A method and system for testing collision effects by combining ground testing and simulation.

Abstract

This invention belongs to the field of high-speed collision simulation technology, specifically relating to a collision effect testing method and system that combines ground testing and simulation. The method includes constructing an equivalent ground testing system and conducting tests under at least two different test conditions to obtain at least two sets of test results; constructing an initial simulation model using a material point meshless method and inputting the test conditions into the initial simulation model to obtain at least two sets of simulation results; calculating the difference results based on the test results and the simulation results; determining whether the difference results are abnormal using a preset anomaly evaluation rule; if so, recording the difference results as abnormal results; correcting the initial simulation model based on the abnormal results; and fitting a damage effect model based on the corrected simulation model. This invention effectively improves the correction efficiency of the simulation model while ensuring the accuracy of the damage effect model.

Description

[0001] Priority application

[0002] This application claims priority to Chinese invention patent application filed on December 24, 2024, entitled "[A method and system for testing collision effects by combining ground testing and simulation]", which is incorporated herein by reference in its entirety. Technical Field

[0003] This invention belongs to the field of high-speed collision simulation technology, specifically involving a collision effect testing method and system that combines ground testing with simulation. Background Technology

[0004] More and more countries and organizations are joining the space race. With the continuous development of various uses of orbital space, the number of satellites orbiting the Earth has increased dramatically, increasing the possibility of collisions that could generate space debris. This has led to a continuous increase in the risk of hypersonic collisions between space debris and satellites in orbit.

[0005] Current research methods for understanding the threat posed by high-speed collisions of space debris to satellites remain limited. Existing research methods include:

[0006] 1. On-orbit experiments: These can obtain relatively accurate and intuitive data, but require launching the necessary equipment into a predetermined orbit and conducting the experiment. This requires harsh conditions and advanced equipment, and takes a lot of time and money. Furthermore, long-term exposure of the equipment in space is costly, time-consuming, and has low repeatability. It may also bring more debris to the orbital space, making it difficult to implement.

[0007] 2. Constructing an environment and launch device on the ground to simulate the space environment and forming a ground test system can largely represent the space environment, but it also faces the problems of high test costs and difficulties in data acquisition.

[0008] 3. Computer numerical simulation test technology: It has the advantages of safety, flexible design, good repeatability, controllable environment and process, and high cost-effectiveness. It has certain advantages in the study of high-speed collision problems of space debris. However, for high-speed collisions, the strong nonlinear physical and mechanical behavior of the medium under extreme conditions such as high speed, high temperature and high pressure has a great influence on the test results.

[0009] Therefore, how to accurately determine the threat posed to satellites by high-speed collisions of space debris while keeping costs low remains a challenge. Summary of the Invention

[0010] The purpose of this invention is to provide a collision effect testing method and system that combines ground testing and simulation to partially alleviate or solve the above-mentioned problems and obtain more accurate simulation test data.

[0011] To solve the aforementioned technical problems, the present invention specifically adopts the following technical solution:

[0012] A first aspect of the present invention is to provide a collision effect testing method that combines ground testing with simulation, comprising:

[0013] S1, construct an equivalent test system on the ground, and conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component.

[0014] S2, construct an initial simulation model, and input the test conditions into the initial simulation model respectively to obtain at least two sets of simulation results; wherein, the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape;

[0015] S3, calculate the difference results based on the results of the experiment and the simulation results, and the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference;

[0016] S4, use the preset anomaly evaluation rules to determine whether the difference result is abnormal. If it is, record the difference result as an abnormal result; otherwise, execute S7.

[0017] The anomaly assessment rules require that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal.

[0018] S5, determine the correction category of the initial simulation model based on the number of abnormalities in the abnormal results;

[0019] Specifically, when the number of abnormalities is greater than or equal to L, the correction category is selected as Class I correction; when the number of abnormalities is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H.

[0020] Wherein, the correction object of the first type of correction is at least one of the first type of correction objects, and the correction object of the second type of correction is at least one of the second type of correction objects; the first type of correction object includes the material model of the component and the material model of the space debris; the second type of correction object includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method.

[0021] S6, Modify the initial simulation model according to the correction category;

[0022] S7. Multiple sets of simulation results are calculated based on the initial simulation model, and each set of simulation results corresponds to a set of test conditions.

[0023] S8. Based on the multiple sets of simulation results and the test conditions, a damage effect model is obtained by fitting.

