Method and system for evaluating service life of aviation towed cable based on modified model

Abstract

The application discloses a kind of aviation tow cable service life evaluation method and system based on correction model, belong to aviation equipment field, this method includes: according to ground basic life test data and preset failure criterion, determine the basic allowable number of times of use of aviation tow cable under current ground test condition;The load and the take-up and pay-off speed applied in ground test are compared with the load and the take-up and pay-off speed of aviation tow cable in actual operation in the air, to obtain the first correction coefficient;The ground test environment parameters of ground test environment are compared with the actual environment parameters of actual environment in the air, to obtain the second correction coefficient;The basic allowable number of times of use, the first correction coefficient and the second correction coefficient are combined to calculate the predicted service life of aviation tow cable under actual use condition in the air.

Description

Technical Field

[0001] This application relates to the field of aviation equipment control, and more specifically, to a method and system for evaluating the service life of aviation towed cables based on a modified model. Background Technology

[0002] The service life of tow cables is a crucial indicator for aircraft towed mission equipment, directly impacting mission success rates and aircraft and equipment safety. An excessively short service life leads to frequent replacements and increased maintenance costs; conversely, an overestimation of service life can result in serious accidents such as in-flight cable breakage. Cable breakage or severe performance degradation during use can lead to mission failure, equipment damage, and even jeopardize aircraft safety. Therefore, accurately assessing the remaining service life of aircraft tow cables is essential for ensuring flight safety, optimizing maintenance strategies, and reducing operating costs.

[0003] Currently, the common method for assessing cable life is to build a test platform on the ground and rely on ground-based testing. Accelerated fatigue or wear tests are conducted by simulating the bending, tension, and friction processes of the cable on components such as winches and pulleys. The cable life is then inferred based on the test results (such as wire breakage, wear, and changes in electrical properties). However, this method has significant limitations, as ground test conditions differ significantly from the actual aerial working environment.

[0004] 1. Load differences: Ground test systems may have difficulty fully simulating complex dynamic aerodynamic loads and high-tension drag loads in the air.

[0005] 2. Speed ​​difference: The deployment and recovery speed in ground tests may be lower than the actual operation speed in the air. High-speed deployment and recovery may introduce additional shocks and vibrations.

[0006] 3. Environmental differences: The temperature, humidity, air pressure and other environmental factors in the air are significantly different from those on the ground, which may affect the mechanical and electrical properties of the cable materials; the air environment has wind vibration caused by airflow disturbances, which will cause additional collisions and friction between the cable and the exit guide device; long-term high-tension towing in the air will bring fatigue accumulation effects that are difficult to be fully simulated by short-term cyclic tests on the ground.

[0007] 4. System differences: Due to space constraints, airborne deployment and recovery systems are usually very compact. The actual layout of airborne deployment and recovery systems may be more complex, with more pulleys and guide wheels, and more path turns, making them more complex than ground test platforms, resulting in more wear points.

[0008] These differences often lead to significant biases in assessing actual service life in the air based solely on ground test results, potentially resulting in overly optimistic or conservative assessments that fail to meet the demands of high-reliability aviation applications. Current technologies for assessing the service life of aviation towed cables often rely on experience, lacking a systematic assessment method that can quantify these differences and effectively correct for ground test results.

[0009] Therefore, there is an urgent need for a method to assess the service life of aircraft towed cables that can comprehensively consider the differences between ground test data and actual working conditions, so as to improve the accuracy and reliability of predictions and thus improve the safety and reliability of aircraft towed mission equipment. Summary of the Invention

[0010] To address at least one deficiency or improvement need in the prior art, this invention provides a method and system for assessing the service life of aircraft towed cables based on a modified model. This method combines ground testing, theoretical wear analysis, and dual corrections for differences in operating conditions, enabling more accurate prediction of the service life of aircraft towed cables in actual aerial environments.

[0011] To achieve the above objectives, according to a first aspect of the present invention, a method for assessing the service life of an aircraft towed cable based on a correction model is provided. The method includes: determining the permissible number of times the foundation of the aircraft towed cable can be used under current ground test conditions based on ground foundation life test data and preset failure criteria; comparing the load and deployment / retraction speed applied during the ground test with the load and deployment / retraction speed of the aircraft towed cable during actual aerial operation to calculate a first correction coefficient; comparing the ground test environment parameters with the actual environmental parameters of the aerial environment to calculate a second correction coefficient; and combining the permissible number of times the foundation can be used, the first correction coefficient, and the second correction coefficient to calculate the predicted service life of the aircraft towed cable under actual aerial use conditions.

[0012] In an exemplary embodiment, the method for determining the permissible number of basic uses of an aircraft towed cable under current ground test conditions based on ground foundation life test data and a preset failure criterion includes: applying a simulated load to a sample of the aircraft towed cable on a ground loading test system equivalent to an airborne deployment and take-up system and performing multiple deployment and take-up cycles; collecting at least one key performance parameter of the sample cable in real time, and comparing the key performance parameter with a preset failure criterion to determine the permissible number of basic uses under current ground test conditions.

