Aircraft component high-speed rain and snow impact simulation test device and test method

Abstract

This invention relates to the field of low-altitude environmental impact simulation testing technology for aircraft, and particularly to a high-speed rain and snow impact simulation test device and method for aircraft components. The device includes a support platform, a test chamber, a rain and snow simulation system, a high-speed airflow generation system, and a sample clamping system. The test chamber is positioned above the support platform. The rain and snow simulation system includes a tubular shroud, cold air nozzles, atomizing nozzles, and a converging nozzle. The tubular shroud is located inside the test chamber. The cold air nozzles and atomizing nozzles are spaced circumferentially along the inner wall of the tubular shroud. The converging nozzle is connected to the outlet of the high-speed airflow generation system and is coaxially arranged with the tubular shroud. The high-speed airflow ejected by the high-speed airflow generation system drives the airflow within the tubular shroud, causing water mist to mix with the deep-cooled air, condense into ice crystals, and be blown towards the sample. The sample clamping system is located inside the test chamber for holding the sample. This invention can realistically simulate the complex physical process of the instantaneous phase change of droplets impacting clouds at high speed when an aircraft passes through them.

Description

Technical Field

[0001] This invention relates to the field of low-altitude environmental impact simulation testing technology for aircraft, and in particular to a high-speed rain and snow impact simulation testing device and method for aircraft components. Background Technology

[0002] When aircraft components such as windows and their surface coatings (typically made of infrared-transmitting materials like sapphire, zinc sulfide, or germanium) are impacted by raindrops, fog, or ice crystals, they undergo a series of complex physical and optical effects: Severe mechanical impacts can cause microscopic or macroscopic brittle cracks, scratches, or even chipping on the surface (especially with ice crystals), significantly increasing surface roughness; the instantaneous temperature difference generated by high-speed impacts can cause localized cracking or thermal stress damage to the material (for ice crystal impacts, the absorption / release of latent heat during phase transitions is also involved); water droplets and fog adhering to or penetrating the surface microcracks can form water films or droplets, while residual frost from the impact can cover... On the surface of the cover, these deposits, due to the difference in refractive index between them and air, induce a strong scattering effect. The combined effect of the above factors causes the incident infrared radiation (especially in the mid- and long-wave bands) to undergo a sharp attenuation (reduced transmittance), significant wavefront distortion (damage to optical homogeneity), and severe backscattering (increased system noise) during transmission. This severely interferes with or even blocks the infrared sensor from acquiring clear and accurate target radiation information, and may also affect the aerodynamic and thermodynamic properties related to the cover. This is essentially a multi-physics coupling process involving fluid dynamics impact, material mechanical response, optical scattering / absorption, and heat exchange.

[0003] Currently, the primary method for real-time simulation of high-speed aircraft is wind tunnel testing. Wind tunnels can provide extremely high gas flow rates to accurately simulate the attitude, stress, and wear of an aircraft during flight. However, this simulation is limited to clean air. In reality, it cannot effectively simulate and analyze environments with high levels of foreign matter, such as sand, rain, and snow, during low-altitude flight. Existing sand erosion devices mainly simulate low-to-medium speed sand erosion through sand ejection, mixing, and jet propulsion. These simulations are suitable for wind turbine blades and low-altitude aircraft, but they do not consider the impact of rain, snow, and water and ice during high-speed cloud penetration.

[0004] In the prior art, Chinese patent application CN114088551A discloses a coating material impact resistance testing device that considers ambient temperature. This device can perform droplet impact tests under different ambient temperatures, but it can only spray droplets and lacks the ability to convert droplets into ice crystals, thus failing to simulate ice crystal impact conditions. Chinese patent application CN214200570U discloses an icing wind tunnel ice crystal simulation system that uses an ice maker, ice crusher, and refrigerant source to generate ice crystals. However, this method involves offline pre-fabrication of ice crystals, which are prone to melting and adhesion during storage and transportation, failing to simulate the real physical process of droplets freezing instantaneously in high-speed airflow. Chinese patent application CN119223573A discloses an ejector-type low-temperature rain and snow environment ice wind tunnel simulation testing device. This device relies on the low-temperature environment of the entire wind tunnel to allow droplets to freeze naturally over long distances, failing to achieve active and rapid phase change of droplets at the nozzle. Therefore, the dedicated testing device for evaluating the performance of aircraft components under high-speed rain and snow impacts is the first of its kind. Summary of the Invention

[0005] The purpose of this invention is to provide a high-speed rain and snow impact simulation test device and test method for aircraft components, so as to simulate the impact damage of aircraft components when they encounter complex meteorological conditions such as rain, snow and ice crystals during high-speed flight, and in particular, to simulate the real physical process of phase change of droplets at the moment of high-speed impact.

