A solid propellant failure mode test device under temperature-pressure coordinated process

Abstract

The present invention relates to the field of solid propellant technology, and in particular to a solid propellant failure mode test device under a temperature-pressure coordinated process. The device comprises a support frame, the support frame is fixedly connected to an outer shell, the interior of the outer shell is fixedly connected to a star-shaped plate, the star-shaped plate divides the interior of the outer shell into a circumferential array of test cavities, a heating plate is installed in the test cavity, the star-shaped plate is slidably connected to a movable block in a circumferential array, the movable block is fixedly connected to a mounting shell, the mounting shell is connected to a delivery pipe, the mounting shell is slidably connected to a first piston rod in a circumferential array, and the first piston rod is fixedly connected to a first locking block. The present invention injects liquid into the delivery pipe so that the first locking block clamps and squeezes the solid propellant, and adjusts the degree of pressurization of the solid propellant according to the amount of liquid, adjusts the heat release of the heating plate, and divides the test cavity in the circumferential array into two groups of test areas, namely, constant temperature and constant pressure, so as to detect the failure of the solid propellant under different temperature and pressure environments.

Description

Technical Field

[0001] The present invention relates to the technical field of solid propellants, and in particular to a solid propellant failure mode test device under a temperature-pressure coordinated process. Background Art

[0002] The temperature-pressure synergistic process is a novel solid propellant production process that utilizes heat processing of solid propellant fuel under high temperature and pressure to produce high-performance solid propellants. Before using solid propellants, failure mode testing is required to ensure proper combustion. Simulating high-temperature and high-pressure environments and conducting combustion tests on solid propellants is a common test method for detecting failures in solid propellants. During these tests, the thrust and combustion time of the solid propellant are measured.

[0003] When simulating a high-pressure environment, a safety clamp is usually used to pressurize the solid propellant. The clamp needs to be fixed to the outer shell of the solid propellant and the pressure is applied by adjusting the clamp tension. However, during the pressurization process, the safety clamp cannot ensure that it applies uniform pressure to the solid propellant, resulting in failure of the high-pressure environment simulation and inaccurate analysis of the failure of the solid propellant by the operator. In addition, the impulse generated at the moment of ignition of the solid propellant causes the detection device to shake, resulting in inaccurate thrust measurement of the solid propellant by the detection device, thereby affecting the test data. Summary of the Invention

[0004] In order to overcome the shortcomings mentioned in the above background technology, the present invention provides a solid propellant failure mode test device under a temperature-pressure coordinated process.

[0005] The technical implementation scheme of the present invention is: a solid propellant failure mode test device under a temperature-pressure coordinated process, including a support frame, the support frame is fixedly connected to an outer shell, the inner part of the outer shell is fixedly connected to a star-shaped plate, the star-shaped plate divides the inner part of the outer shell into a circumferential array of test cavities, the number of test cavities is an even number, a heating plate is installed in the test cavity, the outer shell is rotatably connected to a sealing plate, the side of the outer shell away from the sealing plate is fixedly connected to a fixed frame, the fixed frame is slidably connected to a movable plate of a circumferential array, the fixed frame is provided with a detection member, the detection member is used to detect the thrust of the solid propellant, the star-shaped plate is slidably connected to a movable block of a circumferential array, the movable block is fixed to a cylindrical mounting shell, the mounting shell The number is consistent with the number of test cavities, the mounting shell is provided with a liquid storage cavity, the mounting shell is connected with a delivery pipe, the outer shell is slidably connected with a circumferential array of baffles, the delivery pipe passes through adjacent baffles, the mounting shell is slidably connected with a first piston rod of the circumferential array, the first piston rod is fixedly connected with a first locking block, and liquid is injected into the delivery pipe, so that the first piston rod drives the first locking block to clamp and squeeze the solid propellant, and the degree of pressurization of the solid propellant is adjusted according to the amount of injected liquid, and the heat release of the heating plate is adjusted, so that the test cavity of the circumferential array is divided into two groups of test areas of constant temperature and constant pressure, and the failure conditions of the solid propellant under different temperature and pressure environments are detected.

[0006] More preferably, the sealing plate is a heat insulating plate for maintaining a constant temperature in the test cavity.