[0013] In an exemplary embodiment, the step of comparing the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation to calculate the first correction coefficient includes: determining a load correction factor based on the load applied in the ground test and the average load in actual operation; selecting a speed correction factor for high-speed deployment conditions; and determining the product of the load correction factor and the speed correction factor as the first correction coefficient.

[0014] In an exemplary embodiment, the step of comparing the ground test environment parameters of the ground test environment with the actual environmental parameters of the actual air environment to calculate the second correction coefficient includes: the ground test environment parameters include wind vibration parameters, fatigue parameters, and system configuration parameters; the actual environmental parameters include actual wind vibration parameters, actual fatigue parameters, and air system parameters; a safety factor is determined based on the ground test environment parameters and the actual environmental parameters; and the reciprocal of the safety factor is determined as the second correction coefficient.

[0015] In an exemplary embodiment, calculating the predicted service life of the aerial towed cable under actual air use conditions by combining the basic allowable number of uses, the first correction factor, and the second correction factor includes: determining the product of the basic allowable number of uses, the first correction factor, and the second correction factor as the predicted service life of the aerial towed cable under actual air use conditions.

[0016] In an exemplary embodiment, before comparing the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation to calculate the first correction coefficient, the method further includes: determining the wear coefficient as... ;in, The wear coefficient is... This represents the total displacement between the steel wires. For contact load, The angle formed between the steel wires at the point of contact. This represents the wear depth of the steel wire. The radius of the inner / outer strand contact wire.

[0017] According to a second aspect of the present invention, a service life assessment system for towed aerial cables based on a correction model is also provided, comprising a data processing device and a service life assessment device, for executing the aforementioned service life assessment method for towed aerial cables based on a correction model, comprising: the data processing device comprising a ground operation service life calculation module and a correction coefficient calculation module; the ground operation service life calculation module being used to determine the basic permissible number of uses of the towed aerial cable under current ground test conditions based on ground basic service life test data and preset failure criteria; the correction coefficient calculation module being used to compare the load and deployment / retraction speed applied in the ground test with the load and deployment / retraction speed of the towed aerial cable in actual operation in the air, and calculate a first correction coefficient; and being used to compare the ground test environment parameters with the actual environmental parameters of the actual air environment, and calculate a second correction coefficient; the service life assessment device being used to calculate the predicted service life of the towed aerial cable under actual air use conditions by combining the basic permissible number of uses, the first correction coefficient, and the second correction coefficient.

[0018] In one exemplary embodiment, the aviation towed cable service life assessment system based on the modified model further includes: a ground loading operation test device for applying simulated loads to a sample of the aviation towed cable and performing multiple take-up and release cycle tests, and for real-time acquisition of at least one key performance parameter of the sample cable.

[0019] According to a third aspect of the invention, a computer-readable storage medium is also provided, wherein a computer program is stored therein, wherein the computer program is configured to execute the above-described method for evaluating the service life of aerial towed cables based on a modified model when it is run.

[0020] According to a fourth aspect of the present invention, an electronic device is also provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the above-described method for evaluating the service life of aerial towed cables based on a modified model via the computer program.

[0021] In summary, compared with the prior art, the above-described technical solutions conceived by this invention can achieve the following beneficial effects:

[0022] (1) This invention provides a method for assessing the service life of aerial towed cables based on a modified model, which improves the accuracy of prediction. It proposes to decompose the ground-air difference into differences in operating parameters and differences in environment / system. By introducing dual correction coefficients based on theoretical analysis and empirical data, the key differences between ground tests and actual air conditions are quantified, which significantly improves the consistency between the service life prediction results and the actual service life. This decoupling process makes the model clearer, the physical meaning more explicit, and facilitates engineering applications and parameter adjustments.

[0023] (2) Enhanced safety: More accurate life prediction helps to develop reasonable inspection, maintenance and replacement plans, avoid cable failure due to exceeding service life, ensure the safety of aircraft and mission equipment, and effectively avoid the huge assessment errors brought about by traditional methods. Optimized design and maintenance: The assessment model reveals key factors affecting life (such as load, speed, environment, system design), providing a basis for optimizing cable structure, improving the design of the take-up and take-down system (such as reducing bends, optimizing pulley materials and shapes), and developing more scientific maintenance strategies. Attached Figure Description

[0024] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0025] Figure 1 A flowchart illustrating an optional modified model-based method for evaluating the service life of aerial towed cables, provided as an embodiment of this application;

[0026] Figure 2 A flowchart illustrating another optional method for evaluating the service life of aerial towed cables based on a modified model, provided for an embodiment of this application;

[0027] Figure 3 A schematic diagram of an optional modified model-based aviation towed cable life assessment system provided in this application embodiment;

[0028] Figure 4 A schematic diagram of an optional ground loading operation test device provided for an embodiment of this application;

[0029] Figure 5 A schematic diagram of an optional cable parameter monitoring device provided for an embodiment of this application;

[0030] Figure 6 This is a schematic diagram of an optional electronic device provided in an embodiment of this application. Detailed Implementation

[0031] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0032] The terms "first," "second," "third," etc., in the specification, claims, and accompanying drawings of this application are used to distinguish different objects, not to describe a specific order. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. For example, a process, method, system, product, or apparatus that includes a series of steps or units is not limited to the listed steps or units, but may optionally include steps or units not listed, or may optionally include other steps or units inherent to these processes, methods, products, or apparatuses.

