A solid propellant pressure reduction and flameout device and method thereof

Abstract

The present invention relates to a solid propellant pressure-reducing flameout device and method, belonging to the technical field of solid propellant flameout, and comprising a solid propellant combustion chamber assembly, a pressure measurement assembly, and a membrane rupture device assembly. The solid propellant is placed in the combustion chamber. There are three openings at the top of the combustion chamber. A main nozzle is arranged in one opening, and the solid propellant is ignited through the central small hole of the main nozzle by using high-energy laser. A pressure measurement assembly is arranged in one opening, and a secondary nozzle is arranged in the other opening. A pressure relief glass is arranged below the secondary nozzle. Under the action of the energy storage spring, the membrane rupture device assembly drives the striker to move rapidly downward and strike the pressure relief glass, thereby completing pressure relief. The pressure of the solid propellant is reduced and the flame is extinguished by the method of breaking the window to relieve pressure, so as to analyze the flameout characteristics of the solid propellant and the combustion mechanism of the solid propellant.

Description

Technical Field

[0001] The present invention relates to a solid propellant pressure reduction and flameout device and its method, belonging to the technical field of solid propellant flameout. Background Art

[0002] Within the operating range of solid rocket engines, there are sometimes requirements for the engine to extinguish flames instantaneously. Therefore, the flameout technology is also one of the research topics for the controllability of solid rocket engines. The combustion of solid propellants is characterized by fierceness and uncontrollability. Currently, the existing methods for studying solid propellant flameout tests include: sudden pressure reduction, explosive injection cooling, copper platform heat transfer, etc. Pressure reduction flameout is a commonly used means for studying solid propellants. By means of pressure reduction, the flameout burning surface of solid propellants can be better obtained, and the physical and chemical states during the solid propellant flameout process can be more realistically restored. Invention Patent CN201010531622.9 discloses a solid propellant rapid flameout device, which mainly consists of a combustion chamber, a pressure sensor, an optoelectronic sensor, an ignition power supply, a high-pressure switch solenoid valve, a high-pressure gas cylinder, and a supporting computer acquisition system, etc. The combustion chamber is pressurized by a booster pump and a high-pressure gas cylinder to maintain a relatively stable initial pressure. The ignition power supply is connected to the high-pressure switch solenoid valve, and the solenoid valve is opened simultaneously when the propellant is ignited for rapid flameout. The pressure change curve of the combustion chamber is recorded and collected in real time by the pressure sensor and the supporting system, and the optoelectronic sensor judges whether the propellant has successfully extinguished the flame. However, this device has some problems: the initial pressure of the combustion chamber is increased by a booster pump, and the range is limited and cannot meet future high-pressure (tests above 30 Mpa); the device with a gas cylinder booster pump is bulky, and it is necessary to refill and build pressure before each measurement, with complex operations and increased test costs.

[0003] Therefore, how to achieve a stable, cost-effective, and convenient flameout test is still an important research topic at present. Summary of the Invention

[0004] In order to solve the above technical problems, the present invention provides a solid propellant pressure reduction and flameout device and its method, and the specific technical solutions are as follows:

[0005] A solid propellant pressure reduction and flameout device includes a combustion chamber assembly, a film-breaking assembly, and a pressure measurement assembly. There are 3 threaded holes at the top of the combustion chamber assembly. A main nozzle expansion extension section is installed in one threaded hole, a pressure relief glass is arranged in one opening, and a pressure-taking seat of the pressure measurement assembly is installed in one opening. There is a movable striker in the film-breaking assembly, the tip of the striker faces the pressure relief glass, and the film-breaking assembly can control the movement of the striker to break the pressure relief glass.

[0006] Furthermore, the combustion chamber assembly includes a combustion chamber with a mounting flange. The inner wall of the combustion chamber is fitted with an annular thermal insulation layer, and solid propellant is loaded into the annular thermal insulation layer. The upper end of the annular thermal insulation layer is bonded to the front thermal insulation layer, and the bottom is bonded to the rear thermal insulation layer. The solid propellant is bonded to the rear thermal insulation layer.