[0007] More preferably, the mounting shell is connected with a liquid outlet pipe, which passes through the fixed plate and the adjacent movable plate. Both the liquid outlet pipe and the delivery pipe are equipped with valves to keep the temperature of the liquid in the liquid storage chamber constant.

[0008] More preferably, the detection member includes a thrust detector, which is fixed to a side of the movable plate away from the mounting shell, the fixing frame is fixed to the fixing plate, and springs are fixed between the circumferential array of thrust detectors and the fixing plate.

[0009] More preferably, the shell is equipped with a fan, the fan is connected to an air duct, the air duct runs through the shell, the star-shaped plate is provided with a circumferential array of blowing holes, the direction of the blowing holes is parallel to the axis of the mounting shell, and the fan is connected to the blowing holes through the air duct.

[0010] More preferably, the mounting shell is slidably connected to a second piston rod in a circumferential array, the second piston rod is fixedly connected to a second locking block, the second locking block is provided with a through groove, the second locking block is made of a soft material, and the mounting shell is slidably connected to a third piston rod in a circumferential array, the third piston rod is fixedly connected to a third locking block, and the third locking block is located inside the through groove of the second locking block.

[0011] More preferably, the length of the second piston rod is shorter than that of the first piston rod, so as to prevent the second locking block from getting stuck with the adjacent first locking block.

[0012] More preferably, the first locking block and the third locking block are both made of soft materials for tightly fitting the solid propellant.

[0013] More preferably, the mounting shell is provided with a circumferentially equidistant array of grooves, the grooves are fixed with an arc plate, the second locking block is slidably connected to the first limiting rod, the third locking block is provided with a limiting groove, the first limiting rod is limitedly matched with the limiting groove of the third locking block, the first limiting rod is fixed with a fixed block, a tension spring is fixed between the first limiting rod and the adjacent second locking block, and the arc plate is limitedly matched with the fixed block.

[0014] More preferably, the second locking block is slidably connected to a second limiting rod, a spring is fixed between the second limiting rod and the adjacent second locking block, the mounting shell is provided with a circumferentially equidistant array of special-shaped grooves, an inclined surface is provided inside the special-shaped groove, and the second limiting rod is limitedly matched with the adjacent special-shaped groove.

[0015] Compared with the prior art, the present invention has the following advantages: the present invention divides the outer shell into multiple test chambers through a star-shaped plate, and the operator adjusts the temperature and pressure of the solid propellant in each test chamber, tests the failure of the solid propellant in different environments, and conducts comparative analysis; the solid propellant is buffered by a spring between the thrust detector and the fixed plate to prevent the impulse of the solid propellant from being too large at the moment of ignition, causing the device to shake, thereby affecting the detection accuracy of the thrust detector; the fan blows air into the blowing hole so that the wind blown out of the blowing hole drives the exhaust gas and smoke generated by the combustion of the solid propellant away from the solid propellant, preventing the exhaust gas and smoke from affecting the combustion of the solid propellant; the second locking block cooperates with the first locking block, and the first locking block cooperates with the third locking block, so that solid propellants of different diameters are fully clamped, so that the force area of ​​the solid propellant is close to its surface area, and the pressure is evenly distributed on the solid propellant. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention.

[0017] Figure 2 It is a schematic diagram of the three-dimensional structure of the fixing plate, conveying pipe and other parts of the present invention.

[0018] Figure 3 It is a three-dimensional structural diagram of the movable plate, the fixing frame and other parts of the present invention.

[0019] Figure 4 It is a schematic diagram of the three-dimensional structure of the star-shaped plate, movable block and other parts of the present invention.

[0020] Figure 5 It is a schematic diagram of the three-dimensional structure of the star-shaped plate and the mounting shell and other parts of the present invention.

[0021] Figure 6This is a positional relationship diagram of the mounting shell and the first locking block of the present invention.

[0022] Figure 7 This is a positional relationship diagram of the first locking block, the second locking block and other parts of the present invention.

[0023] Figure 8 This is a positional relationship diagram of the second locking block, the third locking block and other parts of the present invention.

[0024] Figure 9 This is a schematic diagram of the three-dimensional structure of the mounting housing, the third piston rod and other parts of the present invention.