[0024] As an improvement, in S5, when determining the correction category of the initial simulation model based on the number of abnormalities in the abnormal results, if the number of abnormalities is greater than H and less than L, the correction category is selected as the third type of correction.

[0025] Accordingly, the step of making corrections according to the three types of corrections in S6 includes:

[0026] S601, obtain the first type of correction object and the second type of correction object input by the user, and construct a first simulation model based on the first type of correction object and the second type of correction object; at the same time, use a pre-built adjustment system to automatically adjust one of the second type of correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model;

[0027] S602, input the test conditions into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result;

[0028] S603, a first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results;

[0029] S604, obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, determine the first simulation model as the initial simulation model in S7; otherwise, determine whether the trend difference is less than a second preset trend difference. If so, determine the second simulation model as the initial simulation model in S7.

[0030] As an improvement, in S604, when it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset trend difference, the following step is executed:

[0031] S605 prompts the user to adjust one of the two types of correction objects in the first simulation model. The adjustment system synchronously adjusts the second simulation model according to the user's operation. S602-S605 are repeated until the initial simulation model is determined.

[0032] As an improvement, the destructive effect model for:

[0033] ;

[0034] in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

[0035] As an improvement, the component is one of a storage tank, an integrated electronic enclosure, or a main structural plate.

[0036] A second aspect of the present invention is to provide a collision effect testing system that combines ground testing with simulation, comprising:

[0037] Equivalent test module: configured to construct an equivalent test system on the ground, and to conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component.

[0038] Initial simulation module: configured to build an initial simulation model and input the test conditions into the initial simulation model to obtain at least two sets of simulation results; wherein the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape;

[0039] Difference Result Calculation Module: Configured to calculate difference results based on the results of the experiment and the results of the simulation, wherein the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference;

[0040] The difference result processing module is configured to determine whether the difference result is abnormal using a preset anomaly evaluation rule, and if so, record the difference result as an abnormal result.

[0041] The anomaly assessment rules require that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal.

[0042] Correction module: configured to determine the correction category of the initial simulation model based on the number of anomalies in the anomaly results;

[0043] Specifically, when the number of abnormalities is greater than or equal to L, the correction category is selected as Class I correction; when the number of abnormalities is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H.

[0044] Wherein, the correction object of the first type of correction is at least one of the first type of correction objects, and the correction object of the second type of correction is at least one of the second type of correction objects; the first type of correction object includes the material model of the component and the material model of the space debris; the second type of correction object includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method.

[0045] And for modifying the initial simulation model according to the modification category;

[0046] The damage effect model construction module is configured to calculate multiple sets of simulation results based on the initial simulation model, each set of simulation results corresponding to a set of test conditions; and to fit a damage effect model based on the multiple sets of simulation results and the test conditions.

[0047] As an improvement, the correction module is also configured to:

[0048] When determining the correction category of the initial simulation model based on the number of anomalies in the anomaly results, if the number of anomalies is greater than H and less than L, the correction category is selected as the third type of correction.

[0049] Accordingly, when making corrections based on the three types of corrections, it is specifically configured to:

[0050] The system acquires a first-class correction object and a second-class correction object from the user input, and constructs a first simulation model based on the first-class correction object and the second-class correction object. At the same time, it uses a pre-built adjustment system to automatically adjust one of the second-class correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model.

[0051] The test conditions are input into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result.

[0052] A first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results.

[0053] Obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, determine the first simulation model as the initial simulation model; otherwise, determine whether the trend difference is less than a second preset trend difference. If so, determine the second simulation model as the initial simulation model.

[0054] As an improvement, the correction module is also configured to:

[0055] When it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset trend difference, the user is prompted to adjust one of the two types of correction objects in the first simulation model. The adjustment system then adjusts the second simulation model synchronously according to the user's operation.

[0056] As an improvement, the destructive effect model for:

[0057] ;

[0058] in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

[0059] As an improvement, the component is one of a storage tank, an integrated electronic enclosure, or a main structural plate.

[0060] The principle and beneficial technical effects of this invention are as follows:

[0061] In the complex space environment, different space debris has different impacts on different spacecraft components (sub-components). If a large number of tests and analyses are carried out for each case, the workload will be enormous. Therefore, it is particularly important to provide a solution that allows users to quickly find the correspondence between current space debris and sub-components.

