Visual measurement device for electrically controlled solid propellant combustion process and measurement method thereof

Abstract

This invention discloses a visualization measurement device and method for the combustion process of electrically controlled solid propellants. The measurement device includes a propellant sample, a power supply, a control system, a high-speed camera, a constant-volume combustion bomb, a temperature controller, and a gas supply system. The constant-volume combustion bomb includes a heating element, a combustion chamber, and an integrated base. The high-speed camera faces the viewing window. The integrated base includes an adapter and an electrode assembly. The electrode assembly includes an electrode post, an electrode clamp, and an electrode sheet. The electrode sheet is attached to the side of the propellant sample, and the propellant sample is located within the excitation area of ​​the electrode sheet. It includes a core and an insulating layer, with the lower end of the core forming the initial combustion section. This measurement device integrates image technology and a controllable environmental cavity to collect the burning rate of solid propellants under various operating conditions. The non-contact measurement-specific propellant sample and excitation electrode assembly can accurately and without interference measure the burning rate and related combustion parameters under various set operating conditions. The measurement method can achieve simultaneous triggering and acquisition of multiple physical quantities, facilitating the analysis of the multi-physical coupling combustion characteristics of the propellant.

Description

Technical Field

[0001] This invention relates to the technical field of fuel combustion characteristic testing, specifically to a visualization measurement device and method for the combustion process of electronically controlled solid propellants. Background Technology

[0002] The combustion rate of electrically controlled solid propellants refers to the distance the solid phase disappears along the normal direction of the burning surface of the solid propellant per unit time. Electrically controlled solid propellants achieve adjustable control of ignition and burning rate by adjusting the applied voltage or current. They have advantages such as compact structure, rapid response, and easy control. In propellant formulation research and ignition control strategy design, accurately obtaining its burning rate data under different electrical excitation and boundary conditions is a key foundation.

[0003] Currently, propellant burning rate measurement experiments mainly rely on contact methods such as the target line method. These methods require pre-setting a melting line on the propellant sample and calculating the burning rate based on changes in the electrical signal caused by propellant combustion. This method has significant drawbacks: first, the implantation of the target line can damage the propellant's structure, affecting its natural combustion process; second, electrically controlled solid propellants themselves have a certain degree of conductivity, which can easily interfere with electrical signal acquisition, affecting the accuracy of burning rate determination; and third, non-contact measurement is impossible due to the limitations of the electrically controlled fixed propellant structure.

[0004] To overcome the errors introduced by contact testing, existing technologies have proposed non-contact image recording methods. For example, some published patents record the propellant combustion process using high-speed cameras and determine the time point when the combustion light passes through a specific aperture based on the image brightness (RGB values ​​reaching a certain threshold), thereby estimating the propellant burning rate. While this method avoids physical contact, it still has the following problems: First, this method uses a specific aperture as a reference distance and calculates the burning rate based on the combustion time over that distance. Its testing accuracy is low, and it cannot achieve continuous, interference-free measurement of the combustion process. Second, this type of scheme fails to achieve synchronous acquisition with electrical parameters such as current and voltage, and also lacks the ability to control environmental boundaries (pressure, temperature, etc.), making it difficult to meet the needs of systematic research on propellant combustion behavior under complex operating conditions. Summary of the Invention

[0005] The purpose of this invention is to overcome the deficiencies in the prior art and provide a visualization measurement device for the combustion process of electrically controlled solid propellants, so as to overcome one or more problems caused by the limitations and deficiencies of related technologies to a certain extent.

[0006] To achieve the above objectives, the technical solution of the present invention is as follows:

[0007] A visualization measurement device for the combustion process of an electrically controlled solid propellant includes a dedicated propellant sample, a power supply, a control system, a high-speed camera, a constant-volume combustion bomb, a temperature controller, and a gas supply system. The constant-volume combustion bomb includes a heating element, a combustion chamber, and an integrated base. The gas supply system is connected to the combustion chamber. The heating element is located inside the combustion chamber and connected to the temperature controller. At least one viewing window is provided on the side wall of the combustion chamber, and the high-speed camera is positioned directly opposite the viewing window.

