

[0034] The present invention is described in further detail below with reference to the accompanying drawings:

[0035] The purpose of the present invention is to provide a controllable ablation barrier type multi-pulse engine to solve the technical problem in the prior art that when the isolation device in the engine is damaged along the prefabricated defects under the action of the positive pressure of the gas, the isolation device is prone to produce destructive fragments, which has an adverse effect on the engine and reduces the working reliability of the pulse engine.

[0036] Specifically, according to Figure 1 As shown, the controllable ablation barrier type multi-pulse engine includes an engine outer shell 9 and a plurality of pulse units 8; the plurality of pulse units 8 are coaxially assembled in sequence in the engine outer shell 9, according to Figure 2 As shown, the pulse unit 8 includes an electric heating ablation barrier assembly, a drug column 6 and an igniter 7; the electric heating ablation barrier assembly is a cylindrical structure, wherein one end of the electric heating ablation barrier assembly is provided with an ablation side, the drug column 6 is assembled in the ablation barrier assembly, and the igniter 7 passes through the ablation side of the electric heating ablation barrier assembly and contacts the drug column 6.

[0037] Specifically, the outer diameter of the ablation side of the electric heating ablation spacer assembly corresponds to the inner diameter of the engine outer shell 9 .

[0038] Specifically, according to Figure 3 As shown, the electric heating ablation barrier assembly includes a heating ring 1, an ablation layer 2, a supporting insulating assembly and a plurality of electrode pins 5; wherein the supporting insulating assembly is a cylindrical structure, the ablation layer 2 is attached to one end of the supporting insulating assembly to form an ablation side, the heating ring 1 is assembled on the ablation layer 2, and the plurality of electrode pins 5 are vertically arranged in the outer side walls of the supporting insulating assembly, and all of them sequentially penetrate the ablation layer 2 and the heating ring 1 and are connected to an external power supply to form a heating circuit, the drug column 6 is assembled in the supporting insulating assembly, and the igniter 7 sequentially penetrates the heating ring 1, the ablation layer 2 and the end of the ablation barrier assembly and contacts the drug column 6.

[0039] Specifically, according to Figure 4 and Figure 5As shown, the heating ring 1 is an open thin-walled circular ring structure, wherein electrode positioning holes 11 are respectively provided at both ends of the opening of the heating ring 1, and the electrode pin 5 is connected to the external power supply through the electrode positioning holes 11; a plurality of centripetal heating plates 12 are provided on the inner side of the heating ring 1 along the circumference, wherein a plurality of centripetal heating plates 12 have through holes reserved at the center of the heating ring 1 to form a first igniter mounting hole 12 for assembling the igniter 7; a plurality of centripetal plates 12 are assembled on the ablation layer 2 through the heating ring 1.

[0040] The thickness of the plurality of centripetal heating plates 12 is greater than the thickness of the heating ring 1 .

[0041] Specifically, according to Figure 6 and Figure 7 As shown, the ablation layer 2 is a circular boss structure, wherein a plurality of pairs of ablation layer guide holes 21 are distributed on the outer circular ring of the ablation layer 2, and each pair of ablation layer guide holes 21 corresponds to the two electrode positioning holes 11 of the heating ring 1, and is used to pass through the electrode pin 5. The middle boss portion of the ablation layer 2 is provided with a plurality of centripetal grooves 22 along the circumference, and a plurality of centripetal heating plates 12 are correspondingly assembled in the plurality of centripetal grooves 22. A through hole is reserved at the center of the middle boss portion of the plurality of centripetal heating plates 12 to form a second igniter mounting hole 23 for assembling the igniter 7.

[0042] Specifically, the outer diameter of the outer ring of the ablation layer 2 corresponds to the inner diameter of the engine outer casing 9 .

[0043] Specifically, the depth of the centripetal groove 22 corresponds to the thickness of the centripetal heating plate 12 .

