Device and method for testing combustion performance parameters of low-cost solid propellant in wide temperature range

Abstract

The invention belongs to the field of propellant performance testing, and discloses a device and method for testing combustion performance parameters of a low-cost solid propellant in a wide temperature range, and the device comprises a high-pressure combustion chamber, a cylindrical sample stage, a high-precision high-low temperature experiment box, a combustion chamber pressure control module and an electric ignition module. The high-pressure combustion chamber is arranged in the high-precision high-low temperature experiment box, a cylindrical sample table is arranged in the high-pressure combustion chamber, and the combustion chamber pressure control module and the electric ignition module are connected with the high-pressure combustion chamber. The environment temperature of the combustion chamber and the propellant grain is controlled through the high-low temperature test box, the range is from-45 DEG C to 80 DEG C, and the initial temperature requirements of different environments in the solid propellant burning rate test are met. The burning speed, the pressure index, the temperature coefficient and the flame temperature distribution of the propellant are calculated by shooting the end face retreating process and the flame structure image of the propellant under different environment temperatures and different pressures in the closed combustion chamber, and the method has the advantages of being accurate in testing, easy to operate, low in cost and high in safety performance.

Description

Technical Field

[0001] The invention relates to a combustion performance parameter testing device and method for low-cost solid propellant within a wide temperature range, belonging to the field of solid propellant performance testing. Background Art

[0002] The main structural parts of solid rocket engines include combustion chamber, propellant column, nozzle and ignition device. Due to its good maneuverability, high thrust and easy long-term storage, it is widely used in the field of rockets and missiles. The combustion chamber is an important component of the engine. It is the part where the propellant is installed, burned and thrust is generated. Linear burning rate, flame temperature, burning rate pressure index (n) and temperature coefficient (δ p ) are the four most important combustion performance parameters of propellants and are also the basic parameters for the manufacturing and design of missile power systems. They directly affect the pressure, thrust and working time of the solid rocket engine combustion chamber. The linear burning rate refers to the distance moved by the propellant along the normal direction of the combustion surface per unit time. The pressure exponent and the burning rate temperature coefficient represent the influence of pressure and initial ambient temperature on the burning rate of the propellant respectively.

[0003] Common tests for testing the combustion performance of solid propellants mainly use the constant pressure method to test the withdrawal process of the propellant strip, mainly including: target line method, underwater acoustic emission method and video photography. The target line method is a traditional burning rate measurement method. By setting target lines on the propellant strip and measuring the time to burn to each target line, the average burning rate is calculated; this method is simple to operate, but it can only obtain the average burning rate and cannot reflect the dynamic changes of combustion. Underwater acoustic emission uses the characteristics of water coating, sound conduction, and easy pressurization. The effective length of the propellant column is divided by the duration of the acoustic wave signal generated during the combustion process (that is, the combustion time) to obtain the burning rate at constant pressure and temperature. The test process is simple, fast, safe, economical, and highly accurate (water pressure saves nitrogen), but it can only obtain the average burning rate and cannot obtain the transient combustion process. The traditional video photography method uses a camera or high-speed photography to record the withdrawal process of the propellant end face in a constant pressure closed burner, and calculates the instantaneous rate. However, the propellant combustion usually produces a lot of smoke, which can easily cause the combustion flame light to decay seriously, which can easily lead to inaccurate testing and fail to obtain important parameters such as combustion temperature and temperature coefficient. The traditional method of testing the combustion temperature of propellants is mainly to bury thermocouples in the grain to test the combustion wave of the combustion process, which is complicated and costly. It can be seen that the current solid propellant test conditions cannot meet the actual situation, and more accurate, objective, practical and low-cost test methods are needed to characterize multiple combustion performance parameters of propellants. Summary of the invention

[0004] In view of the problem that traditional propellant combustion test equipment has single function and complex burning rate temperature coefficient and combustion temperature tests, it is impossible to simultaneously obtain multiple propellant combustion performance parameters such as burning rate, pressure index, temperature coefficient test and flame temperature distribution. The purpose of the present invention is to provide a low-cost solid propellant combustion performance parameter test equipment within a wide temperature range. The device simulates different environmental conditions through a high-precision high and low temperature test chamber to meet the burning rate and flame temperature test of solid propellant under specific ambient temperature and specific pressure, and has simple operation and low cost.

