Dynamic measurement system for ablation rate of thermal protection material of aircraft under high-temperature fuel gas

Abstract

The invention discloses a dynamic measurement system for the ablation rate of a thermal protection material of an aircraft under high-temperature fuel gas. The dynamic measurement system comprises a sample placement unit, a fuel gas generation unit, laser displacement equipment and a data acquisition and processing system, the sample placement unit is used for placing a thermal protection material sample piece, the fuel gas generation unit comprises a fuel gas generator, and a flame nozzle of the fuel gas generator is used for being aligned with the surface of the thermal protection material sample piece; the laser displacement equipment dynamically captures displacement change signals of surface retreating of the thermal protection material sample piece under the action of the fuel gas generator; and the data acquisition and processing system calculates the dynamic ablation rate of the thermal protection material under the high-temperature fuel gas according to the displacement change signal. The laser displacement equipment is matched with a data acquisition system to finish dynamic acquisition of the retreat amount and calculation of the dynamic ablation rate, a dynamic measurement system is established, and the problems that the ablation rate of the thermal protection material cannot dynamically respond to changes and the accuracy of an ablation model prediction result is low when traditional static measurement is adopted at present are solved.

Description

Technical Field

[0001] This invention belongs to the field of dynamic testing technology for material properties under extreme environments, specifically relating to a dynamic measurement system for the ablation rate of thermal protection materials for aircraft under high-temperature gas conditions. Background Technology

[0002] During the service life of an aircraft, typical parts of the aircraft are subjected to high temperature, high pressure, and high speed jet environments for extended periods. Examples include the combustion chamber and nozzle of a solid rocket engine, the nose cone and leading edge of an aircraft, and the leading edge of the nose and the outer edge of the wing of a high-speed aircraft. To ensure the service safety of these typical parts of an aircraft, the use of thermal protection materials is essential. Aircraft thermal protection materials are the "lifeline" of aerospace technology.

[0003] The thermodynamic properties of thermal protection materials for aircraft, especially their ablation resistance, have a significant impact on the overall performance of the aircraft. The ablation rate of thermal protection materials is related to the thermal protection performance of the aircraft structure, the effective load, and the precise control during flight. Dynamic and accurate measurement of the ablation rate is crucial for the thermal structure design and reliability assessment of aircraft.

[0004] The ablation process of thermal protection materials involves complex physicochemical changes and is influenced by numerous factors, including the material's own composition and ablation environment parameters. These environmental factors include temperature, flow rate, pressure, particle action, and gas composition. Clarifying the ablation rate of thermal protection materials under different influencing factors can provide a theoretical basis for the refined design of aircraft thermal structures. However, current research on online monitoring of the dynamic ablation rate of aircraft thermal protection materials under high temperature and high-speed exhaust gas scouring still has certain shortcomings.

[0005] Currently, the ablation rate of thermal protection materials for aircraft is typically measured using non-dynamic methods. This involves measuring the changes in mass and thickness of the material before and after thermal testing using a precision balance and micrometer to obtain its mass ablation rate and average linear ablation rate. Alternatively, establishing suitable ablation models for thermal protection materials under different thermal environments and using numerical methods to predict the dynamic ablation rate is a convenient, quick, and low-cost method for obtaining parameters. However, the calculation results still require verification with accurate experimental data.

[0006] Therefore, how to design a dynamic measurement system for the ablation rate of thermal protection materials under high-temperature combustion gas, and overcome the problems of insufficient accuracy of the calculation results of the material ablation model and the difficulty of the static ablation rate measurement in reflecting the dynamic response relationship of the thermal structure regression amount with time, is a technical problem that urgently needs to be solved by those skilled in the art. Summary of the Invention

[0007] The technical problem to be solved by the present invention is to provide a dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high temperature gas conditions, which addresses the shortcomings of the prior art. This system is used to solve the problems of insufficient accuracy of calculation results of existing material ablation models and the difficulty in reflecting the dynamic response relationship of thermal structure regression over time in static ablation rate measurement.