[0006] To achieve the above objectives, in a first aspect, the present invention provides a high-speed rain and snow impact simulation test apparatus for aircraft components, comprising: Support platform; The test chamber is located above the support platform; A rain and snow simulation system is used to generate water droplets or ice crystals impacting a medium. The rain and snow simulation system includes: A tubular enclosure is installed inside the test chamber; A cold air nozzle is disposed inside the tubular cover, and multiple cold air nozzles are arranged circumferentially along the inner wall of the tubular cover to spray deep cold air into the tubular cover. Atomizing nozzles are disposed inside the tubular cover, and multiple atomizing nozzles are arranged circumferentially along the inner wall of the tubular cover for spraying water mist into the tubular cover. A high-speed airflow generating system has a converging nozzle at its outlet, which is installed inside the tubular shroud and coaxially arranged with the tubular shroud. The high-speed airflow ejected by the converging nozzle drives the airflow inside the tubular shroud, causing the sprayed water mist to mix with the cryogenic air and condense into ice crystals, which are then blown onto the sample. A sample clamping system, located inside the test chamber, is used to clamp the sample.

[0007] Optionally, the atomizing nozzle is a detachable structure, allowing for the generation of droplets of different sizes by replacing nozzles of different diameters; and / or The atomizing nozzle and the cooling nozzle are spaced apart axially on the tubular cover, with the atomizing nozzle closer to the end of the tubular cover facing the test sample, and the outlet of the converging nozzle closer to the end of the tubular cover facing the test sample than the atomizing nozzle.

[0008] Optionally, the sample clamping system includes: A clamping holder for holding a sample in at least two directions; A pitch adjustment mechanism, connected to the clamping seat, is used to adjust the pitch angle of the sample; A rotating mechanism, connected to the pitch adjustment mechanism, is used to drive the sample to rotate circumferentially; A height adjustment mechanism, connected to the rotation mechanism, is used to adjust the height of the sample; The heating unit and temperature feedback device are used to control the sample temperature from room temperature to the set temperature.

[0009] Optionally, the clamping base includes multiple clamping arms that intersect at the center, each clamping arm is provided with a slide rail and a set of clamping sliders; each set of clamping sliders includes two clamping sliders and is configured to be fixed along the slide rail at any position to achieve clamping of samples of different sizes, and the heating unit and temperature feedback device are located at the center of the clamping base.

[0010] Optionally, the support platform has a receiving space, and the platform surface of the support platform is provided with a waste liquid collection hole that connects the test chamber and the receiving space; The cold air nozzle is connected to the cryogenic air generator, the atomizing nozzle is connected to the water storage tank, and the cryogenic air generator and the water storage tank are arranged within the accommodating space; The containment space is also equipped with a waste liquid recovery tank, which is connected to the waste liquid collection hole and is used to collect the waste liquid in the test chamber.

[0011] Optionally, the high-speed airflow generating system further includes an air compressor and a pressure stabilizing chamber. The pulsed high-pressure gas generated by the air compressor is rectified and stabilized in the pressure stabilizing chamber and then delivered to the contraction nozzle for high-speed ejection.

[0012] Optionally, the high-speed rain and snow impact simulation test device also includes a damaged surface identification system, which is set in the test chamber to collect images of the sample surface and identify and quantitatively evaluate the damaged areas; The damaged surface identification system further includes an identification algorithm, which is configured as follows: Acquire high-resolution digital images of the sample surface; Preprocess the image; Extract the damaged areas from the image; Quantitative analysis of the damaged area was performed to calculate the percentage of the damaged area.

[0013] Optionally, the recognition algorithm is specifically configured as follows: The acquired images are preprocessed by grayscale conversion, filtering and noise reduction, and contrast enhancement. Local Gaussian weighted adaptive thresholding is used for threshold segmentation, and the Canny edge detection operator is used to extract edges. Perform a logical OR operation between the threshold segmentation result and the edge detection result to merge damaged pixels; By connecting the broken edges through morphological manipulation, a complete outline of the damaged area can be formed; The actual damage area is selected based on geometric features; Statistical analysis of pixel area of ​​damaged region Calculate the pixel area of ​​the entire measured region. The percentage of damaged area is calculated according to the following formula. : .

[0014] Optionally, the recognition algorithm is specifically configured to: continuously acquire photos during the rotation of the conformal sample, stitch the photos together to obtain a complete three-dimensional model, and then calculate and evaluate the damage.