[0005] To achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0006] A low-cost solid propellant combustion performance parameter testing device within a wide temperature range, comprising a high-pressure combustion chamber, a cylindrical sample stage, a high-precision high and low temperature test box, a combustion chamber pressure control module and an electric ignition module;

[0007] The high-pressure combustion chamber is arranged in a high-precision high-low temperature experimental box, a cylindrical sample table is arranged in the high-pressure combustion chamber, and a combustion chamber pressure control module and an electric ignition module are connected to the high-pressure combustion chamber.

[0008] A further improvement of the present invention is that the combustion chamber pressure control module includes a PID pressure controller, a solid-state relay, a high-pressure nitrogen bottle, a combustion gas buffer bottle, an air inlet pipeline, an air outlet pipeline and a solenoid valve, wherein the high-pressure nitrogen bottle, the combustion gas buffer bottle, the air inlet pipeline and the air outlet pipeline are connected to the high-pressure combustion chamber, the PID pressure controller is connected to the solid-state relay, the solid-state relay is connected to the solenoid valve, and the solenoid valve is connected to the air outlet pipeline.

[0009] A further improvement of the present invention is that the electric ignition module includes a DC power supply, an ignition circuit and a copper electrode terminal, wherein the copper electrode terminal includes a conical copper column and a plug for sealing the conical copper column, a conical gasket is arranged between the plug and the conical copper column through a phenolic resin, and the conical copper column is fixed to the wall of the high-pressure combustion chamber through the plug.

[0010] A further improvement of the present invention is that the high-pressure combustion chamber includes a cavity, window covers are arranged at the front and rear of the cavity, a sapphire visualization window is arranged above the window cover, and a side boss is arranged above the sapphire visualization window; a high-speed camera is arranged on one side of the sapphire visualization window, and a plurality of holes for installing copper electrode terminals, pressure sensors, air inlet pipes and air outlet pipes are opened at both ends of the cavity.

[0011] A further improvement of the present invention is that a combustion chamber cover plate is provided at one end of the high-pressure combustion chamber, and the combustion chamber cover plate and the high-pressure combustion chamber are sealed by a high-pressure combined sealing gasket.

[0012] A further improvement of the present invention is that two electrodes are fixed on the cylindrical sample table, one of which is connected to a copper electrode terminal on the wall of a high-pressure combustion chamber, an outer end of the copper electrode terminal is connected to a DC power supply through an ignition circuit, and a nickel-chromium wire is arranged between the two electrodes on the cylindrical sample table.

[0013] A method for testing combustion performance parameters of low-cost solid propellant within a wide temperature range comprises the following steps:

[0014] The propellant strip is fixed on the cylindrical sample stage, and the cylindrical sample stage is fixed at the center of the bottom of the high-pressure combustion chamber, the high-pressure combustion chamber is sealed, and the pressure in the high-pressure combustion chamber reaches a preset value;

[0015] The propellant strip is ignited, and the burning rate of the solid propellant is obtained by calculating the change of the burning surface of the solid propellant over time using the flame image taken by a high-speed camera.

[0016] A further improvement of the present invention is that, before the combustion test, high-pressure nitrogen is filled into the combustion chamber. When the pressure is higher than the set pressure, the PID pressure controller releases the pressure to the set value. During the combustion test, when the combustion chamber pressure is higher than the set pressure, the PID pressure controller controls the solenoid valve to release the pressure to the set pressure, thereby releasing the combustion gas while maintaining the combustion chamber pressure stable.