[0008] The propellant sample has a square column structure and is clamped on an integrated base along the vertical direction. The integrated base includes an adapter and an electrode assembly. The electrode assembly is assembled on the adapter. The adapter is detachably inserted into the upper port of the combustion chamber. The electrode assembly includes an electrode post, an electrode clamp, and an electrode sheet. The electrode clamp is mounted on the adapter. The two electrode sheets are respectively attached to the two opposite sides of the propellant sample and are arranged along the combustion direction of the propellant sample. The two electrode clamps are located on the outside of the two electrode sheets and are used to apply relative clamping force to the two electrode sheets to hold the propellant sample. The two electrode sheets are respectively connected to the positive and negative terminals of the power supply through the electrode post.

[0009] At least the lower section of the propellant sample is within the observation range of the viewing window, and either of the other two opposite sides of the propellant sample is directly facing the viewing window. The propellant sample is located within the excitation area of ​​the two electrode plates. The propellant sample includes an inner core and an outer insulating layer. The lower end of the core extends beyond the insulating layer, forming an exposed initial combustion section.

[0010] Furthermore, the control system includes a host computer, an electronic control switch, a synchronous trigger, and an electrical signal acquisition device. The electronic control switch controls the current flow of the electrode posts. The host computer is electrically connected to the high-speed camera, the electronic control switch, and the electrical signal acquisition device through the synchronous trigger, and is used to synchronously send trigger signals to the high-speed camera, the electronic control switch, and the electrical signal acquisition device.

[0011] Furthermore, the insulating layer of the propellant sample is a Teflon film that decomposes upon heating. The Teflon film is wrapped around the propellant core and is used to gradually retract axially as the burning surface advances, exposing the conductive parts of the propellant core.

[0012] Furthermore, one electrode clamp is fixed to the adapter by a fixing block, and the other electrode clamp is fixedly connected to the adapter by an elastic support, so as to form a laterally elastic clamping space between the two electrode clamps.

[0013] Furthermore, both electrode clamps are provided with vertical positioning grooves that extend through the lower end of the electrode clamps. Corresponding positioning protrusions are provided on the electrode plates. The width of the electrode plates is consistent with the width of the drug column sample, and both sides are aligned. The positioning protrusions are inserted into the vertical positioning grooves to position the vertical installation of the drug column sample.

[0014] A method for visually measuring the combustion process of electrically controlled solid propellants includes the following steps:

[0015] S1. Preparation of drug cartridge samples;

[0016] a. Set a molding groove on the mold and mark the no-film etched line on the molding groove. Clean the molding groove and lay a Teflon film. One end of the Teflon film is flush with one end of the molding groove, and the other end is flush with the no-film etched line.

[0017] b. Under set temperature conditions, stir and mix the components of the raw material formula in a mixing container, and perform vacuum degassing treatment on the propellant slurry in a vacuum environment to eliminate air bubbles and obtain propellant slurry.

[0018] c. Slowly inject the degassed propellant slurry into the molding tank until it is full, and cut the Teflon film on both sides of the molding tank, leaving enough film width to wrap the core.

[0019] d. Place the mold filled with propellant slurry into a temperature control chamber, set the curing time, temperature and humidity inside the chamber, and the propellant slurry dries, cures and solidifies, stretches and wraps the reserved Teflon film to obtain the final propellant column sample;

[0020] e. Mark the sample number of the drug cartridge sample, inspect its quality, and measure and record the size and electrical properties of the qualified drug cartridge sample;

[0021] S2. Install the propellant sample; the electrode sheet is attached to the two opposite forming surfaces of the propellant sample. The two opposite forming surfaces are the two opposite sides that contact the side walls of the two grooves of the forming groove, so that the propellant sample is completely placed in the excitation area between the two electrode sheets. Clamp the propellant sample and the electrode sheet, and place them together between the two electrode clamps. Clamp and ensure that the propellant is vertical.

