A device for visualizing solid propellant high-pressure combustion turbulence and its use method

Abstract

A visual solid propellant high-pressure combustion turbulence device and a method for use thereof relate to the technical field of solid propellant high-pressure combustion devices. The high-pressure combustion turbulence device comprises a visual high-pressure combustion chamber, a particle filter, an electric heating wire ignition system, a combustion turbulence device, a flow channel controller, and a powder rod clamp; the powder rod clamp is used to fix the solid propellant powder rod and reduce the shaking of the solid propellant powder rod; gas is introduced into the high-pressure combustion chamber to create different environmental pressures. After the electric heating wire ignites the solid propellant, the combustion phenomenon is observed through four mutually perpendicular visual windows; the flow channel controller can prevent the combustion condensed phase particles carried by the airflow generated by the adjustable speed fan from affecting the observation range of the window, and finally the condensed phase particles are filtered through the particle filter to purify the internal circulating flow gas. The device of the present invention has a reasonable structure and is stable and reliable. It can effectively solve the problem that smoke particles are detrimental to the observation of the combustion phenomenon during solid propellant combustion.

Description

Technical Field

[0001] The present invention relates to the technical field of solid propellant high-pressure combustion devices, and more particularly to a visual solid propellant high-pressure combustion turbulence device and a method for using the device. Background Art

[0002] Solid propellant technology is a common, supporting, and pioneering technology for contemporary missile weapons and aerospace engineering, forming a solid foundation for my country's national defense. The energy source for solid-powered vehicles is inherently high-energy solid propellants, energetic composite materials composed of an oxidizer, a fuel, a binder, and functional additives. During combustion, energy and gaseous combustion products are released to power solid rocket engines, making them widely used in aerospace, missile, and other fields. The combustion performance of solid propellants determines the rate of gaseous release and energy, which in turn affects the payload capacity, flight time, and range of an aircraft, ultimately determining the penetration capability and combat effectiveness of strategic and tactical weapons.

[0003] When solid propellants burn inside an engine, they are accompanied by high-temperature and high-pressure environmental conditions, making it difficult to observe the specific phenomena during combustion. To address this problem, a solid propellant powder combustion experiment is conducted in a closed high-pressure container to simulate its combustion inside a solid engine. By opening a high-pressure transparent combustion window around the closed high-pressure combustion chamber, the measuring instrument can easily observe the combustion phenomenon of the solid propellant in the high-pressure combustion chamber. However, when solid propellants burn, the smoke formed by the metal combustion condensed phase particles and the coke particles produced by the incomplete combustion of organic matter will enter the observation field due to diffusion and turbulence, thereby affecting the observation of the combustion phenomenon. In order to observe the combustion phenomenon of solid propellants inside a closed container clearly for a long time without being affected by the particle turbulence on the observation field, a visual solid propellant high-pressure combustion turbulence device is proposed. Summary of the Invention

[0004] To address at least one of the aforementioned and other technical issues in the prior art, the present invention provides a device for visualizing high-pressure solid propellant combustion turbulence. Its primary purpose is to provide clean, internally circulating gas within the high-pressure combustion chamber, entraining and eliminating smoke particles generated by combustion, effectively addressing the problem of smoke particles interfering with combustion observation. The device, with its rational structure, stability, and reliability, is suitable for observing combustion phenomena in a variety of solid propellant types.

[0005] The present invention also provides a method for using a device for visualizing high-pressure combustion turbulence of solid propellants.

[0006] The technical solution of the present invention is achieved through the following measures:

[0007] A visual solid propellant high-pressure combustion turbulence device comprises a visual high-pressure combustion chamber, a particle filter device, an electric heating wire ignition system, a combustion turbulence device, a flow channel controller and a powder rod clamp; the powder rod clamp is used to fix the solid propellant powder rod to prevent it from tipping over during the combustion process and reduce the shaking of the solid propellant powder rod; gas is introduced into the high-pressure combustion chamber to create different environmental pressures, and after the propellant ignition wire ignites the solid propellant, the combustion phenomenon is observed through four mutually perpendicular visual windows; the flow channel controller can prevent the combustion condensed phase particles carried by the airflow generated by the adjustable speed fan system from affecting the window observation range, and finally the condensed phase particles are filtered through the particle filter device to purify the internal circulating flow gas.

[0008] According to an embodiment of the present disclosure, the rotation of the blades of the adjustable-speed fan forms an internal circulating flow gas inside the high-pressure combustion chamber.

[0009] According to an embodiment of the present disclosure, the above-mentioned adjustable speed fan system can adjust the gas flow rate and carry the condensed phase products generated by the combustion of the solid propellant.

[0010] According to an embodiment of the present disclosure, the porous air distribution plate stabilizes the airflow generated by the blades of the adjustable-speed fan.