[0017] A further improvement of the present invention is that it also includes: by testing the burning rate at multiple ambient temperatures under the same combustion chamber pressure, a curve of the burning rate variation with temperature of the solid propellant is obtained, and the burning rate temperature coefficient of the propellant is calculated; by testing the burning rate at multiple pressures under the same ambient temperature, a curve of the burning rate variation with pressure of the solid propellant is obtained, and the pressure index of the propellant is calculated.

[0018] A further improvement of the present invention is that, based on the flame image taken by the high-speed camera, the flame image is processed by a graphics processing algorithm to obtain RGB three primary colors, and then a flame temperature distribution diagram is obtained.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] The present invention uses a high-precision high and low temperature test box to control the ambient temperature in the high-pressure combustion chamber to meet the different temperature requirements of the solid propellant burning rate test, and can achieve dynamic temperature adjustment within the range of -45 to 80°C. The device of the present invention can not only calculate the burning rate of the propellant, but also use a graphics processing algorithm to process the flame RGB three primary colors to obtain the flame temperature distribution. Two combustion performance data can be obtained in one combustion test, reducing the cost of the test.

[0021] Furthermore, the high-pressure constant-volume combustion chamber of the present invention has a simple structure. The exterior of the cavity is a cube, and the interior is a hollow cylinder. The exterior is connected to the inlet and exhaust pipelines, nitrogen bottles and buffer bottles. The welding process is simple, easy to move and has no complex external line valves, which saves time, labor and raw materials, and has a low manufacturing process cost.

[0022] Furthermore, the present invention utilizes a PID pressure controller and a solenoid valve to monitor the pressure in the combustion chamber to maintain a stable pressure during the solid propellant combustion process.

[0023] Furthermore, the present invention utilizes a window cover plate made of sapphire material, which can not only ignite the solid propellant by electric ignition, but also ignite the solid propellant by laser ignition technology.

[0024] Furthermore, the present invention utilizes a conical boss to achieve sealing to the wire column, and the conical copper column penetrates the wall of the high-pressure combustion chamber and is insulated from the combustion chamber, thereby improving the safety performance of ignition.

[0025] Furthermore, the present invention utilizes a high-speed camera not only to record the propellant grain retreat process through a sapphire window on the combustion chamber to obtain the burning rate, but also to utilize a graphics processing algorithm to process the RGB three-primary colors of the flame captured by the high-speed camera to obtain a flame temperature distribution diagram. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is an overall schematic diagram of the device of the present invention;

[0027] Figure 2 It is a schematic diagram of the assembly of the device of the present invention;

[0028] Figure 3 It is a schematic diagram of electric ignition of the device of the present invention;

[0029] Figure 4 The propellant combustion effect diagram; (a) is 0ms, (b) is 216.92ms, (c) is 401.06ms, and (d) is 800.25ms;

[0030] Figure 5 The combustion process of low burning rate temperature coefficient paraffin wax (PW) composite propellant grain SP-PW at 3MPa, 5MPa and different ambient temperatures;

[0031] Figure 6The RGB three-primary colors obtained by processing the burning image and the burning image by the graphics processing algorithm; among them, (a) is a 0ms burning image, (b) is a 441.53ms burning image, (c) is a 699.01ms burning image, (d) is a 710.27ms burning image, (e) is a 727.15ms burning image, and (f) is a 745.71ms burning image; (g) is the 0ms processed RGB three-primary colors, (h) is the 441.53ms processed RGB three-primary colors, (i) is the 699.01ms processed RGB three-primary colors, (j) is the 710.27ms processed RGB three-primary colors, (k) is the 727.15ms processed RGB three-primary colors, and 1) is the 745.71ms processed RGB three-primary colors;

[0032] Figure 7 The flame temperature distribution map is calculated for the RGB three-primary colors of the combustion image;