[0044] Specifically, the supporting insulating assembly includes a porous material layer 3 and an insulating ring 4. The porous material layer 3 is assembled at the end of the insulating ring 4 to form a cylindrical structure. A plurality of insulating ring guide holes 41 are provided in the insulating ring 4. The electrode pin 5 passes through the ablation layer 2 and the heating ring 1 in sequence along the insulating ring guide hole 41 and is connected to an external power supply to form a heating circuit. The drug column 6 is assembled in the insulating ring 4. A third ignition mounting hole 31 is opened on the porous material layer 3 for assembling the igniter 7.

[0045] The electrode pin 5 of the present invention is connected to the electrode positioning hole 11 of the heating ring 1 and the external power supply through the insulating ring guide hole 41 and the ablation layer guide hole 21 reserved by the insulating ring 4 to form a heating circuit. It is possible to simply connect multiple pulse units in series to form a multi-pulse solid rocket engine, thereby realizing multi-stage energy management of solid rockets, such as Figure 1 shown.

[0046] In the present invention, the heating ring 1, the ablation layer 2, and the porous material layer 3 are bonded together to form an integral composite structure. The heating ring 1 is made of an electrothermal material such as nickel-chromium alloy. The ablation layer 2 is made of a low-melting-point thermoplastic material such as ABS.

[0047] The working principle of a controllable ablation barrier type multi-pulse engine provided by the present invention is:

[0048] When the solid rocket is in an unlaunched state, the electric heating ablation interlayer assembly of the present invention is in an unhardened state. Compared with the traditional prefabricated defect hard interlayer and soft interlayer, it has stronger mechanical properties, can improve the stability and safety of the solid rocket, and reduce the risk of accidental ignition caused by prefabricated defects. After the engine ignition is working and the upper unit is completed, the electric heating circuit is turned on, and the electrode pin 5 is connected to the external power supply to heat the heating ring 1. The heating ring heats the ablation layer 2, and the ablation layer 2 absorbs heat and begins to soften. The engine interlayer is supported only by the porous material layer 3. When the lower unit is needed to work, the igniter 1 works and ignites the end face of the charge 6. The high-pressure gas generated can smoothly open the softened ablation layer 2 and the porous material layer 3, thereby realizing the operation of the lower pulse unit.

[0049] In summary, the present invention provides a controllable ablation barrier type multi-pulse engine, in which multiple pulse units are assembled on the engine outer shell, and each pulse unit is provided with an electrically heated ablation barrier assembly. The hard barrier is converted into a soft barrier by means of electric heating, and the pulse engine barrier opening action is completed safely and controllably. After the gas channel is opened, the isolation material is made of a low-melting-point thermoplastic material, which can be directly ablated under the action of the high-temperature gas in the combustion chamber, reducing the impact on the subsequent working process of the engine. The barrier structure of the present invention has no prefabricated defects, which reduces the risk of failure of the multi-pulse engine barrier. The entire barrier opening action does not produce destructive debris, which greatly improves the working stability and reliability of the multi-pulse engine.

[0050] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit it. Although the present invention has been described in detail with reference to the above embodiments, ordinary technicians in the field should understand that the specific implementation methods of the present invention can still be modified or replaced by equivalents. Any modification or equivalent replacement that does not depart from the spirit and scope of the present invention should be covered by the scope of protection of the claims of the present invention.