[0015] Secondly, the present invention also provides a method for simulating high-speed rain and snow impact on aircraft components, applied to the test apparatus described in any one of the first aspects, comprising the following operating modes: Working mode one, simulating high-speed rain and fog impact: activate the high-speed airflow generation system and atomizing nozzles to spray water droplets; Working mode two, simulating high-speed ice crystal impact: Activate the high-speed airflow generation system, atomizing nozzle and cold air nozzle, so that the water mist sprayed from the atomizing nozzle mixes with the deep cold air sprayed from the cold air nozzle in the tubular hood and condenses into ice crystals. The ice crystals are sprayed out with the high-speed airflow and impact the sample.

[0016] The above-described technical solution of the present invention has the following advantages: The present invention provides a high-speed rain and snow impact simulation test device for aircraft components, comprising a support platform, a test chamber, a rain and snow simulation system, a high-speed airflow generation system, and a sample clamping system. The test chamber is positioned above the support platform. The rain and snow simulation system includes a tubular shroud, cold air nozzles, atomizing nozzles, and a converging nozzle. The tubular shroud is located inside the test chamber. The cold air nozzles and atomizing nozzles are spaced apart circumferentially along the inner wall of the tubular shroud. The converging nozzle is connected to the outlet of the high-speed airflow generation system and is coaxially arranged with the tubular shroud. The high-speed airflow ejected by the high-speed airflow generation system drives the airflow within the tubular shroud, causing water mist to mix with the cryogenic air, condense into ice crystals, and be blown towards the sample. The sample clamping system is located inside the test chamber for clamping the sample. This invention achieves uniform mixing of cryogenic air and water mist by arranging cold air nozzles and atomizing nozzles circumferentially along the inner wall of the tubular cover and under the action of coaxial contraction nozzles. This allows ice crystals to be uniformly generated within the tubular cover and stably transported by high-speed airflow, solving the problems of uneven ice crystal distribution and unstable impact effect in the prior art. It can realistically simulate the complex physical process of instantaneous phase change of droplets when an aircraft passes through clouds at high speed. Attached Figure Description

[0017] The accompanying drawings are provided for illustrative purposes only, and the proportions and quantities of the components in the drawings may not be consistent with the actual product.

[0018] Figure 1 This is a schematic diagram of a high-speed rain and snow impact simulation test device in an embodiment of the present invention. The support platform and test chamber have been cut out. Figure 2 This is a schematic diagram of the orthographic projection of one end of a tubular cover in an embodiment of the present invention; Figure 3 yes Figure 2 A schematic diagram of the AA cross-sectional structure in the diagram; Figure 4 This is a schematic diagram of the structure of a clamping seat in an embodiment of the present invention; Figure 5 This is a schematic diagram of a sample clamping system simulating a pitching flight attitude in an embodiment of the present invention; Figure 6 This is a schematic diagram of a sample clamping system simulating a diving posture in an embodiment of the present invention; Figure 7 This is a damage area identification map output by the damage surface identification system in this embodiment of the invention after scanning a planar sample; Figure 8 This is a damage area identification map output by the damage surface identification system in this embodiment of the invention after scanning a conformal sample.

[0019] In the picture: 1: Support platform; 11: Accommodation space; 2: Experimental chamber; 3: Rain and snow simulation system; 301: Tubular cover; 302: Cold air nozzle; 303: Atomizing nozzle; 304: Cold air guide ring; 305: Antifreeze air pipe; 306: Cryogenic air generator; 307: Cold air throttle valve; 308: Cryogenic air generator valve; 309: Water guide ring; 310: Water supply pipe; 311: Water supply throttle valve; 312: Water pump valve; 313: Water storage tank; 314: Water pump; 315: Cover support frame; 4: High-speed airflow generation system; 41: Contracting nozzle; 42: Airflow duct; 43: Jet throttle valve; 44: Air compressor; 45: Air compressor valve; 46: Pressure stabilizing chamber; 47: Pressure stabilizing chamber barometer; 5: Sample clamping system; 51: Clamping base; 511: Clamping arm; 512: Clamping slider; 513: Slider guide rail; 514: Heating unit; 52: Hinge shaft; 53: Rotation mechanism; 54: Displacement rack; 6: Damaged surface identification system; 61: Camera; 62: Camera baffle; 63: Isolation gate; 64: Gate valve; 7: Waste liquid recovery box; 100: Sample. Detailed Implementation

[0020] 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 embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] This embodiment provides a high-speed rain and snow impact simulation test device for aircraft components, such as... Figure 1 As shown, the device includes a support platform 1, a test chamber 2, a rain and snow simulation system 3, a high-speed airflow generation system 4, and a sample clamping system 5.

[0022] The support platform 1 is used to support the entire device. The test chamber 2 is set above the support platform 1, forming a closed test space to avoid external environmental interference and ensure the accuracy of the test results.

