A kind of optical detection equipment and detection system of solid engine grain under confining pressure

Abstract

This application provides an optical inspection device and system for solid rocket motor propellant grains under confined pressure. The inspection device includes a shell, a first end cap, a second end cap, an adhesive layer and an insulation layer, tempered transparent glass, a fixing component, a mounting component, a first reflector, and a second reflector. The first end cap has a detection hole communicating with the inner cavity of the cylinder. The detection hole is used to house an image acquisition module. The tempered transparent glass is disposed on the extension path of the detection hole. The fixing component is fitted onto the first end cap to fix the tempered transparent glass. The first reflector is disposed on the side of the fixing component away from the tempered transparent glass. The second reflector is sleeved on the connection between the first end cap and the fixing component. The light source module emits illumination light. After being reflected by the first and second reflectors, the illumination light is transmitted to the inner surface of the propellant grain. After being reflected by the inner surface of the propellant grain, it is acquired by the image acquisition module to detect the damage to the inner surface of the propellant grain.

Description

Technical Field

[0001] This application relates to the field of solid rocket / missile engine testing technology, and in particular to an optical testing device and system for solid rocket engine propellant grains under confined pressure. Background Technology

[0002] The propellant grain is the energy core of a solid rocket motor, and its mechanical properties directly affect the motor's lifespan. Throughout the entire process of a solid rocket motor, from production, transportation, and storage to successful ignition and launch, the propellant grain undergoes a series of complex and extreme loads, including natural load conditions such as high / low temperatures and humidity, and mechanical load conditions such as gas pressure and high-frequency vibration. These loads can all potentially damage the propellant grain, leading to engine performance failure or even explosion during operation. Therefore, experimental research on the mechanical properties of propellant grains under various extreme load conditions has become a key focus for researchers in this field.

[0003] Real-world solid rocket motors are large and long, and the inner diameter of the propellant grain is generally small, making it extremely difficult to monitor the lifespan of long-term stored solid rocket motor propellant grains in real time. If the lifespan data of solid rocket motors is inaccurate, the military may very well scrap most missiles / rockets that are still within their service life.

[0004] Currently, there is no mature device in the relevant technology capable of detecting damage to the mechanical properties of propellant grains under extreme conditions in realistic simulated engines or scaled-down engines. Therefore, how to design a detection device to observe the changes in the mechanical properties of solid rocket motor propellant grains in real time under environmental conditions such as high / low temperature, gas pressure, and humidity, using realistic simulated engines or scaled-down engines as the object, is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0005] In a first aspect, embodiments of this application provide an optical inspection device for solid rocket motor propellant grains under confined pressure, applied to damage detection of propellant grains in realistically simulated or scaled-down engines. The optical inspection device includes a housing, a first end cap, a second end cap, an adhesive layer, tempered transparent glass, a fixing component, a mounting component, a first reflector, and a second reflector. The housing includes a hollow cylinder and a first flange and a second flange connected to opposite ends of the cylinder. The first end cap extends into the cylinder and is detachably connected to the first flange. The second end cap extends into the cylinder and is detachably connected to the second flange. The first end cap has a detection hole communicating with the inner cavity of the cylinder, used to house an image acquisition module. The adhesive layer is disposed on the inner wall of the cylinder to bond the propellant grain to the inner wall of the cylinder. The tempered transparent glass is disposed on the inner wall of the cylinder. Along the extension path of the detection hole, the fixing member is fitted onto the first end cap to fix the tempered transparent glass. The mounting member is connected to the side of the fixing member away from the tempered transparent glass and is positioned away from the detection hole. The first reflector is mounted on the mounting member, and the second reflector is sleeved on the connection between the first end cap and the fixing member, with the second reflector facing a portion of the propellant grain. The second end cap is provided with a pressure port communicating with the inner cavity of the cylinder. The pressure port is used to install a pressure device connection module. A signal-adjustable light source module is installed inside the inner cavity of the cylinder. The light source module emits illumination light. After passing through the second reflector, part of the illumination light is transmitted to the inner surface of the propellant grain and reflected by the inner surface of the propellant grain to the first reflector. After being reflected by the first reflector, the light is transmitted through the detection hole and acquired by the image acquisition module to detect the damage to the inner surface of the propellant grain.

[0006] In some embodiments, the first reflector is a regular square pyramid structure. The first reflector includes a bottom surface and a first optical surface, a second optical surface, a third optical surface, and a fourth optical surface that are connected to the bottom surface in sequence. The bottom surface is connected to the fixing member. The first optical surface, the second optical surface, the third optical surface, and the fourth optical surface face the side of the light source hole. The first optical surface, the second optical surface, the third optical surface, and the fourth optical surface are used to reflect the illumination light from the light source module, so that the illumination light is transmitted toward the inner surface of the propellant grain.

[0007] In other embodiments, the angle between the first optical surface and the extension direction of the detection hole is 45 degrees, the angle between the second optical surface and the extension direction of the detection hole is 45 degrees, the angle between the third optical surface and the extension direction of the detection hole is 45 degrees, and the angle between the fourth optical surface and the extension direction of the detection hole is 45 degrees.

[0008] In some other embodiments, the second reflector is conical in shape and has a through hole in the middle. The radial dimension of the second reflector gradually increases from one side of the pressure hole toward the side of the detection hole. The second reflector is used to reflect more of the illumination light toward the inner surface of the propellant grain.