[0062] For hypersonic collisions in air traffic, this invention integrates limited parameter results (considering only residual velocity, puncture size, and debris cloud shape, i.e., explicit parameters strongly correlated with the damage outcome), and first performs fuzzy judgment and correction on the model based on the number of abnormal results. Furthermore, for unclear results, a semi-automatic test correction scheme is introduced, while simultaneously restricting the selection of correction objects. This provides a comprehensive "semi-automatic correction scheme based on limited data and hierarchical structure," which effectively improves the correction efficiency of the simulation model while ensuring the accuracy of the damage effect model.

[0063] Specifically, firstly, the present invention performs a fuzzy qualitative analysis of the model based on the number of abnormal results, and matches it with two distinct correction categories (correcting the material model or correcting the model's parameters) based on the qualitative results.

[0064] Furthermore, for cases where qualitative analysis is difficult and the correction falls between two categories, a restrictive semi-automatic correction scheme is introduced. Specifically, a scheme combining human intervention and machine recommendation is adopted to comprehensively determine a correction scheme with a better trend. In this process, on the one hand, the objects corrected by the machine are restricted (only one of the two types of objects is corrected). Furthermore, when the two schemes are not significantly different, the limited objects (such as one type of object) are further slightly corrected to select a more reliable correction scheme. Attached Figure Description

[0065] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. In all the drawings, similar elements or parts are generally identified by similar reference numerals. The elements or parts in the drawings are not necessarily drawn to scale. Obviously, the drawings described below are some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without any creative effort.

[0066] Figure 1 This is a flowchart of the collision effect test method combining ground testing and simulation in an embodiment of the present invention;

[0067] Figure 2 This is a schematic diagram of the modular structure of the collision effect test system that combines ground testing and simulation in an embodiment of the present invention. Detailed Implementation

[0068] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some, not all, of the embodiments of the present invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0069] In this document, suffixes such as "module," "component," or "unit" used to denote elements are used solely for the purpose of illustrative purposes and have no specific meaning in themselves. Therefore, "module," "component," or "unit" may be used interchangeably. In this document, terms such as "upper," "lower," "inner," "outer," "front," "rear," "one end," and "the other end," indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are used only for the convenience of describing the invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0070] In this document, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, a direct connection, or an indirect connection through an intermediate medium; it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances. In this document, "multiple" means two or more, that is, it includes two, three, four, five, etc.

[0071] Example 1

[0072] This invention provides a collision effect testing method that combines ground testing and simulation, comprising:

[0073] S1, construct an equivalent test system on the ground, and conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component.

[0074] In some embodiments, the test conditions include at least the destructive parameters of the space debris (initial collision velocity). Angle of incidence First attitude angle Second attitude angle Third attitude angle The results include at least the following parameter types: residual velocity value, puncture size, and debris cloud shape.

[0075] In some embodiments, the first attitude angle, the second attitude angle, and the third attitude angle are the yaw angle, the pitch angle, and the roll angle, respectively.

[0076] In some embodiments, the equivalent test system comprises a space environment simulation platform, a parameter testing platform, a launch device, and components (also referred to as targets).

[0077] The space environment simulation platform mainly includes a vacuum target track test system and related measurement and monitoring equipment. It primarily provides a simulated high-vacuum environment for experiments, while also providing a platform and flight path for the high-speed space debris launcher and target. It is mainly divided into three parts: an equipment room, a flight monitoring section, and a damage assessment room. The launcher is located in the equipment room, with power and data cables connected to it via flanges on the tank wall, providing power and communication. Components are placed in the damage assessment room, and a high-speed camera is placed outside the room to measure the impact position of space debris and monitor the collision effect through an observation window. A dual-light-curtain high-precision laser velocimetry device is placed in the flight monitoring section to monitor the flight speed of the space debris.

[0078] The parameter testing platform is mainly used to measure and record the velocity of space debris, the collision process with the target, and the degree of target damage. It mainly includes a dual-light-curtain laser velocimetry device and a high-speed camera device.

[0079] The dual-light-curtain laser velocimetry device is mainly used to measure the flight speed of high-speed moving objects (space debris) in a vacuum environment. Two light curtain detection sensors are placed inside a vacuum chamber along the trajectory. A data acquisition instrument collects the signals output by the space debris as it passes through the two detection light curtains. The time interval between the two signals and the flight speed of the space debris are calculated using a space debris signal recognition algorithm.

[0080] The high-speed camera device is controlled by a remote interface to trigger itself. It is triggered in a post-trigger manner and can take pictures within a few seconds before and after the moment when space debris hits the target, so as to obtain images of the space debris's attitude and destructive effects.