[0033] In the figure, 1 is a high-pressure combustion chamber, 2 is a cylindrical sample table, 3 is a high and low temperature experimental box, 4 is a PID pressure controller, 5 is a DC power supply, 6 is a high-speed camera, 7 is a nitrogen bottle, 8 is a combustion gas buffer bottle, 9 is a side boss, 10 is a sapphire visualization window, 11 is a window cover, 12 is an air inlet pipe, 13 is an air outlet pipe, 14 is a copper electrode terminal, 15 is a sensor, 16 is a combustion chamber cover, 17 is a thread, 18 is an electrode, and 19 is a conical copper column. DETAILED DESCRIPTION

[0034] In order to facilitate the understanding of the present invention, the present invention will be described more fully below with reference to the relevant drawings. The preferred embodiments of the present invention are given in the drawings. However, the present invention can be implemented in many different forms and is not limited to the embodiments described herein. On the contrary, the purpose of providing these embodiments is to make the disclosure of the present invention more thoroughly and comprehensively understood.

[0035] In addition, when an element in the present invention is referred to as being "fixed to" or "disposed on" another element, it may be directly on the other element or there may be a central element. When an element is considered to be "connected to" another element, it may be directly connected to the other element or there may be a central element at the same time. The terms "vertical", "horizontal", "left", "right" and similar expressions used herein are for illustrative purposes only and are not intended to be the only embodiment.

[0036] See also Figure 1-Figure 6 The present invention discloses a low-cost solid propellant combustion performance parameter testing device within a wide temperature range, comprising a high-pressure combustion chamber 1, a cylindrical sample table 2, a high-precision high and low temperature test box 3, a combustion chamber pressure control module and an electric ignition module.

[0037] The combustion chamber pressure control module includes a PID pressure controller 4, a solid-state relay, a high-pressure nitrogen bottle 7, a combustion gas buffer bottle 8, an air inlet line 12, an air outlet line 13 and a solenoid valve, wherein the high-pressure nitrogen bottle 7, the combustion gas buffer bottle 8, the air inlet line 12 and the air outlet line 13 are connected to the high-pressure combustion chamber 1, the PID pressure controller 4 is connected to the solid-state relay, the solid-state relay is connected to the solenoid valve, and the solenoid valve is connected to the air outlet line 13. The problem of unclear combustion flames caused by the large amount of smoke produced by the combustion of the propellant is solved to a certain extent by quickly releasing the combustion gas products, while maintaining the stability of the cavity pressure.

[0038] When the pressure of the high-pressure combustion chamber 1 is greater than the set value of the PID pressure controller 4, the PID pressure controller 4 energizes or de-energizes the solid-state relay, thereby controlling the opening or closing of the solenoid valve, and achieving the pressure stability of the high-pressure combustion chamber 1 through high-frequency air release, while reducing combustion smoke. The pressure range of the high-pressure combustion chamber 1 is 1.0-15MPa.

[0039] The electric ignition module includes a DC power supply 5, an ignition circuit and a copper electrode terminal 14. The copper electrode terminal 14 is composed of a conical copper column 19, an NPT1 / 4 stainless steel plug with a conical inner hole and a phenolic resin conical gasket. The DC power supply 5 is connected to the copper electrode terminal 14 via the ignition circuit. The conical copper column 19 is fixed to the side of the high-pressure combustion chamber 1 through the external thread of the NPT1 / 4 stainless steel plug, and a phenolic resin conical gasket is arranged between the conical copper column 19 and the NPT1 / 4 stainless steel plug. The conical copper column 19 is sealed by a conical boss, and the conical copper column 19 passes through the wall of the high-pressure combustion chamber 1 and is insulated from the high-pressure combustion chamber 1.

[0040] See also Figure 2 The high-pressure combustion chamber 1 includes a cavity, a high-pressure combined sealing gasket, a side boss 9 and a combustion chamber cover plate 16.