[0022] S3. Generate the measurement environment; Insert the integrated base into the upper port of the combustion chamber and seal the connection. The temperature controller is preset to the temperature control temperature, the gas supply system is preset to the gas supply pressure, high-pressure gas is input into the combustion chamber, and the heating element heats the high-pressure gas in the combustion chamber to generate a measurement environment with specified parameters.

[0023] S4. Burning Rate Measurement: The host computer simultaneously sends trigger signals to the high-speed camera, electronic control switch, and electrical signal acquisition unit via a synchronous trigger. All three start synchronously and have the same time phase. The electrode plate is energized to ignite the initial combustion section at the lower end of the propellant sample. At the same time, the electrical signal acquisition unit synchronously acquires the voltage and current signals within the electrode assembly, and the high-speed camera synchronously acquires images of the propellant sample in the combustion chamber. All of these are sent to the host computer. The image data is analyzed and calculated to obtain the burning rate of the propellant sample under the corresponding excitation conditions.

[0024] Compared with the prior art, the visualization measurement device and measurement method for the electronically controlled solid propellant combustion process of the present invention have the following advantages:

[0025] This measuring device integrates image processing-assisted non-contact measurement technology and a controllable environmental cavity design. It can simulate high pressure, high temperature and electrical excitation conditions to test the burning rate of electrically controlled solid propellants. It is designed with a special propellant grain sample and its excitation electrode assembly for non-contact measurement. It can accurately and without interference measure the burning rate and related combustion parameters of electrically controlled solid propellants under various set conditions. This measuring device can avoid sample structure damage and measurement errors caused by traditional target line method and coarse light emission threshold method, thus improving the accuracy and reliability of burning rate measurement.

[0026] The outer layer of the propellant grain sample is coated with an insulating layer, which is used to hold the electrode plates in contact with the sample. This avoids the risk of electrical breakdown. Since the electrode plates are not in direct contact with the combustion surface of the propellant core, the interference of the electrodes on the temperature field of the combustion surface and the combustion characteristics of the propellant is effectively avoided, ensuring the authenticity and repeatability of the experimental data. An initial combustion section is preset at the lower end of the propellant grain sample to control the initial combustion surface. As the combustion surface advances, the insulating layer moves axially backward to avoid interfering with the advancement of the combustion surface and to continuously and orderly expose the propellant core to form new conductive parts, which is conducive to orderly advancement and combustion.

[0027] This measurement method can simulate the combustion of propellants under multiple operating conditions and can simultaneously trigger the acquisition of multiple physical quantities. It is beneficial to unify the time reference of signals such as current, voltage, and images, and facilitate in-depth analysis of the multi-physical coupling combustion characteristics of propellants under electrical excitation. The propellant grain sample forming method can realize the integral forming of the propellant core and Teflon insulating film, which simplifies the process flow, improves the consistency and reliability of propellant grain sample forming, and effectively enhances the insulation performance of propellant grain samples. Attached Figure Description

[0028] Figure 1 This is a schematic diagram of the overall structure of the measuring device disclosed in this invention;

[0029] Figure 2 for Figure 1 A schematic diagram of the structure of the mesoaptamer;

[0030] Figure 3 for Figure 2 A magnified view of a section at point I;

[0031] Figure 4 This is a flowchart of the measurement method disclosed in this invention.