[0081] The launching device mainly consists of an integrated control subsystem, a launching subsystem, a charging subsystem, a pulse power supply subsystem, and an integrated installation structure.

[0082] The main components include the storage tank, integrated electronic enclosure, main structural plate, solar panels, and other vulnerable components of the satellite.

[0083] For example, the equivalent test system is used as follows:

[0084] The launching device is fixed as a whole in the equipment room of the vacuum test target track by structural tooling, and the fire line is calibrated by a laser rangefinder to ensure that the center of its fire line and components is coaxial.

[0085] The components are fixed in the effect evaluation chamber of the vacuum test target track via a structural assembly platform;

[0086] A dual-light-curtain high-precision laser velocimetry device is placed in the flight monitoring section of the vacuum test target track to measure the initial velocity of space debris launch in each test.

[0087] Two orthogonal high-speed camera devices were placed on the side and top of the effect evaluation room, respectively, to monitor the debris cloud and the state of space debris in real time during the collision process through the observation window;

[0088] Other measuring devices are deployed at corresponding positions on the side of the vacuum test target track to monitor the launch device and the corresponding state of the vacuum environment during the test.

[0089] All test data measured by each measuring device are transmitted to the corresponding industrial control computer in the integrated control room through the corresponding data transmission. The corresponding operators can monitor the status of each participating device in real time before, during and after the test through the industrial control computer. After the test, the monitoring video of the high-speed camera device is played back to perform quantitative analysis on key parameters such as the remaining velocity value, hole size and debris cloud shape, and the corresponding parameters of the launching device are statistically recorded.

[0090] S2, construct an initial simulation model and input the test conditions into the initial simulation model to obtain at least two sets of simulation results; wherein the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape. The initial simulation model is a meshless simulation model, constructed using a material point meshless method.

[0091] S3, calculate the difference results based on the results of the experiment and the simulation, and the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference.

[0092] In other words, the types of the experimental results and the simulation results are consistent, and they can be matched one-to-one. For example, the experimental results have a residual velocity value, and correspondingly, the simulation results have a simulated residual velocity value. The residual velocity difference is the difference between the experimental residual velocity value and the simulated residual velocity value. Similarly, the difference in air gap size and the difference in debris cloud shape can also be calculated in the same way.

[0093] S4, using a preset anomaly evaluation rule to determine whether the difference result is abnormal. If so, the difference result is recorded as an abnormal result; otherwise, S7 is executed. The anomaly evaluation rule requires that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal.

[0094] In other words, if at least one of the remaining velocity difference, hole size difference, and debris cloud shape difference is abnormal, the difference result is recorded as an abnormal result, indicating that the initial simulation model needs to be corrected; if none of the remaining velocity difference, hole size difference, and debris cloud shape difference are abnormal, the difference result is recorded as a normal result, indicating that the initial simulation model is basically accurate and can be directly used for subsequent processing.

[0095] S5, determine the correction category of the initial simulation model based on the number of abnormalities in the abnormal results; the number of abnormalities refers to the type of abnormal data in the abnormal results. For example, when it is determined that the remaining velocity difference is abnormal, while the hole size difference and the debris cloud shape difference are normal, the number of abnormalities is 1.

[0096] Specifically, when the number of anomalies is greater than or equal to L, the correction category is selected as Class I correction; when the number of anomalies is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H. The values ​​of L and H are obtained based on extensive testing, but can also be set by the user based on experience. Furthermore, the values ​​of L and H are limited by the number of parameter types in the results; the larger the number of parameter types, the greater the value of L may be, while the greater the value of H may be.

[0097] Wherein, the correction object of the first type of correction is at least one of the correction objects of the first type, and the correction object of the second type of correction is at least one of the correction objects of the second type; the correction object of the first type includes the material model of the component in the initial simulation model and the material model of the space debris; the correction object of the second type includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method.

[0098] In some embodiments, when the close-contact algorithm is enabled, the second type of correction object also includes a minimum spacing calculation coefficient. By adjusting the minimum spacing calculation coefficient, the calculation of the contact force can be changed, thereby making the simulation results closer to the experimental results.

[0099] In some embodiments, the failure threshold may be the maximum principal stress, equivalent plastic strain, maximum shear strain, or maximum principal strain; the material model may be an ideal elastoplastic model, a kinematic hardening model, or a Johnson-Cook model; and the failure handling method is the handling method after the failure of a component mass point (including cases where the mass point can be subjected to both tension and compression after failure, can only be subjected to tension and not compression after failure, and can only be subjected to compression and not tension after failure).