[0011] According to an embodiment of the present disclosure, the porous air distribution plate is fixed to the adjustable speed fan system placement platform to prevent the airflow generated by the adjustable speed fan from blowing the powder strip clamp platform, causing the solid propellant powder strip to shake, thereby affecting the observation of combustion phenomena. The adjustable speed fan system placement platform includes a cylinder, and a circle of annular positioning bosses are arranged at the lower end of the cylinder. The upper surface B of the annular positioning bosses is used to position the blade support parts of the adjustable speed fan system. The outer ring surface A of the annular positioning bosses cooperates with the inner ring of the punched filter mesh tube for positioning. The outer wall of the lower end of the cylinder has a radially outward extending mounting plate, which is mounted on the lower flange end cover via a support rod and a platform fixing nut. The upper end of the cylinder has a groove for positioning the porous air distribution plate.

[0012] The porous air distribution plate includes a circular disk, the inner ring of which has a small cylinder for placing a medicine strip clamp extending axially for placing a clamp platform, a plurality of gas uniform circulation holes distributed on the circular disk, and the edge of the circular disk has more than two bosses that cooperate with the grooves.

[0013] According to an embodiment of the present disclosure, the flow channel controller divides the circulation return channel into four gas circulation channels. The flow channel controller is located above the visualization window; the flow channel controller includes an annular cylinder, the central cavity of the annular cylinder is the central circulation channel, and the annular cylinder wall is composed of a plurality of flow channel controller recesses and flow channel controller protrusions arranged alternately in sequence; the flow channel controller recesses form circulation return flow channels, and each circulation return flow channel is connected to the central circulation channel; the flow channel controller protrusions are used to change the flow direction of the internal circulation gas, and the interior of the flow channel controller protrusions is a hollow trough for weight reduction. The bottom of the flow channel controller protrusions has a recess for making way for the visualization window, and the axis of the recess corresponds to the axis of each visualization window.

[0014] According to an embodiment of the present disclosure, the above-mentioned internal circulating flow gas adjusts the airflow area through the flow channel controller after hitting the upper flange end cover of the high-pressure combustion chamber, so as to avoid the particles carried by the internal circulating flow gas from causing an impact within the observation field of view.

[0015] According to an embodiment of the present disclosure, after the internal circulating flow gas carrying condensed phase particles passes through the particle filtering device, the particles are retained on the high temperature resistant activated carbon filter cotton, while the clean gas continues the internal circulating flow process.

[0016] According to an embodiment of the present disclosure, the above-mentioned high-temperature resistant activated carbon filter cotton needs to be supported by a punched filter mesh tube.

[0017] According to an embodiment of the present disclosure, the above-mentioned electric heating wire ignition electrode, powder rod clamp, combustion turbulence device, flow channel controller and particle filter device are all installed inside the high-pressure combustion chamber.

[0018] According to the high-pressure combustion device provided by the present invention, a solid propellant strip is ignited by a propellant ignition wire connected to an electric heating wire ignition electrode, and the solid propellant strip burns vertically downward. The rotation of the above-mentioned adjustable-speed fan blades generates an internal circulating flow gas that carries away the condensed phase particles generated by the combustion of the solid propellant, thereby weakening the impact of the turbulence of the condensed phase particles of the local combustion jet or the backflow of the combustion gaseous products on the observation field of view; the constructed flow channel controller is placed above the observation field of view and can be used to change the gas flow channel that flows in the opposite direction after impacting the upper cover plate, so that the combustion condensed phase products carried by the airflow do not pass through the observation field of view area when flowing, thereby avoiding affecting the instrument when observing the combustion phenomenon; when the refluxed gas mixed with the combustion condensed phase products passes through the high-temperature resistant activated carbon filter cotton in the particle filter device, the particulate matter is retained, and the gas can pass smoothly and continue to circulate internally, so that the entire combustion chamber is filled with gaseous phase combustion products, which is closer to the combustion condition of the solid propellant column inside a real solid rocket engine.

[0019] A method for using a visual solid propellant high-pressure combustion turbulence device. During use, a visual high-pressure combustion chamber is placed on an experimental platform and fixed, an ignition electrode terminal is connected to an external control voltage, and a reserved port for a fan motor connection line is connected to an electric wire and sealed; the electromagnetic control valve at the combustion chamber air outlet is in an open state, and the electromagnetic control valve at the combustion chamber air inlet is in a closed state; the upper flange end cover of the visual high-pressure combustion chamber is opened, and the sealed visual high-pressure combustion chamber is in an open state;

[0020] Insert the high temperature resistant activated carbon filter cotton into the punched filter mesh tube to form a particle filter device, and place the particle filter device in the middle of the lower flange end cover;

[0021] When installing the combustion turbulence device, place the adjustable-speed fan system inside the adjustable-speed fan system placement platform, with the small cylinder of the porous air distribution plate's medicine strip fixture on top for installation. Then, slightly rotate the porous air distribution plate counterclockwise so that the protruding bosses on both sides can fit into the grooves in the adjustable-speed fan system placement platform to prevent the airflow generated by the adjustable-speed fan system from fluctuating on the porous air distribution plate.