[0032] In the diagram: 1. Host computer; 2. Synchronous trigger; 3. Electrical control switch; 4. Electrical signal acquisition device; 5. Power supply; 6. Integrated base; 61. Adapter; 62. Electrode post; 63. Fixing block; 64. Fixed electrode clamp; 65. Movable electrode clamp; 66. Elastic support; 67. Propellant sample; 67a. Propellant core; 67b. Electrode sheet; 67c. Insulating layer; 7. Constant volume combustion bomb; 71. Heating element; 72. Viewing window; 73. Combustion chamber; 8. High-speed camera; 9. Temperature controller; 10. High-pressure gas source; 11. Gas supply system; L. Initial combustion section length. Detailed Implementation

[0033] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are merely the best embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0034] Based on non-contact measurement technology, this embodiment provides a visualization measurement device for the combustion process of electrically controlled solid propellants, such as... Figures 1-3 As shown, it includes a dedicated measuring sample 67, a power supply 5, a control system, a high-speed camera 8, a constant volume combustion bomb 7, a temperature controller 9, and a gas supply system 11.

[0035] The gas supply system 11 includes a high-pressure gas source 10, a gas supply branch and an exhaust branch. The high-pressure gas source 10 is equipped with a pressure regulator and can preset the gas supply pressure. Automatic valves and manual valves are connected in parallel on both the gas supply branch and the exhaust branch. The exhaust branch is used for exhausting and adjusting the gas after or during the measurement. The gas supply system 11 provides a simulated gas pressure environment for various actual combustion conditions for the given volume combustion bomb 7.

[0036] like Figure 2 As shown, the constant volume combustion bomb 7 includes a heating element 71, a combustion chamber 73 and an integrated base 6. The heating element 71 is located at the bottom of the combustion chamber 73 and is connected to a temperature controller 9 to heat the high-pressure gas in the combustion chamber 73 to a preset temperature. The gas supply branch is connected to the bottom of the combustion chamber 73 and is in communication with it.

[0037] At least one viewing window 72 is provided on the side wall of the combustion chamber 73. Multiple viewing windows 72 should be evenly distributed circumferentially. The high-speed camera 8 is positioned directly opposite the velocity measuring side of the propellant sample 67 through the corresponding viewing window 72.

[0038] To reduce interference and facilitate non-contact measurement of the drug cartridge sample 67, the drug cartridge sample 67 is designed as a square column structure, clamped on the integrated base 6 and arranged vertically, with its electrical excitation input from two opposite sides, as shown below. Figure 2As shown, the integrated base 6 can be completely disassembled to facilitate the installation of the propellant sample 67. The integrated base 6 includes an adapter 61 and an electrode assembly. The adapter 61 can be detachably inserted into the upper port of the combustion chamber 73 and sealed and installed on the top of the constant volume combustion bomb 7. The electrode assembly includes an electrode post 62, an electrode clamp, and an electrode plate 67b assembled on the adapter 61. Two electrode posts 62 are inserted through the adapter 61 and are symmetrical. The lower end of the electrode post 62 is connected to the electrode clamp on the corresponding side through an electrode wire, and the upper end is connected to the power supply 5 through an electrode wire. The two electrode clamps are installed in parallel on the adapter 61 and are in a vertical state, with a clamping space in the middle.

[0039] Electrode 67b is detachably inserted into the electrode clamp, which facilitates the assembly of the propellant sample 67 outside the combustion chamber 73 and enables precise positioning and assembly of the propellant sample 67 and electrode 67b. This ensures that the entire propellant sample 67 falls into the excitation area between the two electrode 67b. The two electrode 67b are respectively attached to the two opposite sides of the propellant sample 67 and are set along the combustion direction of the propellant sample 67. The two electrode 67b of the assembled propellant sample 67 are placed in the clamping space. The electrode clamp provides elastic clamping force while electrically conducting the electrode 67b.