[0007] Furthermore, there are flange plates at both ends of the combustion chamber. The flange plates at the corresponding ends of the combustion chamber are respectively connected to the flange bottom cover and the front flange cover. The flange plate at the bottom of the combustion chamber is connected to the flange bottom cover by bolts. The front flange cover and the transition flange plate are sequentially connected from the inside to the outside of the top of the combustion chamber and are connected by passing through with a number of bolts.

[0008] Furthermore, the transition flange plate is provided with a film rupture device installation threaded hole, a nozzle installation threaded hole, and a pressure measurement component protective sleeve installation hole. At the corresponding position of the nozzle installation threaded hole on the front flange cover, there is a main nozzle expansion extension section. The main nozzle expansion extension section is bonded to the main nozzle. The lower surface of the main nozzle is bonded to the main nozzle convergent extension section. At the corresponding position of the main nozzle convergent extension section on the front thermal insulation layer, there is an opening and it is communicated with the inside of the combustion chamber. The channel diameter after the docking of the main nozzle expansion extension section and the main nozzle convergent extension section converges first and then expands from top to bottom. At the corresponding position of the pressure measurement component protective sleeve installation hole on the front flange cover, there is a pressure measurement component installation hole. The pressure measurement component installation hole is an internal thread structure for installing the pressure measurement component.

[0009] Furthermore, at the corresponding position of the film rupture device installation threaded hole on the front flange cover, there is a vertical hole. The bottom of the vertical hole is located in the front flange cover. In the vertical hole, a secondary nozzle expansion extension section and a pressure relief glass are fixedly arranged. The secondary nozzle expansion extension section has an axial opening, and the diameter gradually decreases from top to bottom to form a secondary nozzle. The pressure relief glass is located at the lower end of the secondary nozzle and the inner bottom of the vertical hole and blocks the vertical hole. Below the vertical hole, there is a pressure relief hole coaxial with it and passing through the front flange cover and the front thermal insulation layer. The secondary nozzle expansion extension section is screwed into the front flange cover and presses the pressure relief glass against the front flange cover.

[0010] Furthermore, the flanges at both ends of the combustion chamber and the flange bottom cover and the front flange cover at the corresponding ends are all sealed by a sealing limit ring and the flange end face.

[0011] Further, the film-breaking assembly further includes a sliding cylinder, a tungsten infiltrated copper heat-resistant part, and a cylinder assembly. The periphery around the axial middle of the tungsten infiltrated copper heat-resistant part is provided with a rectangular groove for discharging the high-temperature and high-pressure gas ejected by the auxiliary nozzle. The upper end is connected to the sliding cylinder, and the lower end is connected to the film-breaking device installation threaded hole. An inner sleeve that can move up and down along it is arranged inside the sliding cylinder. The top of the striker is connected to the center of the inner sleeve. A rectangular groove is provided on the side wall of the inner sleeve. The working end of the cylinder assembly is fixedly connected to the piston rod. The other end of the piston rod, a long rod, is inserted into the rectangular groove on the side wall of the inner sleeve to resist the force of the energy storage spring pressing on the inner sleeve and maintain the axial position of the inner sleeve. The pneumatic push-pull rod is fixed on the cylinder seat.

[0012] Further, the pressure measurement assembly includes a pressure tapping seat, a pressure tapping pipe, a sensor seat, and a pressure measurement assembly protective sleeve. The lower part of the pressure tapping pipe is vertically downward, and the end is the pressure tapping end, which is connected to the pressure tapping seat. The upper part is vertically arc-bent into a horizontal state, and the end is the pressure measurement end, which is connected to the sensor seat. The pressure measurement assembly protective sleeve is sleeved outside the pressure tapping seat and the pressure tapping seat and tightly connects them. The lower end of the pressure tapping seat is provided with an external thread and is fixedly connected to the pressure measurement assembly installation hole through threaded connection. The pressure measurement assembly protective sleeve is arranged outside the pressure tapping seat.