[0008] The present invention adopts the following technical solution: a dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high temperature gas, comprising a sample placement unit, a gas generation unit, a laser displacement device and a data acquisition and processing system; The sample placement unit is used to place a thermal protection material sample. The gas generating unit includes a gas generator, which is arranged laterally at a distance from the sample placement unit. The flame nozzle of the gas generator is used to aim at the surface of the thermal protection material sample. The laser displacement device is used to dynamically capture the displacement change signal of the surface of the thermal protection material sample under the action of the gas generator; The data acquisition and processing system calculates the dynamic ablation rate of the thermal protection material sample under high-temperature gas based on the displacement change signal and the acquisition interval of the displacement change signal.

[0009] Preferably, the sample placement unit includes an optical air-float support frame and an optical air-float vibration-damping platform disposed thereon, wherein the optical air-float vibration-damping platform is provided with a sample holder for mounting thermal protection material samples.

[0010] Preferably, the optical air-bearing vibration isolation platform includes an optical vibration isolation table and an air-bearing support, wherein the air-bearing support is positioned between the optical air-bearing support frame and the optical vibration isolation table.

[0011] Preferably, the laser displacement device is located between the sample holder and the gas generator, the laser displacement device and the sample holder are arranged longitudinally at intervals, and the laser path of the laser displacement device extends obliquely to the surface of the heat protection material sample.

[0012] Preferably, the gas generating unit includes a mounting bracket, and a rotating platform is provided at the upper end of the mounting bracket. The rotating platform has a built-in rotating motor with its axis extending vertically. The gas generator is mounted on the rotating platform and is driven to rotate by the rotating motor.

[0013] Preferably, the rotating platform is slidably mounted on the mounting bracket in a lateral direction.

[0014] Preferably, a movable slide rail is arranged below the rotating platform, and the rotating platform is slidably mounted on the mounting bracket via the movable slide rail.

[0015] Preferably, the mounting bracket is a telescopic bracket that can be raised and lowered vertically.

[0016] Preferably, the gas generator includes a gas premixed combustion chamber, a flame nozzle, an air intake channel, a flow regulating valve, an igniter, a gas cylinder, and an oxygen cylinder. The air intake channel includes two channels, which respectively connect the gas cylinder and the oxygen cylinder, and the gas premixed combustion chamber. The flow regulating valve controls the flow rate and ratio of gas and oxygen in the gas premixed combustion chamber.

[0017] Preferably, both the sample placement unit and the gas generating unit are provided with travel wheels at their lower ends.

[0018] Compared with the prior art, the present invention has at least the following beneficial effects: The gas generator and the sample placement unit are arranged laterally at intervals. The flame nozzle of the gas generator can be directly facing the surface of the thermal protection material sample. The flame nozzle sprays high-temperature gas and evenly irradiates the surface of the thermal protection material sample, simulating the heating process of the aircraft thermal protection material sample during service. The surface of the thermal protection material sample undergoes ablation and regression under the action of high-temperature gas.

[0019] By capturing the displacement changes on the surface of thermal protection material samples using laser displacement equipment, and combining these displacement changes with the acquisition interval, the data acquisition system can calculate the dynamic ablation rate of the aircraft's thermal protection material under high-temperature exhaust gases. This enables dynamic, accurate, and real-time acquisition and output of the ablation rate of thermal protection materials under high-temperature exhaust gases, establishing a dynamic system for the ablation rate of thermal protection materials under high-temperature exhaust gases. This overcomes the problems of traditional static measurements of thermal protection material ablation rates, which cannot dynamically respond to changes, and the low accuracy of ablation model predictions.

[0020] Furthermore, the sample holder can be used to stably mount thermal protection material samples, and the optical air-bearing anti-vibration platform can achieve frictionless suspension, effectively isolating vibrations from the environment and providing a high level of stability for measurements.

[0021] Furthermore, the air-floating support utilizes high-pressure air to form a stable air mold between the optical isolation table and the optical air-floating support frame, suspending the optical isolation table. At the same time, the air mold has sufficient rigidity and load-bearing capacity to support the weight of the optical isolation table and attenuate external vibrations through damping, achieving frictionless suspension and efficient vibration isolation.