[0040] Because the two sides of the propellant sample 67 are in complete contact with the electrodes and fall entirely into the excitation area of ​​the two electrode plates 67b, in order to ignite the propellant sample 67 at a specific point and continuously propagate combustion from bottom to top, the propellant sample 67 includes an inner core 67a and an outer insulating layer 67c. The lower end of the core 67a extends beyond the insulating layer 67c, forming an exposed initial combustion section, such as... Figure 3 As shown, the initial combustion section length L is 1mm ± 0.1mm. When the excitation voltage is released between the electrode plates 67b, the initial combustion section exposed in the excitation area is ignited. The heat generated by the combustion of the propellant sample 67 causes the insulating layer 67c near the burning surface to ablate, melt, or decompose. As the burning surface advances, the propellant core 67a is continuously exposed, forming a new conductive part. After being exposed in the excitation area, the excitation combustion is promoted in an orderly manner, realizing continuous and interference-free burning rate measurement of the combustion process. The insulating layer 67c of the propellant sample 67 is made of Teflon film. Teflon film is an insulating film that is not resistant to high temperature but has excellent dielectric properties and is easy to coat. It can be well wrapped around the propellant core 67a. As the burning surface advances, the Teflon film near the burning surface is rapidly decomposed by heat and thus axially retracts to form the conductive area of ​​the propellant core 67a.

[0041] To facilitate observation and acquisition of the burning surface image of the propellant sample 67, at least the lower section of the propellant sample 67 is within the observation range of the viewing window 72, and either of the other two opposite sides of the propellant sample 67, i.e. the velocity measuring side that does not contact the electrode plate 67b, is directly opposite the viewing window 72.

[0042] As a further technical solution, in order to synchronously acquire the burning surface image and corresponding electrical parameters such as current and voltage at the corresponding time phase, the control system includes a host computer 1, an electric control switch 3, a synchronous trigger 2, and an electrical signal acquisition device 4. The electrical signal acquisition device 4 is used to acquire electrical parameters such as excitation voltage and excitation current, such as... Figure 1 As shown, the electronic control switch 3 is set on the electrode wire connecting the electrode post 62 and the positive terminal of the power supply 5. The host computer 1 is electrically connected to the high-speed camera 8, the electronic control switch 3 and the electrical signal acquisition device 4 through the synchronous trigger 2. The working instructions issued by the host computer 1 can be sent synchronously through the synchronous trigger 2 to trigger the start of the high-speed camera 8, the electronic control switch 3 and the electrical signal acquisition device 4, so as to achieve precise synchronization of excitation combustion and voltage, current and image acquisition, which is convenient for system research work. The image values ​​are transmitted to the host computer 1 in real time.

[0043] As a further technical solution, in order to accommodate drug core samples 67 of different thicknesses, the clamping space between the electrode clamps is a laterally elastic variable area. Specifically, the fixed electrode clamp 64 is fixed to the adapter 61 by the fixing block 63 to provide a stable support base, and the movable electrode clamp 65 is fixedly connected to the adapter 61 by the elastic support member 66. The elastic support member 66 can be laterally elastically extended and retracted. The movable electrode clamp 65 is set at its end to adapt to the thickness of the drug core sample 67 and provide clamping force, and to prevent the drug core 67a from deforming or breaking. The assembly of the fixed electrode clamp 64 and the movable electrode clamp 65 should ensure that the two are aligned and vertical.

[0044] As a further technical solution, the verticality of the propellant sample 67 should be ensured during installation to guarantee the accuracy of the burning rate measurement. To facilitate the positioning of the propellant sample 67, the width of the electrode plate 67b is designed to be consistent with the width of the propellant sample 67. The dual-purpose electrode plate 67b positions the propellant sample 67. A strip-shaped positioning protrusion (not shown in the figure) is raised on the contact surface of the electrode plate 67b with the electrode clamp. The positioning protrusion is parallel to the side edge of the electrode plate 67b. Both electrode clamps are provided with corresponding vertical positioning grooves (not shown in the figure). The vertical positioning grooves penetrate through the lower end of the electrode clamps. After the propellant sample 67 is installed on the two electrode plates 67b, it should be ensured that the propellant sample 67 falls completely into the excitation area and the sides of the electrode plate 67b are aligned with those of the propellant sample 67. This can be achieved by hand, wrapping with a binding rope, or using a clamp. The electrode plate 67b and the propellant sample 67 are kept aligned. The positioning protrusion is aligned with the vertical positioning groove. The assembly is inserted into the clamping space until the electrode clamp is fully clamped, thus completing the accurate installation of the propellant sample 67.