[0009] In some other embodiments, the propellant grain is spaced apart from the first end cap, and the fixing member has an annular groove on the side facing the mounting member. The damage detection device further includes a driving member and a telescopic member, which are located in the annular groove. The mounting member is connected to the telescopic member, and the driving member is used to drive the telescopic member to selectively extend and shorten, so that the first reflector reciprocates relative to the inner wall of the propellant grain.

[0010] In some other embodiments, the telescopic member has a ring-shaped structure, is connected to the end of the mounting member, and is made of a non-transparent material so that more illumination light is transmitted toward one side of the detection hole.

[0011] In some other embodiments, the damage detection device further includes a first sealing ring, a second sealing ring, and a third sealing ring. The first sealing ring is an explosion-proof soft gasket. The first sealing ring is disposed at the connection between the first end cap and the end face of the tempered transparent glass. The first sealing ring is disposed away from the detection hole. The second sealing ring is disposed at the connection between the tempered transparent glass and the end face of the fixing member. The third sealing ring is disposed at the connection and mating part between the fixing member and the first end cap.

[0012] In some other embodiments, the damage detection device further includes a fourth sealing ring and a fifth sealing ring, wherein the fourth sealing ring is disposed at the connection and mating part between the first end cover and the outer shell, and the fifth sealing ring is disposed at the connection and mating part between the second end cover and the outer shell.

[0013] Secondly, this application provides a damage detection system, which includes a light source module, an image acquisition module, a pneumatic device connection module, and a damage detection device as provided in any of the above embodiments. The pneumatic device connection module is disposed in the pneumatic hole, the light source module is installed in the inner cavity of the cylinder, and the image acquisition module is disposed on the outside of the first end cap, and the image acquisition module is disposed corresponding to the detection hole.

[0014] Thirdly, embodiments of this application provide a damage detection method, which is applied to the damage detection device provided in any of the above embodiments, the damage detection method comprising:

[0015] A light source module provides illumination to the cylinder. After passing through the second reflector, part of the illumination light is transmitted to the inner surface of the propellant grain, and then reflected by the inner surface of the propellant grain to the first reflector. After being reflected by the first reflector, part of the light is transmitted to the inner surface of the propellant grain.

[0016] An image acquisition module is used to receive the illumination light transmitted from the detection hole after being reflected by the inner surface of the propellant grain;

[0017] The damage to the inner surface of the propellant grain is detected based on the received illumination light.

[0018] The damage detection equipment, damage detection system, and damage detection method provided in this application test various mechanical performance indicators by placing a propellant grain within a sealed environment consisting of a shell, a first end cap, and a second end cap. A through-hole is provided on the second end cap for connecting a pressure device module. A signal-adjustable light source module is installed inside the cylindrical cavity, providing illumination towards the cavity of the damage detection equipment. A second reflector reflects the illumination towards the inner surface of the propellant grain. A through-hole is provided on the first end cap, reflecting the illumination towards one side of the detection hole via a first reflector. An image acquisition module detects the light reflected from the inner surface of the propellant grain at the location corresponding to the detection hole. The damage to the inner surface of the propellant grain is analyzed based on the detected light. This technical solution allows for the analysis of the impact of multiple extreme load coupling effects on the mechanical properties of the propellant grain, including pressure, temperature, humidity, and vibration conditions. By simulating the structural composition of engine components, the left end cap component, and the right end cap component, the accuracy of solid propellant mechanical performance testing is improved. Attached Figure Description

[0019] To more clearly illustrate the structural features and effects of this application, a detailed description is provided below in conjunction with the accompanying drawings and specific embodiments. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 This is a schematic diagram of the planar structure of the damage detection device provided in the embodiments of this application;

[0021] Figure 2 yes Figure 1 A structural schematic diagram of a cross-sectional view of the provided damage detection equipment;

[0022] Figure 3 yes Figure 1 A schematic diagram of the structure of the first reflector of the provided damage detection device;

[0023] Figure 4 yes Figure 1 A schematic diagram of the structure of the provided damage detection equipment with the telescopic component in a shortened state in a cross-sectional view;

[0024] Figure 5 yes Figure 1 A schematic diagram of the telescopic component in an extended state in the cross-sectional view of the provided damage detection equipment;

[0025] Figure 6 yes Figure 1 Another structural schematic diagram of the cross-sectional view of the provided damage detection equipment;

[0026] Figure 7 This is a flowchart of the damage detection method provided in the embodiments of this application. Detailed Implementation

[0027] The technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this application, not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of this application without creative effort should fall within the scope of protection of this application.

[0028] In solid rocket motors, the propellant grain is the energy source for ignition. Due to the overall length of the motor, the damage state of the propellant grain is difficult to observe, and this difficulty increases further when the propellant grain is under extreme load conditions. Therefore, this device simulates motor components, the left end cap component, and the right end cap component to achieve real-time observation of the engine's propellant grain. Actual tests have proven that this device can achieve real-time observation under a pressure range of 0–20 MPa and a wide temperature range of -70℃ to 120℃ under extreme load conditions.