[0033] According to one aspect of the embodiments of this application, a method for evaluating the service life of aerial towed cables based on a modified model is provided. The following is in conjunction with... Figure 1 This application describes a method for evaluating the service life of aerial towed cables based on a modified model, as provided in the embodiments of this application.

[0034] Figure 1 This is a flowchart illustrating an optional method for assessing the service life of aerial towed cables based on a modified model, as provided in an embodiment of this application. Figure 1 As shown, the process of this method may include the following steps:

[0035] S102, Based on ground foundation life test data and preset failure criteria, determine the number of times the foundation of the aircraft towed cable can be used under the current ground test conditions;

[0036] S104. The load and deployment speed applied in the ground test are compared with the load and deployment speed of the aerial towed cable in actual operation in the air, and the first correction coefficient is calculated.

[0037] S106, compare the ground test environment parameters with the actual environmental parameters of the actual air environment to calculate the second correction coefficient;

[0038] S108, calculate the predicted service life of the aviation towed cable under actual use conditions in the air by combining the basic allowable number of uses, the first correction factor and the second correction factor.

[0039] This application provides a method for evaluating the service life of aircraft tow cables based on a modified model, which can be used to evaluate the remaining service life (number of uses) of aircraft tow cables under actual air use conditions.

[0040] It should be noted that aerial towing cables are key load-bearing and functional components in aerial towing mission equipment (such as target towing systems and airborne communication towed antenna systems). For example, in aerial target towing systems, the cable is used to tow the target; in TACAMO (Take Charge and Move Out) systems, the towing cable not only bears enormous towing tension but also serves as the radiator of a very low frequency (VLF) communication antenna. These cables typically bear enormous towing tension and need to be repeatedly deployed and wound at high speeds in the air and on winch systems, while also enduring complex dynamic loads and harsh environmental influences.

[0041] Combination Figure 1 and Figure 2 As shown, the aviation towed cable service life assessment method based on a modified model in this application includes the following steps:

[0042] (1) Ground foundation life test procedure:

[0043] Use a ground loading test system (including winch, pulley block, loading device, etc.) similar to or equivalent to the actual equipment, and select a sample cable of the same specifications as the actual cable or a representative sample cable. Conduct repeated winding and unwinding cycle tests under simulated load conditions.

[0044] During or between tests, monitor the cable’s key performance parameters regularly, such as cable outer diameter (to measure wear) and resistance per unit length (for cables that also function as antennas, to assess electrical performance degradation).

[0045] Establish failure criteria, such as: the reduction in cable outer diameter reaching a predetermined threshold (e.g., 5% allowable for winch cable laying), or the increase in loss resistance reaching a predetermined threshold (e.g., a limit affecting antenna radiation efficiency). Based on ground foundation life test data and failure criteria, determine the number of times the cable can be used on the foundation under the current ground test conditions (Nground).

[0046] (2) First correction step:

[0047] The differences between the loads and deployment / retraction speeds applied in ground tests and the average or peak loads and rated deployment / retraction speeds of the cable during actual aerial operations are analyzed. Based on theoretical analysis of the cable wear failure mechanism and / or relevant empirical data, a first correction factor (K1) is determined. In other words, the contact problem of the cable wires is transformed into the study of the contact problem between elastic cylinders, and Hertzian contact theory is used. When the contact angle between the inner and outer strands is... This will produce a saddle-shaped wear mark, which unfolds into an ellipse on a plane. The amount of cable wear can be represented by the wear volume of the steel wire at a wear depth of h, which is approximately:

[0048]

[0049] In the formula: This refers to the wear depth of the steel wire; Let r1 be the angle between the steel wires at the contact point; r2 be the radius of the inner strand contacting the steel wire; and r3 be the radius of the outer strand contacting the steel wire. When the radii of the inner and outer strands are the same, r1 = r2 = r, and the expression can be rewritten as:

[0050]

[0051] For the wear problem of steel wire rope cables, the Archard model is closer to the actual engineering situation. The Archard wear coefficient is introduced to characterize the degree of wear in the cable wire wear process.

[0052]

[0053] In the formula: The wear coefficient; This represents the total displacement between the steel wires; Contact load. Wear coefficient. It can also be expressed as:

[0054]

[0055] From the above equation, we can derive a formula for the wear depth h:

[0056]

[0057] Based on the above theoretical derivation, wear is directly proportional to the contact load; the greater the load, the greater the wear. In the aviation towed cable life model described below, the ground test data will be corrected according to the differences between the ground test environment and actual in-flight conditions, based on the aforementioned quantitative relationship.