[0013] A method for reducing pressure and extinguishing the fire of solid propellant. This method for reducing pressure and extinguishing the fire of solid propellant is based on the above-mentioned device for reducing pressure and extinguishing the fire of solid propellant, and includes the following steps:

[0014] Step 1: Place solid propellant in the combustion chamber and bond it to the rear insulation layer at the bottom of the combustion chamber; Step 2: Use high-energy laser to ignite the solid propellant through the central small hole of the main nozzle. Based on the physical and chemical properties of the solid propellant and the structure of the combustion chamber, the pressure in the combustion chamber is jointly determined;

[0015] Step 3: The cylinder assembly of the film-breaking device pulls out the piston rod in the horizontal direction. The piston rod releases the axial limit on the inner sleeve. Under the action of the energy storage spring, the inner sleeve drives the striker to move quickly downward and strike the pressure relief glass;

[0016] Step 4: The pressure relief glass is penetrated, and the high-pressure gas in the combustion chamber is immediately discharged through the auxiliary nozzle. The air pressure in the combustion chamber drops sharply, the burning rate of the solid propellant decreases and the fire goes out;

[0017] Step 5: The pressure measurement assembly records the pressure change during the whole experiment process.

[0018] The beneficial effects of the present invention are:

[0019] The present invention conducts the extinguishing test by the method of reducing pressure and extinguishing the fire, and adopts the method of breaking the window to relieve pressure to realize the reduction of pressure and extinguishing of the solid propellant, so as to analyze the extinguishing characteristics of the solid propellant and study the combustion mechanism of the propellant.

[0020] The present invention conducts a pressure reduction and flameout test by means of breaking the window and relieving pressure. The test cost is low, and it can better simulate the working conditions of solid propellants in a real environment, so as to study the flameout characteristics of solid propellants at different combustion stages, chamber pressures, propellant components, and gas environments. Through the study of combustion during the pressure reduction process, a deeper understanding of the combustion mechanism of solid propellants, especially the unstable combustion mechanism, can be obtained, and the research on pressure reduction and flameout of propellants has a wider scope of application.

[0021] The present invention conducts a flameout test by means of pressure reduction and flameout. Compared with other flameout methods, pressure reduction and flameout is a common means for studying solid propellants. By means of pressure reduction, the flameout burning surface of solid propellants can be obtained, and the physical and chemical states during the flameout process of solid propellants can be more realistically restored. Description of the Drawings

[0022] Figure 1 is the overall three-dimensional schematic diagram of the present invention,

[0023] Figure 2 is the three-dimensional schematic diagram of the combustion chamber assembly of the present invention,

[0024] Figure 3 is the side view of the combustion chamber assembly of the present invention,

[0025] Figure 4 is Figure 3 the D-D cross-sectional view of

[0026] Figure 5 is the top view of the film-breaking assembly of the present invention,

[0027] Figure 6 is Figure 5 the E-E cross-sectional view of

[0028] Figure 7 is the side view of the pressure measurement assembly of the present invention,