[0041] The volume of the cavity is 1.571L, the diameter is 10cm, and the height is 20cm. Four holes are opened on the left and right sides of the cavity, which are used to install the copper electrode terminal 14, the pressure sensor 15, the air inlet pipeline 12 and the air outlet pipeline 13 respectively. The pressure sensor 15 is connected to the solenoid valve, and the solenoid valve is connected to the PID pressure controller 4 and the solid-state relay to transmit the electrical signal to the PID pressure controller 4 for the logic control of the high-pressure combustion chamber 1 to release gas. Two window covers 11 are respectively arranged at the front and back of the cavity, and a sapphire visualization window 10 is arranged above the window cover 11, and a side boss 9 is arranged above the sapphire visualization window 10. A high-speed camera 6 is arranged on one side of the window cover 11, and the high-speed camera 6 is adjusted to be parallel to the visualization window of the high-pressure combustion chamber 1 to record the flame image of the combustion process. Specifically, the high-speed camera 6 observes the flame combustion state in real time through the sapphire window on the combustion chamber, records the propellant grain retreat process, and then obtains the burning rate, and can also use the graphics processing algorithm to process the flame RGB three-primary color captured by the high-speed camera 6 to obtain the flame temperature distribution. The real-time combustion state of the solid propellant and the time taken for the burning surface to move a certain distance are observed and recorded through the sapphire visualization window 10 and the high-speed camera 6.

[0042] A combustion chamber cover plate 16 is provided on the upper part of the high-pressure combustion chamber 1. The combustion chamber cover plate 16, the sapphire visualization window 10 and the window cover plate 11 are tightened by means of a high-pressure combined sealing gasket and a thread 17, so that the cavity is in a completely sealed state, thereby ensuring the accuracy of the test results.

[0043] The high-pressure combustion chamber 1 is arranged in a high-precision high and low temperature experimental box 3. A cylindrical sample table 2 is arranged at the center position of the bottom of the cavity of the high-pressure combustion chamber 1. Two electrodes 18 are fixed on the cylindrical sample table 2. One of the electrodes is connected to the copper electrode terminal 14 on the wall of the high-pressure combustion chamber 1. The copper electrode terminal 14 is connected to the DC power supply 5 through an ignition circuit. A nickel-chromium wire is arranged between the two electrodes for igniting the propellant.

[0044] The propellant strip is fixed on the cylindrical sample stage 2 and burns. The high-precision high and low temperature test box 3 is connected to an external refrigerator. The high-precision high and low temperature test box 3 controls the ambient temperature required by the high-pressure combustion chamber 1, which can not only achieve dynamic temperature adjustment within the range of -45 to 80°C, but also observe the combustion of the propellant in the combustion chamber.

[0045] The method for using the combustion performance parameter testing device for low-cost solid propellant within a wide temperature range as described above comprises the following steps:

[0046] In the first step, plasticizer (DOA), curing agent (IPDI), binder (HTPB), curing catalyst (TIN) and burning rate regulator (Al) are mixed evenly, poured into a mold, and prepared into a propellant strip, and the propellant strip is fixed on a cylindrical sample stage 2, and the cylindrical sample stage 2 is fixed at the bottom center of the high-pressure combustion chamber 1; then, nickel-chromium wire is wound around the two electrodes of the cylindrical sample stage 2 and contacts with the surface of the propellant strip; finally, it is blocked by a combustion chamber cover plate 16 with a sealing ring and tightened with a thread 17, and the inside of the cavity is in a completely sealed state.

[0047] The second step is to set the temperature of the high-precision high and low temperature test box 3. When the high-pressure combustion chamber 1 drops to the set temperature value, continue to refrigerate for about 1 hour to make the temperature inside and outside the cavity of the high-pressure combustion chamber 1 consistent.

[0048] In the third step, the DC power supply 5 of the electric ignition module is respectively in contact with the copper electrode terminal 14 of the high-pressure combustion chamber 1 and the outside of the cavity of the high-pressure combustion chamber 1.

[0049] In the fourth step, the valve of the nitrogen bottle 7 is opened, and the nitrogen enters the high-pressure combustion chamber 1 through the air intake pipe 12. The pressure sensor 15, the PID pressure controller 4 and the solenoid valve work together to make the preset pressure value in the high-pressure combustion chamber 1. Specifically, when the pressure in the high-pressure combustion chamber is greater than the PID set value, the PID pressure controller energizes the solid-state relay, thereby controlling the opening of the solenoid valve to reduce the pressure in the high-pressure combustion chamber by venting.