[0022] The combustion turbulence device is placed above the particle filter device. The lower end surface of the adjustable speed fan system placement platform is provided with an annular positioning boss. The axis of the annular positioning boss is installed to coincide with the axis of the punched filter mesh tube, ensuring that the outer ring surface A is closely fitted with the inner wall surface of the punched filter mesh tube; the adjustable speed fan system placement platform is installed on the support rod of the adjustable speed fan system support platform, and then the platform fixing nut is tightened to ensure that the lower end surface of the adjustable speed fan system support platform is in close contact with the upper end surface of the high-temperature resistant activated carbon filter cotton, and the lower end surface of the high-temperature resistant activated carbon filter cotton is in close contact with the lower flange end cover, thereby preventing the condensed phase particles generated by the combustion of the solid propellant powder from flowing in the gap between the contact surfaces;

[0023] Pass the propellant ignition wire through the upper end of the solid propellant strip so that the solid propellant strip is located in the middle of the propellant ignition wire. Place the solid propellant strip between the fixed clip and the movable clip on the fixture platform and clamp the solid propellant strip with the strip fastening bolts. Place the solid propellant strip and the fixture holding the solid propellant strip in the small cylinder of the strip fixture above the porous air distribution plate in the combustion turbulence device. Adjust the position of the strip and the fixture so that the largest surface of the solid propellant strip is aligned with the observation field of view.

[0024] Tightly wind the two ends of the propellant ignition wire around the heating wire ignition electrode; place the flow channel controller on the flow channel controller placement boss, and rotate and adjust the flow channel controller so that the axis of the recessed portion corresponds to the axis of each visualization window without affecting the observation field of view; use the upper flange end cover bolts and upper flange end cover nuts to ensure close contact between the combustion chamber upper flange end cover and the combustion chamber cavity to prevent gas leakage when under pressure. During installation, the upper flange end cover handle is outside the high-pressure combustion chamber;

[0025] Close the electromagnetic control valve at the combustion chamber outlet, open the electromagnetic control valve at the combustion chamber inlet, introduce high-pressure gas into the visualized high-pressure combustion chamber, monitor the pressure inside the combustion chamber using a pressure sensor until the set pressure value is reached, close the electromagnetic control valve at the combustion chamber inlet, and maintain no gas leakage for 30 seconds; turn on the adjustable speed fan system and set the required speed; energize the propellant ignition wire to ignite the solid propellant pellets, and use external instruments and equipment to observe the phenomena accompanying the combustion process of the solid propellant pellets;

[0026] After the solid propellant powder is burned, the adjustable speed fan system is continuously operated for no less than 2 minutes to allow all the condensed phase particles generated by the burning of the solid propellant powder to be adsorbed on the high-temperature resistant activated carbon filter cotton. The adjustable speed fan system is then shut down and the electromagnetic control valve at the combustion chamber outlet is opened to discharge the high-pressure gas in the combustion chamber.

[0027] When the gas pressure in the visualized high-pressure combustion chamber is consistent with the external environmental pressure, open the upper flange end cover of the visualized high-pressure combustion chamber, take out the flow channel controller, then take out the fixture platform of the solid propellant strip, clamp it again to prepare a new solid propellant strip sample, and repeat the measurement; to measure multiple solid propellant strip combustion experiments, it is necessary to replace the high-temperature resistant activated carbon filter cotton, take out the flow channel controller, then take out the fixture platform of the solid propellant strip, remove the platform fixing nut, then take out the combustion turbulence device, and finally take out the particle filter device, replace it with a new high-temperature resistant activated carbon filter cotton, and re-install it in sequence to complete multiple solid propellant strip combustion phenomenon observation experiments.

[0028] The device of the present invention has a reasonable and compact structure and an ingenious design. By designing a gas flow channel with a fixed shape, the influence of condensed phase smoke particles produced by the combustion of solid propellant carried by the internal circulating flow gas in the high-pressure combustion chamber on the observation of combustion phenomena is avoided; a particle filtering device is used to remove condensed phase particle products, and the clean gas phase combustion products make the combustion of solid propellant closer to the combustion environment inside the solid rocket engine; the device is stable and reliable, can be easily disassembled and maintained, and has a low cost, and can be applied to the observation experiment of high-pressure combustion phenomena of solid propellant under any formula. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] These and / or other aspects and advantages of the present invention will become more apparent and more readily understood from the following detailed description of embodiments of the present invention in conjunction with the accompanying drawings, in which:

[0030] Figure 1 It is a cross-sectional view of the structure of the present invention;

[0031] Figure 2 for Figure 1 Visualized high-pressure combustion chamber structure cross-sectional view;

[0032] Figure 3 for Figure 1 A cross-sectional view of the particle filter structure;

[0033] Figure 4 for Figure 1 A cross-sectional view of the combustion turbulence device structure;

[0034] Figure 5 for Figure 1 Cross-sectional view of the platform structure for placing the adjustable speed fan system;

[0035] Figure 6 for Figure 1 Schematic diagram of the adjustable speed fan system structure;

[0036] Figure 7 for Figure 1 Schematic diagram of the porous air distribution plate structure;

[0037] Figure 8 for Figure 1 Schematic diagram of the medicine strip and fixture structure;

