Solid rocket engine ignition safety mechanism

Abstract

The application relates to the technical field of rocket engine ignition, in particular to a solid rocket engine ignition safety insurance mechanism which comprises a body, a gas storage cover, an electric control ignition unit, an insurance plug unit, a piston and an electromagnetic action execution unit; a sliding cavity is arranged in the body, the two ends of the sliding cavity are respectively arranged on the opposite two end faces of the body, the piston is slidably assembled in the sliding cavity along the axial direction of the sliding cavity, the electromagnetic action execution unit and the gas storage cover are respectively and sealingly connected to the opposite two end faces of the body, the electromagnetic action execution unit is connected with the piston, and the electromagnetic action execution unit is used for driving the piston to slide back and forth between a first position and a second position; a first channel and a second channel are arranged in the body, and a third channel and a fourth channel are arranged in the piston. The application can effectively prevent the risk of misignition, has very good reliability and safety, can adapt to various strong impact forces after ignition, is more durable and more stable in operation.

Description

Technical Field

[0001] This application relates to the field of rocket engine ignition technology, and in particular to a solid rocket engine ignition safety insurance mechanism. Background Technology

[0002] A solid propellant rocket engine is a chemical rocket engine that uses solid propellant. It is also called a solid propellant rocket engine. After the solid propellant is ignited, it burns in the combustion chamber, converting chemical energy into heat energy and producing high-temperature, high-pressure combustion products. These products flow through the nozzle, where they expand and accelerate, converting heat energy into kinetic energy, and are expelled at high speed from the nozzle to generate thrust.

[0003] A solid rocket motor consists of a propellant grain, a combustion chamber, a nozzle assembly, and an ignition device. The propellant grain is a hollow cylinder made of propellant and a small amount of additives (the hollow part is the combustion surface, and its cross-sectional shape can be circular, star-shaped, etc.). The propellant grain is placed in the combustion chamber (generally the engine casing). During propellant combustion, the combustion chamber must withstand temperatures of 2500–3500 degrees Celsius and pressures of 10²–2 × 10⁷ bar, therefore it must be made of high-strength alloy steel, titanium alloy, or composite materials, and a heat-insulating liner is installed between the propellant grain and the inner combustion chamber wall.

[0004] The igniter is the starting device for a solid rocket engine. It is the most dangerous and most prone to failure component. An igniter generally consists of an electric ignition tube, propellant, and a connecting seat.

[0005] A Chinese patent application with application number 201911137927.9 discloses an electromagnetic mechanical safety solid rocket engine igniter. An electromagnetic mechanical safety device is placed in the gas ignition channel between the ignition tube and the ignition cartridge in the igniter. The opening and closing of the gas ignition channel is controlled by an electrical signal through the electromagnetic mechanical safety device. The electromagnetic mechanical safety device mainly consists of an electromagnetic chuck, an electromagnetic chuck power supply cable, a gas ignition channel valve, and a spring. The electromagnetic mechanical safety device is placed in a connecting seat, with the electromagnetic chuck fixed to the connecting seat. One end of the spring is fixed to the connecting seat, and the other end is fixed to the gas channel valve. The gas channel valve can reciprocate within the connecting seat under the action of the electromagnetic chuck and the spring. A gas ignition channel is provided within the gas channel valve.

[0006] Regarding the aforementioned related technologies, the inventors believe that the following defects exist:

[0007] Conventional ignition safety mechanisms use only springs to connect the channel converter, which cannot withstand impacts and vibrations. This makes them prone to changes in state due to impacts and vibrations, posing a significant safety hazard. In the safe state, the igniter outlet is simply blocked. However, if ignition occurs accidentally, the high-temperature and high-pressure gas has no way to escape, which can easily cause the entire mechanism to explode. Summary of the Invention

[0008] This application provides an ignition safety mechanism for solid rocket motors to improve the following technical problems:

[0009] Conventional ignition safety mechanisms use only springs to connect the channel converter, which cannot withstand impacts and vibrations. This makes them prone to changes in state due to impacts and vibrations, posing a significant safety hazard. In the safe state, the igniter outlet is simply blocked. However, if ignition occurs accidentally, the high-temperature and high-pressure gas has no way to escape, which can easily cause the entire mechanism to explode.