[0058] Here, the first correction factor K1 is usually a factor less than 1, reflecting that actual aerial operation conditions are usually more stringent than ground test conditions (greater load, faster speed).

[0059] (3) Second correction step:

[0060] This study analyzes the main differences between the ground test environment and the actual aerial working environment and their impact on cable life. The main differences in environmental parameters include:

[0061] Airborne vibration: Airflow causes cable vibration, increasing collisions and friction between the cable and the guide device, and may cause load fluctuations.

[0062] Prolonged high-tension fatigue: Cables may need to be dragged under high tension for a long time (several hours) in the air, accumulating fatigue damage, while ground tests are usually short-term cycles.

[0063] System configuration differences: The number and layout of pulleys in the actual airborne deployment and recovery system may differ from those in the ground test system, and are usually more complex, resulting in more bending and friction points.

[0064] A second correction factor (K2) is determined by comprehensively assessing the combined effects of these environmental factors on cable wear and fatigue. This typically requires relying on empirical data, experience with similar equipment, or more complex fluid-structure interaction simulation analysis. K2 is usually a factor less than 1, reflecting the reduction in cable lifespan caused by the complex aerial environment compared to the ground environment.

[0065] (4) Life prediction calculation steps: Multiply the basic allowable number of uses (Nground) obtained from the ground test by two correction coefficients to obtain the final predicted actual service life (Nair) of the aerial towed cable.

[0066] The calculation formula is: Nair = Nground × K1 × K2. The obtained Nair is the predicted lifetime value after taking into account the differences in actual operating conditions (usually rounded to the nearest integer).

[0067] Through steps S102 to S108, the permissible number of uses of the aviation towed cable foundation under the current ground test conditions is determined based on ground foundation life test data and preset failure criteria. The load and deployment / retraction speed applied during the ground test are compared with the load and deployment / retraction speed of the aviation towed cable during actual aerial operation to calculate a first correction coefficient. The ground test environment parameters are compared with the actual environmental parameters of the aerial environment to calculate a second correction coefficient. The predicted service life of the aviation towed cable under actual aerial operating conditions is calculated by combining the permissible number of uses, the first correction coefficient, and the second correction coefficient. This combination of ground testing, theoretical wear analysis, and dual corrections for differences in operating conditions allows for a more accurate prediction of the service life of the aviation towed cable in the actual aerial environment.

[0068] In one exemplary embodiment, the method for determining the permissible number of uses of the aviation towed cable foundation under current ground test conditions based on ground foundation life test data and preset failure criteria includes:

[0069] S11, On a ground loading test system equivalent to an airborne deployment and take-up system, a simulated load is applied to a sample of an aircraft towed cable and multiple deployment and take-up cycles are performed.

[0070] S12, collect at least one key performance parameter of the sample cable in real time, and compare the key performance parameter with a preset failure criterion to determine the basic allowable number of uses under the current ground test conditions.

[0071] In this embodiment, the TACAMO system's towed antenna cable is used as an example. This cable is not only used for towing but also serves as a VLF antenna radiator; therefore, its outer diameter wear and electrical performance (loss resistance) are key limiting factors for its lifespan. The ground-based foundation lifespan test includes the following specific steps:

[0072] Test preparation: Fabricate a sample cable with the same specifications as the cable used in the TACAMO system (e.g., a diameter of approximately 4.28 mm), and build a ground-based loading test device to simulate a winch (such as a Lebus double-folded groove drum), pulleys, and a certain drag load.

[0073] Test execution: Under the set load (such as a portion of the average tension in the air) and speed, conduct repeated cyclic tests of retraction and extension.

[0074] Parameter monitoring: During the test, the outer diameter of key parts of the cable and the loss resistance per unit length at a specific frequency (e.g., 20kHz) are measured periodically. For example, the initial outer diameter is 4.28mm and the initial loss resistance is 12.4mΩ / m.

[0075] Data Recording and Analysis: Record the results of each measurement and calculate the outer diameter wear rate and the rate of increase in loss resistance. For example, after 30 cycles of opening and closing tests, the outer diameter decreased to 4.12 mm, and the loss resistance increased to 13.0 mΩ / m. The calculated average wear rate is (4.28-4.12) / 30 = 0.00533 mm / cycle, and the rate of increase in loss resistance is (13.0-12.4) / 30 = 0.02 mΩ / (m•cycle).

[0076] Determining the baseline life Nground: Failure Criterion 1 (Outer Diameter): The Lebus reel cable used in the TACAMO system allows for a diameter variation of approximately 5%. With an initial diameter of 4.28 mm, the allowable reduction is 4.28 * 5% = 0.214 mm. Based on the wear rate, the number of cycles required to reach this outer diameter limit is approximately 0.214 / 0.00533 ≈ 40 cycles. Failure Criterion 2 (Electrical Performance): Assuming the mission requires a loss resistance not exceeding 13 mΩ / m. Based on the loss resistance increase rate, the number of cycles required to increase from the initial 12.4 mΩ / m to 13.0 mΩ / m is (13.0 - 12.4) / 0.02 = 30 cycles.