[0038] Figure 9 for Figure 1 Schematic diagram of the flow channel controller structure;

[0039] In the drawings, the meanings of the reference numerals are as follows:

[0040] 101 is the handle of the upper flange end cover; 102 is the temperature sensor; 103 is the bolt of the upper flange end cover; 104 is the pressure sensor; 105 is the upper flange end cover of the combustion chamber; 106 is the nut of the upper flange end cover; 107 is the combustion chamber cavity; 108 is the observation window cover; 109 is the boss for placing the flow channel controller; 110 is the transparent observation window; 111 is the observation window bolt; 112 is the observation window nut; 113 is the electromagnetic control valve for the combustion chamber air inlet; 114 is the reserved port for the fan motor connection line; 115 is the nut of the lower flange end cover; 116 is the bolt of the lower flange end cover; 117 is the lower flange end cover of the combustion chamber; 118 is the electromagnetic control valve for the combustion chamber air outlet;

[0041] 201 is the ignition electrode terminal; 202 is the heating wire ignition electrode;

[0042] 301 is high-temperature resistant activated carbon filter cotton; 302 is a punched filter mesh tube; 303 is a fan motor; 304 is a platform support rod; 305 is a platform fixing nut; 306 is an adjustable-speed fan blade; 307 is a platform for placing an adjustable-speed fan system; 308 is a blade support part; 309 is a porous air distribution plate; 310 is a fixture platform; 311 is a pill strip fastening bolt; 312 is a movable clip; 313 is a solid propellant pill strip; 314 is a fixed clip; 315 is a mounting plate; 316 is an annular positioning boss; 317 is a cylinder; 318 is a groove; 319 is a boss; 320 is a circular disk; 321 is a gas uniform flow hole; 322 is a small cylinder for the pill strip fixture;

[0043] 401 is the propellant ignition wire;

[0044] 501 is a flow channel controller; 502 is a central flow channel; 503 is a concave portion of the flow channel controller; 504 is a convex portion of the flow channel controller; 505 is a hollow tank body; and 506 is a recessed portion for clearance. DETAILED DESCRIPTION

[0045] In order to make the purpose, technical solution and advantages of this embodiment clearer, the technical solution is described in more detail below in combination with specific embodiments and with reference to the accompanying drawings.

[0046] In this embodiment, for the convenience of description, the relative position relationship of each component is described based on the Figure 1 The positional relationships of front, back, top, bottom, left, and right are described in the layout of the manual. Figure 1 The layout direction is determined by the

[0047] In the description of this embodiment, unless otherwise clearly defined, terms such as setting, installing, and connecting should be understood in a broad sense, and technicians in the relevant technical field can reasonably determine the specific meanings of the above terms in this embodiment based on the specific content of the technical solution.

[0048] The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present invention. The present embodiments are described in detail below with reference to the accompanying drawings:

[0049] Attachment Figure 1 It is a schematic cross-sectional view of the overall structure of the visualized solid propellant high-pressure combustion turbulence device according to this embodiment, including a visualized high-pressure combustion chamber, a heating wire ignition system, a particle filtering device, a combustion turbulence device, a flow channel controller 501, and a propellant clamp.

[0050] Attachment Figure 2It is a cross-sectional view of the structure of a visualized high-pressure combustion chamber. The visualized high-pressure combustion chamber is a closed container. The combustion chamber cavity 107 and the combustion chamber lower flange end cover 117 are connected and fastened with the lower flange end cover bolts 116 and the lower flange end cover nuts 115; the combustion chamber cavity 107 and the combustion chamber upper flange end cover 105 are connected and fastened with the upper flange end cover bolts 103 and the upper flange end cover nuts 106; a flow channel controller placement boss 109 is provided in the middle position of the combustion chamber cavity 107 for placing the flow channel controller 501; four mutually perpendicular visualization windows are opened in the middle position of the combustion chamber cavity 107; the visualization window is formed by the observation window cover 108 between the observation window bolts 111 and the observation window The transparent observation window piece 110 is compressed by the connection and tightening action of the measuring window nut 112; the lower part of the combustion chamber cavity 107 is connected to the combustion chamber air inlet solenoid valve controller 113, and the combustion chamber air outlet solenoid valve controller 118 is connected to it at the opposite position, and a reserved opening 114 for the fan motor connection line is left in the vertical direction of the air inlet and air outlet axes; a temperature sensor 102 and a pressure sensor 104 are set on the upper part of the combustion chamber upper flange end cover 105; the lower flange end cover 117 is reserved with a small hole for installing the heating wire ignition electrode 202, and the support rods 304 of the three adjustable speed fan system support platforms are evenly welded on the lower flange end cover 117 in a 120° direction.

[0051] Attachment Figure 3 It is a cross-sectional view of the particle filter structure. The particle filter device consists of two parts, namely, high-temperature resistant activated carbon filter cotton 301 and punched filter mesh tube 302. The high-temperature resistant activated carbon filter cotton 301 is sleeved on the outside of the punched filter mesh tube 302 which has a supporting function.