[0010] This application provides a safety plug unit, which adopts the following technical solution:

[0011] A solid rocket motor ignition safety mechanism includes a main body, a gas storage cover, an electronically controlled ignition unit, a piston, an electromagnetic actuation unit, and a safety plug unit.

[0012] The body has a sliding chamber inside, with its two openings located on opposite end faces of the body. The piston is slidably mounted in the sliding chamber along its axial direction. A gap is left between the piston and the inner wall of the sliding chamber to achieve a micro-sealed sliding connection between them. The electromagnetic actuator and the gas storage cover are respectively sealed and connected to opposite end faces of the body. A portion of the electromagnetic actuator is connected to the piston. The electromagnetic actuator is used to drive the piston to slide back and forth between a first position and a second position.

[0013] The body is provided with a first channel and a second channel, which are respectively connected to the opposite sides of the sliding chamber. The electronic ignition unit is installed at the end of the first channel away from the sliding chamber, and the safety plug unit is installed at the end of the second channel away from the sliding chamber.

[0014] The piston is provided with a third channel and a fourth channel, and the outer surface of the piston is provided with a first working hole, a second working hole, a first safety hole and a second safety hole. The first working hole and the second working hole are respectively located at both ends of the third channel, and the first safety hole and the second safety hole are respectively located at both ends of the fourth channel.

[0015] When the piston slides to the first position, the first channel, the third channel, and the second channel are connected in sequence; when the piston slides to the second position, the first channel, the fourth channel, and the gas storage hood are connected in sequence.

[0016] Optionally, the safety plug unit includes a plug frame, a diaphragm, a fixing member, and an annular fluorosilicone rubber gasket. The plug frame is sealed and installed in the ignition channel through which the high-temperature and high-pressure gas passes after ignition. The plug frame has an installation groove near the end where the high-temperature and high-pressure gas enters. The diaphragm is located at the bottom of the installation groove. The fixing member is installed in the installation groove. The diaphragm is clamped between the bottom of the installation groove and the fixing member. Both the plug frame and the fixing member have perforations for the high-temperature and high-pressure gas to pass through. The annular fluorosilicone rubber gasket is sandwiched between the plug frame and the main body.

[0017] Optionally, the fixing component includes a pressure cap and a screw. The pressure cap has an annular structure, and the membrane blocking frame has a cylindrical structure. The pressure cap has multiple through holes for the screw to pass through, and the end of the membrane blocking frame has a threaded hole. The through holes and the threaded holes are arranged in a one-to-one correspondence. The screw passes through the through holes and the membrane in sequence and is then threaded into the threaded hole.

[0018] Optionally, the diaphragm is made of aluminum foil, which is punctured when the gas pressure in the ignition channel exceeds 7 MPa.

[0019] Optionally, the electromagnetic actuation unit is a bidirectional holding electromagnet.

[0020] Optionally, the fourth channel is L-shaped, the second safety hole is located on the end face of the piston away from the electromagnetic actuation unit, and the first safety hole is located on the outer peripheral wall of the piston.

[0021] Optionally, the third channel is straight and arranged along the diameter direction of the piston, and both the first working hole and the second working hole are located on the outer peripheral wall of the piston.

[0022] Optionally, a connecting cylinder is provided on the end face of the piston near the electromagnetic actuation unit.

[0023] Optionally, the inner wall of the sliding chamber is provided with a guide groove, and the piston is provided with a guide pin that slides back and forth in the guide groove.

[0024] Optionally, the first channel is Y-shaped, and two openings are provided at the end of the first channel away from the sliding chamber. The electronically controlled ignition unit is provided with two units, which are respectively installed at the two openings of the first channel.