[0077] Minimum value: Compare the lifetimes obtained from the two criteria, and take the smaller one as the allowable number of uses for the ground foundation. Therefore, Nground = 30 times.

[0078] It is not limited to the above embodiments. For example, the failure threshold can be adjusted according to different cable application scenarios, and it has universality.

[0079] In an exemplary embodiment, the step of comparing the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation to calculate the first correction factor includes:

[0080] S21, determine the load correction factor based on the load applied during ground testing and the average load of actual aerial operations;

[0081] S22, For high-speed deployment and recovery, select the speed correction factor;

[0082] S23, the product of the load correction factor and the speed correction factor is determined as the first correction coefficient.

[0083] See Figure 2 Determining the first correction coefficient K1 through the first correction step includes the following steps:

[0084] Analyze the differences: Compare the loads and speeds of the ground loading test with the loads (which may be higher and fluctuate more) and speeds (which may be faster) of the TACAMO system during actual aerial deployment and towing.

[0085] Theoretical Application (Load): Using the Archard wear model, the wear depth h is related to the load Fn. The ratio of the average effective load in the air, Fn,air, to the ground test load, Fn,ground, is estimated. Assuming that the wear amount is approximately proportional to the load, the correction factor for the load component is approximately Fn,ground / Fn,air.

[0086] Application of experience (speed): Considering the impact and vibration effects caused by high-speed deployment and retraction, a speed correction factor is introduced based on the experience of relevant cable manufacturers or specific test data.

[0087] K1 is determined by combining the correction effects of load and speed differences to obtain a comprehensive first correction coefficient K1. The average load Fn,air of the cable during actual in-flight deployment and retrieval is obtained through flight data analysis or aerodynamic calculations. Assuming a ground test load Fn,ground = 500N and an average in-flight deployment and retrieval load Fn,air = 713N, the load correction factor K_F = Fn,ground / Fn,air = 500 / 713 ≈ 0.701. Theoretically, in a pure wear model, the amount of wear is not significantly related to speed. However, high-speed deployment and retrieval exacerbate the vibration and impact of the system, and this dynamic effect generates additional wear. Currently, there is a lack of accurate theoretical models to describe this high-speed impact wear. Therefore, this invention adopts a semi-empirical method, introducing a speed correction factor K_V less than 1. Based on the engineering experience and research of relevant cable manufacturers, an empirical value can be taken for high-speed deployment and retrieval conditions. For example, here K_V = 0.9 is taken. In this case, after comprehensive consideration, K1 is taken as 0.701 × 0.9 = 0.631 (where 0.701 is the load correction and 0.9 is the empirical value of the speed correction).

[0088] This embodiment demonstrates how analyzing the composition and influence weights of each correction factor can provide inverse guidance for the optimized design of aircraft towed cables and their deployment and retrieval systems. For example, if the correction amount caused by wind vibration is large, it indicates that efforts should be focused on optimizing the aerodynamic shape of the cable or adding vibration suppression devices.

[0089] In an exemplary embodiment, the step of comparing the ground test environment parameters with the actual environmental parameters of the actual air environment to calculate the second correction coefficient includes:

[0090] S31, the ground test environment parameters include wind vibration parameters, fatigue parameters and system configuration parameters;

[0091] S32, the actual environmental parameters include actual wind vibration parameters, actual fatigue parameters, and air system parameters;

[0092] S33, determine the safety factor based on the ground test environment parameters and the actual environment parameters;

[0093] S34, the reciprocal of the safety factor is determined as the second correction factor.

[0094] Optionally, the second correction coefficient K2 is determined through a second correction step:

[0095] Analysis of differences: Considering the unique influencing factors of the air environment (actual wind vibration parameters, actual fatigue parameters, and air system parameters). Wind vibration: The cable vibrates in the air due to airflow, increasing friction and impact with the exit hatch and guide wheels. Fatigue: Long-term (e.g., 0.5-3.5 hours) high-tension towing conditions lead to cumulative fatigue damage. System differences: The actual number of pulleys on the aircraft may be greater than that of the ground test system.

[0096] The second correction factor K2 is determined empirically: Since accurately quantifying these factors is extremely complex, empirical data from similar aviation equipment or systems are typically used as a reference. Referring to the design guidelines for relevant aviation equipment, a safety factor of 1.5 (i.e., lifespan divided by 1.5) is usually introduced for finished aviation equipment to convert its ground-tested lifespan to its actual in-flight lifespan. Therefore, K2 = 1 / 1.5 ≈ 0.667 can be taken.

[0097] In one exemplary embodiment, calculating the predicted service life of the aerial towed cable under actual aerial use conditions by combining the base permissible number of uses, the first correction factor, and the second correction factor includes:

[0098] S41, the product of the basic allowable number of uses, the first correction factor, and the second correction factor is determined as the predicted service life of the aviation towed cable under actual use conditions in the air.

[0099] Optionally, the lifetime prediction calculation steps are as follows:

[0100] To calculate the predicted lifetime Nair, substitute the base lifetime and two correction factors into the formula:

[0101] Nair = Nground × K1 × K2, for example, it can be 30 × 0.631 × 0.667 ≈ 12.6 times.