[0025] Figure 10 For the present invention Figure 9 A magnified view of the three-dimensional structure in FIG.

[0026] Figure 11 This is a diagram showing the positional relationship between the first limiting rod and the fixing block and other parts of the present invention.

[0027] Figure 12 This is a positional relationship diagram of the second limiting rod, the second locking block and other parts of the present invention.

[0028] Among them, the above-mentioned drawings include the following drawing marks: 101, support frame, 102, outer shell, 1021, fixed frame, 103, star-shaped plate, 104, sealing plate, 105, movable plate, 106, thrust detector, 107, fixed plate, 108, fan, 109, blowing hole, 201, movable block, 202, mounting shell, 2021, liquid storage chamber, 203, delivery pipe, 2031, baffle, 204, first locking block, 205, second locking block, 206, third locking block, 207, arc plate, 208, first limiting rod, 209, fixed block, 210, liquid outlet pipe, 211, first piston rod, 212, second piston rod, 213, third piston rod, 214, second limiting rod, 215, special-shaped groove. DETAILED DESCRIPTION

[0029] The following is a clear and complete description of the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0030] Example 1: A solid propellant failure mode test device under temperature and pressure synergistic process, such as Figure 1-Figure 7As shown, it includes a support frame 101, a ring-shaped shell 102 is fixedly connected to the top of the support frame 101, a star-shaped plate 103 is fixedly connected to the inside of the shell 102, the star-shaped plate 103 divides the inside of the shell 102 into six test cavities in a circumferential array, a heating plate is installed in the test cavity, and the heating plate heats each test cavity, the shell 102 is rotatably connected to a sealing plate 104, the sealing plate 104 is located in front of the shell 102, the sealing plate 104 is a heat insulation plate, used to keep the temperature in the test cavity constant and prevent heat from different test cavities from being transferred to each other, a fixed frame 1021 is fixed to the rear side of the shell 102, the fixed frame 1021 is slidably connected to six movable plates 105 in a circumferential array, the fixed frame 1021 is provided with a detection piece for detecting the thrust of the solid propellant, the star-shaped plate 103 is slidably connected to a movable block 201 in a circumferential array, and the movable block 201 is fixed There are six cylindrical mounting shells 202, and a liquid storage cavity 2021 is provided inside the mounting shell 202. The mounting shell 202 is connected to a delivery pipe 203, and the delivery pipe 203 is used to deliver liquid to the adjacent liquid storage cavity 2021. The outer shell 102 is slidably connected to six baffles 2031 in a circumferential array. The delivery pipe 203 passes through the adjacent baffles 2031. The mounting shell 202 is slidably connected to a first piston rod 211 in a circumferential array. The first piston rod 211 is fixedly connected to the first locking block 204. By injecting liquid into the delivery pipe 203, the first piston rod 211 drives the first locking block 204 to clamp and squeeze the solid propellant, and the degree of pressurization of the solid propellant is adjusted according to the amount of injected liquid, and the heat release of the heating plate is adjusted, so that the test cavity of the circumferential array is divided into two groups of test areas of constant temperature and constant pressure, so as to detect the failure of the solid propellant under different temperature and pressure environments.

[0031] like Figure 1-Figure 3 and Figure 5 As shown, the detection part includes a thrust detector 106, which is fixed to the rear side of the movable plate 105, and a fixed plate 107 is fixed to the rear side of the fixed frame 1021. Springs for buffering solid propellants are fixed between the circumferential array of thrust detectors 106 and the fixed plate 107. The outer shell 102 is equipped with a fan 108, and the fan 108 is connected to an air duct, which runs through the outer shell 102. The star-shaped plate 103 is provided with a circumferential array of blowing holes 109, and the direction of the blowing holes 109 is parallel to the axis of the mounting shell 202. The fan 108 is connected to the blowing holes 109 through the air duct, and the fan 108 blows air forward from the blowing holes 109 through the air duct, so that the wind drives the smoke generated by the combustion of the solid propellant to move forward, thereby preventing the smoke from affecting the combustion of other solid propellants.