[0023] The sample clamping system 5 is installed inside the test chamber 2 and is used to clamp the aircraft component sample 100.

[0024] The rain and snow simulation system 3 is installed inside the test chamber 2 to generate water droplets or ice crystals impacting the medium. The rain and snow simulation system 3 includes a tubular hood 301, cold air nozzles 302, atomizing nozzles 303, and a converging nozzle 41. The tubular hood 301 is installed inside the test chamber 2. Multiple cold air nozzles 302 are installed inside the tubular hood 301, and are spaced apart circumferentially along the inner wall of the tubular hood 301, for spraying deeply cold air into the tubular hood 301. Multiple atomizing nozzles 303 are installed inside the tubular hood 301, and are spaced apart circumferentially along the inner wall of the tubular hood 301, for spraying water mist into the tubular hood 301.

[0025] The high-speed airflow generating system 4 has a converging nozzle 41 at its outlet for accelerating the airflow. Its structure is a smooth, arc-shaped converging pipe (converging towards the sample). The converging nozzle 41 is located inside the tubular shroud 301 and is coaxially aligned with it. The converging nozzle 41 increases the velocity of the ejected air, thereby accelerating the airflow within the tubular shroud 301. This ensures that the ice crystals impact the sample with the shortest path and fastest speed, reducing melting and adhesion of the ice crystals during transport and guaranteeing the stability and authenticity of the impact effect.

[0026] This embodiment achieves uniform mixing of cryogenic air and water mist by arranging the cold air nozzle 302 and atomizing nozzle 303 circumferentially along the inner wall of the tubular cover 301 and under the action of the coaxial contraction nozzle 41. This allows ice crystals to be uniformly generated in the tubular cover 301 and stably transported by the high-speed airflow, solving the problems of uneven ice crystal distribution and unstable impact effect in the prior art.

[0027] See one example. Figure 2 In the axial orthogonal projection direction of the tubular cover 301, a plurality of cold air nozzles 302 and a plurality of atomizing nozzles 303 are arranged alternately. This further improves the mixing uniformity of the cryogenic air and water mist.

[0028] See one example. Figure 2 and Figure 3 The atomizing nozzle 303 has a detachable structure, and droplets of different sizes can be obtained by replacing nozzles of different diameters.

[0029] Along the axial direction of the tubular cover 301, the atomizing nozzle 303 and the cooling nozzle 302 are spaced apart, with the atomizing nozzle 303 being closer to the end of the tubular cover 301 facing the test sample, and the outlet of the constricting nozzle 41 being closer to the end of the tubular cover 301 facing the test sample than the atomizing nozzle 303.

[0030] During operation, the high-speed airflow generated by the high-speed airflow generation system 4 is ejected at high speed through the converging nozzle 41, forming a low-pressure zone in front of the converging nozzle 41, which attracts airflow within the tubular shroud 301. Water mist ejected from the atomizing nozzle 303 mixes with cryogenic air ejected from the cooling nozzle 302 within the tubular shroud 301, condensing into ice crystals. The airflow causes the cryogenic air to carry the ice crystals towards the sample 100, ejecting the condensed ice crystals along with the high-speed airflow, impacting the sample surface. This scheme simulates the real physical process of a droplet undergoing a phase change just before impact when passing through clouds at high speed, improving experimental accuracy. Preferably, the tubular shroud 301 is converging at one end towards the sample 100, i.e., the tubular shroud 301 is flared overall, further increasing the upper limit of the impact velocity of the ice crystals.

[0031] See one example. Figure 1 and Figure 3 Multiple cold air nozzles 302 are evenly distributed circumferentially along a cold air guide ring 304, which is installed on the inner wall of the tubular shroud 301 and connected to a cryogenic air generator 306 via an antifreeze pipe 305. A cryogenic air generator valve 308 is located on the connecting pipe and is used to control the flow rate of the cryogenic air, which can be adjusted via a cold air throttle valve 307. Multiple atomizing nozzles 303 are evenly distributed circumferentially along a water guide ring 309, which is installed on the inner wall of the tubular shroud 301 and connected to a water storage tank 313 via a water supply pipe 310. A water supply throttle valve 311 is located on the pipe between a water pump 314 and the atomizing nozzles 303 and is used to adjust the water flow rate. A water pump valve 312 is used to control the start and stop of the water pump 314. The tubular shroud 301 is fixed inside the test chamber 2 by a shroud support frame 315.

[0032] See one example. Figures 4 to 6 The sample clamping system 5 includes a clamping base 51, a pitch adjustment mechanism, a rotation mechanism 53, a height adjustment mechanism, a heating unit 514, and a temperature feedback device (not shown in the figure).