[0102] Rounding: Considering that the service life is usually taken as an integer, that is, the integer part of the calculation result is taken as the final predicted service life, and to ensure safety, it should be rounded down, that is, the predicted actual service life of the TACAMO towed antenna cable in the air is 12 times.

[0103] Verification: The prediction results were compared with actual usage experience or publicly reported data (such as 10-12 times reported in the report). The high degree of agreement demonstrated the effectiveness and accuracy of this evaluation method.

[0104] This embodiment combines operable ground tests with systematic theoretical corrections. The steps are clear, and the required parameters can be obtained through theoretical calculations, empirical data, or supplementary tests. It is easy to promote in engineering practice and can be widely applied to the life assessment of various types of aircraft towed cables. For different types and uses of aircraft towed cables, only the corresponding failure thresholds and correction coefficients need to be adjusted for applicability.

[0105] In an exemplary embodiment, before comparing the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation and calculating the first correction factor, the method further includes:

[0106] S51, the wear coefficient is determined to be... ;

[0107] in, The wear coefficient is... This represents the total displacement between the steel wires. For contact load, The angle formed between the steel wires at the point of contact. This represents the wear depth of the steel wire. The radius of the inner / outer strand contact wire.

[0108] Furthermore, a formula for the wear depth can be obtained. The above equations are rearranged into... In the form of unknowns:

[0109]

[0110] Therefore, the wear depth is the solution to this cubic equation concerning h. It is evident that the greater the contact load, the greater the wear. Based on the above quantitative relationship, and considering the differences between the ground test environment and actual in-flight conditions, the ground test data is corrected.

[0111] This embodiment quantifies the key differences between ground tests and actual air conditions, significantly improving the consistency between life prediction results and actual lifespan.

[0112] According to another aspect of the embodiments of this application, an aviation towed cable service life assessment system is also provided for implementing the above-described modified model-based aviation towed cable service life assessment method, including a data processing device and a service life assessment device, the system comprising:

[0113] The data processing device includes a ground operation life calculation module and a correction coefficient calculation module;

[0114] The ground operation life calculation module is used to determine the number of times the aviation towed cable can be used under the current ground test conditions based on the ground foundation life test data and preset failure criteria.

[0115] The correction coefficient calculation module is used to compare the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation, and calculate the first correction coefficient; and,

[0116] The second correction factor is calculated by comparing the ground test environment parameters with the actual environmental parameters of the actual air environment.

[0117] The life assessment device is used to calculate the predicted lifespan of the aviation towed cable under actual use conditions in the air by combining the basic allowable number of uses, the first correction factor, and the second correction factor.

[0118] In one exemplary embodiment, the aviation towed cable life assessment system based on the modified model further includes:

[0119] The ground-based loading and operation test device is used to apply simulated loads to a prototype of an aircraft towed cable and perform multiple retrieval and deployment cycles, and to collect at least one key performance parameter of the prototype cable in real time.

[0120] See Figure 3 The system includes a ground loading test device, a cable parameter monitoring device, a data processing device, and a life assessment device.

[0121] See further Figure 4 The ground-based loading test apparatus includes a winch, a loading device (i.e., a cable loading device), and a pulley system (i.e., a cable guide pulley assembly). This test bench, equipped with launch, loading, control, and data acquisition functions, applies simulated loads to a prototype aerial towed cable and performs multiple launch and recovery cycles. It collects at least one key performance parameter of the prototype cable in real time, such as periodically measuring the outer diameter of key cable components and the loss resistance per unit length at specific frequencies.

[0122] like Figure 5 As shown, the cable parameter monitoring device includes an outer diameter measuring instrument, an electrical performance tester, and a display screen. The outer diameter measuring instrument monitors the outer diameter of key parts of the cable, and the electrical performance tester measures the loss resistance per unit length of the cable at a specific frequency. The monitoring data can be displayed on the screen. Furthermore, the cable parameter monitoring device can transmit the detection data to a data processing device and a lifespan assessment device for processing.

[0123] Specifically, the ground operational life calculation module in the data processing device calculates ground life data and transmits this data to the correction coefficient calculation module to calculate the first and second correction coefficients. Finally, the airborne service life calculation module in the life assessment device is called to calculate the predicted service life.

[0124] Preferably, based on the evaluation model and failure mechanism analysis of the present invention, technical approaches to extend the life of aviation towed cables can be proposed as follows:

[0125] Optimize the design of the cable reeling system: reduce the number of bends and angles along the cable's path from the drum to the hatch, thereby reducing the number of pulleys and the degree of bending required. Optimize the design of the winch cable laying mechanism to make it more tolerant of changes in cable diameter.

[0126] Optimize pulley design: Use lightweight, wear-resistant, and self-lubricating pulley materials. Rationally design the pulley groove shape and surface hardness to match the cable hardness, reducing contact stress and frictional wear.

[0127] Optimize cable structure: Improve the cable twisting structure and materials (such as using higher strength, more wear-resistant steel wire, or using composite materials) to enhance its resistance to bending fatigue and wear.