[0029] Please refer to the following: Figure 1 and Figure 2 This application provides an optical inspection device 10 for solid rocket motor propellant grains under confined pressure, applied to damage detection of propellant grains T in simulated or scaled-down engines. The damage inspection device 10 includes a housing 100, a first end cap 110, a second end cap 120, an adhesive layer 130, tempered transparent glass 140, a fixing component 150, a mounting component 155, a first reflector 160, and a second reflector 170. The housing 100 includes a hollow cylinder 102 and a first flange 101 and a second flange 103 connected to opposite ends of the cylinder 102. The first end cap 110 extends partially into the cylinder. The first end cap 110 is detachably connected to the first flange 101 within the cylinder 102. The second end cap 120 extends partially into the cylinder 102 and is detachably connected to the second flange 103. The first end cap 110 has a detection hole 111 communicating with the inner cavity of the cylinder 102. The detection hole 111 is used to house the image acquisition module 30. The adhesive layer 130 is disposed on the inner wall of the cylinder 102 to bond the propellant grain T to the inner wall of the cylinder 102 by adhesive bonding. The tempered transparent glass 140 is disposed on the extension of the detection hole 111. Along the extension path, the fixing member 150 covers the first end cap 110 to fix the tempered transparent glass 140. The mounting member 155 is connected to the side of the fixing member 150 away from the tempered transparent glass 140. The mounting member 155 is positioned to avoid the detection hole 111. The first reflector 160 is mounted on the mounting member 155. The second reflector 170 is sleeved on the connection between the first end cap 110 and the fixing member 150, and the second reflector 170 is positioned directly opposite a portion of the propellant grain T. The second end cap 120 is provided with a pressure hole communicating with the inner cavity of the cylinder 102. 121, the pressure port 121 is used to install the pressure device connection module 15 to pressurize the inner cavity of the cylinder 102, ensuring that the pressure in the inner cavity is controllable. A signal-adjustable light source module 20 is installed inside the inner cavity of the cylinder 102. The light source module 20 emits illumination light, which is reflected by the second reflector 170, with a portion of the light transmitted to the inner surface of the propellant grain T. The light is then reflected by the inner surface of the propellant grain T to the first reflector 160, and after reflection by the first reflector 160, it is transmitted through the detection port 111 and acquired by the image acquisition module 30 to detect damage to the inner surface of the propellant grain T. The signal-adjustable light source module 20 can withstand a wide range of pressure and temperature variations.

[0030] The outer shell 100 is used to simulate the housing of a real engine or a scaled-down engine. The outer shell 100 is a hollow cylindrical shell, including a first flange 101, a cylinder 102 and a second flange 103 connected in sequence. The first flange 101 is used to form a detachable connection with the first end cap 110 by screws, and the second flange 103 is used to form a detachable connection with the second end cap 120 by screws. Through the connection between the first end cap 110, the outer shell 100 and the second end cap 120, an inner cavity can be formed on the damage detection device 100. An adhesive layer 130 is provided on the inner side of the outer shell 100. The adhesive layer 130 is attached to the inner side wall of the outer shell 100 and is used to bond the propellant grain T to the inner side wall of the outer shell 100 so as to facilitate subsequent damage detection on the inner surface of the propellant grain T.

[0031] The first end cap 110 has a detection hole 111 that communicates with the inner cavity of the outer shell 100. The position corresponding to the detection hole 111 is used to set up an image acquisition module 30. The image acquisition module 30 can be a DIC device, which is used to detect the changes in the mechanical properties of the propellant grain T in the inner cavity under the condition of changes in the inner cavity environment through the detection hole 111, and to detect the damage of the propellant grain T. A tempered transparent glass 140 is provided on the extension path of the detection hole 111. The mounting member 155 is connected to the side of the fixing member 150 away from the tempered transparent glass 140. The mounting member 155 is set away from the detection hole 111. The first reflector 160 is installed on the mounting member 155. The second reflector 170 is sleeved on the connection part between the first end cap 110 and the fixing member 150. The second reflector 170 is spaced apart from and directly opposite a portion of the propellant grain T. The light source module 20 emits illumination light. After passing through the second reflector 170, part of the illumination light is transmitted to the inner surface of the propellant grain T and reflected by the inner surface of the propellant grain T to the first reflector 160. After being reflected by the first reflector 160, it is transmitted from the detection hole 111 and acquired by the image acquisition module 30 to detect the damage to the inner surface of the propellant grain T.

[0032] The second end cap 120 has a pressure port 121 that connects to the inner cavity of the outer shell 100. The pressure port 121 is used to pressurize the inner cavity of the cylinder 102 to ensure that the pressure inside the cavity is controllable. A signal-adjustable light source module 20 is installed inside the inner cavity of the cylinder 102. The light source module 20 provides illumination light to the inner cavity of the outer shell 100 to ensure the brightness inside the cavity. The light source module 20 emits illumination light. After passing through the second reflector 170, part of the illumination light is transmitted to the inner surface of the propellant grain T, and reflected by the inner surface of the propellant grain T to the first reflector 160. After being reflected by the first reflector 160, it is transmitted through the detection hole 111 and then acquired by the image acquisition module 30 to detect the damage to the inner surface of the propellant grain T.

[0033] The adhesive layer 130 is made to simulate a real engine and includes an insulation layer, adhesive, lining, and additives. It is used to bond the propellant grain T to the inner wall of the outer shell 100 and to provide insulation. This simulation method can make the damage detection of the propellant grain T more accurate.