[0045] Based on the visualization measurement device of the above-described preferred embodiment, this embodiment provides a measurement method for the visualization measurement device used in the combustion process of the electrically controlled solid propellant, such as... Figure 4 As shown, it includes the following steps:

[0046] S1. The fabrication process of the drug cartridge sample 67 with an integrated thin-film structure of drug core 67a is as follows:

[0047] a. A forming groove is set on the mold. The length of the forming groove is less than or equal to the length of the electrode sheet 67b. A no-film marking line is marked on the forming groove. The no-film marking line is 1mm ± 0.1mm away from the end face of the groove. The surface of the forming groove of the mold is cleaned and dried to ensure that no impurities are attached. A Teflon film is laid. One end of the Teflon film is flush with one end of the forming groove, and the other end is flush with the no-film marking line. The Teflon film is required to be flat, wrinkle-free, and bubble-free to ensure that the sidewall of the core 67a forms a continuous and complete insulating layer 67c after forming. Sufficient width of the coating film outside the forming groove is reserved on both sides or one side of the Teflon film.

[0048] b. Two-stage mixing and degassing of raw material formulation to improve the density and uniformity of the cured propellant. First, under set temperature conditions, LiClO4, pure water, HBO3, plasticizer, etc. are poured into a mixing container and stirred. The container is then placed in a vacuum chamber for a first-stage temperature-controlled vacuum degassing to eliminate air bubbles, completing the first-stage mixing. PVA, after being washed with alcohol and heat-treated, is poured into a mixing container and stirred. The container is then placed in a vacuum chamber for a second-stage temperature-controlled vacuum degassing, completing the second-stage mixing; thus obtaining the propellant slurry.

[0049] c. After degassing, the propellant slurry is slowly injected into the molding tank until it is full. It should be ensured that the slurry covers the tank evenly and fills the mold fully. After the slurry is injected, the Teflon film is protected by pressure. If the Teflon film is too long, the Teflon film on both sides of the molding tank can be cut to leave enough film width to wrap the propellant core 67a.

[0050] d. Place the mold filled with propellant slurry into a temperature control chamber, set the curing time, temperature and humidity inside the chamber, and the propellant slurry dries, cures and solidifies to form a square column structure with good mechanical and insulating properties. Stretch and wrap the reserved Teflon film to obtain the final propellant column sample 67.

[0051] e. Demold and mark the sample number of the propellant column sample 67, and inspect its molding quality. Propellant column sample 67 that meets the quality requirements should have its dimensions and electrical properties measured and recorded.

[0052] S2. Install the propellant sample 67; remove the electrode plate 67b from the electrode clamp, and attach the two opposite forming surfaces of the propellant sample 67 to the electrode plate 67b. To ensure uniform clamping, the two opposite forming surfaces are the two opposite sides that contact the two side walls of the forming groove. Use a flat surface to align the four end faces of the electrode plate 67b and the propellant sample 67, ensuring that the two electrode plates 67b are aligned and that the propellant sample 67 falls completely into the excitation area and that its two sides are aligned and flat with the sides of the electrode plate 67b. Clamp the propellant sample 67 and the electrode plate 67b, and place them together between the two electrode clamps, clamping them and ensuring that the propellant is in a vertical position.