[0033] The clamping base 51 is used to clamp the sample in at least two directions. A pitch adjustment mechanism is connected to the clamping base 51 to adjust the pitch angle of the sample (see [reference]). Figure 5 and Figure 6 The rotation mechanism 53 is connected to the pitch adjustment mechanism to drive the sample to rotate 100 degrees circumferentially. The altitude adjustment mechanism is connected to the rotation mechanism 53 to adjust the altitude of the sample. The multi-degree-of-freedom adjustment capability (pitch, rotation, altitude) of this design allows the device to simulate the impact conditions of rain and snow on an aircraft in various flight attitudes such as level flight, pitching flight, diving, and rolling, providing a possibility for comprehensively evaluating the impact resistance performance of aircraft components under different flight conditions.

[0034] The heating unit 514 and temperature feedback device are used to control the sample temperature from room temperature to a set temperature (e.g., 200°C). This enables precise control of the sample surface temperature and can simulate the extreme "hot substrate-cold impact" condition where an aircraft suddenly encounters ice crystals from cold clouds during hot flight (such as surface heating caused by supersonic cruise). It covers the typical temperature range of an aircraft from cold start to high-speed flight, making the test results closer to the actual service conditions.

[0035] It is worth noting that the pitch adjustment mechanism, rotation mechanism 53, and height adjustment mechanism can all achieve the present invention using existing structures. In a specific example, the pitch adjustment mechanism employs a hinge structure. For instance, the clamping seat 51 is hinged to the rotation mechanism 53 via a hinge shaft 52. The rotation mechanism 53 is a segmented rotating seat, divided into two sections: a rotating section connected to the clamping seat 51 and a fixed section connected to the height adjustment mechanism. A rotary motor is installed in the fixed section, driving the rotating section to rotate, thereby causing the clamping seat 51 to rotate. The height adjustment mechanism employs a gear and displacement rack 54 mechanism. The displacement rack 54 is vertically positioned, and the gear (not shown in the figure) is located within the fixed section of the rotation mechanism 53 and is driven by a motor (not shown in the figure), causing the entire rotation mechanism 53 to move up and down along the displacement rack 54.

[0036] See one example. Figure 4 The clamping base 51 includes multiple clamping arms 511 that intersect at the center (on the same plane). Each clamping arm 511 is provided with a slide rail 513 and a set of clamping sliders 512. Each set of clamping sliders 512 includes two clamping sliders configured to slide along the slide rail 513 and can be fixed at any position by bolts, which can adapt to aircraft component samples of different sizes and shapes (such as flat windows, curved fairings, etc.), improving the versatility of the device. The heating unit 514 is located at the center of the clamping base 51. This ensures that heat is evenly conducted from the center of the sample to the surrounding area, avoiding local overheating or temperature unevenness, ensuring the consistency of the sample surface temperature, and making the "hot substrate-cold shock" simulation more realistic and reliable. In this embodiment, the heating unit 514 can use existing heating equipment such as electric heating wire. The temperature feedback device can use an existing thermal sensor, which is set on the clamping base 51. The clamping base 51 is formed by two clamping arms 511 arranged vertically, with the electric heating wire coiled in the middle of the two clamping arms 511.

[0037] See one example. Figure 1 The support platform 1 has a receiving space 11. A waste liquid collection hole is provided on the surface of the support platform 1, connecting the test chamber 2 and the receiving space 11. A cold air nozzle 302 is connected to a cryogenic air generator 306. An atomizing nozzle 303 is connected to a water storage tank 313. The cryogenic air generator 306 and the water storage tank 313 are located within the receiving space 11.

[0038] The containment space 11 is also equipped with a waste liquid recovery tank 7. The waste liquid recovery tank 7 is connected to the waste liquid collection hole and is used to collect the waste liquid in the test chamber 2. The waste liquid generated by the test is automatically guided to the waste liquid recovery tank 7 through the waste liquid collection hole, which avoids the accumulation of waste liquid in the test chamber 2 and affects subsequent tests. At the same time, it realizes the centralized treatment of waste liquid and meets environmental protection requirements.

[0039] The integrated design of this example solution centrally houses the cryogenic air generator 306, water storage tank 313, waste liquid recovery tank 7, and other equipment within the accommodating space 11 of the support platform 1. This results in a compact structure with minimal space requirements, eliminating the need for external water or air sources and facilitating laboratory setup and operation. Simultaneously, it shortens the transport distance between the cold air nozzle 302 and the cryogenic air generator 306, and between the atomizing nozzle 303 and the water storage tank 313, reducing energy loss and media state changes, and ensuring a stable output of the impact medium.