[0034] In some embodiments, the second reflector 170 is conical in shape, and the middle of the second reflector 170 is a through hole. The radial dimension of the second reflector 170 gradually increases from one side of the pressure hole 121 toward the side of the detection hole 111. The second reflector 170 is used to reflect more of the illumination light toward the inner surface of the propellant grain T.

[0035] Specifically, the second reflector 170 has a hollow cone-shaped structure. The second reflector 170 is sleeved on the connection between the first end cap 110 and the fixing member 150. The side of the second reflector 170 with a smaller radial dimension is located near the air pressure hole 121, and the side of the second reflector 170 with a larger radial dimension is located near the detection hole 111. The second reflector 170 is used to reflect more of the illumination light toward the inner surface of the propellant grain T, so that the illumination light covers the entire inner surface of the propellant grain T as much as possible. The light reflected by the inner surface of the propellant grain T is reflected again by the first reflector 160 toward the detection hole 111, so that the illumination light after multiple reflections is received by the image acquisition module 30. The image acquisition module 30 detects the damage to the inner surface of the propellant grain T based on the received reflected light.

[0036] In some embodiments, the first end cap 110 has a first detection cavity K1 and a second detection cavity K2 that are connected to each other. The first detection cavity K1 is closer to the outer side of the damage detection device 100 than the second detection cavity K2, and the radial dimension of the first detection cavity K1 is greater than the radial dimension of the second detection cavity K2. The first detection cavity K1 and the second detection cavity K2 together form the detection hole 111, and the first reflector 160 is located on the extension path of the second detection cavity K2.

[0037] Specifically, since an image acquisition module 30 needs to be installed on the outer side of the outer casing 100 at the position corresponding to the detection hole 111, allowing more illumination light to enter the image acquisition module 30, the radial dimension of the first detection cavity K1 is made larger than the radial dimension of the second detection cavity K2. That is, the radial dimension of the cavity on the outer side of the outer casing 100 is larger than the radial dimension of the cavity on the inner side of the outer casing 100, allowing more illumination light to enter the image acquisition module 30, thereby acquiring more damage information about the inner surface of the propellant grain T. In addition, the purpose of the first detection cavity K1 includes, but is not limited to, the following: first, to reduce weight; second, to increase the extension range of the image acquisition module 30. Furthermore, the second detection cavity K2 is smaller, and its diameter is set according to the tempered transparent glass 140. The size of the tempered transparent glass 140 is calculated using finite element method to set a reasonable diameter.

[0038] In some possible implementations, both the first detection cavity K1 and the second detection cavity K2 are cylindrical cavities, which facilitates manufacturing. In other possible implementations, both the first detection cavity K1 and the second detection cavity K2 are conical structures, and their radial dimensions gradually increase from the inner cavity of the outer shell 100 towards the outer side of the outer shell 100, while always maintaining that the radial dimension of the first detection cavity K1 is larger than that of the second detection cavity K2. This helps to improve the utilization rate of the illumination light, allowing more illumination light to be transmitted to one side of the image acquisition module 30, thereby enabling the image acquisition module 30 to perform a more comprehensive analysis of the damage information on the inner surface of the propellant grain T. In some other possible implementations, the first detection cavity K1 is conical in shape, and the second detection cavity K2 is cylindrical, with the radial dimension of the first detection cavity K1 always being larger than that of the second detection cavity K2. This can also improve the light utilization rate to a certain extent.

[0039] In some other embodiments, the second end cap 120 has a first air pressure chamber K3 and a second air pressure chamber K4 that are connected to each other. The first air pressure chamber K3 is closer to the outer side of the damage detection device 10 than the second air pressure chamber K4, and the radial dimension of the first air pressure chamber K3 is larger than the radial dimension of the second air pressure chamber K4. The first air pressure chamber K3 and the second air pressure chamber K4 together constitute the air pressure hole 121, and the extension paths of the first air pressure chamber K3 and the second air pressure chamber K4 are consistent.

[0040] Specifically, since a pneumatic device connection module 15 needs to be installed on the outer side of the outer casing 100 corresponding to the pneumatic port 121, the radial dimension of the first pneumatic chamber K3 is larger than that of the second pneumatic chamber K4. That is, the radial dimension of the cavity on the outer side of the outer casing 100 is larger than that of the cavity on the inner side of the outer casing 100. This reduces the sealed volume of the inner cavity of the damage detection device 10, thereby increasing the gas pressurization rate. In addition, the purpose of the first pneumatic chamber K3 includes, but is not limited to, the following: first, to reduce weight; second, to make the gas pressure value in the inner cavity of the damage detection device 10 rise more quickly, reaching the ignition pressurization time standard.

[0041] In some possible embodiments, both the first pressure chamber K3 and the second pressure chamber K4 are cylindrical cavities, which facilitates manufacturing. In other possible embodiments, both the first pressure chamber K3 and the second pressure chamber K4 are conical structures, and their radial dimensions gradually increase from the inner cavity of the outer shell 100 towards the outer side of the outer shell 100, while always maintaining that the radial dimension of the first pressure chamber K3 is greater than that of the second pressure chamber K4, which helps to improve the gas pressurization rate. In still other possible embodiments, the first pressure chamber K3 is conical in shape and the second pressure chamber K4 is cylindrical in shape, and always maintaining that the radial dimension of the first pressure chamber K3 is greater than that of the second pressure chamber K4, which can also improve the gas pressurization rate to a certain extent.