[0053] S3. Generate the measurement environment; Insert the integrated base 6 into the upper port of the combustion chamber 73 and seal the connection. The temperature controller 9 presets the temperature control temperature, and the gas supply system 11 presets the gas supply pressure. High-pressure gas is input into the combustion chamber 73, and the heating element 71 heats the high-pressure gas in the combustion chamber 73. A measurement environment with specified temperature and pressure boundary conditions can be generated in the cavity. The power supply 5 can be set with different excitation voltages to simulate combustion parameters under different working conditions. The measuring device supports the generation of the measurement environment, which is beneficial to adjust different environmental pressures, temperatures and electrical excitation conditions according to the working conditions such as the initial ignition and secondary ignition of the propellant sample 67. It has good adaptability and scalability, and meets the needs of visualization and quantitative research on the combustion behavior of electrically controlled solid propellants under complex working conditions.

[0054] S4. Burning rate measurement: The high-speed camera 8 is set to acquire the frame rate of the images. The electrical signal acquisition device 4 is connected to the power supply electrode wire of the electrode post 62. The excitation voltage of the power supply 5 is set. The host computer 1 sends a trigger signal to the high-speed camera 8, the electronic control switch 3, and the electrical signal acquisition device 4 simultaneously through the synchronous trigger 2. The three start synchronously and have the same time phase. The electrode plate 67b is energized to ignite the initial combustion section at the lower end of the propellant sample 67. At the same time, the electrical signal acquisition device 4 synchronously acquires the voltage and current signals in the electrode assembly. The high-speed camera 8 synchronously and continuously acquires the combustion images of the propellant sample 67 in the combustion chamber 73 and sends them to the host computer 1 in real time. The image processing program of the host computer 1 extracts the burning surface position frame by frame and calculates the instantaneous burning rate curve by combining the time interval of each frame. The voltage and current signals acquired by the electrical signal acquisition device 4 are synchronously and in real time uploaded to the host computer 1. The image processing program aligns and synchronously processes the image data and electrical signal data in order to determine the burning rate and to study the coupling relationship between the burning rate and electrical parameters under electronic control.

[0055] The directional terms "upper," "lower," "side," "end," "bottom," "inner," and "outer" mentioned in this article are based on... Figures 1-3 The description is based on the orientation or positional relationships shown in the corresponding figures. These terms are primarily for the purpose of better describing the invention and its embodiments, and are not intended to limit the indicated devices, elements, or components to having a particular orientation, or to be constructed and operated in a particular orientation;

[0056] Furthermore, in addition to indicating direction or positional relationship, some of the aforementioned terms may also have other meanings. For example, the terms "above" and "inside" may, in certain circumstances, indicate a certain dependency or connection relationship. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0057] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A visualization measurement device for the combustion process of electrically controlled solid propellants, characterized in that: The system includes a dedicated measuring propellant sample, a power supply, a control system, a high-speed camera, a constant-volume combustion bomb, a temperature controller, and a gas supply system. The constant-volume combustion bomb includes a heating element, a combustion chamber, and an integrated base. The gas supply system is connected to the combustion chamber. The heating element is located inside the combustion chamber and connected to the temperature controller. At least one viewing window is provided on the side wall of the combustion chamber, and the high-speed camera is positioned directly opposite the viewing window. The propellant sample has a square column structure and is clamped on the integrated base along the vertical direction. The integrated base includes an adapter and an electrode assembly. The electrode assembly is assembled on the adapter. The adapter is detachably inserted into the upper port of the combustion chamber. The electrode assembly includes an electrode post, an electrode clamp, and electrode plates. The electrode clamp is mounted on the adapter. The two electrode plates are respectively attached to two opposite sides of the propellant sample and are arranged along the combustion direction of the propellant sample. The two electrode clamps are respectively located outside the two electrode plates and are used to apply relative clamping force to the two electrode plates to hold the propellant sample. The two electrode plates are respectively connected to the positive and negative terminals of the power supply through the electrode post. At least the lower section of the propellant sample is within the observation range of the viewing window, and either of the other two opposite sides of the propellant sample faces the viewing window. The propellant sample is located within the excitation areas of the two electrode plates. The propellant sample includes an inner core and an outer insulating layer. The lower end of the core extends beyond the insulating layer, forming an exposed initial combustion section. The insulating layer is a Teflon film that decomposes upon heating. The Teflon film is wrapped around the core and is used to gradually axially retract to expose the conductive parts of the core as the combustion surface advances. The control system includes a host computer, an electronic control switch, a synchronous trigger, and an electrical signal acquisition device. The electronic control switch controls the current flow of the electrode post. The host computer is electrically connected to the high-speed camera, the electronic control switch, and the electrical signal acquisition device through the synchronous trigger, and is used to synchronously send trigger signals to the high-speed camera, the electronic control switch, and the electrical signal acquisition device.