Claims

1. A controllable ablation barrier type multi-pulse engine, characterized in that: It comprises an engine outer shell (9) and a plurality of pulse units (8); the plurality of pulse units (8) are coaxially assembled in sequence in the engine outer shell (9), the pulse units (8) comprising an electric heating ablation barrier assembly, a drug column (6) and an igniter (7); the electric heating ablation barrier assembly is a cylindrical structure, wherein one end of the electric heating ablation barrier assembly is provided with an ablation side, the drug column (6) is assembled in the ablation barrier assembly, and the igniter (7) penetrates the ablation side of the electric heating ablation barrier assembly and contacts the drug column (6); The electric heating ablation barrier assembly comprises a heating ring (1), an ablation layer (2), a supporting insulation assembly and a plurality of electrode pins (5); wherein the supporting insulation assembly is a cylindrical structure, the ablation layer (2) is attached to one end of the supporting insulation assembly to form an ablation side, the heating ring (1) is assembled on the ablation layer (2), and the plurality of electrode pins (5) are vertically arranged in the outer wall of the supporting insulation assembly, and all of them sequentially penetrate the ablation layer (2) and the heating ring (1) and are connected to an external power supply to form a heating circuit, the drug column (6) is assembled in the supporting insulation assembly, and the igniter (7) sequentially penetrates the heating ring (1), the ablation layer (2) and the end of the ablation barrier assembly and contacts the drug column (6); After the engine is ignited and the upper unit has finished working, the electric heating circuit is turned on, the electrode pin (5) is connected to the external power supply to heat the heating ring (1), and the heating ring heats the ablation layer (2). The ablation layer (2) absorbs the heat and begins to soften. When the lower unit needs to work, the igniter (1) works to ignite the end face of the charge column (6), and the high-pressure gas generated can open the softened ablation layer (2).

2. A controllable ablation barrier type multi-pulse engine according to claim 1, characterized in that: The outer diameter of the ablation side of the electric heating ablation barrier component corresponds to the inner diameter of the engine outer casing (9).

3. The controllable ablation barrier type multi-pulse engine according to claim 1, characterized in that: The heating ring (1) is an open thin-walled circular ring structure, wherein electrode positioning holes (11) are respectively provided at both ends of the opening of the heating ring (1), and the electrode pin (5) is connected to an external power supply through the electrode positioning holes (11); a plurality of centripetal heating plates (12) are provided along the circumference of the inner side of the heating ring (1), wherein a plurality of centripetal heating plates (12) have through holes reserved at the center of the heating ring (1) to form a first igniter mounting hole (13) for assembling the igniter (7); and the plurality of centripetal plates (12) are assembled on the ablation layer (2) through the heating ring (1).

4. A controllable ablation barrier type multi-pulse engine according to claim 3, characterized in that: The thickness of the plurality of centripetal heating plates (12) is greater than the thickness of the heating ring (1).

5. The controllable ablation barrier type multi-pulse engine according to claim 3, characterized in that: The ablation layer (2) is in the form of a circular boss structure, wherein a plurality of pairs of ablation layer guide holes (21) are distributed on the outer circular ring of the ablation layer (2), and each pair of ablation layer guide holes (21) corresponds to two electrode positioning holes (11) of the heating ring (1) and is used to penetrate the electrode pin (5). The middle boss portion of the ablation layer (2) is provided with a plurality of centripetal grooves (22) along the circumference, and a plurality of centripetal heating plates (12) are correspondingly assembled in the plurality of centripetal grooves (22). A through hole is reserved at the center of the middle boss portion of the plurality of centripetal heating plates (12) to form a second igniter mounting hole (23) for assembling the igniter (7).

6. The controllable ablation barrier type multi-pulse engine according to claim 5, characterized in that: The outer diameter of the outer ring of the ablation layer (2) corresponds to the inner diameter of the engine outer casing (9).

7. The controllable ablation barrier type multi-pulse engine according to claim 5, characterized in that: The depth of the centripetal groove (22) corresponds to the thickness of the centripetal heating plate (12).

8. The controllable ablation barrier type multi-pulse engine according to claim 1, characterized in that: The supporting insulating assembly comprises a porous material layer (3) and an insulating ring (4), wherein the porous material layer (3) is assembled at the end of the insulating ring (4) to form a cylindrical structure, wherein a plurality of insulating ring guide holes (41) are provided in the insulating ring (4), wherein the electrode pin (5) passes through the ablation layer (2) and the heating ring (1) in sequence along the insulating ring guide holes (41) and is connected to an external power source to form a heating circuit, wherein the drug column (6) is assembled in the insulating ring (4), and a third ignition mounting hole (31) is provided on the porous material layer (3) for assembling an igniter (7).

9. The controllable ablation barrier type multi-pulse engine according to claim 1, characterized in that: The material of the ablation layer (2) is ABS thermoplastic material.

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