[0042] In some other embodiments, the damage detection device 10 further includes a pressure sensor, and the second end cap 120 is provided with a through second mounting hole. The pressure sensor is provided corresponding to the second mounting hole, and the pressure sensor extends to the outside of the second end cap 120. The pressure sensor is used to detect the pressure parameters of the inner cavity of the cylinder 102.

[0043] Specifically, the air pressure hole 121 is located at the center of the second end cover 120, and the second end cover 120 has a first mounting hole and a second mounting hole symmetrically arranged with respect to the air pressure hole 121. The first mounting hole is used to install a pressure sensor, and the pressure sensor extends to the outside of the second end cover 120. The pressure sensor is used to detect the pressure parameters inside the cylinder 102.

[0044] Furthermore, the second mounting hole is a temperature control hole, used to connect a temperature sensor to monitor the interior wall temperature of the simulated engine in real time.

[0045] The damage detection device 10 provided in this application embodiment tests various mechanical performance indicators by placing the propellant grain T in a sealed environment formed by the outer shell 100, the first end cap 110, and the second end cap 120. A through-hole air pressure hole 121 is provided on the second end cap 120 for a gas pressure device connection module 15 to pressurize the inner cavity of the cylinder 102, ensuring controllable pressure within the cavity. A signal-adjustable light source module 20 is installed inside the inner cavity of the cylinder 102. The light source module 20 emits illumination light, which is reflected towards the inner surface of the propellant grain T by a second reflector 170 and then reflected onto the first end cap 110. A through-hole 111 is provided on the top, and the illumination light is reflected towards one side of the detection hole 111 by the first reflector 160. The image acquisition module 30 detects the light reflected by the inner surface of the propellant grain T at the position corresponding to the detection hole 111. The damage of the inner surface of the propellant grain T is detected based on the detected light. Through the technical solution of this application, the influence of multiple extreme load coupling on the mechanical properties of the propellant grain T can be analyzed, including pressure, temperature, humidity and vibration conditions. By simulating the structural composition of engine components, left end cover components and right end cover components, the accuracy of solid propellant mechanical property detection is improved.

[0046] Please continue reading. Figure 3 In some embodiments, the first reflector 160 is a regular square pyramid structure. The first reflector 160 includes a bottom surface 161 and a first optical surface 162, a second optical surface 163, a third optical surface 164, and a fourth optical surface 165 connected to the bottom surface 161 in sequence. The periphery of the mounting member 155 is a hollow structure. The bottom surface 161 is connected to the mounting member 155. The first optical surface 162, the second optical surface 163, the third optical surface 164, and the fourth optical surface 165 face the side of the detection hole. The first optical surface 162, the second optical surface 163, the third optical surface 164, and the fourth optical surface 165 are used to reflect the illumination light from the light source module 20, so that the illumination light is transmitted toward the inner surface of the propellant grain T.

[0047] Specifically, the angle formed between the first optical surface 162 and the extending direction of the detection hole 111 is 45 degrees, the angle formed between the second optical surface 163 and the extending direction of the detection hole 111 is 45 degrees, the angle formed between the third optical surface 164 and the extending direction of the detection hole 111 is 45 degrees, and the angle formed between the fourth optical surface 165 and the extending direction of the detection hole 111 is 45 degrees. In other words, the first reflector 160 is a completely symmetrical spatial three-dimensional structure. The first optical surface 162, the second optical surface 163, the third optical surface 164, and the fourth optical surface 165 of the first reflector 160 can simultaneously reflect the illumination light emitted by the light source module 20 towards the inner surface of the propellant grain T, achieving 360° observation. This improves the efficiency of detecting damage to the inner surface of the propellant grain T and increases the utilization rate of the illumination light.

[0048] Please continue reading. Figure 4 and Figure 5 In some other embodiments, the propellant grain T is spaced apart from the first end cap 110, the fixing member 150 has an annular groove on the side facing the mounting member 155, the damage detection device 10 also includes a driving member 40 and a telescopic member 45, the driving member 40 and the telescopic member 45 are located in the annular groove, the mounting member 155 is connected to the telescopic member 45, the driving member 40 is used to drive the telescopic member 45 to selectively extend and shorten, so that the first reflector 160 reciprocates relative to the inner wall of the propellant grain T.

[0049] For damage detection on the inner surface of the elongated propellant grain T, since the area of ​​light reflected by the first reflector 160 is relatively limited, in this embodiment, the first reflector 160 is configured to be selectively movable relative to the propellant grain T. Specifically, an annular groove is provided on the side of the fixing member 150 facing the mounting member 155, and a driving member 40 is provided in the annular groove. The driving member 40 can be used to drive the extension and retraction of the telescopic member 45. The mounting member 155 and the first reflector 160 are mounted on the telescopic member 45 away from the driving member. On one side of 40, when the driving member 40 drives the telescopic member 45 to extend and retract, it can selectively drive the mounting member 155 and the first reflector 160 to reciprocate relative to the inner wall of the propellant grain T, thereby reflecting the illumination light emitted from the light source module 20 to the entire inner surface of the inner wall of the propellant grain T, and reflecting the illumination light reflected by the inner surface of the propellant grain T to one side of the detection hole 111, which can improve the comprehensiveness of the detection of damage to the inner surface of the propellant grain T, and improve the utilization rate of the illumination light.