[0040] See one example. Figure 1 and Figure 3 The high-speed airflow generation system 4 includes an air compressor 44 and a pressure stabilizing chamber 46. The pulsed high-pressure gas generated by the air compressor 44 is rectified and stabilized in the pressure stabilizing chamber 46, then transported through the airflow duct 42 into the tubular housing 301 and ejected at high speed through the converging nozzle 41. The rectification and stabilization effect of the pressure stabilizing chamber 46 transforms the pulsed high-pressure gas generated by the air compressor 44 into a stable and uniform high-speed airflow, eliminating the influence of airflow pulsation on the impact effect and ensuring the consistency of each impact. The stable airflow allows ice crystals to be ejected at a constant speed at the exit of the converging nozzle 41, making the impact angle and impact force more controllable, and significantly improving the repeatability and reliability of the test results. In this example, the high-speed airflow generation system 4 is configured with a maximum airflow speed of Mach 0.8 to simulate the typical operating conditions of low-altitude high-speed flight of an aircraft, covering the actual service conditions of most aircraft components.

[0041] In a specific example, a pressure gauge 47 is provided in the pressure stabilizing chamber to monitor the pressure. An air compressor valve 45 is provided at the outlet of the air compressor 44 to control airflow interruption and coarsely adjust the airflow pressure, providing a basis for subsequent precise adjustments. An air jet throttle valve 43 is provided on the airflow duct 42 between the pressure stabilizing chamber 46 and the contraction nozzle 41 for fine-tuning the airflow velocity, achieving precise control of the airflow velocity and allowing operators to set appropriate impact intensities according to different test requirements.

[0042] To enhance the in-situ identification capabilities of the device and ensure the accuracy of the evaluation results, in one example, the high-speed rain and snow impact simulation test device also includes a damaged surface identification system 6, which is installed inside the test chamber 2. This system is used to acquire images of the sample surface and identify and quantitatively evaluate the damaged areas. The damaged surface identification system 6 includes a camera 61 and an identification algorithm.

[0043] The recognition algorithm is configured as follows: Acquire high-resolution digital images of the sample surface; Preprocess the image; Extract the damaged areas from the image; Quantitative analysis of the damaged area was performed to calculate the percentage of the damaged area.

[0044] After the impact test is completed, the rain and snow simulation system and the high-speed airflow generation system are first shut down. After the medium in test chamber 2 settles or is discharged, the isolation gate 63 is raised for damage identification, avoiding secondary damage that may occur during sample transfer and ensuring the accuracy of the evaluation results. Furthermore, quantitative analysis replaces manual visual inspection, elevating traditional qualitative observation (such as the presence or absence of cracks) to quantitative calculation (damage area ratio), providing objective and quantifiable evaluation indicators for the material's impact resistance. Automated identification significantly improves evaluation efficiency; from the completion of the impact test to obtaining damage data takes only a few minutes, truly achieving the integration of working condition simulation and rapid detection.

[0045] In a specific example, the recognition algorithm is configured as follows: The acquired images undergo preprocessing including grayscale conversion, denoising filtering, and contrast enhancement. Grayscale conversion converts the color RGB image to a grayscale image, reducing data volume and improving processing speed. Denoising filtering employs algorithms such as Gaussian filtering and median filtering to suppress random noise in the image while preserving damage edge information as much as possible. Contrast enhancement uses methods such as histogram equalization to enhance the contrast between the damaged area and the background area, making features such as scratches and cracks more prominent.

[0046] Local Gaussian weighted adaptive thresholding is used for threshold segmentation, while the Canny edge detection operator is used to extract edges. The local Gaussian weighted adaptive thresholding calculates the threshold separately based on the distribution of pixel values ​​in the neighborhood of each pixel in the image, thereby effectively segmenting damaged areas with gray values ​​that differ from the background (such as dark scratches and pits); the Canny edge detection operator can capture the clear edges of linear damage such as cracks very well.

[0047] The binarized region obtained from threshold segmentation is logically ORed with the edge contour obtained from edge detection to merge all possible damaged pixels. Morphological operations (such as dilation and erosion) are then used to connect broken edges and fill small holes, forming a complete and connected damaged region contour. Based on geometric features such as the aspect ratio of the scratch and the roundness of the pit, the connected regions are filtered to remove minor false features caused by noise, ultimately determining the true damaged region.

[0048] Statistical analysis of pixel area of ​​damaged region Calculate the pixel area of ​​the entire measured region. The percentage of damaged area is calculated according to the following formula. : .

[0049] See Figure 7 This is a damage area identification map output after scanning a planar sample. After calculation using pixel statistics methods, the percentage of the damaged area is... It is 15%. Figure 8 This is a damage area identification map output after scanning a conformal sample. After calculation using pixel statistics methods, the percentage of the damage area is... It is 20%.