[0029] Figure 8 is Figure 7 the F-F cross-sectional view of

[0030] Reference Numerals: A—Combustion Chamber Assembly, B—Film-Breaking Assembly, C—Pressure Measuring Assembly, 1—Cylinder Block, 2—Cylinder Assembly, 3—Sensor Block, 4—Sliding Cylinder, 5—Front Flange, 6—Combustion Chamber, 7—Flange Bottom Cover, 8—Transition Flange, 9—Tungsten-Impregnated Copper Temperature-Bearing Component, 10—Auxiliary Nozzle, 11—Threaded Hole for Installing Film-Breaker, 12—Nozzle Installation Hole, 13—Extension Section of Auxiliary Nozzle, 14—Pressure-Relief Glass, 15—Front Thermal Insulation Layer, 16—Rear Thermal Insulation Layer, 17—Annular Thermal Insulation Layer, 18—Limit Ring, 19—Main Nozzle, 20—Expansion Extension Section of Main Nozzle, 21—Convergent Extension Section of Main Nozzle, 22—Punch, 23—Inner Sleeve, 24—Piston Rod, 25—Pressure-Relief Hole, 26—Vertical Hole, 27—Solid Propellant, 28—Energy Storage Spring, 29—Pressure-Taking Pipe, 30—Pressure-Taking Seat, 31—Installation Hole for Pressure Measuring Assembly Protective Sleeve, 32—Pressure Measuring Assembly Protective Sleeve, 33—Installation Hole for Pressure Measuring Assembly. Embodiment

[0031] The present invention will now be described in further detail with reference to the accompanying drawings. These drawings are all simplified schematic diagrams, only illustrating the basic structure of the present invention in a schematic manner, so they only show the components related to the present invention.

[0032] As Figure 1 shown, the solid propellant pressure-reducing flameout device of the present invention can generally be understood as including three main parts, namely a combustion chamber assembly A and a film-breaking assembly B. The combustion chamber assembly A is an internally sealed combustion chamber, and the inside of the combustion chamber assembly A is the combustion space of the solid propellant. The film-breaking assembly B is used to extinguish the combustion in the combustion chamber assembly A, and the pressure measuring assembly C is used to detect the change in the pressure inside the combustion chamber during the flameout process.

[0033] Next, the structure of the combustion chamber assembly A will be specifically introduced: The combustion chamber assembly A includes a combustion chamber 6 in the shape of a circular tube that penetrates up and down. An annular thermal insulation layer 17 is laid on the inner wall of the combustion chamber 6, a front thermal insulation layer 15 is laid on the top of the combustion chamber 6, and a rear thermal insulation layer 16 is laid on the bottom. The annular thermal insulation layer 17, the front thermal insulation layer 15, and the rear thermal insulation layer 16 are all used to isolate high temperatures.

[0034] As Figure 2 Both ends of the combustion chamber are provided with flanges. The flange at the bottom is fixedly connected to the flange bottom cover 7 by bolts, and the transition flange 8 is fixedly connected to the front flange 5 by bolts. The flange bottom cover and the front flange cover are respectively opposite to the flange plates at the corresponding ends of the combustion chamber 6 and are fixedly connected and sealed by bolts evenly distributed in the circumferential direction. The transition flange 8 is provided with a threaded hole 11 for installing a film-breaker, a nozzle installation hole 12, and an installation hole 31 for a pressure measuring assembly protective sleeve. At the corresponding position of the installation hole 31 for the pressure measuring assembly protective sleeve on the front flange cover 5, a pressure measuring assembly installation hole 33 is provided. The pressure measuring assembly installation hole 33 is an internal thread structure and is used to install the pressure measuring assembly C.

[0035] AsFigure 4 An excessive flange 8 is provided at the top of the combustion chamber. The excessive flange 8 is provided with a film rupture device installation threaded hole 11 for the fixed installation of the film rupture device assembly. A vertical hole 26 is provided in the front flange 5 at the corresponding position of the film rupture device installation threaded hole 11. The bottom of the vertical hole is located in the front flange 5. A secondary nozzle expansion extension section 13 and a pressure relief glass 14 are fixedly arranged in the vertical hole 26. The secondary nozzle expansion extension section 13 is axially provided with holes, and the diameter gradually decreases from top to bottom to form a secondary nozzle 10. The lower end of the secondary nozzle 10 is provided with a pressure relief glass 14, and the pressure relief glass 14 seals the vertical hole 26. A pressure relief hole 25 coaxial with and penetrating the front flange cover 5 and the front thermal insulation layer 15 is provided below the vertical hole 26, as Figure 4 The flanges at both ends of the combustion chamber are sealed with the corresponding flange bottom cover 7 and front flange cover 5 through a sealing limit ring and the flange end face, and the connection is more compact.