[0050] In some other embodiments, the telescopic member 45 has a ring-shaped structure and is connected to the end of the mounting member 155. The telescopic member 45 is made of a non-transparent material so that more illumination light is transmitted toward one side of the detection hole 111, thereby improving the utilization rate of the illumination light and improving the accuracy of damage detection.

[0051] Specifically, the telescopic member 45 has a ring-shaped structure. The telescopic member 45 is connected to the bottom surface 161 of the end of the mounting member 155. The telescopic member 45 will not block the reflection of the lighting light by the first reflector 160. In addition, the telescopic member 45 is made of a non-transparent material, which allows more lighting light to be transmitted towards the side of the detection hole 111, which helps to improve the utilization rate of the lighting light and reduce the loss of the lighting light.

[0052] Please continue reading. Figure 6 In some embodiments, the damage detection device 10 further includes a first sealing ring M1, a second sealing ring M2, and a third sealing ring M3. The first sealing ring M1 is an explosion-proof soft gasket. The first sealing ring M1 is disposed at the connection between the end face of the first end cap 110 and the tempered transparent glass 140, and the first sealing ring M1 is disposed away from the detection hole 111. The second sealing ring M2 is disposed at the connection between the end face of the tempered transparent glass 140 and the fixing member 150. The third sealing ring M3 is disposed at the connection and mating part between the fixing member 150 and the first end cap 110.

[0053] Specifically, the fixing member 150 has a first mounting groove on its end face near the tempered transparent glass 140, the second sealing ring M2 is installed in the first mounting groove, the fixing member 150 has a second mounting groove on its peripheral side that connects and cooperates with the first end cover 110, and the third sealing ring M3 is installed in the second mounting groove.

[0054] In some other embodiments, the damage detection device 10 further includes a fourth sealing ring M4 and a fifth sealing ring M5. The fourth sealing ring M4 is disposed at the connection and mating part between the first end cover 110 and the outer shell 100, and the fifth sealing ring M5 is disposed at the connection and mating part between the second end cover 120 and the outer shell 100.

[0055] Specifically, the damage detection device 10 can be constructed as a sealed environment using the first sealing ring M1, the second sealing ring M2, the third sealing ring M3, the fourth sealing ring M4, and the fifth sealing ring M5. This facilitates the creation of extremely complex conditions within the internal cavity of the damage detection device 10, such as a temperature range of -70℃ to 120℃ and a pressure range of 0 to 20 MPa. When these extremely complex conditions are applied, the operating mode of a real engine can be better simulated, thereby allowing the detection device to detect changes in the mechanical properties of the propellant grain T and determine the damage status of the propellant grain T.

[0056] The damage detection device 10 provided in this application embodiment requires a sealed environment to be formed by the outer shell 100, the first end cover 110 and the second end cover 120. Therefore, the gap between the three is very small due to the control of dimensional tolerances. In addition, the fourth sealing ring M4 and the fifth sealing ring M5 make disassembly very difficult. Therefore, four additional threaded holes are provided on the first end cover 110 and the second end cover 120 respectively, for the first end cover 110 and the second end cover 120 to be pushed out by rotating screws, so as to facilitate the disassembly of the first end cover 110 and the second end cover 120 from the outer shell 100.

[0057] It should also be noted that the damage detection device 10 provided in this application embodiment is assembled using the following assembly method, the specific steps of which are described below:

[0058] S1: Based on existing technology, cast a simulated engine, including the outer shell 100, the adhesive layer 130 (insulation layer, adhesive, lining and additives), propellant grains T, etc.

[0059] S2: The tempered transparent glass 140 is positioned corresponding to the detection hole 111 of the first end cap 110, so that the tempered transparent glass 140 is located on the extension path of the detection hole 111. Then, the fixing member 150 is closed and connected to the first end cap 110 to fix the tempered transparent glass 140. Then, the mounting member 155 and the first reflector 160 are installed on the side of the fixing member 150 away from the tempered transparent glass 140, and the second reflector 170 is installed at the connection between the first end cap 110 and the fixing member 150. During this process, a first sealing ring M1 needs to be set at the end face connection between the first end cap 110 and the tempered transparent glass 140, a second sealing ring M2 needs to be set at the end face connection between the tempered transparent glass 140 and the fixing member 150, and a third sealing ring M3 needs to be set at the connection and mating part between the fixing member 150 and the first end cap 110.

[0060] S3: The first end cap 110, tempered transparent glass 140, fixing part 150, mounting part 155, first reflector 160 and second reflector 170 are connected to the end of the outer shell 100 as a whole by means of screws for detachable connection, and the first reflector 160 is positioned directly opposite a portion of the propellant grain T. In this process, a fourth sealing ring M4 needs to be provided at the connection and mating part between the first end cap 110 and the outer shell 100.

[0061] S4: The second end cap 120 is detachably connected to the end of the outer shell 100 by means of screws. During this process, a fifth sealing ring M5 needs to be set at the connection and mating part between the second end cap 120 and the outer shell 100.