[0100] S6, Modify the initial simulation model according to the correction category.

[0101] S7. Based on the initial simulation model, multiple sets of simulation results are calculated, and each set of simulation results corresponds to a set of test conditions.

[0102] S8. Based on the multiple sets of simulation results and the test conditions, a damage effect model is fitted. The fitting method uses a second-order response surface model without interaction terms to fit the test conditions and the product of the major and minor axes of the hole (obtained by analyzing the hole size).

[0103] In some embodiments, the destructive effect model for:

[0104] ;

[0105] in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

[0106] The aforementioned destructive effect model is only affected by the test conditions (i.e., the initial attitude of the space debris). In other words, the results expressed by the above model are only related to the initial collision velocity of the space debris in its initial state. Angle of incidence First attitude angle Second attitude angle Third attitude angle It is related to the launching device and other factors. In other words, the destructive effect model in this application only applies to the endpoint effect and is not affected by other factors.

[0107] In some embodiments, step S8 is followed by:

[0108] S9. Verify the model parameters. If the iteration conditions are met, use the current model parameters; otherwise, adjust the model parameters.

[0109] The iteration condition requires that the minimum error be satisfied:

[0110] , ;

[0111] in, For the first Second simulation. For the first The hole size value in the simulation results and These are the major and minor axes of the holes created by space debris on the components, respectively. To achieve the destructive effect model in the first... The function values ​​calculated under the conditions of this simulation.

[0112] For example, when the difference results include the difference in remaining velocity, the difference in hole size, and the difference in debris cloud shape, and the number of abnormalities is less than or equal to H (preferably 1), for example, the difference in remaining velocity is abnormal while the other two are normal, it indicates that the selection of the basic model (including the material model of the space debris and the component) is correct. It is only necessary to reduce the failure threshold of the space debris so that the difference in remaining velocity is less than or equal to the preset velocity difference value, and at the same time, fine-tune the failure threshold of the component to ensure that the hole size and the shape of the debris cloud remain basically unchanged.

[0113] For example, when the number of abnormalities is greater than or equal to L (preferably 2), such as the difference in residual velocity, the difference in hole size, and the difference in debris cloud shape, it indicates that there is a qualitative difference (that is, there is a problem with the selection of material models for space debris and / or components). In this case, the material model of the component is changed from the current ideal elastoplastic model to the Johnson Cook model. In addition, the second correction object can be adjusted simultaneously. For example, the close contact algorithm can be enabled to increase the contact force, thereby increasing the residual velocity value. At the same time, the failure threshold of space debris is reduced, thereby reducing the hole size. Finally, the failure handling method of the mass point is fine-tuned to adjust the debris cloud shape.

[0114] In some embodiments, when determining the correction category of the initial simulation model in S5 based on the number of abnormalities in the abnormal results, if the number of abnormalities is greater than H and less than L, the correction category is selected as three-category correction.

[0115] Accordingly, the step of making corrections according to the three types of corrections in S6 includes:

[0116] S601: Obtain a first-class correction object and a second-class correction object input by the user; construct a first simulation model based on the first-class correction object and the second-class correction object; simultaneously, use a pre-built adjustment system to automatically adjust one of the second-class correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model.

[0117] The adjustment system can be preset and includes adjustment modes for various situations.

[0118] For example, in some embodiments, the adjustment system can generate a set of mapping rules based on historical data, that is, for different difference results, a corresponding adjustment value is matched. When the current difference result is input into the adjustment system, the system can automatically match a set of correction schemes (including correction objects and correction values) for it.

[0119] S602, the test conditions are input into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result.

[0120] S603, a first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results.

[0121] In some embodiments, the trend of change can be represented by the difference between the current simulation result (first simulation result or second simulation result) and the experimental result (referred to as the current difference result), divided by the difference result in S3, and then multiplied by 100%.

[0122] When calculating the difference in the difference results, the difference can be obtained by subtracting the difference in the remaining velocity, the difference in the puncture size, and the difference in the debris cloud shape from the difference results in S3.

[0123] S604, obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, it means that the first simulation model is significantly better than the second simulation model, and the simulation results obtained based on the first simulation model are more reliable. At this time, the first simulation model is determined as the initial simulation model in S7. Otherwise, determine whether the trend difference is less than the second preset trend difference. If so, it means that the second simulation model is better. At this time, the second simulation model is determined as the initial simulation model in S7.