[0025] In summary, this application includes at least one of the following beneficial technical effects:

[0026] By activating the electromagnetic actuator and driving the piston to slide, the switching and locking between the safe state and the working state can be achieved. The structure is simple and reasonable, requires fewer parts, has high structural strength of the parts, and has very good reliability. It can withstand various powerful impacts after ignition, making it more durable and more stable in operation.

[0027] A safety plug unit is added to the ignition channel. When the piston is in the safe state, if the electronic ignition unit ignites accidentally, the high-temperature, high-pressure gas will reach the gas reservoir through the piston's internal channel. Because the gas reservoir has a large enough volume, the pressure of the high-temperature, high-pressure gas will not exceed 7MPa. Due to the insufficient pressure, the diaphragm will not be ruptured, so the ignition channel remains closed and normal ignition is impossible. When the piston switches to the working state, the piston's internal channel directly connects to the electronic ignition unit and the safety plug unit. At this time, the high-temperature, high-pressure gas has difficulty reaching the gas reservoir through the gap between the piston and the cavity in a short time. The high-temperature, high-pressure gas is mainly concentrated in the channel, where the pressure will far exceed 7MPa, which can quickly rupture the diaphragm. Therefore, the ignition channel is open, achieving normal ignition. Thus, the safety plug unit can effectively prevent the risk of accidental ignition, making it safer. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram of the solid rocket engine ignition safety mechanism in the embodiments of this application.

[0030] Figure 2 This is a cross-sectional structural schematic diagram of the solid rocket engine ignition safety mechanism in the embodiments of this application.

[0031] Figure 3 This is a schematic diagram of the piston structure in an embodiment of this application.

[0032] Figure 4 This is a cross-sectional structural schematic diagram of the safety plug unit in the embodiment of this application.

[0033] Explanation of reference numerals in the attached figures:

[0034] 1. Body; 11. Sliding chamber; 12. First channel; 13. Second channel; 14. Guide groove; 2. Gas storage cover; 3. Electrically controlled ignition unit; 4. Safety plug unit; 41. Diaphragm holder; 42. Diaphragm; 43. Pressure cap; 44. Screw; 5. Piston; 51. Third channel; 511. First working hole; 512. Second working hole; 52. Fourth channel; 521. First safety hole; 522. Second safety hole; 53. Connecting cylinder; 54. Guide pin; 6. Electromagnetic actuation unit; 7. Mounting plate; 71. Mounting hole; 8. First flange structure; 9. Second flange structure. Detailed Implementation

[0035] To make the technical problems, technical solutions, and beneficial effects to be solved by this application clearer, the following detailed description is provided in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and are not intended to limit the scope of this application.

[0036] It should be noted that when a component is referred to as being "fixed to" or "set on" another component, it can be directly on or indirectly on that other component. When a component is referred to as being "connected to" another component, it can be directly connected to or indirectly connected to that other component.

[0037] It should be understood that the terms "length", "width", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0038] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this application, "multiple" means two or more, unless otherwise explicitly specified.

[0039] The following is in conjunction with the appendix Figure 1-4 This application will be described in further detail.

[0040] This application discloses an ignition safety mechanism for solid rocket engines, referring to... Figure 1 , Figure 2 and Figure 3It includes the main body 1, the gas storage cover 2, the electronic ignition unit 3, the safety plug unit 4, the piston 5, and the electromagnetic actuation unit 6;

[0041] The body 1 has a sliding chamber 11 inside. The openings at both ends of the sliding chamber 11 are located on two opposite end faces of the body 1. The piston 5 is slidably assembled in the sliding chamber 11 along the axial direction of the sliding chamber 11. A gap is left between the piston 5 and the inner wall of the sliding chamber 11 to achieve a micro-sealed sliding connection between the two. The electromagnetic actuator 6 and the gas storage cover 2 are respectively sealed and connected to the two opposite end faces of the body 1. A part of the electromagnetic actuator 6 is connected to the piston 5. The electromagnetic actuator 6 is used to drive the piston 5 to slide back and forth between the first position and the second position.