[0022] Furthermore, the laser displacement device is positioned between the sample holder and the gas generator, and the laser displacement device and the sample holder are arranged longitudinally at intervals, forming a triangle in space. This allows the flame path of the laser displacement device to be separated from that of the gas generator, thus avoiding damage to the laser displacement device. By solving the displacement change of the laser to the sample surface under a certain spatial angle, the ablation and retreat distance of the thermal protection material sample surface can be obtained.

[0023] Furthermore, the gas generating unit includes a separate mounting bracket on which the gas generator is mounted, facilitating adjustment of the distance between the gas generator and the heat protection material sample. The gas generator is rotatably mounted on the mounting bracket via a rotating platform. Before testing, the gas generator is rotated away from the heat protection material sample, and the flame nozzle is ignited and adjusted to spray a suitable amount of high-temperature gas. Then, the gas generator is rotated back to align with the heat protection material sample, ensuring the accuracy of the experiment.

[0024] Furthermore, the rotating platform is slidably mounted on the mounting bracket in the lateral direction, which facilitates the adjustment of the distance between the gas generator and the thermal protection material sample, thereby improving practicality.

[0025] Furthermore, the use of movable slide rails can guide the sliding of the rotating platform, ensuring the flexibility of gas generator displacement adjustment.

[0026] Furthermore, the mounting bracket is a telescopic bracket, which facilitates adjustment of the height of the gas generator to ensure that experimental measurements can be carried out at a suitable height.

[0027] Furthermore, the gas generator includes two air intake channels, allowing selection of different gas and oxygen mixtures. The flow rate and ratio of gas and oxygen in the gas premixing laboratory can be controlled by a flow regulating valve, enabling gas testing at different temperatures and making it suitable for different heating gas environments.

[0028] Furthermore, both the sample placement unit and the gas generation unit are equipped with travel wheels at their lower ends to facilitate the determination of appropriate laser paths, experimental positions, and directions.

[0029] In summary, the dynamic measurement system for the ablation rate of aircraft thermal protection materials under high-temperature gas conditions of the present invention can realize the dynamic and accurate measurement of the ablation rate of aircraft thermal protection materials under the action of high-temperature gas conditions. It makes up for the shortcomings of the current low accuracy and mostly static measurement of the dynamic measurement rate of aircraft thermal protection materials. It can reveal the dynamic change law of surface ablation and regression of aircraft thermal protection materials during service, and thus provide a theoretical basis for the refined design of ablation thermal protection system for aircraft thermal structures.

[0030] The technical solution of the present invention will be further described in detail below with reference to the accompanying drawings and embodiments. Attached Figure Description

[0031] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the following description of the relative embodiments will be briefly introduced. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0032] Figure 1 This is a front view of a dynamic measurement system for the ablation rate of thermal protection materials for aircraft under high-temperature gas conditions, according to the present invention. Figure 2 This is a top view of a dynamic measurement system for the ablation rate of thermal protection materials for aircraft under high-temperature gas conditions, according to the present invention. Figure 3 This is a schematic diagram of the ablation and migration process of a thermal protection material sample.

[0033] The components include: 1. Sample placement unit; 11. Optical air-float support frame; 111. Support base; 12. Optical air-float vibration isolation platform; 121. Optical vibration isolation table; 122. Air-float support; 13. Sample holder; 2. Gas generation unit; 21. Mounting bracket; 211. Handrail; 212. Braking device; 22. Rotating platform; 23. Gas generator; 231. Gas premixed combustion chamber; 232. Flame nozzle; 233. Air intake channel; 24. Moving slide rail; 3. Laser displacement device; 4. Thermal protection material sample; 5. Traveling wheels. Detailed Implementation

[0034] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0035] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "one side," "one end," and "one side," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0036] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0037] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described features, integrals, steps, operations, elements and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components and / or collections thereof.