[0036] As Figure 6 The film rupture assembly further includes a sliding cylinder 4, a tungsten copper infiltrated heat-resistant part 9 and a cylinder assembly 2. The periphery of the middle part of the tungsten copper infiltrated heat-resistant part 9 in the axial direction is provided with a rectangular groove for discharging the high-temperature and high-pressure gas ejected from the secondary nozzle 10. The upper end is connected to the sliding cylinder 4, and the lower end is connected to the film rupture device installation threaded hole 11; a movable inner sleeve 23 is arranged inside the sliding cylinder 4. The top of the impact pin 22 is connected to the center of the inner sleeve 23. A rectangular groove is provided on the side wall of the inner sleeve 23. The working end of the cylinder assembly 2 is fixedly connected to the piston rod 24. The other end of the piston rod 24, a long rod, is inserted into the rectangular groove on the side wall of the inner sleeve to resist the acting force of the energy storage spring 28 pressing tightly on the inner sleeve 23 and maintain the axial position of the inner sleeve 23. The cylinder assembly 2 is fixedly connected to the cylinder seat 1 through a threaded connection.

[0037] As Figure 8 The pressure measurement assembly C includes a pressure tapping seat 30, a pressure tapping pipe 29, a sensor seat 3, and a pressure measurement assembly protective sleeve 32. The two ends of the pressure tapping pipe 29 are welded with a pressure tapping seat 30 and a sensor seat 3. The head of the pressure tapping seat 30 is a threaded structure and is fixedly connected to the pressure measurement assembly installation hole 33 through a threaded connection. The pressure measurement assembly protective sleeve 32 is arranged outside the pressure tapping seat to protect the pressure measurement assembly from being damaged by high temperature.

[0038] The method for reducing the pressure and extinguishing the fire of the solid propellant includes the following steps:

[0039] Step 1: Place the solid propellant in the combustion chamber 6 and bond it to the rear thermal insulation layer 16 at the inner bottom of the combustion chamber 6;

[0040] Step 2: Use a high-energy laser to ignite the solid propellant through the central small hole of the main nozzle 19. Based on the physical and chemical properties of the solid propellant and the structure of the combustion chamber 6, the combustion chamber pressure in the combustion chamber 6 is jointly determined

[0041] Step 3: The cylinder assembly 2 of the membrane breaker assembly B pulls out the piston rod 24 horizontally. The piston rod 24 releases the axial limit on the inner sleeve 23. Under the action of the energy storage spring 28, the inner sleeve 23 drives the striker 22 to move downward rapidly and strike the pressure relief glass 14.

[0042] Step 4: The pressure relief glass 14 is penetrated, and the high-pressure gas in the combustion chamber 6 is immediately released through the secondary nozzle 10. The air pressure in the combustion chamber 6 drops sharply, the burning rate of the solid propellant decreases and the combustion stops.

[0043] Step 5: The pressure measurement assembly C records the pressure change during the whole experiment.

[0044] Currently, there are three types of extinguished states: 1. Instantaneous extinguishing after rapid pressure reduction; 2. Re-ignition after extinguishing due to pressure reduction; 3. Non-extinguishing all the time. This situation is mainly determined by the properties of the propellant. In this experimental device, the solid propellant is ignited by the central small hole of the main nozzle. The pressure change in the combustion chamber is observed through a pressure sensor. During the experiment, the release time of the energy storage spring is controlled according to a predetermined program to complete the pressure relief. The extinguishing characteristics under different pressures in the combustion chamber are analyzed. The pressure change during the whole extinguishing dynamic process is recorded during the experiment. After the experiment, the gas-phase and condensed-phase products after pressure relief and extinguishing are collected, as well as the surface morphology characteristics of the propellant after extinguishing. This experimental scheme is simple and feasible, can study the extinguishing characteristics of different propellants under different pressures, and has high popularization and application value.