[0042] The main body 1 is provided with a first channel 12 and a second channel 13. The first channel 12 and the second channel 13 are respectively connected to the opposite sides of the sliding chamber 11. The electronic ignition unit 3 is installed at the end of the first channel 12 away from the sliding chamber 11, and the safety plug unit 4 is installed at the end of the second channel 13 away from the sliding chamber 11.

[0043] The piston 5 is provided with a third channel 51 and a fourth channel 52. The outer surface of the piston 5 is provided with a first working hole 511, a second working hole 512, a first safety hole 521 and a second safety hole 522. The first working hole 511 and the second working hole 512 are respectively located at the two ends of the third channel 51, and the first safety hole 521 and the second safety hole 522 are respectively located at the two ends of the fourth channel 52.

[0044] When piston 5 slides to the first position, the first channel 12, the third channel 51 and the second channel 13 are connected in sequence, which is the working state; when piston 5 slides to the second position, the first channel 12, the fourth channel 52 and the gas storage cover 2 are connected in sequence, which is the safe state.

[0045] The fourth channel 52 is L-shaped, the second safety hole 522 is located on the end face of the piston 5 away from the electromagnetic action execution unit 6, and the first safety hole 521 is located on the outer peripheral wall of the piston 5.

[0046] The third channel 51 is straight and arranged along the diameter of the piston 5. The first working hole 511 and the second working hole 512 are both located on the outer peripheral wall of the piston 5.

[0047] The first channel 12 is Y-shaped, and two openings are provided at the end of the first channel 12 away from the sliding chamber 11. Two electronic ignition units 3 are provided and installed at the two openings of the first channel 12 respectively.

[0048] Through the above technical solutions, the structure of piston 5 and body 1 is more compact and the spatial layout is more reasonable. This not only facilitates the early processing and later assembly of parts, but also allows the two electronic ignition units 3 to serve as backups for each other. Whether in a safe state or a working state, they are very stable.

[0049] A connecting cylinder 53 is provided on the end face of the piston 5 near the electromagnetic actuator 6. The design of the connecting cylinder 53 facilitates a firm connection between the piston 5 and the telescopic rod of the electromagnetic actuator 6.

[0050] To ensure that the piston 5 does not easily rotate when sliding linearly in the sliding chamber 11, the inner wall of the sliding chamber 11 is provided with a guide groove 14, and the piston 5 is provided with a guide pin 54 that slides back and forth in the guide groove 14. The guide pin 54 and the guide groove 14 cooperate with each other to have a good limiting and blocking effect, effectively preventing the piston 5 from rotating.

[0051] A mounting plate 7 is provided on the side of the main body 1 away from the electronic ignition unit 3. Multiple mounting holes 71 are provided on both sides of the mounting plate 7. The design of the mounting plate 7 is conducive to the installation and fixation of the entire ignition safety mechanism.

[0052] The electromagnetic actuator 6 and the main body 1 are sealed together by the first flange structure 8, and are sealed by an O-ring. The gas storage cover 2 and the main body 1 are sealed together by the second flange structure 9, and are also sealed by an O-ring. This ensures a firm connection between the gas storage cover 2, the electromagnetic actuator 6 and the main body 1, and provides very high airtightness.

[0053] The main body 1 is made of titanium alloy, which has very high mechanical strength and is relatively lightweight.

[0054] Piston 5 is made of aluminum bronze alloy. To ensure wear resistance, aluminum bronze alloy is the best material to choose for piston 5. In view of the principle of meeting design requirements at the lowest cost, aluminum bronze alloy is chosen as the material for piston 5. Aluminum bronze alloy has the advantages of good processing performance, high mechanical properties, fatigue resistance, wear resistance, corrosion resistance, low temperature resistance, and no sparks generated during impact.