[0052] Attachment Figure 4 This is a cross-sectional view of the combustion turbulence device structure. Figures 5 to 7 They are schematic diagrams of the component structures of the combustion turbulence device, namely, an adjustable-speed fan system placement platform 307, an adjustable-speed fan system and a porous air distribution plate 309; the adjustable-speed fan system includes a fan motor 303, adjustable-speed fan blades 306 and blade support parts 308; after the adjustable-speed fan system is installed inside the adjustable-speed fan system placement platform 307, the porous air distribution plate 309 is placed on the upper part of the adjustable-speed fan system placement platform 307 and can be rotated slightly to prevent the motor fan airflow from affecting the porous air distribution plate 309.

[0053] Figure 5In the figure, the adjustable speed fan system placement platform 307 includes a cylinder 317, and a circle of annular positioning bosses 316 are arranged at the lower end of the cylinder 317. The upper surface B of the annular positioning bosses 316 is used to position the fan blade support parts 308 of the adjustable speed fan system. The outer ring A of the annular positioning bosses 316 cooperates with the inner ring of the punched filter mesh tube 302 for positioning. The outer wall of the lower end of the cylinder has a radially outward extending mounting plate 315, and the mounting plate 315 is mounted on the lower flange end cover 117 through the support rod 304 and the platform fixing nut 305; the upper end of the cylinder 317 has a groove 318 for positioning the porous air distribution plate 309.

[0054] Figure 6 In the figure, the adjustable speed fan system includes a fan motor 303, adjustable speed fan blades 306 and blade supporting parts 308; the adjustable speed fan blades 306 are placed in the blade supporting parts 308, and the fan motor 303 is placed at the lower part of the blade supporting parts 308.

[0055] Figure 7 In the figure, the porous air distribution plate 309 includes a circular disk 320, the inner ring of which has a small cylinder 322 for placing a medicine strip clamp extending axially for placing a clamp platform, and a plurality of gas uniform circulation holes 321 are distributed on the circular disk. The edge of the circular disk 320 has more than two bosses 319 that cooperate with the groove 318.

[0056] Attachment Figure 8 Schematic diagram of the propellant strip and fixture structure, including a fixture platform 310, a fixed clip 314, a movable clip 312, and a strip fastening bolt 311 for clamping a solid propellant strip 313 mounted between the fixed clip 314 and the movable clip 312. On the fixture platform 310, the strip fastening bolt 311 and the movable clip 312 are used to clamp the solid propellant strip 313 of a fixed length and shape to prevent shaking and tipping during the combustion of the solid propellant.

[0057] Attachment Figure 9 This is a structural diagram of the flow channel controller 501, the flow channel controller 501 is placed above the flow channel controller placement boss 109; the flow channel controller 501 is located above the visualization window; the flow channel controller 501 includes an annular cylinder, the middle cavity of the annular cylinder is the central circulation channel 502, and the annular cylinder wall is composed of multiple flow channel controller recesses 503 and flow channel controller protrusions 504 that are alternately arranged in sequence; the flow channel controller recesses 503 form a circulating return flow channel, and each circulating return flow channel is connected to the central circulation channel 502; the flow channel controller protrusions 504 are used to change the flow direction of the internal circulating gas, and the internal hollow groove body 505 reduces the weight of the flow channel controller, and there is a clearance recess 506 at the bottom of the protrusion 504 for making way for the visualization window, and the axis of the clearance recess 506 corresponds to the axis of each visualization window to avoid particulate matter entrained by the airflow in the circulation channel from affecting the observation.

[0058] During use, the visualized high-pressure combustion chamber is placed on the experimental platform and fixed, the ignition electrode terminal 201 is connected to the external control voltage, the fan motor connection line reserved port 114 is connected to the wire and sealed; the combustion chamber air outlet electromagnetic control valve 118 is in the open state, and the combustion chamber air inlet electromagnetic control valve 113 is in the closed state; the upper flange end cover 105 of the visualized high-pressure combustion chamber is opened, and the sealed high-pressure combustion chamber is in the open state.

[0059] Place the adjustable speed fan system inside the adjustable speed fan system placement platform 307, so that the small cylinder 319 of the porous air distribution plate 309 is on the top for installation, and then rotate the porous air distribution plate 309 slightly counterclockwise so that the protruding bosses 321 on both sides can enter the pits in the adjustable speed fan system placement platform 307 to achieve fit, thereby preventing the airflow generated by the adjustable speed fan system from causing fluctuations in the porous air distribution plate 309.

[0060] The high temperature resistant activated carbon filter cotton 301 is inserted into the punched filter mesh tube 302 to form a particle filter device, and the particle filter device is placed in the middle position of the lower flange end cover 117.