[0038] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0039] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0040] The accompanying drawings illustrate various structural schematic diagrams according to embodiments disclosed in this invention. These drawings are not to scale, and some details have been enlarged for clarity, and some details may have been omitted. The shapes of the various regions and layers shown in the drawings, as well as their relative sizes and positional relationships, are merely exemplary and may deviate from reality due to manufacturing tolerances or technical limitations. Furthermore, those skilled in the art can design regions / layers with different shapes, sizes, and relative positions as needed.

[0041] This invention provides a dynamic measurement system for the ablation rate of thermal protection materials for aircraft under high-temperature combustion gases. It enables dynamic and accurate measurement of the ablation rate of thermal protection materials under high-temperature combustion gases, overcoming the shortcomings of current methods which have low accuracy and are mostly static measurements. This system can reveal the dynamic changes in the ablation and regression of thermal protection materials during service, thus providing a theoretical basis for the refined design of ablation protection systems for aircraft thermal structures.

[0042] Please see Figure 1 , 2 As shown, in this embodiment, the spacing between the sample placement unit 1 and the gas generating unit 2 is in the horizontal direction, and the direction perpendicular to the horizontal direction is in the vertical direction.

[0043] The present invention provides a dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high temperature gas conditions (hereinafter referred to as the dynamic measurement system), comprising a sample placement unit 1, a gas generation unit 2, a laser displacement device 3, and a data acquisition and processing system.

[0044] The sample placement unit 1 is used to place the thermal protection material sample 4. The gas generating unit 2 includes a gas generator 23, which is arranged laterally with the sample placement unit 1. The flame nozzle 232 of the gas generator 23 is used to aim at the surface of the thermal protection material sample 4.

[0045] The laser displacement device 3 is used to dynamically capture the displacement change signal of the surface of the thermal protection material sample 4 under the action of the gas generator 23. The data acquisition and processing system calculates the dynamic ablation rate of the thermal protection material under high-temperature gas based on the displacement change signal and the acquisition interval of the displacement change signal.

[0046] In summary, the gas generator 23 and the sample placement unit 1 are arranged laterally at intervals. The flame nozzle 232 of the gas generator 23 can be directly facing the surface of the thermal protection material sample 4. The flame nozzle 232 sprays high-temperature gas and evenly irradiates the surface of the thermal protection material sample 4, simulating the heating process of the aircraft thermal protection material sample 4 during service. The surface of the thermal protection material sample 4 undergoes surface ablation and regression under the action of high-temperature gas.

[0047] By capturing the displacement change signal of the surface retreat of the thermal protection material sample 4 using laser displacement device 3, and combining the displacement change signal with the acquisition interval, the data acquisition system can calculate the dynamic ablation rate of the aircraft's thermal protection material under high-temperature exhaust gases. This enables dynamic, accurate, real-time acquisition and output of the ablation rate of the thermal protection material under high-temperature exhaust gases, establishing a dynamic system for the ablation rate of the thermal protection material under high-temperature exhaust gases. This overcomes the problems of current methods that traditional static measurements of the ablation rate of thermal protection materials cannot dynamically respond to changes and the ablation model prediction results have low accuracy.

[0048] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0049] Please see Figure 1 and Figure 2 In this embodiment, the sample placement unit 1 of the dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to the present invention includes an optical air-bearing support frame 11 and an optical air-bearing vibration-damping platform 12 disposed thereon. A sample holder 13 is disposed on the optical air-bearing vibration-damping platform 12, and the sample holder 13 is used to install the thermal protection material sample 4. The sample holder 13 can stably install the thermal protection material sample 4, and the optical air-bearing vibration-damping platform can achieve frictionless suspension, effectively isolating vibrations from the environment and providing a high level of stability for measurement.

[0050] Specifically, in this embodiment, such as Figure 1 As shown, the sample holder 13 is an L-shaped mounting bracket, and the thermal protection material sample 4 is fixedly mounted on the vertical end face of the sample holder 13 facing the gas generator 23.

[0051] Preferably, a slot (not shown in the figure) is provided on the vertical end face of the sample holder 13. Specifically, the slot can be a T-shaped groove extending vertically at the center of the vertical end face. A T-shaped slider adapted to the groove is provided on the side of the thermal protection material sample 4 facing the sample holder 13. The thermal protection material sample 4 is slidably locked in the T-shaped groove by the T-shaped slider.