[0045] Taking the above ideal embodiments of the present invention as an inspiration, through the above description, relevant staff can completely make various changes and modifications without departing from the technical idea of this invention. The technical scope of this invention is not limited to the content in the specification, and its technical scope must be determined according to the scope of the claims.

Claims

1. A solid propellant pressure-reducing and flame-extinguishing device, characterized in that: It includes a combustion chamber assembly (A), a membrane-breaking assembly (B), and a pressure-measuring assembly (C). There are 3 threaded holes at the top of the combustion chamber assembly (A). A main nozzle expansion extension section (20) is arranged in one threaded hole, a pressure-relief glass (14) is arranged in one threaded hole, and a pressure-taking seat (30) of the pressure-measuring assembly (C) is arranged in one threaded hole. A movable striker (22) is arranged inside the membrane-breaking assembly (B). The tip of the striker (22) faces the pressure-relief glass (14). The membrane-breaking assembly (B) controls the movement of the striker (22) to break the pressure-relief glass (14); The membrane-breaking assembly (B) further includes a sliding cylinder (4), a tungsten-impregnated copper heat-resistant part (9), and a cylinder assembly (2). Rectangular grooves are provided around the axial middle of the tungsten-impregnated copper heat-resistant part (9) to discharge the high-temperature and high-pressure gas ejected from the auxiliary nozzle (10). The upper end is connected to the sliding cylinder (4), and the lower end is fixed on the combustion chamber assembly (A) through a membrane-breaking device mounting threaded hole (11). An inner sleeve (23) that can move up and down along it is arranged inside the sliding cylinder (4). The top of the striker (22) is connected to the center of the inner sleeve (23). Rectangular grooves are provided on the side wall of the inner sleeve (23). The working end of the cylinder assembly (2) is fixedly connected to a piston rod (24). The other end of the piston rod (24) is inserted into the rectangular groove on the side wall of the inner sleeve (23) with a long rod to resist the force of the energy storage spring (28) pressing on the inner sleeve (23) and maintain the axial position of the inner sleeve (23). The cylinder assembly (2) is fixed on a cylinder seat (1).

2. The solid propellant pressure-reducing and flame-extinguishing device according to claim 1, characterized in that: The combustion chamber assembly (A) includes a combustion chamber (6). An annular heat-insulating layer (17) is pasted on the inner wall of the combustion chamber (6). Solid propellant (27) is installed in the combustion chamber (6). The upper end of the annular heat-insulating layer (17) is bonded to the front heat-insulating layer (15), and the lower end is bonded to the rear heat-insulating layer (16). The solid propellant (27) is bonded to the rear heat-insulating layer (16).

3. The solid propellant pressure-reducing and flame-extinguishing device according to claim 2, characterized in that: Flange plates are provided at both ends of the combustion chamber (6). The flange plates at the corresponding ends of the combustion chamber (6) are respectively connected to a flange bottom cover (7) and a front flange cover (5). The flange plate at the bottom of the combustion chamber (6) is connected to the flange bottom cover (7) through bolts. The top of the combustion chamber (6) is connected to the front flange cover (5) and a transition flange plate (8) in sequence from the inside to the outside and is connected through a plurality of bolts passing through.

4. The solid propellant pressure-reducing and flame-extinguishing device according to claim 3, characterized in that: The membrane rupture device mounting threaded hole (11) is opened on the transition flange (8). The transition flange (8) is also provided with a nozzle mounting threaded hole (12) and a pressure measurement component protective sleeve mounting hole (31). At the corresponding position of the nozzle mounting threaded hole (12) on the front flange cover (5), a main nozzle expansion extension section (20) is provided. The main nozzle expansion extension section (20) is bonded to the main nozzle (19). The lower surface of the main nozzle (19) is bonded to the main nozzle convergent extension section (21). At the corresponding position of the main nozzle convergent extension section (21), the front heat insulation layer (15) is perforated and communicates with the combustion chamber (6) inside. The channel diameter after the docking of the main nozzle expansion extension section (20) and the main nozzle convergent extension section (21) first converges and then expands from top to bottom. At the corresponding position of the pressure measurement component protective sleeve mounting hole (31) on the front flange cover (5), a pressure measurement component mounting hole (33) is provided. The pressure measurement component mounting hole (33) is an internal thread structure for installing the pressure measurement component (C).