[0124] In some embodiments, in S604, when it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset trend difference, it indicates that the simulation effects of the first simulation model and the second simulation model are not significantly different. At this time, the following steps are executed:

[0125] S605 prompts the user to adjust one of the two types of correction objects in the first simulation model. The adjustment system synchronously adjusts the second simulation model according to the user's operation. S602-S605 are repeated until the initial simulation model is determined.

[0126] In some embodiments, the two types of correction objects include at least three types of objects: a first type, a second type, and a third type. The first type of object is the failure threshold for space debris and the failure threshold for components; the second type of correction object is the on / off state of the close contact algorithm; and the third type of correction object is the failure handling method. Accordingly, the object adjusted in S605 is limited to a first type of object. Different correction objects are classified according to their impact on the simulation results, and adjustments are made according to these levels during the adjustment process, ensuring correction efficiency without excessively increasing the computational load.

[0127] When a user actively adjusts one of the two types of correction objects (preferably one type) in the first simulation model, the adjustment system similarly adjusts the same type of object. That is, this application provides a scheme for parallel experiments on a model based on a single factor. By restricting the correction objects—that is, focusing the variables on one type (e.g., one type of object)—other unselected correction objects are in a "locked state." Factors related to these unselected correction objects will not affect the results, thus reducing the number of influencing factors and making the results more reliable.

[0128] In other words, when the number of anomalies is significantly large, it is highly likely that there is a problem with the material model itself, while when the number of anomalies is significantly small, it is very likely that some parameter settings in the material model are not accurate. This application first performs a qualitative analysis of the initial simulation model based on the number of anomalies.

[0129] Specifically, the finite parameter results (considering only the residual velocity value, hole size, and debris cloud shape, i.e., the explicit parameters strongly correlated with the damage result) are first integrated, and the model is first fuzzy judged according to the number of abnormal results to qualitatively determine the initial simulation model. If the qualitative determination is clear, it is selected whether the first correction object needs to be corrected. If so, it is further determined whether the second correction object needs to be synchronously adjusted; otherwise, the second correction object is directly adjusted.

[0130] Furthermore, for situations where the qualitative nature is unclear, a semi-automatic test-based correction scheme is introduced. Specifically, firstly, a manual intervention is used to determine whether the problem lies with the parametric model. Then, a correction scheme is provided manually. Simultaneously, based on the above results, the system automatically matches a test-based correction scheme with the opposite qualitative nature to the manual correction scheme, resulting in two sets of corrected simulation results. The changing trends of the two are then compared, and the scheme with the better trend is determined as the new initial simulation scheme. In this way, if the user continues to correct the initial simulation scheme based on this scheme, the results obtained will be more reliable.

[0131] Furthermore, when the results obtained from the manually corrected scheme and the test scheme automatically matched by the system are not significantly different, a further restrictive correction (or secondary correction) is applied to some of the second-type correction objects in both schemes, resulting in two sets of results after further correction, and thus a reliable correction scheme is selected. In the above process, by restricting the second-type correction objects, the amount of data processing remains within a controllable range even when two sets of correction schemes are provided in parallel.

[0132] In summary, this application addresses the scenario of hypersonic collisions in aviation orbits. This invention integrates limited parameter results (considering only residual velocity values, puncture size, and debris cloud shape—i.e., explicit parameters strongly correlated with the damage outcome), and first performs fuzzy judgment and correction on the model based on the number of abnormal results. Furthermore, for unclear results, a semi-automatic test-based correction scheme is introduced, while simultaneously restricting the selection of correction targets. This comprehensively provides a "semi-automatic correction scheme based on limited data and hierarchical structure," effectively improving the correction efficiency of the simulation model while ensuring the accuracy of the damage effect model.

[0133] In other words, the high-speed collision process involves the strongly nonlinear physical and mechanical behavior of the medium under extreme conditions such as high speed, high temperature, and high pressure. This application can reduce the influence of extreme conditions such as high speed, high temperature, and high pressure by modifying the key parameters (material model and its parameters), and significantly improve the confidence of the simulation results.

[0134] Example 2

[0135] This application also provides a collision effect testing system that combines ground testing with simulation, including:

[0136] Equivalent test module: configured to construct an equivalent test system on the ground, and to conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component.