2. The visualization measurement device for the electrically controlled solid propellant combustion process according to claim 1, characterized in that: One electrode clamp is fixed to the adapter by a fixing block, and the other electrode clamp is fixedly connected to the adapter by an elastic support member, so as to form a laterally elastic clamping space between the two electrode clamps.

3. The visualization measurement device for the electrically controlled solid propellant combustion process according to claim 1 or 2, characterized in that: Both electrode clamps are provided with vertical positioning grooves that penetrate the lower end of the electrode clamps. The electrode plates are provided with corresponding positioning protrusions. The width of the electrode plates is the same as the width of the drug column sample, and both sides are aligned. The positioning protrusions are inserted into the vertical positioning grooves to position the vertical installation of the drug column sample.

4. A visualization measurement method for the combustion process of electrically controlled solid propellants, based on the visualization measurement device for the combustion process of electrically controlled solid propellants as described in claim 1, characterized in that, Includes the following steps: S1. Preparation of drug cartridge samples; a. Set a molding groove on the mold and mark the no-film etched line on the molding groove. Clean the molding groove and lay a Teflon film. One end of the Teflon film is flush with one end of the molding groove, and the other end is flush with the no-film etched line. b. Under set temperature conditions, stir and mix the components of the raw material formula in a mixing container, and perform vacuum degassing treatment on the propellant slurry in a vacuum environment to eliminate air bubbles and obtain propellant slurry. c. Slowly inject the degassed propellant slurry into the molding tank until it is full, and cut the Teflon film on both sides of the molding tank, leaving enough film width to wrap the core. d. Place the mold filled with propellant slurry into a temperature control chamber, set the curing time, temperature and humidity inside the chamber, and the propellant slurry dries, cures and solidifies, stretches and wraps the reserved Teflon film to obtain the final propellant column sample; e. Mark the sample number of the drug cartridge sample, inspect its quality, and measure and record the size and electrical properties of the qualified drug cartridge sample; S2. Install the drug column sample; the electrode sheet is attached to the two opposite forming surfaces of the drug column sample. The two opposite forming surfaces are the two opposite sides that contact the side walls of the two grooves of the forming groove, so that the drug column sample is completely placed in the excitation area between the two electrode sheets. Clamp the drug column sample and the electrode sheet, and place them together between the two electrode clamps. Clamp and ensure that the drug column sample is in a vertical state. S3. Generate the measurement environment; Insert the integrated base into the upper port of the combustion chamber and seal the connection. The temperature controller is preset to the temperature control temperature, the gas supply system is preset to the gas supply pressure, high-pressure gas is input into the combustion chamber, and the heating element heats the high-pressure gas in the combustion chamber to generate a measurement environment with specified parameters. S4. Burning Rate Measurement: The host computer simultaneously sends trigger signals to the high-speed camera, electronic control switch, and electrical signal acquisition unit via a synchronous trigger. All three start synchronously and have the same time phase. The electrode plate is energized to ignite the initial combustion section at the lower end of the propellant sample. At the same time, the electrical signal acquisition unit synchronously acquires the voltage and current signals within the electrode assembly, and the high-speed camera synchronously acquires images of the propellant sample in the combustion chamber. All of these are sent to the host computer. The image data is analyzed and calculated to obtain the burning rate of the propellant sample under the corresponding excitation conditions.

Images