[0052] Of course, in other embodiments, when meeting actual usage requirements, the thermal protection material sample 4 can be fixed to the sample holder 13 by adhesive bonding. The specific bonding method and the choice of adhesive are common knowledge known to those skilled in the art, and will not be elaborated here.

[0053] In this embodiment, preferably, the optical air-float vibration isolation platform 12 includes an optical isolation stage 121 and an air-float support 122. The air-float support 122 is supported between the optical air-float support frame 11 and the optical isolation stage 121, connecting the optical isolation stage 121 and the optical air-float support frame 11. The sample holder 13 is disposed at the upper end of the optical isolation stage 121. The air-float support 122 uses high-pressure air to form a stable air mold between the optical isolation stage 121 and the optical air-float support frame 11, suspending the optical isolation stage 121. At the same time, the air mold has sufficient rigidity and load-bearing capacity to support the weight of the optical isolation stage 121 and attenuate external vibrations through damping, achieving frictionless suspension and efficient vibration isolation.

[0054] In this embodiment, the air flotation support 122 is an existing structure, and its specific structure and installation method are common knowledge known to those skilled in the art, and will not be described in detail here.

[0055] In this embodiment, as Figure 1 As shown, the upper surface of the optical vibration isolation stage 121 is a perforated plate, and the sample holder 13 is fastened to the perforated plate by bolt assembly. The perforated plate can be used to easily adjust the test position of the thermal protection material sample 4, and at the same time facilitate the calibration work before system testing.

[0056] Preferably, in this embodiment, the laser displacement device 3 is located between the sample holder 13 and the gas generator 23, and the laser displacement device 3 and the sample holder 13 are arranged longitudinally at intervals. Specifically, as shown... Figure 2 As shown, the laser displacement device 3 is set on the side of the optical vibration isolation table 121 facing the gas generation unit 2. The laser displacement device 3 and the sample holder 13 are arranged at intervals on the optical vibration isolation table 121, and the laser path of the laser displacement device 3 extends obliquely to the surface of the heat protection material sample 4.

[0057] Specifically, in this embodiment, the laser displacement device 3 includes a laser displacement meter. The laser displacement meter is selected as the measuring element for the dynamic ablation and migration of the thermal protection material sample 4. Its displacement accuracy can reach 1 μm, enabling dynamic measurement of the material's ablation displacement at high resolution. When the thermal protection material sample 4 undergoes surface ablation due to high-temperature combustion gas, the laser displacement meter can capture high-precision distance changes at the micrometer level from the laser displacement meter to the sample surface. Simultaneously, the sampling frequency of the laser displacement meter can be set up to a maximum of 392 kHz, enabling ultra-high frequency rapid acquisition of the dynamic ablation rate of the thermal protection material sample 4 under high-temperature combustion gas.

[0058] The laser displacement device 3 is positioned laterally between the sample holder 13 and the gas generator 23, and longitudinally spaced from the sample holder 13. Simultaneously, the laser displacement device 3 is positioned below the gas generator 23 in height, and its laser path extends obliquely to the surface of the heat-protective material sample 4. This triangular spatial arrangement separates the laser displacement device 3 from the flame path of the gas generator 23, preventing damage to the laser displacement device 3.

[0059] Since the ablation and regression changes of the thermal protection material sample 4 are measured under high-temperature combustion gases, the laser path of the laser displacement device 3 cannot be completely perpendicular to the material (i.e., not parallel to the flame direction). Therefore, the laser displacement device 3 needs to be placed on one side of the longitudinal direction, resulting in a certain spatial angle between the surface of the thermal protection material sample 4 and the laser. By solving for the displacement change of the laser to the sample surface at a certain spatial angle, the ablation and regression distance of the surface of the thermal protection material sample 4 can be obtained. Figure 3 The specific calculation process is as follows: Let position A be the location of laser displacement device 3, and let point O be the point on the surface of heat-protective material sample 4 where the laser beam from laser displacement device 3 strikes horizontally. Let X be the horizontal plane where the laser beam is located, and let L1 be the line on X parallel to the flame direction. Let B be the point where a perpendicular line drawn from point A intersects L1. OB Perpendicular to the sample surface. Establish triangle ABO.