[0128] Optimize operating procedures: Standardize the retraction and extension speeds to avoid excessively rapid speed changes and impact loads.

[0129] The proposed method for assessing the service life of towed cables in aviation, through a logically clear and step-by-step process of ground testing → first correction → second correction, successfully transforms readily available ground test data into in-flight service life estimates that can guide practical applications. This method not only provides accurate service life predictions for specific cables, but its core ideas and framework also offer valuable references for service life assessments of other similar equipment. By combining ground testing, theoretical wear analysis, and dual correction coefficients, the accuracy of service life predictions can be significantly improved. This method is not only applicable to towed antenna cables similar to the TACAMO system, but can also be extended to the service life assessment of other types of aviation towed cables, such as aerial target wire ropes, and has significant engineering application value for ensuring flight safety and guiding maintenance decisions.

[0130] It should be noted that the ground operation life calculation module in this embodiment can be used to perform the above step S102, the correction coefficient calculation module in this embodiment can be used to perform the above step S104, the correction coefficient calculation module in this embodiment can be used to perform the above step S106, and the life assessment device in this embodiment can be used to perform the above step S108.

[0131] According to another aspect of the embodiments of this application, a storage medium is also provided. Optionally, in this embodiment, the storage medium can be used to execute the program code of any of the above-described methods for evaluating the service life of aerial towed cables based on a modified model in the embodiments of this application.

[0132] Optionally, in this embodiment, the storage medium is configured to store program code for performing the following steps:

[0133] S1. Based on ground foundation life test data and preset failure criteria, determine the number of times the aviation tow cable foundation can be used under the current ground test conditions;

[0134] S2, compare the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation, and calculate the first correction coefficient;

[0135] S3, compare the ground test environment parameters with the actual environmental parameters of the air environment to calculate the second correction coefficient;

[0136] S4. Calculate the predicted service life of the aviation towed cable under actual air use conditions by combining the basic allowable number of uses, the first correction factor, and the second correction factor.

[0137] Optionally, specific examples in this embodiment can refer to the examples described in the above embodiments, and will not be repeated in this embodiment.

[0138] The computer-readable storage medium may include, but is not limited to, any type of disk, including floppy disks, optical disks, DVDs, CD-ROMs, microdrives, as well as magneto-optical disks, ROMs, RAMs, EPROMs, EEPROMs, DRAMs, VRAMs, flash memory devices, magnetic cards or optical cards, nanosystems (including molecular memory ICs), or any type of medium or device suitable for storing instructions and / or data.

[0139] According to another aspect of the embodiments of this application, an electronic device is also provided for implementing the above-described method for evaluating the service life of aerial towed cables based on a modified model. The electronic device may be a server, a terminal, or a combination thereof.

[0140] Figure 6 This is a schematic diagram of the structure of an optional electronic device according to an embodiment of this application, such as... Figure 6 As shown, it includes a processor 602, a communication interface 604, a memory 606, and a communication bus 608. The processor 602, communication interface 604, and memory 606 communicate with each other via the communication bus 608.

[0141] Memory 606 is used to store computer programs;

[0142] When processor 602 executes a computer program stored in memory 606, it performs the following steps:

[0143] S1. Based on ground foundation life test data and preset failure criteria, determine the number of times the aviation tow cable foundation can be used under the current ground test conditions;

[0144] S2, compare the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation, and calculate the first correction coefficient;

[0145] S3, compare the ground test environment parameters with the actual environmental parameters of the air environment to calculate the second correction coefficient;

[0146] S4. Calculate the predicted service life of the aviation towed cable under actual air use conditions by combining the basic allowable number of uses, the first correction factor, and the second correction factor.

[0147] Optionally, the communication bus can be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. This communication bus can be divided into an address bus, a data bus, a control bus, etc. For ease of representation, Figure 6 The symbol is represented by a single thick line, but this does not indicate that there is only one bus or one type of bus. The communication interface is used for communication between the aforementioned electronic device and other devices.

[0148] The memory may include RAM, or non-volatile memory, such as at least one disk storage device. Optionally, the memory may also be at least one storage device located remotely from the aforementioned processor.

[0149] The processors mentioned above can be general-purpose processors, including but not limited to: CPU (Central Processing Unit), NP (Network Processor), etc.; they can also be DSP (Digital Signal Processor), ASIC (Application Specific Integrated Circuit), FPGA (Field-Programmable Gate Array), or other programmable logic devices, discrete gate or transistor logic devices, or discrete hardware components.

[0150] Optionally, specific examples in this embodiment can refer to the examples described in the above embodiments, and will not be repeated here.

[0151] It should be noted that, for the sake of simplicity, the foregoing method embodiments are all described as a series of actions. However, those skilled in the art should understand that this application is not limited to the described order of actions, as some steps may be performed in other orders or simultaneously according to this application. Furthermore, those skilled in the art should also understand that the embodiments described in the specification are preferred embodiments, and the actions and modules involved are not necessarily essential to this application.