[0032] like Figure 7-11As shown, the mounting shell 202 is slidably connected to a second piston rod 212 in a circumferential array, and the second piston rod 212 is fixedly connected to a second locking block 205. The second locking block 205 is provided with a through groove, and the mounting shell 202 is slidably connected to a third piston rod 213 in a circumferential array, and the third piston rod 213 is fixedly connected to a third locking block 206. The third locking block 206 is located inside the through groove of the second locking block 205. The second locking block 205, the first locking block 204 and the third locking block 206 are all made of soft materials and are used to fit the solid propulsion unit tightly. The mounting shell 202 is provided with a circumferentially equidistant array of grooves, and an arc plate 207 is fixed inside the groove. The arc plate 207 gradually tilts forward in the direction close to the mounting shell 202. The second locking block 205 is slidably connected to the first limiting rod 208, and the third locking block 206 is provided with a limiting groove. The first limiting rod 208 and the third limiting rod 206 are fixedly connected to the third locking block 206. The limiting groove of the third locking block 206 is limited and matched, and the first limiting rod 208 limits the third locking block 206 through the limiting groove. The first limiting rod 208 is fixedly connected to a fixed block 209, and the fixed block 209 is a sphere. A tension spring for resetting the first limiting rod 208 is fixedly connected between the first limiting rod 208 and the adjacent second locking block 205. The front side of the arc plate 207 is limited and matched with the fixed block 209. The mounting shell 202 is connected to a liquid outlet pipe 210. The liquid outlet pipe 210 passes through the fixed plate 107 and the adjacent movable plate 105. Valves are installed on the liquid outlet pipe 210 and the delivery pipe 203. The liquid outlet pipe 210 discharges the liquid in the liquid storage chamber 2021. The liquid outlet pipe 210 cooperates with the delivery pipe 203 to keep the liquid in the liquid storage chamber 2021 in a flowing state, thereby keeping the liquid temperature in the liquid storage chamber 2021 constant, ensuring that the solid propellant is evenly heated.

[0033] When using this device to test the failure of solid propellant, the operator places six solid propellants into six mounting shells 202 respectively, and presses the sealing end of each solid propellant against the adjacent movable plate 105. Then the operator closes the sealing plate 104 and turns on the heating plate to make the three test chambers on the lower side at the same temperature and the three test chambers on the upper side at different temperatures. Then the operator injects heated liquid into the delivery pipe 203. The temperature of the liquid is consistent with the temperature of the adjacent heating plate. The liquid enters the adjacent mounting shell 202 through the delivery pipe 203. The liquid gradually increases in the liquid storage chamber 2021. The liquid squeezes the first piston rod 211 of the circumferential array, so that the first piston rod 211 drives the adjacent first locking block 204 to protrude. When the first locking block 204 contacts the solid propellant, the end of the first locking block 204 in contact with the solid propellant is deformed to adapt to the diameter of the solid propellant. The first locking block 204 preliminarily fixes and clamps the solid propellant.

[0034] As the first piston rod 211 drives the adjacent first locking block 204 to extend, the liquid squeezes the second piston rod 212 of the circumferential array, and the second piston rod 212 drives the adjacent second locking block 205 to extend. The second locking block 205 drives the adjacent third locking block 206 to move, and the second locking block 205 drives the adjacent first limiting rod 208 and the adjacent fixed block 209 to approach the solid propulsion device. The fixed block 209 moves along the adjacent curved plate 207, so that the fixed block 209 drives the adjacent first limiting rod 208 away from the adjacent third locking block 206, and the first limiting rod 208 and the adjacent second locking block 205 are in a closed position. The tension spring between the two parts is stretched. Due to the different diameters of different solid propellants, when the second locking block 205 contacts the solid propellant during movement, the second locking block 205 further clamps the solid propellant. The operator adjusts the extrusion force of the second locking block 205 and the first locking block 204 on the solid propellant by controlling the amount of liquid delivered by the delivery pipe 203. The second locking block 205 and the first locking block 204 cooperate to clamp solid propellants of different diameters, so that the extruded area of ​​the solid propellant is close to the surface area of ​​the solid propellant, so that the solid propellant is subjected to uniform extrusion force, thereby ensuring the accuracy of the test.