5. The solid propellant pressure reduction and flameout device according to claim 4, characterized in that: At the corresponding position of the membrane rupture device mounting threaded hole (11) on the front flange cover (5), a vertical hole (26) is provided. The bottom of the vertical hole (26) is located in the front flange cover (5). A secondary nozzle expansion extension section (13) and a pressure relief glass (14) are fixedly arranged in the vertical hole. The secondary nozzle expansion extension section (13) has an axial hole, and the diameter gradually decreases from top to bottom to form a secondary nozzle (10). The pressure relief glass (14) is located at the lower end of the secondary nozzle (10) and the inner bottom of the vertical hole, and blocks the vertical hole (26). A pressure relief hole (25) coaxial with the vertical hole (26) and passing through the front flange cover (5) and the front heat insulation layer (15) is provided below the vertical hole (26). The secondary nozzle expansion extension section (13) is screwed into the front flange cover (5) and presses the pressure relief glass (14) against the front flange cover (5).

6. The solid propellant pressure reduction and flameout device according to claim 3, characterized in that: The flanges at both ends of the combustion chamber (6) are sealed with the corresponding flange bottom cover (7) and front flange cover (5) through a sealing limit ring (18) and the flange end face.

7. The solid propellant pressure reduction and flameout device according to claim 3, characterized in that: The pressure measurement component (C) includes a pressure tapping seat (30), a pressure tapping pipe (29), a sensor seat (3) and a pressure measurement component protective sleeve (32). The lower part of the pressure tapping pipe (29) is vertically downward, and the lower end of the pressure tapping pipe (29) is the pressure tapping end, which is connected to the pressure tapping seat (30). The upper part of the pressure tapping pipe (29) is vertically arc-bent to a horizontal state, and the upper end of the pressure tapping pipe (29) is the pressure measurement end, which is connected to the sensor seat (3). The pressure measurement component protective sleeve (32) is sleeved outside the pressure tapping seat (30) and the pressure tapping seat (30) and fixedly connects them. The lower end of the pressure tapping seat (30) is provided with an external thread and is fixedly connected to the pressure measurement component mounting hole (33) through a threaded connection. The pressure measurement component protective sleeve (32) is arranged outside the pressure tapping seat.

8. The solid propellant pressure reduction and flameout method, characterized in that: The method is based on the solid propellant pressure-reducing flameout device described in any one of the above-mentioned claims 1-7, and includes the following steps: Step 1: Place the solid propellant in the combustion chamber (6) and bond it to the rear insulation layer (16) at the bottom inside the combustion chamber (6); Step 2: Use a high-energy laser to ignite the solid propellant through the central small hole of the main nozzle (19). Based on the physical and chemical properties of the solid propellant and the structure of the combustion chamber (6), the pressure inside the combustion chamber (6) is jointly determined; Step 3: The cylinder assembly (2) of the membrane-breaking assembly (B) pulls out the piston rod (24) in the horizontal direction. The piston rod (24) releases the axial limit on the inner sleeve (23). The inner sleeve (23) drives the striker (22) to move quickly downward under the action of the energy storage spring (28) and strikes the pressure relief glass (14); Step 4: The pressure relief glass (14) is penetrated, and the high-pressure gas inside the combustion chamber (6) is immediately discharged through the secondary nozzle (10). The air pressure inside the combustion chamber (6) drops sharply, the burning rate of the solid propellant decreases and the flame goes out; Step 5: The pressure measurement assembly (C) records the pressure change during the whole experiment process.

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