[0061] The combustion turbulence device is placed above the particle filter device, and the lower end surface of the adjustable speed fan system placement platform 307 has a boss structure (i.e., an annular positioning boss 316), which ensures that the adjustable speed fan system placement platform 307 can closely cooperate with the punched filter mesh tube 302; the adjustable speed fan system placement platform 307 is installed on the support rod 304 of the adjustable speed fan system support platform, and then the platform fixing nut 305 is tightened to ensure that the lower end surface of the adjustable speed fan system support platform 307 is in close contact with the upper end surface of the high temperature resistant activated carbon filter cotton 301 and the lower end surface of the high temperature resistant activated carbon filter cotton 301 is in close contact with the lower flange end cover 117, so as to prevent the condensed phase particles generated by the combustion of the solid propellant powder from flowing in the gap of the contact surface.

[0062] Cut a solid propellant strip 313 with a thickness of 3 mm, a width of 10 mm, and a length of 40 mm. Pass the propellant ignition wire 401 through the upper end of the solid propellant strip 313 so that the solid propellant strip 313 is in the middle of the propellant ignition wire 401. Place the solid propellant strip 313 on the clamp platform 310 and clamp the solid propellant strip 313 with the strip fastening bolt 311 and the movable clamp 312. Place the solid propellant strip 313 and the clamp holding the solid propellant strip 313 in the small cylinder 319 above the porous air distribution plate 309 in the combustion turbulence device. Adjust the position of the strip and the clamp so that the largest surface of the solid propellant strip is aligned with the observation line.

[0063] Wrap the two ends of the propellant ignition wire 401 around the heating wire ignition electrode 202 respectively; place the flow channel controller 501 on the flow channel controller placement boss 109, and rotate and adjust the flow channel controller 501 so that it does not affect the observation field of view; use the upper flange end cover bolts 103 and the upper flange end cover nuts 106 to make the combustion chamber upper flange end cover 105 in close contact with the combustion chamber cavity 107. During the installation process, the upper flange end cover handle 101 is on the outside of the high-pressure combustion chamber.

[0064] Close the combustion chamber air outlet electromagnetic control valve 118, open the combustion chamber air inlet electromagnetic control valve 113, introduce high-pressure gas into the visualized high-pressure combustion chamber, use the pressure sensor 104 to monitor the pressure inside the combustion chamber until the set pressure value is reached, close the combustion chamber air inlet electromagnetic control valve 113, and maintain no gas leakage for 30 seconds; turn on the adjustable speed fan system and set the required speed; energize the propellant ignition wire 401 to ignite the solid propellant strip 313, and use external instruments and equipment to observe the phenomena accompanying the combustion process of the solid propellant strip 313.

[0065] After the solid propellant pellets 313 are burned, the adjustable-speed fan system is continuously operated for 3 minutes to allow all the condensed phase particles generated by the combustion of the solid propellant pellets 313 to be adsorbed on the high-temperature resistant activated carbon filter cotton 301. The adjustable-speed fan system is then shut down, and the electromagnetic control valve 118 at the combustion chamber outlet is opened to discharge the high-pressure gas in the combustion chamber.

[0066] When the gas pressure in the combustion chamber is consistent with the external environmental pressure, open the upper flange end cover 105 of the visualized high-pressure combustion chamber, take out the flow channel controller 501, then take out the solid propellant strip clamp platform 310, clamp it again to prepare a new solid propellant strip 313 sample, and repeat the measurement; to measure multiple solid propellant strip 313 combustion experiments, it is necessary to replace the high-temperature resistant activated carbon filter cotton 301, take out the flow channel controller 501, then take out the solid propellant strip clamp platform 310, remove the platform fixing nut 305, then take out the combustion turbulence device, and finally take out the particle filter device, replace it with a new high-temperature resistant activated carbon filter cotton 301, and re-install it in sequence to complete multiple solid propellant strip 313 combustion phenomenon observation experiments.

Claims

1. A device for visualizing solid propellant high-pressure combustion turbulence, characterized in that: The invention comprises a visual high-pressure combustion chamber, a particle filter device, a combustion turbulence device, a flow channel controller (501), and a medicine strip clamp; the visual high-pressure combustion chamber comprises a combustion chamber cavity (107), a plurality of visual windows are provided on the side of the combustion chamber cavity (107), the combustion chamber cavity (107) is equipped with a particle filter device, a combustion turbulence device placed above the particle filter device, a medicine strip clamp for fixing a solid propellant medicine strip (313), and a flow channel controller (501); The upper end of the combustion chamber cavity (107) is provided with an upper flange end cover (105), the lower end of the combustion chamber cavity (107) is provided with a lower flange end cover (117), and the particle filter device is placed in the middle of the lower flange end cover (117); The combustion turbulence device includes an adjustable speed fan system, an adjustable speed fan system placement platform (307), and a porous air distribution plate (309); The adjustable speed fan system placement platform (307) includes a cylinder (317), a ring-shaped positioning boss (316) for positioning the adjustable speed fan system and the particle filter device is provided at the lower end of the cylinder (317), and a mounting plate (315) extending radially outward is provided on the outer wall of the lower end of the cylinder. The mounting plate (315) is mounted on the lower flange end cover (117) via a support rod (304) and a platform fixing nut (305); a groove (318) for positioning the porous air distribution plate (309) is provided at the upper end of the cylinder (317); The porous air distribution plate (309) includes a circular disk (320), the inner ring of which has a small medicine strip clamp cylinder (322) extending axially for placing a clamp platform, a plurality of gas uniform circulation holes (321) distributed on the circular disk, and an edge of the circular disk (320) has two or more bosses (319) that cooperate with the grooves (318); The flow channel controller (501) is located above the visualization window; the flow channel controller (501) includes an annular column, the central cavity of the annular column is a central circulation channel (502), and the annular column wall is composed of a plurality of flow channel controller recesses (503) and flow channel controller protrusions (504) arranged alternately in sequence; the flow channel controller recesses (503) form a circulation return flow channel, and each circulation return flow channel is connected to the central circulation channel (502); the flow channel controller protrusion (504) is used to change the flow direction of the internal circulation gas, and the interior of the flow channel controller protrusion (504) is a hollow groove body (505) for reducing weight, and the bottom of the flow channel controller protrusion (504) is provided with a clearance recess (506) for making way for the visualization window, and the axis of the clearance recess (506) corresponds to the axis of each visualization window.

2. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 1, characterized in that: The invention also includes a heating wire ignition system for igniting the solid propellant strip (313), wherein the heating wire ignition system includes a propellant ignition wire (401), a heating wire ignition electrode (202) connected to the propellant ignition wire (401), and an ignition electrode terminal (201) connected to the heating wire ignition electrode (202); the propellant ignition wire (401) passes through the upper end of the solid propellant strip (313), and the two ends of the propellant ignition wire (401) are respectively wound around the heating wire ignition electrode (202), the heating wire ignition electrode (202) is fixed to the inner end of the lower flange end cover (117), and the ignition electrode terminal (201) of the heating wire ignition electrode (202) is placed outside the lower flange end cover (117) and is connected to an external control voltage.

3. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 2, characterized in that: The medicine strip clamp comprises a clamp platform (310), on which are provided a fixed clamp (314), a movable clamp (312), and a medicine strip fastening bolt (311) for clamping a solid propellant medicine strip (313) mounted between the fixed clamp (314) and the movable clamp (312); the clamp platform (310) is placed in a medicine strip clamp small cylinder (322) above a porous air distribution plate (309) in a combustion turbulence device, and a flange at the upper end of the clamp platform (310) is positioned at the barrel mouth of the medicine strip clamp small cylinder (322) above the porous air distribution plate (309).

4. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 3, characterized in that: A flow channel controller placement boss (109) is provided in the middle of the inner wall of the combustion chamber cavity (107). The flow channel controller placement boss (109) is an annular structure composed of a plurality of arcuate boss segments arranged in an annular pattern. A space is provided between two adjacent arcuate boss segments for accommodating a visualization window.

5. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 4, characterized in that: The combustion chamber cavity (107) has an air inlet and an air outlet at the lower part, a combustion chamber air inlet solenoid valve controller (113) is installed at the air inlet, and a combustion chamber air outlet solenoid valve controller (118) is installed at the air outlet, and a fan motor connection line reserved opening (114) is left in the vertical direction of the air inlet and the air outlet axis; a temperature sensor (102) and a pressure sensor (104) are set on the upper part of the combustion chamber upper flange end cover (105); a small hole is reserved in the lower flange end cover (117) for installing an electric heating wire ignition electrode (202), and three support rods (304) of the adjustable speed fan system support platform are evenly welded to the lower flange end cover (117) in a 120° direction.

6. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 5, characterized in that: The adjustable speed fan system comprises a fan motor (303), adjustable speed fan blades (306) and a blade support part (308); the adjustable speed fan blades (306) are placed in the blade support part (308), and the fan motor (303) is placed below the blade support part (308); the upper surface B of the annular positioning boss (316) is used to position the blade support part (308) of the adjustable speed fan system; the combustion turbulence fan motor (303) is placed above the particle filter device and extends into the particle filter device; and a reserved opening (114) for a fan motor connection line is left on the side surface of the lower part of the combustion chamber cavity (107).

7. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 6, characterized in that: The particle filtering device comprises a perforated filter mesh tube (302) and a high-temperature resistant activated carbon filter cotton (301), wherein the high-temperature resistant activated carbon filter cotton (301) is sleeved on the outside of the perforated filter mesh tube (302) having a supporting function; and the outer ring surface A of the annular positioning boss (316) cooperates with the inner ring of the perforated filter mesh tube (302) for positioning.

8. The device for visualizing solid propellant high-pressure combustion turbulence according to claim 7, characterized in that: The visualization window is provided with an observation transparent window sheet (110), which is pressed by the observation window cover (108) under the connection and tightening action of the observation window bolt (111) and the observation window nut (112).