[0055] The gas hood 2 is made of 2Cr13 material that conforms to the GJB2294-95 standard. It has good processing performance, high mechanical properties, and is not easily deformed and leaks easily.

[0056] The ignition safety mechanism in this application embodiment has two states:

[0057] Safety condition: Even if the electronic ignition unit 3 is accidentally detonated, the high-temperature and high-pressure gas generated by the electronic ignition unit 3 flows directly to the gas storage shroud 2. Since the volume of the gas storage shroud 2 is large enough, the pressure will not exceed 7MPa. Even if it leaks slightly through the gap between the piston 5 and the cavity to the safety plug unit 4, the aluminum foil will not be broken. The high-temperature and high-pressure gas is closed inside the ignition safety mechanism and cannot reach the ignition powder box (connected to the outer end of the second channel 13). Therefore, the powder box will not be ignited, thus ensuring that the solid rocket engine is not accidentally ignited.

[0058] In the working state, the ignition safety mechanism opens the channel between the electronic ignition unit 3 and the gunpowder box. If the electronic ignition unit 3 is detonated, the high-temperature and high-pressure gas will be concentrated in the gas channel for a short time. Even if a small amount of gas leaks into the gas storage shroud 2, it will not be enough to reduce the pressure. At this time, the pressure will be far greater than 7MPa, which will directly ignite the gunpowder box. Then the ignition engine connected to the gunpowder box will be ignited, and then the main engine will be ignited. The solid rocket engine will be successfully ignited.

[0059] The ignition safety insurance mechanism has two functions:

[0060] Safety condition: Even if the electronic ignition unit 3 is accidentally detonated, it must be ensured that the solid rocket motor will not be ignited;

[0061] In operation, if the electronic ignition unit 3 is detonated, it must be ensured that ignition is successful.

[0062] Therefore, by activating the electromagnetic actuator 6 and driving the piston 5 to slide, the switching and locking between the safe state and the working state can be achieved. The structure is simple and reasonably designed, requires fewer parts, has high structural strength of the parts, and has very good reliability. It can withstand various powerful impacts after ignition, making it more durable and more stable in operation.

[0063] Please refer to Figure 3 and Figure 4 The safety plug unit 4 includes a diaphragm frame 41, a diaphragm 42, a fixing member, and an annular fluorosilicone rubber gasket 45. The diaphragm frame 41 is sealed and installed in the ignition channel through which the high-temperature and high-pressure gas passes after ignition. The end of the diaphragm frame 41 near the entrance of the high-temperature and high-pressure gas is provided with an installation groove. The diaphragm 42 is located at the bottom of the installation groove, and the fixing member is installed in the installation groove. The diaphragm 42 is clamped between the bottom of the installation groove and the fixing member. Both the diaphragm frame 41 and the fixing member are provided with perforations for the high-temperature and high-pressure gas to pass through. The annular fluorosilicone rubber gasket 45 is sandwiched between the diaphragm frame 41 and the main body 1. The annular fluorosilicone rubber gasket 45 is about 1.5 mm in diameter. When the safety plug unit 4 is installed, the annular fluorosilicone rubber gasket 45 will be squeezed, thereby increasing the sealing effect.

[0064] The fasteners include a pressure cap 43 and a screw 44. The pressure cap 43 is a ring structure, and the membrane blocking frame 41 is a cylindrical structure. The pressure cap 43 is provided with multiple through holes for the screw 44 to pass through. The end of the membrane blocking frame 41 is provided with a threaded hole. The through holes and the threaded holes are arranged in a one-to-one correspondence. The screw 44 passes through the through holes and the membrane 42 in sequence and is then threaded into the threaded hole.

[0065] The diaphragm 42 is made of aluminum foil. When the gas pressure in the ignition channel is higher than 7 MPa, the aluminum foil is ruptured.