[0035] As the second locking block 205 moves, the first limiting rod 208 moves away from the adjacent third locking block 206. When the first limiting rod 208 loses contact with the adjacent third locking block 206, the first limiting rod 208 releases the limit of the third locking block 206. At the same time, the piston of the second piston rod 212 fits with the mounting shell 202, and the second piston rod 212 and the second locking block 205 no longer move, preventing the second locking block 205 from contacting and getting stuck with the adjacent first limiting rod 208. As the operator continues to deliver liquid to the liquid storage chamber 2021, under the action of the pressure of the liquid, the third piston rod 213 drives the third locking block 206 to move, and the surrounding The third locking block 206 of the array approaches the solid propulsion device along the adjacent second locking block 205. When the third locking block 206 contacts the solid propulsion device, the third locking block 206 further fixes and clamps the solid propulsion device. The operator adjusts the squeezing force of the first locking block 204 and the third locking block 206 on the solid propellant by controlling the amount of liquid delivered by the delivery pipe 203. The third locking block 206 cooperates with the first locking block 204 to clamp the solid propulsion devices of different diameters, so that the squeezed area of ​​the solid propulsion device is close to the outer surface area of ​​the solid propulsion device, so that the solid propellant is subjected to uniform squeezing force, thereby ensuring the accuracy of the test.

[0036] The operator delivers liquid to the delivery pipe 203 so that the pressure on the solid propellant reaches the value required by the operator. The operator then opens the valve of the liquid outlet pipe 210 to allow the liquid to flow out of the liquid outlet pipe 210 and adjusts the speed at which the liquid is delivered by the delivery pipe 203 to keep the pressure on the solid propellant unchanged, the liquid in the liquid storage chamber 2021 in a flowing state, and the temperature of the liquid in the liquid storage chamber 2021 unchanged, thereby ensuring that the solid propellant is in an environment with a balanced temperature, thereby ensuring the accuracy of the test data. The operator subjects the three solid propellants on the upper side to different pressures and the three solid propellants on the lower side to the same pressure. The three solid propellants on the upper side are at the same temperature but different pressures, while the three solid propellants on the lower side are at the same pressure but different temperature, thereby forming a comparison, which helps the operator analyze the failure of the solid propellant.

[0037] The operator places the solid propellant in the test chamber. When the solid propellant has been placed for a time set by the operator, the operator opens the sealing plate 104 to prevent the formation of a closed environment inside the shell 102, thereby affecting the thrust and burning time of the solid propellant. The operator turns on the fan 108, and the wind from the fan 108 blows out from the blowing hole 109. Then the operator ignites six solid propellants at the same time through the igniter and times the burning time of each solid propellant. The solid propellant drives the adjacent mounting shell 202 and the adjacent movable block 201 to move backward, and the solid propellant drives the delivery pipe 203 and the liquid outlet pipe 210 to move backward, so that the block The piece 2031 moves backward, and the solid propellant squeezes the thrust detector 106 through the movable plate 105. The spring between the thrust detector 106 and the fixed plate 107 is compressed, and the solid propellant is buffered to prevent the instantaneous impulse after the solid propellant is ignited from being too large, causing the device to shake, thereby affecting the thrust accuracy measured by the thrust detector 106. When the solid propellant is burning, a large amount of exhaust gas generated by the solid propellant moves upward, and the wind blown out of the blowing hole 109 blows the exhaust gas generated by the combustion of the solid propellant forward, avoiding the exhaust gas generated by the solid propellant below interfering with the combustion of the solid propellant above, resulting in the thrust generated by the combustion of the solid propellant and the burning time being affected.

[0038] After the six solid propellants have been burned, the operator stops delivering liquid to the delivery pipe 203 and discharges the liquid from the liquid storage chamber 2021 through the liquid outlet pipe 210 so that the solid propellant is no longer subjected to the squeezing force. The operator turns off the heating plate and removes the solid propellant to observe the residual condition of the grain. The operator observes the combustion condition of the solid propellant and conducts a comparative analysis of each solid propellant to determine the failure condition of the solid propellant under different environments.

[0039] Example 2: Based on Example 1, Figure 10 and 12As shown, the second locking block 205 is slidably connected to the second limiting rod 214, and a spring that is always in a compressed state is fixed between the second limiting rod 214 and the adjacent second locking block 205. The mounting shell 202 is provided with a circumferentially equidistant array of special-shaped grooves 215, and the interior of the special-shaped grooves 215 is provided with an inclined surface, and the second limiting rod 214 is limitedly matched with the inclined surface of the adjacent special-shaped grooves 215.