[0152] In the above embodiments, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions in other embodiments.

[0153] Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, which may include: a flash drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk, or an optical disk, etc.

[0154] The foregoing description is merely an exemplary embodiment of this disclosure and should not be construed as limiting the scope of this disclosure. Any equivalent changes and modifications made in accordance with the teachings of this disclosure shall still fall within the scope of this disclosure. Those skilled in the art will readily conceive of embodiments of this disclosure upon considering the specification and practicing the disclosure herein. This application is intended to cover any variations, uses, or adaptations of this disclosure that follow the general principles of this disclosure and include common knowledge or customary techniques in the art not described herein. The specification and embodiments are to be considered exemplary only, and the scope and spirit of this disclosure are defined by the claims.

[0155] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0156] Those skilled in the art will readily understand that the above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. A method for evaluating the service life of aerial towed cables based on a modified model, characterized in that, include: Based on ground foundation life test data and preset failure criteria, determine the number of times the aviation tow cable foundation can be used under the current ground test conditions; The first correction factor was calculated by comparing the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation. The ground test environment parameters are compared with the actual environmental parameters of the air environment to calculate the second correction coefficient. The predicted service life of the aerial towed cable under actual use conditions in the air is calculated by combining the basic allowable number of uses, the first correction factor, and the second correction factor. The process of comparing the load and deployment speed applied during the ground test with the load and deployment speed of the aerial towed cable during actual operation, and calculating the first correction factor, includes: The load correction factor is determined based on the load applied during ground testing and the average load of actual aerial operations. For high-speed deployment and recovery operations, a speed correction factor is selected; The product of the load correction factor and the velocity correction factor is determined as the first correction coefficient; The process of comparing the ground test environment parameters with the actual air environment parameters to calculate the second correction factor includes: The ground test environment parameters include wind vibration parameters, fatigue parameters, and system configuration parameters; The actual environmental parameters include actual wind vibration parameters, actual fatigue parameters, and air system parameters; The safety factor is determined based on the ground test environment parameters and the actual environment parameters. The reciprocal of the safety factor is determined as the second correction factor; The calculation of the predicted service life of the aerial towed cable under actual air use conditions, combining the basic permissible number of uses, the first correction factor, and the second correction factor, includes: The product of the basic allowable number of uses, the first correction factor, and the second correction factor is determined as the predicted service life of the aerial towed cable under actual use conditions in the air.

2. The method for evaluating the service life of aerial towed cables based on a modified model as described in claim 1, characterized in that, The method for determining the permissible number of uses of an aircraft towed cable foundation under current ground test conditions based on ground foundation life test data and preset failure criteria includes: On a ground loading test system equivalent to an airborne deployment and take-up system, a simulated load was applied to a prototype of an aircraft towed cable and multiple deployment and take-up cycles were performed. At least one key performance parameter of the sample cable is collected in real time, and the key performance parameter is compared with a preset failure criterion to determine the basic allowable number of uses under the current ground test conditions.

3. The method for evaluating the service life of aerial towed cables based on a modified model as described in claim 1, characterized in that, Before comparing the load and deployment speed applied during the ground test with the load and deployment speed of the aerial towed cable during actual operation to calculate the first correction factor, the method further includes: The wear coefficient is determined to be ; in, The wear coefficient is... This represents the total displacement between the steel wires. For contact load, The angle formed between the steel wires at the point of contact. This represents the wear depth of the steel wire. This refers to the radius of the inner strand contact wire or the radius of the outer strand contact wire.

4. A system for assessing the service life of aircraft towed cables based on a modified model, comprising a data processing device and a service life assessment device, for executing the method for assessing the service life of aircraft towed cables based on a modified model as described in any one of claims 1-3, characterized in that, include: The data processing device includes a ground operation life calculation module and a correction coefficient calculation module; The ground operation life calculation module is used to determine the number of times the aviation towed cable can be used under the current ground test conditions based on the ground foundation life test data and preset failure criteria. The correction coefficient calculation module is used to compare the load and deployment speed applied in the ground test with the load and deployment speed of the aerial towed cable in actual operation in the air, and calculate the first correction coefficient. as well as, The second correction factor is calculated by comparing the ground test environment parameters with the actual environmental parameters of the actual air environment. The life assessment device is used to calculate the predicted lifespan of the aviation towed cable under actual use conditions in the air by combining the basic allowable number of uses, the first correction factor, and the second correction factor.

5. The aviation towed cable service life assessment system based on a modified model as described in claim 4, characterized in that, The aviation towed cable life assessment system based on the modified model also includes: The ground-based loading and operation test device is used to apply simulated loads to a prototype of an aircraft towed cable and perform multiple retrieval and deployment cycles, and to collect at least one key performance parameter of the prototype cable in real time.

6. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored program, wherein the program is executed by a processor to perform the method of any one of claims 1 to 3.

7. An electronic device comprising a memory and a processor, characterized in that, The memory stores a computer program, and the processor is configured to execute the method of any one of claims 1 to 3 through the computer program.

Images