[0060] After the test begins, following ablation, the surface of the heat-protective material sample 4 shifts from position a1 to position a2. The laser displacement device 3 then strikes the surface of the heat-protective material at point A1. A perpendicular line is drawn from point B to the sample surface, intersecting at point O1, thus establishing triangle A1O1O. BO The length becomes L BO1 Calculate L BO1 With L BO The difference OO1 can be used to obtain the backshift x.

[0061] Specifically, triangles ABO and A1O1O are similar triangles. The length of the laser length change A1O can be obtained through laser displacement device 3. The length of OO1 can be obtained by solving trigonometric functions, which is the ablation and relocation distance on the surface of the thermal protection material sample 4, i.e., the displacement x.

[0062] The above solution process is just one solution process. Of course, there are many other solution methods in other embodiments, as long as the ablation retreat distance can be obtained. They will not be elaborated on here.

[0063] During dynamic measurement, the data acquisition and processing system uses the time interval t between two displacement acquisitions and the ablation and retraction amount obtained from the two displacement acquisitions as the displacement amount x. Using the formula x / t=v, v is the calculated dynamic ablation rate.

[0064] Preferably, in this embodiment, the gas generating unit 2 further includes a mounting bracket 21, with a rotating platform 22 at its upper end. The gas generator 23 is mounted on the rotating platform 22, and the rotating platform 22 drives the gas generator to rotate. The gas generating unit 2 includes a separate mounting bracket 21, which facilitates adjusting the distance between the gas generator 23 and the thermal protection material sample 4.

[0065] Specifically, in this embodiment, the rotating platform 22 has a built-in rotating motor with its axis extending vertically, which drives the gas generator 23 to rotate. Before testing, the gas generator 23 is rotated away from the heat protection material sample 4, the flame nozzle 232 is ignited and adjusted to spray a suitable amount of high-temperature gas, and then the gas generator 23 is rotated back to align with the heat protection material sample 4 to ensure the accuracy of the experiment. At the same time, by rotating the gas generator 23 to align with the heat protection material sample 4, no manual adjustment is required, improving the safety and controllability of the experiment.

[0066] Preferably, in this embodiment, the rotating platform 22 is slidably mounted on the mounting bracket 21 in a lateral direction. This facilitates adjustment of the distance between the gas generator 23 and the heat protection material sample 4, improving practicality. Specifically, a movable slide rail 24 is arranged below the rotating platform 22, and the rotating platform 22 is mounted on the mounting bracket 21 via the movable slide rail 24.

[0067] Specifically, the length of the movable slide rail 24 extends laterally, and a matching slide groove is provided at the upper end of the mounting bracket 21 corresponding to the position of the movable slide rail 24. The movable slide rail 24 is slidably disposed in the slide groove, thereby driving the rotating platform 22 to slide laterally.

[0068] After the rotating platform 22 slides to the designated position, it needs to be fixed to the mounting bracket 21 to secure the position of the gas generator 23. Specifically, a locking groove is provided on the side of the mounting bracket 21 at the position corresponding to the slide groove. The length of the locking groove extends laterally, and the inner side of the locking groove communicates with the inside of the slide groove. A screw hole adapted to the width of the locking groove is provided on the movable slide rail 24 at the position corresponding to the locking groove. A locking bolt is inserted through the locking groove and screwed into the screw hole to clamp the movable slide rail 24 and the slide groove, thus fixing the position of the rotating platform 22.

[0069] Preferably, in this embodiment, the mounting bracket 21 is a telescopic bracket that can be raised and lowered vertically, which facilitates adjustment of the height of the gas generator 23 and ensures that experimental measurements can be carried out at a suitable height. Specifically, as shown... Figure 1As shown, the mounting bracket 21 is a telescopic bracket with a scissor lift structure. The scissor lift structure is used to achieve vertical lifting. Specifically, the scissor lift structure can be driven by a cylinder for lifting. At the same time, using the scissor lift structure to achieve lifting is a conventional setting for those skilled in the art, and will not be described in detail here.