[0050] The fifth step is to aim the high-speed camera 6 at any visible window of the high-pressure combustion chamber 1 and adjust the high-speed camera 6 to focus it.

[0051] The sixth step is to turn on the DC power supply 5, ignite the propellant, and use the high-speed camera 6 to capture the flame image through the sapphire window 10 on the high-pressure combustion chamber 1 to record the propellant grain retreat process.

[0052] In the seventh step, when the combustion is terminated, the solenoid valve opens, and the gas in the high-pressure combustion chamber 1 reaches the combustion gas buffer bottle 8 through the gas outlet pipeline 13 and is discharged.

[0053] In the eighth step, the image of the propellant grain combustion process taken by the high-speed camera 6 is used to obtain the solid propellant burning rate by dividing the distance traveled by the grain by the time.

[0054] The ninth step is to plot the trend of the calculated burning rate versus pressure to obtain the pressure index of the propellant.

[0055] The tenth step is to plot the trend of the calculated burning rate versus temperature to obtain the burning rate temperature coefficient of the propellant.

[0056] In the eleventh step, the flame image captured by the high-speed camera 6 is processed by a graphics processing algorithm to obtain RGB three-primary colors, and then the RGB three-primary colors are used to obtain a flame temperature distribution diagram.

[0057] The present invention controls the ambient temperature of the combustion chamber and the propellant grain through a high and low temperature test chamber, and the temperature control range is -45°C to 80°C, which meets the initial temperature requirements of different environments for solid propellant burning rate testing. The end face retreat process and flame structure images of the propellant under different ambient temperatures and pressures in a closed combustion chamber are photographed by high-speed photography, and the burning rate, pressure index, temperature coefficient and flame temperature distribution of the propellant are calculated, which has the advantages of accurate testing, simple operation, low cost and high safety performance.

[0058] Moreover, the high-pressure combustion chamber of the present invention has a simple structure and a small volume. The exterior of the cavity is a cubic shape, and the interior is a hollow cylinder. The exterior is connected to the inlet and exhaust pipelines, the nitrogen bottle and the buffer bottle. The welding process is simple, and it is easy to move without complex external line valves, which saves time, labor and raw materials, and has a low manufacturing process cost.

[0059] The above description is only for the best embodiment of the present invention, but it should not be understood as limiting the claims. The present invention is not limited to the above embodiments, and its specific structure is allowed to be changed. However, all changes made within the protection scope of the independent claims of the present invention are within the protection scope of the present invention.

[0060] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used herein in the specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention. The term "and / or" used herein includes any and all combinations of one or more related listed items.

Claims

1. A low-cost solid propellant combustion performance parameter testing device within a wide temperature range, characterized in that: It comprises a high-pressure combustion chamber (1), a cylindrical sample stand (2), a high-precision high and low temperature experimental box (3), a combustion chamber pressure control module and an electric ignition module; The high-pressure combustion chamber (1) is arranged in a high-precision high-low temperature experimental box (3), a cylindrical sample table (2) is arranged in the high-pressure combustion chamber (1), and a combustion chamber pressure control module and an electric ignition module are connected to the high-pressure combustion chamber (1).

2. The combustion performance parameter testing device for low-cost solid propellant in a wide temperature range according to claim 1, characterized in that: The combustion chamber pressure control module comprises a PID pressure controller (4), a solid-state relay, a high-pressure nitrogen bottle (7), a combustion gas buffer bottle (8), an air inlet pipeline (12), an air outlet pipeline (13) and a solenoid valve, wherein the high-pressure nitrogen bottle (7), the combustion gas buffer bottle (8), the air inlet pipeline (12) and the air outlet pipeline (13) are connected to the high-pressure combustion chamber (1), the PID pressure controller (4) is connected to the solid-state relay, the solid-state relay is connected to the solenoid valve, and the solenoid valve is connected to the air outlet pipeline (13).