9. A method for using a device for visualizing high-pressure combustion turbulence of solid propellants, using the device for visualizing high-pressure combustion turbulence of solid propellants as claimed in claim 8, characterized in that: During use, the visualized high-pressure combustion chamber is placed on the experimental platform and fixed, the ignition electrode terminal (201) is connected to the external control voltage, the fan motor connection line reserved port (114) is connected to the wire and sealed; the combustion chamber air outlet electromagnetic control valve (118) is in the open state, and the combustion chamber air inlet electromagnetic control valve (113) is in the closed state; the upper flange end cover (105) of the visualized high-pressure combustion chamber is opened, and the sealed visualized high-pressure combustion chamber is in the open state; Insert the high temperature resistant activated carbon filter cotton (301) into the punched filter mesh tube (302) to form a particle filter device, and place the particle filter device in the middle of the lower flange end cover (117); When installing the combustion turbulence device, the adjustable speed fan system is placed inside the adjustable speed fan system placement platform (307), so that the small cylinder (322) of the medicine strip clamp of the porous air distribution plate (309) is located at the top for installation, and then the porous air distribution plate (309) is rotated slightly counterclockwise so that the protruding bosses (319) on both sides can enter the grooves (318) in the adjustable speed fan system placement platform (307) to achieve fit, thereby preventing the airflow generated by the adjustable speed fan system from fluctuating on the porous air distribution plate (309); The combustion turbulence device is placed above the particle filter device, and the lower end surface of the adjustable speed fan system placement platform (307) has an annular positioning boss (316), and the axis of the annular positioning boss (316) is installed to coincide with the axis of the punched filter mesh tube (302), thereby ensuring that the outer ring surface A is closely fitted with the inner wall surface of the punched filter mesh tube (302); the adjustable speed fan system placement platform (307) is installed on the support rod (304) of the adjustable speed fan system support platform, and then the platform fixing nut (305) is tightened to ensure that the lower end surface of the adjustable speed fan system support platform (307) is in close contact with the upper end surface of the high temperature resistant activated carbon filter cotton (301) and the lower end surface of the high temperature resistant activated carbon filter cotton (301) is in close contact with the lower flange end cover (117), thereby preventing the condensed phase particles generated by the combustion of the solid propellant powder strip from flowing in the gap of the contact surface; Pass the propellant ignition wire (401) through the upper end of the solid propellant strip (313) so that the solid propellant strip (313) is located in the middle of the propellant ignition wire (401), place the solid propellant strip (313) between the fixed clip (314) and the movable clip (312) on the fixture platform (310), and clamp the solid propellant strip (313) with the strip fastening bolt (311); place the strip and the fixture holding the solid propellant strip (313) in the strip fixture small cylinder (322) above the porous air distribution plate (309) in the combustion turbulence device, and adjust the position of the strip and the fixture so that the largest surface of the solid propellant strip (313) is aligned with the observation field of view; The two ends of the propellant ignition wire (401) are tightly wound around the electric heating wire ignition electrode (202); the flow channel controller (501) is placed on the flow channel controller placement boss (109), and the flow channel controller (501) is rotated and adjusted so that the axis of the recessed portion (506) corresponds to the axis of each visualization window without affecting the observation field; the upper flange end cover bolt (103) and the upper flange end cover nut (106) are used to make the combustion chamber upper flange end cover (105) closely contact with the combustion chamber cavity (107) to prevent gas leakage when under pressure. During the installation process, the upper flange end cover handle (101) is outside the high-pressure combustion chamber; The combustion chamber air outlet electromagnetic control valve (118) is closed, the combustion chamber air inlet electromagnetic control valve (113) is opened, high-pressure gas is introduced into the visual high-pressure combustion chamber, the pressure inside the combustion chamber is monitored by the pressure sensor (104), until the pressure reaches the set pressure value, the combustion chamber air inlet electromagnetic control valve (113) is closed, and no gas leakage is maintained for r seconds; the adjustable speed fan system is turned on and the required speed is set; the propellant ignition wire (401) is energized to ignite the solid propellant strip (313), and the phenomena accompanying the combustion process of the solid propellant strip (313) are observed by using external instruments and equipment; After the solid propellant strip (313) is burned, the adjustable speed fan system is continuously operated for not less than f minutes, so that all the condensed phase particles generated by the combustion of the solid propellant strip (313) are adsorbed on the high temperature resistant activated carbon filter cotton (301), the adjustable speed fan system is shut down, and the electromagnetic control valve (118) at the combustion chamber outlet is opened to discharge the high pressure gas in the combustion chamber; When the gas pressure in the visualized high-pressure combustion chamber is consistent with the external environmental pressure, the upper flange end cover (105) of the visualized high-pressure combustion chamber is opened, the flow channel controller (501) is taken out, and then the fixture platform (310) of the solid propellant strip is taken out, and a new solid propellant strip (313) sample is clamped again and the measurement is repeated; to measure multiple solid propellant strip (313) combustion experiments, the high-temperature resistant activated carbon filter cotton (301) needs to be replaced, the flow channel controller (501) is taken out, and then the fixture platform (310) of the solid propellant strip is taken out, the platform fixing nut (305) is removed, and then the combustion turbulence device is taken out, and finally the particle filter device is taken out, and a new high-temperature resistant activated carbon filter cotton (301) is replaced. The solid propellant strip (313) combustion phenomenon observation experiment can be completed multiple times.

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