[0070] Preferably, in this embodiment, the gas generator 23 includes a gas premixed combustion chamber 231, a flame nozzle 232, an air intake channel 233, a flow regulating valve, an igniter, a gas cylinder, and an oxygen cylinder. The flame nozzle 232 and the air intake channel are respectively arranged on both sides of the gas premixed combustion chamber 231. The air intake channel 233 includes two paths, one connecting the gas cylinder to the gas premixed combustion chamber 231, and the other connecting the oxygen cylinder to the gas premixed combustion chamber 231. Both air intake channels 233 are equipped with flow regulating valves to control the flow rate and ratio of gas and oxygen in the gas premixed combustion chamber 231. The gas generator 23 includes two air intake channels 233, allowing for the selection of different gas and oxygen mixtures. By controlling the flow rate and ratio of gas and oxygen in the gas premixed combustion chamber through the flow regulating valves, it can achieve gas testing at different temperatures and is suitable for different heating gas environments.

[0071] Preferably, in this embodiment, multiple traveling wheels 5 are provided at the lower end of the optical air-bearing support frame 11 and the lower end of the mounting bracket 21 to facilitate the determination of a suitable laser path, experimental position and direction.

[0072] Specifically, a support base 111 is provided at the lower end of the optical air buoyancy support frame 11. The upper end of the support base 111 is screwed into the support leg of the optical air buoyancy support frame 11. After it is moved into place, the support base 111 is screwed on to support it on the ground, fixing the position of the optical air buoyancy support frame 11. A handle 211 is provided on the side of the mounting bracket 21 facing away from the optical air buoyancy support frame 11 to facilitate the movement of the mounting bracket 21. At the same time, a brake device 212 is also provided on the lower part of this side of the mounting bracket 21 to fix the position of the mounting bracket 21. The specific structure of the brake device 212 is the same as that of a conventional trolley brake device 212, which is common knowledge known to those skilled in the art and will not be described in detail here.

[0073] Preferably, in this embodiment, the dynamic measurement system further includes a high-temperature colorimeter and an infrared thermal imager for detecting temperature and for calibrating flame temperature.

[0074] The testing process of the dynamic measurement system of the present invention is as follows: Before the test, the measurement accuracy of the laser displacement meter was calibrated. Samples were placed at fixed intervals along the same direction on the optical vibration isolation table 121. The laser displacement meter was used to confirm that the deviation between the measured distance and the actual distance was within ±5%, ensuring the accuracy of the displacement captured by the laser displacement meter during the dynamic retraction of the material.

[0075] Before testing, the temperature measuring devices, such as the high-temperature colorimeter and infrared thermal imager used to monitor the surface temperature of sample 4 of thermal protection material, were calibrated, and the temperature measuring accuracy of the two devices was verified by comparison.

[0076] Before testing, the gas generator 23 is rotated 90° clockwise to extend its length longitudinally. The gas flow rate and velocity in the inlet channel 233 of the gas generator 23 are adjusted by the flow regulating valve. Ignition is achieved by electric excitation, and the gas flame is ejected through the flame nozzle 232, ensuring that the flame nozzle 232 ejects a suitable size of high-temperature gas. A suitable size of high-temperature gas means that the flame can evenly irradiate the sample surface, avoiding a flame that is too large or too small.

[0077] Before testing, check the connections of all equipment, ensure that all components are assembled correctly, and that the displacement signals in the data acquisition and processing system are normal.

[0078] After ensuring the above operations are correct, the rotating bracket is rotated 90° counterclockwise using the electronic control device, so that the high-temperature gas flame emitted by the flame nozzle 232 evenly irradiates the surface of the thermal protection material sample 4. When the thermal protection material sample 4 exhibits ablation and migration, the dynamic ablation and migration amount of the thermal protection material sample 4 monitored by the laser displacement gauge during the thermal test is recorded by the data acquisition and processing system. Then, the data is calculated to obtain the dynamic ablation rate of the aircraft's thermal protection material under high-temperature gas. This completes the establishment of a dynamic and accurate measurement system for the ablation rate of thermal protection materials under high-temperature gas.