[0050] The recognition algorithm in this example effectively improves image quality through multi-step image preprocessing, making subsequent damage identification more accurate, and achieving reliable recognition results even under complex conditions such as low light or residual media. By employing a two-pronged approach of threshold segmentation and edge detection, it can simultaneously identify planar damage (such as pits and spalling) and linear damage (such as scratches and cracks), avoiding the limitations of single methods and achieving comprehensive detection of all types of damage. Morphological operations and geometric feature screening eliminate noise interference, ensuring the authenticity and reliability of the identified damage areas and avoiding false positives and false negatives. The use of pixel statistics to quantitatively calculate the damage level provides an intuitive and comparable numerical indicator, facilitating performance comparisons under different materials and working conditions.

[0051] In one example, the identification algorithm is specifically configured to: continuously acquire photographs during the rotation of the conformal sample, stitch the photographs together to obtain a complete 3D model, and then calculate and evaluate the damage. This addresses the challenge of identifying curved surface samples. For non-planar samples such as conformal windows and curved fairings, traditional methods struggle to acquire complete surface images in a single operation. This solution, through continuous rotational acquisition and photographic stitching, unfolds the 3D curved surface into a 2D plane, enabling quantitative analysis.

[0052] The all-around, blind-spot-free inspection is achieved by driving the sample to rotate through the rotating mechanism 53. The camera 61 can collect images from multiple angles, ensuring that every area of ​​the sample surface is covered and no damage on the back side is missed.

[0053] Photo stitching ensures the accuracy of the 3D model, making the calculated damage area proportion accurate. It accurately reflects the overall degree of damage and provides a reliable means for evaluating the impact resistance of curved components.

[0054] See one example. Figure 1 The damaged surface identification system 6 includes a camera 61, a camera baffle 62, an isolation gate 63, and a gate valve 64. The camera 61 is mounted facing the sample 100. Camera baffles 62 are provided in multiple directions around the camera 61, forming a shell-like structure that surrounds the camera 61 to protect it. In this example, the camera baffles 62 are made of transparent material, with at least one transparent material at the end facing the sample 100. The isolation gate 63 is positioned between the tubular cover 301 and the sample 100, and can be moved up and down within the test chamber 2 by operating the gate valve 64 located outside the test chamber 2. This allows for easy adjustment to a suitable position to protect the camera 61 as much as possible without affecting the test.

[0055] This embodiment also provides a method for simulating high-speed rain and snow impact on aircraft components using any of the above-mentioned simulation test devices, including the following operating modes: Working mode one, simulating high-speed rain and fog impact: activate the high-speed airflow generation system and atomizing nozzles to spray water droplets; Working mode two, simulating high-speed ice crystal impact: Activate the high-speed airflow generation system, atomizing nozzle and cold air nozzle, so that the water mist sprayed from the atomizing nozzle mixes with the deep cold air sprayed from the cold air nozzle in the tubular hood and condenses into ice crystals. The ice crystals are sprayed out with the high-speed airflow and impact the sample.

[0056] This method can simulate both rain / fog impact and ice crystal impact using the same set of equipment, significantly reducing equipment costs and improving laboratory space utilization. Standardized operation provides a standardized test procedure for evaluating the rain and snow impact resistance of aircraft components, making test results from different laboratories and batches comparable.

[0057] Any aspects of this invention not described in detail are common knowledge or prior art in the field.

[0058] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that not every embodiment contains only one independent technical solution, and in the absence of conflict between solutions, the various technical features mentioned in each embodiment can be combined in any way to form other implementation methods that can be understood by those skilled in the art.

[0059] Furthermore, without departing from the scope of the present invention, modifications to the technical solutions described in the foregoing embodiments, or equivalent substitutions of some of the technical features, shall not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A high-speed rain and snow impact simulation test device for aircraft components, characterized in that, include: Support platform; The test chamber is located above the support platform; A rain and snow simulation system is used to generate water droplets or ice crystals impacting a medium. The rain and snow simulation system includes: A tubular enclosure is installed inside the test chamber; A cold air nozzle is disposed inside the tubular cover, and multiple cold air nozzles are arranged circumferentially along the inner wall of the tubular cover to spray deep cold air into the tubular cover. Atomizing nozzles are disposed inside the tubular cover, and multiple atomizing nozzles are arranged circumferentially along the inner wall of the tubular cover for spraying water mist into the tubular cover. A high-speed airflow generating system has a converging nozzle at its outlet, which is installed inside the tubular shroud and coaxially arranged with the tubular shroud. The high-speed airflow ejected by the converging nozzle drives the airflow inside the tubular shroud, causing the sprayed water mist to mix with the cryogenic air and condense into ice crystals, which are then blown onto the sample. A sample clamping system, located inside the test chamber, is used to clamp the sample.