[0062] S5: A pneumatic device connection module 15 is set on one side adjacent to the pneumatic port 121, and a signal-adjustable light source module 20 is set in the inner cavity of the cylinder 102. An image acquisition module 30 is set on one side adjacent to the detection port 111. At the same time, the distance between the image acquisition module 30 and the first end cap 110 is adjusted so that the image acquisition module 30 can acquire a clearer image of the damage to the propellant column T.

[0063] S6: A pressure sensor and a temperature sensor are connected to the second end cover 120, which are used to detect the pressure parameters of the inner cavity of the damage detection device 10 and to regulate the temperature parameters of the inner cavity of the damage detection device 10, respectively.

[0064] Furthermore, this application provides a damage detection system, which includes a light source module 20, an image acquisition module 30, a pneumatic device connection module 15, and a damage detection device 10 as provided in any of the above embodiments. The pneumatic device connection module 15 is disposed in the pneumatic hole 121 to pressurize the inner cavity of the cylinder 102, ensuring that the pressure in the inner cavity is controllable. The light source module 20 is installed inside the inner cavity of the cylinder 102. The image acquisition module 30 is disposed on the outside of the first end cap 110, and the image acquisition module 30 is disposed corresponding to the detection hole 111.

[0065] Specifically, the signal-tunable light source module 20 can withstand a wide range of pressure and temperature changes. The light source module 20 can be detachably connected to the second end cap 120 via screws. The light source module 20 is located inside the cylinder 102, allowing more of the illumination light emitted by the light source module 20 to enter the inner cavity of the damage detection device 10 through the air pressure port 121, thereby illuminating the inner cavity of the damage detection device 10. An image acquisition module 30 is positioned corresponding to the detection port 111. The image acquisition module 30 is used to detect the light reflected from the inner surface of the propellant grain T. The damage to the inner surface of the propellant grain T is analyzed based on the detected light. Through the technical solution of this application, the influence of multiple extreme load coupling effects on the mechanical properties of the propellant grain T, including pressure, temperature, humidity, and vibration conditions, can be analyzed. By simulating the structural composition of engine components, left end cap components, and right end cap components, the accuracy of solid propellant mechanical property detection is improved.

[0066] The damage detection system provided in this application embodiment tests various mechanical performance indicators by placing the propellant grain T in a sealed environment formed by the outer shell 100, the first end cap 110, and the second end cap 120. A through-hole pressure hole 121 is provided on the second end cap 120 to pressurize the inner cavity of the cylinder 102, ensuring that the pressure in the inner cavity is controllable. The second reflector 170 reflects the illumination light toward the inner surface of the propellant grain T. A through-hole detection hole 111 is provided on the first end cap 110, and the first reflector 160 reflects the illumination light toward the side of the detection hole 111. The image acquisition module 30 detects the light reflected from the inner surface of the propellant grain T at the position corresponding to the detection hole 111. The damage condition of the inner surface of the propellant grain T is detected based on the detected light. Through the technical solution of this application, the influence of multiple extreme load coupling effects on the mechanical performance of the propellant grain T, including pressure, temperature, humidity, and vibration conditions, can be analyzed. By simulating the structural composition of engine components, left end cap components, and right end cap components, the accuracy of solid propellant mechanical performance detection is improved.

[0067] Please see Figure 7 Furthermore, this application provides a damage detection method, which is applied to the damage detection device provided in any of the above embodiments. The damage detection method includes, but is not limited to, steps S100, S200, and S300. Steps S100, S200, and S300 are described below:

[0068] S100: The light source module 20 provides illumination light to the inside of the cylinder 102. After passing through the second reflector 170, part of the illumination light is transmitted to the inner surface of the propellant grain T, and is reflected by the inner surface of the propellant grain T to the first reflector 160. After being reflected by the first reflector 160, part of the light is transmitted to the inner surface of the propellant grain T.

[0069] S200: The image acquisition module 30 receives the illumination light transmitted from the detection hole 111 after being reflected by the inner surface of the propellant grain T;

[0070] S300: Detect the damage to the inner surface of the propellant grain T based on the received illumination light.

[0071] The damage detection method provided in this application involves testing various mechanical performance indicators by placing the propellant grain T within a sealed environment formed by the outer shell 100, the first end cap 110, and the second end cap 120. A through-hole pressure hole 121 is provided on the second end cap 120 to pressurize the inner cavity of the cylinder 102, ensuring controllable pressure. A signal-adjustable light source module 20 is installed inside the inner cavity of the cylinder 102. The light source module 20 emits illumination light, which is reflected towards the inner surface of the propellant grain T by a second reflector 170. A through-hole detection hole is provided on the first end cap 110. 111, and the first reflector 160 reflects the illumination light toward one side of the detection hole 111. The image acquisition module 30 detects the light reflected by the inner surface of the propellant grain T at the position corresponding to the detection hole 111. The damage to the inner surface of the propellant grain T is analyzed based on the detected light. Through the technical solution of this application, the influence of multiple extreme load coupling effects on the mechanical properties of the propellant grain T, including pressure, temperature, humidity and vibration conditions, can be analyzed. By simulating the structural composition of engine components, left end cap components and right end cap components, the accuracy of solid propellant mechanical property detection is improved.