[0079] In summary, this invention provides a dynamic measurement system for the ablation rate of thermal protection materials in aircraft under high-temperature gas conditions. This system simulates the operational environment of an aircraft and measures the dynamic ablation rate of thermal protection materials under the scouring of high-temperature gas. It overcomes the shortcomings of current methods, which often rely on static measurements for dynamic ablation rate measurement of thermal protection materials. The system optimizes existing optical image measurement methods by using lasers to monitor displacement, thus achieving the goal of dynamic and accurate measurement of the ablation rate of thermal protection materials under high-temperature gas conditions.

[0080] The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made to the technical solution based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. A dynamic measurement system for the ablation rate of thermal protection materials for aircraft under high-temperature gas conditions, characterized in that, It includes a sample placement unit (1), a gas generation unit (2), a laser displacement device (3), and a data acquisition and processing system; The sample placement unit (1) is used to place the thermal protection material sample (4). The gas generating unit (2) includes a gas generator (23). The gas generator (23) and the sample placement unit (1) are arranged laterally at intervals. The flame nozzle (232) of the gas generator (23) is used to aim at the surface of the thermal protection material sample (4). The laser displacement device (3) is used to dynamically capture the displacement change signal of the surface of the thermal protection material sample (4) under the action of the gas generator (23); The data acquisition and processing system calculates the dynamic ablation rate of the thermal protection material sample (4) under high temperature gas based on the displacement change signal and the acquisition interval of the displacement change signal.

2. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 1, characterized in that, The sample placement unit (1) includes an optical air-bearing support frame (11) and an optical air-bearing vibration-damping platform (12) disposed thereon. The optical air-bearing vibration-damping platform (12) is provided with a sample holder (13) for installing a thermal protection material sample (4).

3. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 2, characterized in that, The optical air-bearing vibration isolation platform (12) includes an optical vibration isolation table (121) and an air-bearing support (122), wherein the air-bearing support (122) is supported between the optical air-bearing support frame (11) and the optical vibration isolation table (121).

4. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 2, characterized in that, The laser displacement device (3) is located between the sample holder (13) and the gas generator (23). The laser displacement device (3) and the sample holder (13) are arranged longitudinally at intervals. The laser path of the laser displacement device (3) extends obliquely to the surface of the thermal protection material sample (4).

5. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 1, characterized in that, The gas generating unit (2) includes a mounting bracket (21), and a rotating platform (22) is provided at the upper end of the mounting bracket (21). The rotating platform (22) has a built-in rotating motor with its axis extending vertically. The gas generator (23) is mounted on the rotating platform (22) and is driven to rotate by the rotating motor.

6. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 5, characterized in that, The rotating platform (22) is slidably mounted on the mounting bracket (21) in the lateral direction.

7. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 6, characterized in that, A movable slide rail (24) is arranged below the rotating platform (22), and the rotating platform (22) is slidably mounted on the mounting bracket (21) via the movable slide rail (24).

8. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 5, characterized in that, The mounting bracket (21) is a telescopic bracket that can be raised and lowered vertically.

9. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 1, characterized in that, The gas generator (23) includes a gas premixed combustion chamber (231), a flame nozzle (232), an air intake channel (233), a flow regulating valve, an igniter, a gas cylinder and an oxygen cylinder. The air intake channel (233) includes two channels, which connect the gas cylinder and the oxygen cylinder to the gas premixed combustion chamber (231) respectively. The flow regulating valve controls the flow rate and ratio of gas and oxygen in the gas premixed combustion chamber (231).

10. The dynamic measurement system for the ablation rate of thermal protection materials of aircraft under high-temperature gas conditions according to claim 1, characterized in that, Both the sample placement unit (1) and the gas generating unit (2) are equipped with travel wheels (5) at their lower ends.

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