[0137] Initial simulation module: configured to build an initial simulation model and input the test conditions into the initial simulation model to obtain at least two sets of simulation results; wherein the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape;

[0138] Difference Result Calculation Module: Configured to calculate difference results based on the results of the experiment and the results of the simulation, wherein the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference;

[0139] The difference result processing module is configured to determine whether the difference result is abnormal using a preset anomaly evaluation rule, and if so, record the difference result as an abnormal result.

[0140] The anomaly assessment rules require that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal.

[0141] Correction module: configured to determine the correction category of the initial simulation model based on the number of anomalies in the anomaly results;

[0142] Specifically, when the number of abnormalities is greater than or equal to L, the correction category is selected as Class I correction; when the number of abnormalities is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H.

[0143] Wherein, the correction object of the first type of correction is at least one of the first type of correction objects, and the correction object of the second type of correction is at least one of the second type of correction objects; the first type of correction object includes the material model of the component and the material model of the space debris; the second type of correction object includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method.

[0144] And for modifying the initial simulation model according to the modification category;

[0145] The damage effect model construction module is configured to calculate multiple sets of simulation results based on the initial simulation model, each set of simulation results corresponding to a set of test conditions; and to fit a damage effect model based on the multiple sets of simulation results and the test conditions.

[0146] In some embodiments, the correction module is further configured to:

[0147] When determining the correction category of the initial simulation model based on the number of anomalies in the anomaly results, if the number of anomalies is greater than H and less than L, the correction category is selected as the third type of correction.

[0148] Accordingly, when making corrections based on the three types of corrections, it is specifically configured to:

[0149] The system acquires a first-class correction object and a second-class correction object from the user input, and constructs a first simulation model based on the first-class correction object and the second-class correction object. At the same time, it uses a pre-built adjustment system to automatically adjust one of the second-class correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model.

[0150] The test conditions are input into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result.

[0151] A first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results.

[0152] Obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, determine the first simulation model as the initial simulation model; otherwise, determine whether the trend difference is less than a second preset trend difference. If so, determine the second simulation model as the initial simulation model.

[0153] In some embodiments, the correction module is further configured to:

[0154] When it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset difference, the user is prompted to adjust one of the two types of correction objects in the first simulation model. The adjustment system then adjusts the second simulation model synchronously according to the user's operation.

[0155] In some embodiments, the destructive effect model for:

[0156] ;

[0157] in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

[0158] In some embodiments, the component is one of a storage tank, an integrated electronic chassis, or a main structural plate.

[0159] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes that element.

[0160] The embodiments of the present invention have been described above with reference to the accompanying drawings. However, the present invention is not limited to the specific embodiments described above. The specific embodiments described above are merely illustrative and not restrictive. Those skilled in the art can make many other forms under the guidance of the present invention without departing from the spirit and scope of the claims. All of these forms are within the protection scope of the present invention.

Claims

1. A collision effect testing method combining ground testing and simulation, characterized in that, include: S1, construct an equivalent test system on the ground, and conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component. S2, construct an initial simulation model, and input the test conditions into the initial simulation model respectively to obtain at least two sets of simulation results; wherein, the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape; S3, calculate the difference results based on the results of the experiment and the simulation results, and the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference; S4, use the preset anomaly evaluation rules to determine whether the difference result is abnormal. If it is, record the difference result as an abnormal result; otherwise, execute S7. The anomaly assessment rules require that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal. S5, determine the correction category of the initial simulation model based on the number of abnormalities in the abnormal results; Specifically, when the number of abnormalities is greater than or equal to L, the correction category is selected as Class I correction; when the number of abnormalities is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H. Wherein, the correction object of the first type of correction is at least one of the first type of correction objects, and the correction object of the second type of correction is at least one of the second type of correction objects; the first type of correction object includes the material model of the component and the material model of the space debris; the second type of correction object includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method. Specifically, when determining the correction category of the initial simulation model based on the number of abnormalities in the abnormal results, if the number of abnormalities is greater than H and less than L, the correction category is selected as three-category correction. Accordingly, the step of making corrections according to the three types of corrections in S6 includes: S601, obtain the first type of correction object and the second type of correction object input by the user, and construct a first simulation model based on the first type of correction object and the second type of correction object; at the same time, use a pre-built adjustment system to automatically adjust one of the second type of correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model; S602, input the test conditions into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result; S603, a first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results; S604, obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, determine the first simulation model as the initial simulation model in S7; otherwise, determine whether the trend difference is less than a second preset trend difference. If so, determine the second simulation model as the initial simulation model in S7. S6, Modify the initial simulation model according to the correction category; S7. Multiple sets of simulation results are calculated based on the initial simulation model, and each set of simulation results corresponds to a set of test conditions. S8, Based on the multiple sets of simulation results and the test conditions, a damage effect model is obtained. for: ； in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

2. The collision effect testing method combining ground testing and simulation according to claim 1, characterized in that, In S604, when it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset trend difference, the following steps are executed: S605 prompts the user to adjust one of the two types of correction objects in the first simulation model. The adjustment system synchronously adjusts the second simulation model according to the user's operation. S602-S605 are repeated until the initial simulation model is determined.