[0040] In the process of the second piston rod 212 driving the adjacent second locking block 205 to extend, the second locking block 205 drives the adjacent second limiting rod 214 to move along the special-shaped groove 215. When the second locking block 205 contacts the inclined surface of the adjacent special-shaped groove 215, the spring between the second limiting rod 214 and the adjacent second locking block 205 gradually rebounds. When the plug rod of the second piston rod 212 contacts the mounting shell 202, the second locking block 205 stops moving, and the second limiting rod 214 is located on the side of the adjacent special-shaped groove 215 close to the solid propellant.

[0041] During the process of the liquid outlet pipe 210 discharging the liquid from the liquid storage chamber 2021, the squeezing force of the liquid on the first piston rod 211, the second piston rod 212 and the third piston rod 213 is reduced, thereby reducing the squeezing force of the first locking block 204, the second locking block 205 and the third locking block 206 on the solid propellant. As the liquid decreases, the first piston rod 211 drives the adjacent first locking block 204 to gradually move away from the adjacent solid propellant, and the third piston rod 213 drives the adjacent third locking block 206 to gradually move away from the adjacent solid propellant. Since the spring between the second limiting rod 214 and the mounting shell 202 is always in a compressed state, the reset of the second locking block 205 requires first making the second limiting rod 214 move away from the solid propellant along the inclined surface of the adjacent special-shaped groove 215, so that the second limiting rod 214 and the mounting shell 20 2 is further compressed. At this time, the reduction of liquid is not enough to make the second piston rod 212 drive the second locking block 205 away from the solid propulsion device. As the third locking block 206 continues to move, the axis of the first limiting rod 208 coincides with the axis of the limiting groove of the third locking block 206. Under the action of the tension of the tension spring between the first limiting rod 208 and the adjacent second locking block 205, the first limiting rod 208 extends into the limiting groove of the third locking block 206. The liquid drives the third locking block 206 and the second locking block 205 to move through the third piston rod 213, so that the second locking block 205 drives the second limiting rod 214 to move along the inclined surface of the special-shaped groove 215. The spring between the second limiting rod 214 and the mounting shell 202 is further compressed, and the second locking block 205 and the third locking block 206 are gradually reset.

[0042] Although the present disclosure has been shown and described with reference to certain exemplary embodiments thereof, it will be understood by those skilled in the art that various changes in form and details may be made to the present disclosure without departing from the spirit and scope of the present disclosure as defined by the appended claims and their equivalents. Therefore, the scope of the present disclosure should not be limited to the above-described embodiments, but should be determined not only by the appended claims but also by the equivalents of the appended claims.

Claims

1. A solid propellant failure mode test device under temperature and pressure synergistic process, characterized by comprising A support frame (101) is provided, the top of the support frame (101) is fixedly connected to an annular shell (102), the inside of the shell (102) is fixedly connected to a star-shaped plate (103), the star-shaped plate (103) divides the inside of the shell (102) into a circumferential array of test cavities, the number of the test cavities is an even number, a heating plate is installed in the test cavity, the shell (102) is rotatably connected to a sealing plate (104), a side of the shell (102) away from the sealing plate (104) is fixedly connected to a fixed frame (1021), the inside of the fixed frame (1021) is slidably connected to a movable plate (105) of a circumferential array, a movable block (201) of a circumferential array is slidably connected to the star-shaped plate (103), a cylindrical mounting shell (202) is fixedly connected to the movable block (201), the number of the mounting shells (202) is consistent with the number of the test cavities, and a liquid storage cavity (202) is provided on the inner side of the mounting shell (202). 1) The mounting shell (202) is connected to a delivery pipe (203), the delivery pipe (203) is used to deliver liquid to an adjacent liquid storage chamber (2021), a circumferential array of baffles (2031) is slidably connected to the outer shell (102), the delivery pipe (203) passes through the adjacent baffles (2031), the inner side of the mounting shell (202) is slidably connected to a circumferential array of first piston rods (211), the first piston rods (211) are fixedly connected to a first locking block (204), and by injecting liquid into the delivery pipe (203), the first piston rods (211) drive the first locking block (204) to clamp and squeeze the solid propellant, and the degree of pressurization of the solid propellant is adjusted according to the amount of injected liquid, and the heat release of the heating plate is adjusted, so that the test chamber of the circumferential array is divided into two groups of test areas of constant temperature and constant pressure, and the failure conditions of the solid propellant under different temperature and pressure environments are detected; The detection member includes a thrust detector (106), which is fixed to a side of the movable plate (105) away from the mounting shell (202).

2. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 1 is characterized in that: The sealing plate (104) is a heat insulating plate used to maintain a constant temperature in the test cavity.

3. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 2 is characterized in that: The mounting shell (202) is connected to a liquid outlet pipe (210), which passes through the fixed plate (107) and the adjacent movable plate (105). The liquid outlet pipe (210) and the delivery pipe (203) are both equipped with valves to keep the temperature of the liquid in the liquid storage chamber (2021) constant.

4. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 3 is characterized in that: A fixing plate (107) is fixedly connected to one side of the fixing frame (1021) away from the housing (102), and springs are fixedly connected between the thrust detectors (106) of the circumferential array and the fixing plate (107).

5. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 4 is characterized in that: The support frame (101) is equipped with a fan (108), the fan (108) is connected to an air duct, the air duct passes through the shell (102), the star plate (103) is provided with a circumferential array of blowing holes (109), the direction of the blowing holes (109) is parallel to the axis of the mounting shell (202), and the fan (108) is connected to the blowing holes (109) through the air duct.

6. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 5 is characterized in that: The inner side of the mounting shell (202) is slidably connected to a second piston rod (212) in a circumferential array, the first piston rod (211) and the second piston rod (212) are spaced apart, the second piston rod (212) is fixedly connected to a second locking block (205), the second locking block (205) is provided with a through groove, the second locking block (205) is made of a soft material, the mounting shell (202) is slidably connected to a third piston rod (213) in a circumferential array, the third piston rod (213) is fixedly connected to a third locking block (206), and the third locking block (206) is located inside the through groove of the second locking block (205).

7. The solid propellant failure mode test device under temperature-pressure coordinated process according to claim 6, characterized in that: The length of the second piston rod (212) is shorter than that of the first piston rod (211), thereby preventing the second locking block (205) from being stuck with the adjacent first locking block (204).

8. The solid propellant failure mode test device under temperature-pressure coordinated process according to claim 7, characterized in that: The first locking block (204) and the third locking block (206) are both made of soft material and are used to fit tightly against the solid propellant.

9. The solid propellant failure mode test device under the temperature-pressure coordinated process according to claim 8, characterized in that: The mounting shell (202) is provided with a circumferentially equidistant array of grooves, the grooves are fixedly connected to an arc plate (207), the arc plate (207) gradually tilts forward in a direction close to the mounting shell (202), a through groove is provided on the arc plate (207), the second locking block (205) is slidably connected to a first limiting rod (208), the third locking block (206) is provided with a limiting groove, the first limiting rod (208) is limitedly matched with the limiting groove of the third locking block (206), the first limiting rod (208) is fixedly connected to a fixed block (209), the fixed block (209) slides along the through groove of the arc plate (207), a tension spring is fixedly connected between the first limiting rod (208) and the adjacent second locking block (205), and the front side of the arc plate (207) is limitedly matched with the fixed block (209).

10. The solid propellant failure mode test device under temperature-pressure coordinated process according to claim 9, characterized in that: The second locking block (205) is slidably connected to a second limiting rod (214), a spring is fixed between the second limiting rod (214) and the adjacent second locking block (205), the mounting shell (202) is provided with a circumferentially equidistant array of special-shaped grooves (215), an inclined surface is provided inside the special-shaped grooves (215), and the second limiting rod (214) is limitedly matched with the adjacent special-shaped grooves (215); When the second piston rod (212) drives the adjacent second locking block (205) to extend, the second locking block (205) drives the adjacent second limiting rod (214) to move along the special-shaped groove (215). When the second locking block (205) contacts the inclined surface of the adjacent special-shaped groove (215), the spring between the second limiting rod (214) and the adjacent second locking block (205) gradually rebounds.

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