[0066] The safety plug unit 4 is designed to be added to the ignition channel. When the amount of leaked high-temperature and high-pressure gas is small, the pressure it forms is not large enough to break the diaphragm 42. Therefore, the ignition channel remains closed and cannot ignite normally. When there is a lot of high-temperature and high-pressure gas, the pressure it forms is very large and can quickly break the diaphragm 42. Therefore, the ignition channel is connected and normal ignition is achieved. Thus, the safety plug unit 4 can effectively prevent the risk of accidental ignition and is safer.

[0067] Since there is no complete seal between the piston 5 and the sliding chamber 11, but rather a certain gap, this application refers to it as a "micro-seal".

[0068] Even in a safe state, there may be a slight leak of high-temperature and high-pressure gas into the membrane holder 41 and the diaphragm 42 (i.e., the safety plug unit 4). However, since most of the high-temperature and high-pressure gas has already reached the gas storage hood 2, and the volume of the gas storage hood 2 is designed to be about 103ml, the pressure of the high-temperature and high-pressure gas will not exceed 7MPa, so the diaphragm 42 will not be ruptured.

[0069] When in operation, the first channel 12, the third channel 51, and the second channel 13 are connected in sequence (i.e., ignition channels) and aligned with the diaphragm 42. Even if some high-temperature and high-pressure gas leaks through the gap between the piston 5 and the sliding chamber 11 into the gas storage cover, the pressure inside the ignition channel is still much higher than 7MPa. The diaphragm 42 will be easily ruptured, thus igniting the gunpowder box.

[0070] In this application, the electronically controlled ignition unit 3 can be a common electric detonator, and the electromagnetic actuation unit 6 in this embodiment is a bidirectional holding electromagnet. A bidirectional holding electromagnet does not require prolonged energization; a short energization of less than 0.5 seconds is sufficient to complete the state transition, and it retains its state even after power is cut off. Because the electromagnet uses a neodymium iron boron permanent magnet with extremely strong magnetic force, the holding force after power is cut off is very large, sufficient to withstand strong impact vibrations. In other embodiments, the electromagnetic actuation unit 6 can also be a common electrically controlled push rod or a telescopic component similar to a cylinder or hydraulic cylinder.

[0071] Because this application employs "micro-sealing" technology, O-rings are no longer needed for sealing on piston 5 (complete sealing). Simultaneously, the sliding transition of piston 5 is extremely smooth with virtually no resistance. Due to the minimal resistance, this application can utilize a bidirectional holding electromagnet to pull piston 5 for state switching. Compared to common electromagnetic chucks, it does not require prolonged power supply to operate. For space-going equipment like rocket engines, this further conserves power and enhances safety.

[0072] If a "fully sealed" system (i.e., an O-ring is added to piston 5 for sealing) is used instead of "micro-sealing" technology, then it cannot be driven by an electromagnet and can only be driven by a motor. Although the driving force of a motor is greater than that of an electromagnet, its operating speed is very slow and cannot meet the requirements of rapid switching. Moreover, the structure of the motor and the reduction mechanism is complex, the failure rate is high, the low-temperature performance is far inferior to that of an electromagnet, and the cost is also very high.

[0073] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this application should be included within the protection scope of this application.