3. The collision effect testing method combining ground testing and simulation according to claim 1, characterized in that, The component is one of the following: storage tank, integrated electronic chassis, and main structural plate.

4. A collision effect testing system combining ground testing and simulation, characterized in that, include: Equivalent test module: configured to construct an equivalent test system on the ground, and to conduct tests under at least two different test conditions through the equivalent test system to obtain at least two sets of test results; the equivalent test system is used to simulate the process of space debris impacting the component. Initial simulation module: configured to build an initial simulation model and input the test conditions into the initial simulation model to obtain at least two sets of simulation results; wherein the results include at least the following parameter types: residual velocity value, hole size, and debris cloud shape; Difference Result Calculation Module: Configured to calculate difference results based on the results of the experiment and the results of the simulation, wherein the difference results include at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference; The difference result processing module is configured to determine whether the difference result is abnormal using a preset anomaly evaluation rule, and if so, record the difference result as an abnormal result. The anomaly assessment rules require that when the remaining velocity difference is greater than a preset velocity difference value, the remaining velocity value is determined to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is determined to be abnormal; and when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is determined to be abnormal. Correction module: configured to determine the correction category of the initial simulation model based on the number of anomalies in the anomaly results; Specifically, when the number of abnormalities is greater than or equal to L, the correction category is selected as Class I correction; when the number of abnormalities is less than or equal to H, the correction category is selected as Class II correction, where L is greater than H. Wherein, the correction object of the first type of correction is at least one of the first type of correction objects, and the correction object of the second type of correction is at least one of the second type of correction objects; the first type of correction object includes the material model of the component and the material model of the space debris; the second type of correction object includes the failure threshold of the space debris, the failure threshold of the component, the opening and closing state of the close contact algorithm and the failure handling method. And for modifying the initial simulation model according to the modification category; When determining the correction category of the initial simulation model based on the number of anomalies in the anomaly results, if the number of anomalies is greater than H and less than L, the correction category is selected as Class III correction. Accordingly, when making corrections based on the three types of corrections, it is specifically configured to: The system acquires a first-class correction object and a second-class correction object from the user input, and constructs a first simulation model based on the first-class correction object and the second-class correction object. At the same time, it uses a pre-built adjustment system to automatically adjust one of the second-class correction objects in the initial simulation model according to the difference results obtained in S3, so as to adjust the initial simulation model into a second simulation model. The test conditions are input into the first simulation model and the second simulation model respectively to obtain the first simulation result and the second simulation result. A first trend of change is calculated based on the results of the experiment and the first simulation results, and a second trend of change is calculated based on the results of the experiment and the second simulation results. Obtain the trend difference between the first trend and the second trend, and determine whether the trend difference is greater than a first preset trend difference. If so, determine the first simulation model as the initial simulation model; otherwise, determine whether the trend difference is less than a second preset trend difference. If so, determine the second simulation model as the initial simulation model. The damage effect model construction module is configured to calculate multiple sets of simulation results based on the initial simulation model, each set of simulation results corresponding to a set of test conditions; and to fit a damage effect model based on the multiple sets of simulation results and the test conditions. for: ； in, Initial collision velocity, For the angle of incidence, For the first attitude angle, For the second attitude angle, The third attitude angle, These are the model parameters.

5. The collision effect testing system combining ground testing and simulation according to claim 4, characterized in that, The correction module is also configured to: When it is determined that the trend difference is greater than or equal to the second preset trend difference and less than or equal to the first preset trend difference, the user is prompted to adjust one of the two types of correction objects in the first simulation model. The adjustment system then adjusts the second simulation model synchronously according to the user's operation.

6. The collision effect testing system combining ground testing and simulation according to claim 4, characterized in that, The component is one of the following: storage tank, integrated electronic chassis, and main structural plate.

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