3. The combustion performance parameter testing device for low-cost solid propellant in a wide temperature range according to claim 1, characterized in that: The electric ignition module comprises a direct current power supply (5), an ignition circuit and a copper electrode terminal (14), wherein the copper electrode terminal (14) comprises a conical copper column (19) and a plug for sealing the conical copper column (19), a conical gasket made of phenolic resin is arranged between the plug and the conical copper column (19), and the conical copper column (19) is fixed to the wall surface of the high-pressure combustion chamber (1) through the plug.

4. The combustion performance parameter testing device for low-cost solid propellant in a wide temperature range according to claim 3, characterized in that: The high-pressure combustion chamber (1) comprises a cavity, window covers (11) are arranged at the front and rear of the cavity, a sapphire visualization window (10) is arranged above the window cover (11), and a side boss (9) is arranged above the sapphire visualization window (10); a high-speed camera (6) is arranged on one side of the sapphire visualization window (10), and a plurality of holes for installing copper electrode terminals (14), a pressure sensor (15), an air inlet pipeline (12) and an air outlet pipeline (13) are opened at both ends of the cavity.

5. The combustion performance parameter testing device for low-cost solid propellant in a wide temperature range according to claim 4, characterized in that: A combustion chamber cover plate (16) is provided at one end of the high-pressure combustion chamber (1), and the combustion chamber cover plate (16) and the high-pressure combustion chamber (1) are sealed via a high-pressure combined sealing gasket.

6. The combustion performance parameter testing device for low-cost solid propellant in a wide temperature range according to claim 5, characterized in that: Two electrodes (18) are fixed on the cylindrical sample stage (2), one of which is connected to a copper electrode terminal (14) on the wall of the high-pressure combustion chamber (1), the outer end of the copper electrode terminal (14) is connected to a direct current power supply (5) via an ignition circuit, and a nickel-chromium wire is arranged between the two electrodes on the cylindrical sample stage (2).

7. A method for testing combustion performance parameters of low-cost solid propellant in a wide temperature range based on the device of claim 4, characterized in that: The following steps are involved: The propellant strip is fixed on a cylindrical sample stage (2), and the cylindrical sample stage (2) is fixed at the center of the bottom of the high-pressure combustion chamber (1), the high-pressure combustion chamber (1) is sealed, and the pressure in the high-pressure combustion chamber (1) reaches a preset value; The propellant powder strip is ignited, and the burning rate of the solid propellant is obtained by calculating the change of the burning surface of the solid propellant over time using the flame image taken by the high-speed camera (6).

8. A method for testing combustion performance parameters of low-cost solid propellant in a wide temperature range according to claim 7, characterized in that: Before the combustion test, high-pressure nitrogen is filled into the combustion chamber. When the pressure is higher than the set pressure, the PID pressure controller releases the pressure to the set value. During the combustion test, when the pressure in the combustion chamber is higher than the set pressure, the PID pressure controller controls the solenoid valve to release the pressure to the set pressure, and maintains the pressure stable by releasing the combustion gas.

9. A method for testing combustion performance parameters of low-cost solid propellant in a wide temperature range according to claim 7, characterized in that: Also includes: By testing the burning rate at multiple ambient temperatures under the same combustion chamber pressure, the burning rate versus temperature curve of the solid propellant is obtained, and the burning rate temperature coefficient of the propellant is calculated; By testing the burning rate at multiple pressures at the same ambient temperature, the burning rate versus pressure curve of the solid propellant is obtained, and the pressure index of the propellant is calculated.

10. A method for testing combustion performance parameters of low-cost solid propellant in a wide temperature range according to claim 7, characterized in that: According to the flame image taken by the high-speed camera, the flame image is processed by the graphic processing algorithm to obtain the RGB three-primary color, and then the flame temperature distribution map is obtained.

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