Claims

1. A solid rocket motor ignition safety mechanism, characterized in that, It includes the main body (1), gas storage cover (2), electronic ignition unit (3), piston (5), electromagnetic action execution unit (6) and safety plug unit (4); The body (1) is provided with a sliding chamber (11) inside. The openings at both ends of the sliding chamber (11) are located on two opposite end faces of the body (1). The piston (5) is slidably assembled in the sliding chamber (11) along the axial direction of the sliding chamber (11). A gap is left between the piston (5) and the inner wall of the sliding chamber (11) to achieve a micro-sealed sliding connection between the two. The electromagnetic actuator (6) and the gas storage cover (2) are respectively sealed and connected to the two opposite end faces of the body (1). A part of the electromagnetic actuator (6) is connected to the piston (5). The electromagnetic actuator (6) is used to drive the piston (5) to slide back and forth between the first position and the second position. The main body (1) is provided with a first channel (12) and a second channel (13), the first channel (12) and the second channel (13) are respectively connected to the opposite sides of the sliding chamber (11), the electronic ignition unit (3) is installed at the end of the first channel (12) away from the sliding chamber (11), and the safety plug unit (4) is installed at the end of the second channel (13) away from the sliding chamber (11); The piston (5) is provided with a third channel (51) and a fourth channel (52). The outer surface of the piston (5) is provided with a first working hole (511), a second working hole (512), a first safety hole (521) and a second safety hole (522). The first working hole (511) and the second working hole (512) are respectively located at both ends of the third channel (51), and the first safety hole (521) and the second safety hole (522) are respectively located at both ends of the fourth channel (52). When the piston (5) slides to the first position, the first channel (12), the third channel (51) and the second channel (13) are connected in sequence; when the piston (5) slides to the second position, the first channel (12), the fourth channel (52) and the gas storage cover (2) are connected in sequence.

2. The solid rocket engine ignition safety mechanism according to claim 1, wherein the safety plug unit (4) includes a plug frame (41), a diaphragm (42), a fixing member and an annular fluorosilicone rubber gasket (45), the plug frame (41) is sealed and installed in the ignition channel through which the high-temperature and high-pressure gas passes after ignition, the plug frame (41) is provided with an installation groove near the end where the high-temperature and high-pressure gas enters, the diaphragm (42) is provided at the bottom of the installation groove, the fixing member is installed in the installation groove, the diaphragm (42) is clamped between the bottom of the installation groove and the fixing member, the plug frame (41) and the fixing member are both provided with perforations for the high-temperature and high-pressure gas to pass through, and the annular fluorosilicone rubber gasket (45) is clamped between the plug frame (41) and the body (1).

3. The solid rocket engine ignition safety mechanism according to claim 2, wherein the fixing component includes a pressure cap (43) and a screw (44), the pressure cap (43) is an annular structure, the diaphragm holder (41) is a cylindrical structure, the pressure cap (43) is provided with a plurality of through holes for the screw (44) to pass through, the end of the diaphragm holder (41) is provided with a threaded hole, the through holes and the threaded holes are arranged in a one-to-one correspondence, and the screw (44) passes through the through hole and the diaphragm (42) in sequence and is then threaded into the threaded hole.

4. In the solid rocket engine ignition safety mechanism according to claim 2, the diaphragm (42) is an aluminum foil, and the aluminum foil is ruptured when the gas pressure in the ignition channel is higher than 7 MPa.

5. The solid rocket motor ignition safety mechanism according to claim 1, characterized in that, The electromagnetic action execution unit (6) is a bidirectional holding electromagnet.

6. The solid rocket engine ignition safety mechanism according to claim 1, characterized in that, The fourth channel (52) is L-shaped, the second safety hole (522) is located on the end face of the piston (5) away from the electromagnetic action execution unit (6), and the first safety hole (521) is located on the outer peripheral wall of the piston (5).

7. The solid rocket motor ignition safety mechanism according to claim 1, characterized in that, The third channel (51) is straight and arranged along the diameter direction of the piston (5), and the first working hole (511) and the second working hole (512) are both located on the outer peripheral wall of the piston (5).

8. The solid rocket motor ignition safety mechanism according to claim 1, characterized in that, A connecting cylinder (53) is provided on the end face of the piston (5) near the electromagnetic action execution unit (6).

9. The solid rocket motor ignition safety mechanism according to claim 1, characterized in that, The inner wall of the sliding chamber (11) is provided with a guide groove (14), and the piston (5) is provided with a guide pin (54) that slides back and forth in the guide groove (14).

10. The solid rocket motor ignition safety mechanism according to claim 1, characterized in that, The first channel (12) is Y-shaped, and two openings are provided at one end of the first channel (12) away from the sliding chamber (11). The electronic ignition unit (3) is provided with two openings respectively installed at the two openings of the first channel (12).

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