[0072] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The description of the above embodiments is only for the purpose of helping to understand the method and core ideas of this application. At the same time, for those skilled in the art, there will be changes in the specific implementation methods and application scope based on the ideas of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A damage detection device, used for damage detection of propellant grains in simulated or scaled-down engines, characterized in that, The damage detection device includes a housing, a first end cap, a second end cap, an adhesive layer, tempered transparent glass, a fixing component, a mounting component, a first reflector, and a second reflector. The housing includes a hollow cylinder and a first flange and a second flange connected to opposite ends of the cylinder. The first end cap extends into the cylinder and is detachably connected to the first flange. The second end cap extends into the cylinder and is detachably connected to the second flange. The first end cap has a detection hole communicating with the inner cavity of the cylinder, which is used to house an image acquisition module. The adhesive layer is disposed on the inner wall of the cylinder to bond propellant grains to the inner wall of the cylinder. The tempered transparent glass is disposed along the extension path of the detection hole. The fixing component covers the first end cap to reflect the tempered transparent glass. The glass is fixed in place, and the mounting component is connected to the side of the fixed component away from the tempered transparent glass. The mounting component is positioned away from the detection hole. The first reflector is mounted on the mounting component, and the second reflector is sleeved on the connection between the first end cap and the fixed component. The second reflector is positioned directly opposite a portion of the propellant grain. The second end cap has a pressure port communicating with the inner cavity of the cylinder. The pressure port is used to install a pressure device connection module. A signal-adjustable light source module is installed inside the inner cavity of the cylinder. The light source module emits illumination light. After passing through the second reflector, part of the illumination light is transmitted to the inner surface of the propellant grain and reflected by the inner surface of the propellant grain to the first reflector. After being reflected by the first reflector, the light is transmitted through the detection hole and acquired by the image acquisition module to detect the damage to the inner surface of the propellant grain.

2. The damage detection device as described in claim 1, characterized in that, The first reflector is a regular square pyramid structure. The first reflector includes a bottom surface and a first optical surface, a second optical surface, a third optical surface, and a fourth optical surface that are connected to the bottom surface in sequence. The periphery of the mounting component is a hollow structure. The bottom surface is connected to the mounting component. The first optical surface, the second optical surface, the third optical surface, and the fourth optical surface face the side of the detection hole. The first optical surface, the second optical surface, the third optical surface, and the fourth optical surface are used to reflect the illumination light from the light source module, so that the illumination light is transmitted toward the inner surface of the propellant grain.

3. The damage detection device as described in claim 2, characterized in that, The angle between the first optical surface and the extension direction of the detection hole is 45 degrees, the angle between the second optical surface and the extension direction of the detection hole is 45 degrees, the angle between the third optical surface and the extension direction of the detection hole is 45 degrees, and the angle between the fourth optical surface and the extension direction of the detection hole is 45 degrees.

4. The damage detection device as described in claim 1, characterized in that, The second reflector is cone-shaped and has a through hole in the middle. The radial dimension of the second reflector gradually increases from one side of the pressure hole toward the side of the detection hole. The second reflector is used to reflect more of the illumination light toward the inner surface of the propellant grain.

5. The damage detection device as described in claim 1, characterized in that, The propellant grain is spaced apart from the first end cap. The fixing member has an annular groove on the side facing the mounting member. The damage detection device also includes a driving member and a telescopic member. The driving member and the telescopic member are located in the annular groove. The mounting member is connected to the telescopic member. The driving member is used to drive the telescopic member to selectively extend and shorten, so that the first reflector moves back and forth relative to the inner wall of the propellant grain.

6. The damage detection device as described in claim 5, characterized in that, The telescopic component has a circular structure and is connected to the end of the mounting component. The telescopic component is made of a non-transparent material so that more illumination light is transmitted toward one side of the detection hole.

7. The damage detection device as described in claim 1, characterized in that, The damage detection device further includes a first sealing ring, a second sealing ring, and a third sealing ring. The first sealing ring is an explosion-proof soft gasket. The first sealing ring is disposed at the connection between the first end cap and the end face of the tempered transparent glass. The first sealing ring is disposed away from the detection hole. The second sealing ring is disposed at the connection between the tempered transparent glass and the end face of the fixing member. The third sealing ring is disposed at the connection and mating part between the fixing member and the first end cap.

8. The damage detection device as described in claim 1, characterized in that, The damage detection device further includes a fourth sealing ring and a fifth sealing ring. The fourth sealing ring is disposed at the connection and mating part between the first end cover and the outer shell, and the fifth sealing ring is disposed at the connection and mating part between the second end cover and the outer shell.

9. A damage detection system, characterized in that, The damage detection system includes a light source module, an image acquisition module, a pneumatic device connection module, and a damage detection device as described in any one of claims 1-8. The pneumatic device connection module is disposed at the pneumatic hole, the light source module is installed inside the inner cavity of the cylinder, and the image acquisition module is disposed on the outside of the first end cap, and the image acquisition module is disposed corresponding to the detection hole.

10. A damage detection method, characterized in that, The method is applied to the damage detection device as described in any one of claims 1-8, and the damage detection method includes: A light source module provides illumination to the cylinder. After passing through the second reflector, part of the illumination light is transmitted to the inner surface of the propellant grain and reflected by the inner surface of the propellant grain to the first reflector. After being reflected by the first reflector, the light is transmitted through the detection hole and captured by the image acquisition module to detect the damage to the inner surface of the propellant grain.

Images