2. The high-speed rain and snow impact simulation test device according to claim 1, characterized in that: The atomizing nozzle has a detachable structure, allowing for the replacement of nozzles with different diameters to obtain droplets of different sizes; and / or The atomizing nozzle and the cooling nozzle are spaced apart axially on the tubular cover, with the atomizing nozzle closer to the end of the tubular cover facing the test sample, and the outlet of the converging nozzle closer to the end of the tubular cover facing the test sample than the atomizing nozzle.

3. The high-speed rain and snow impact simulation test device according to claim 1, characterized in that, The sample clamping system includes: A clamping holder for holding a sample in at least two directions; A pitch adjustment mechanism, connected to the clamping seat, is used to adjust the pitch angle of the sample; A rotating mechanism, connected to the pitch adjustment mechanism, is used to drive the sample to rotate circumferentially; A height adjustment mechanism, connected to the rotation mechanism, is used to adjust the height of the sample; The heating unit and temperature feedback device are used to control the sample temperature from room temperature to the set temperature.

4. The high-speed rain and snow impact simulation test device according to claim 3, characterized in that: The clamping base includes multiple clamping arms that intersect at the center. Each clamping arm is provided with a slide rail and a set of clamping sliders. Each set of clamping sliders includes two clamping sliders and is configured to be fixed along the slide rail at any position to achieve clamping of samples of different sizes. The heating unit and temperature feedback device are located at the center of the clamping base.

5. The high-speed rain and snow impact simulation test device according to claim 1, characterized in that: The support platform has a receiving space, and the platform surface of the support platform is provided with a waste liquid collection hole that connects the test chamber and the receiving space; The cold air nozzle is connected to the cryogenic air generator, the atomizing nozzle is connected to the water storage tank, and the cryogenic air generator and the water storage tank are arranged within the accommodating space; The containment space is also equipped with a waste liquid recovery tank, which is connected to the waste liquid collection hole and is used to collect the waste liquid in the test chamber.

6. The high-speed rain and snow impact simulation test device according to claim 1, characterized in that: The high-speed airflow generation system also includes an air compressor and a pressure stabilizing chamber. The pulsed high-pressure gas generated by the air compressor is rectified and stabilized in the pressure stabilizing chamber and then delivered to the contraction nozzle for high-speed ejection.

7. The high-speed rain and snow impact simulation test device according to claim 1, characterized in that, It also includes a damaged surface identification system, which is set inside the test chamber to acquire images of the sample surface and identify and quantitatively assess the damaged areas; The damaged surface identification system further includes an identification algorithm, which is configured as follows: Acquire high-resolution digital images of the sample surface; Preprocess the image; Extract the damaged areas from the image; Quantitative analysis of the damaged area was performed to calculate the percentage of the damaged area.

8. The high-speed rain and snow impact simulation test device according to claim 7, characterized in that, The specific configuration of the recognition algorithm is as follows: The acquired images are preprocessed by grayscale conversion, filtering and noise reduction, and contrast enhancement. Local Gaussian weighted adaptive thresholding is used for threshold segmentation, and the Canny edge detection operator is used to extract edges. Perform a logical OR operation between the threshold segmentation result and the edge detection result to merge damaged pixels; By connecting the broken edges through morphological manipulation, a complete outline of the damaged area can be formed; The actual damage area is selected based on geometric features; Statistical analysis of pixel area of ​​damaged region Calculate the pixel area of ​​the entire measured region. The percentage of damaged area is calculated according to the following formula. : 。 9. The high-speed rain and snow impact simulation test device according to claim 7, characterized in that, The specific configuration of the recognition algorithm is as follows: the recognition algorithm is further configured to continuously acquire photos during the rotation process of the conformal sample, stitch the photos together to obtain a complete three-dimensional model, and then perform calculations to evaluate the damage.

10. A method for simulating high-speed rain and snow impact on aircraft components, applied to the test apparatus described in any one of claims 1-9, characterized in that, The following working modes are included: Working mode one, simulating high-speed rain and fog impact: activate the high-speed airflow generation system and atomizing nozzles to spray water droplets; Working mode two, simulating high-speed ice crystal impact: Activate the high-speed airflow generation system, atomizing nozzle and cold air nozzle, so that the water mist sprayed from the atomizing nozzle mixes with the deep cold air sprayed from the cold air nozzle in the tubular hood and condenses into ice crystals. The ice crystals are sprayed out with the high-speed airflow and impact the sample.

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