Collision effect test method and system combining ground test and analogue simulation

Abstract

The invention belongs to the technical field of high-speed collision simulation, and particularly relates to a ground test and analogue simulation combined collision effect test method and system, and the method comprises the steps: constructing a ground equivalent test system, and carrying out the testing through the equivalent test system under at least two different test conditions, correspondingly obtaining results of at least two groups of tests; constructing an initial simulation model by adopting a substance point meshless method, and respectively inputting the test conditions into the initial simulation model to correspondingly obtain at least two groups of simulation results; calculating a difference result according to the test result and the simulation result; and judging whether the difference result is abnormal or not by adopting a preset abnormality evaluation rule, if so, recording the difference result as an abnormal result, correcting the initial simulation model according to the abnormal result, and fitting the damage effect model according to the corrected simulation model. And the correction efficiency of the simulation model is effectively improved.

Description

[0001] Priority Application This application claims priority from the Chinese invention patent application 【2024119183224】 “

Collision Effect Test Method and System Combining Ground Test and Simulation

[0002] The present invention belongs to the technical field of high-speed collision simulation, and specifically relates to a collision effect test method and system combining ground test and simulation. Background Art

[0003] More and more countries and organizations are participating in the space race. With the continuous development of various uses in orbital space, the number of satellites orbiting the Earth has increased dramatically, increasing the possibility of collisions and generating space debris. This has continuously increased the risk of the threat of hypervelocity collisions of space debris to on-orbit satellites.

[0004] Regarding the threat posed by high-speed collisions of space debris to satellites, the current research methods are still weak. The existing research methods are as follows: 1. On-orbit experiments: Relatively accurate and intuitive data can be obtained, but it is necessary to launch the equipment required for the experiment into a predetermined orbit and conduct the experiment, which requires harsh conditions and advanced devices, takes a lot of time and money, and the cost of long-term exposure of the device in space is high, time-consuming, has low repeatability, and may bring more debris to the orbital space, so it is very difficult to implement.

[0005] 2. Construct a set of environment and launch device on the ground to simulate the space environment and form a ground test system, which can largely equivalent the space environment, but also faces the problems of high test costs and difficult data acquisition.

[0006] 3. Computer numerical simulation test technology: It has the advantages of safety, flexible design, good repeatability, controllable environment and process, high cost-effectiveness, etc., and has certain advantages in the research of high-speed collisions of space debris. However, for high-speed collision situations, the strong non-linear physical and mechanical behaviors of the medium under extreme conditions such as high speed, high temperature, and high pressure have a great impact on the test results.

[0007] Therefore, how to more accurately understand the threat posed by high-speed collisions of space debris to satellites while ensuring a relatively low cost remains a difficult problem. Summary of the Invention

[0008] The purpose of the present invention is to provide a collision effect test method and system combining ground test and simulation to partially alleviate or solve the above problems and obtain higher-precision simulation test data.

[0009] To solve the above-mentioned technical problems, the present invention specifically adopts the following technical solutions: In a first aspect of the present invention, there is provided a collision effect test method combining ground test and simulation, including: S1, constructing an equivalent test system on the ground, and testing through the equivalent test system under at least two different test conditions to correspondingly obtain the results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting on components; S2, constructing an initial simulation model, and inputting the test conditions into the initial simulation model respectively to correspondingly obtain the results of at least two groups of simulations; wherein, the results at least include the following parameter types: residual velocity value, perforation size, debris cloud shape; S3, calculating a difference result based on the results of the tests and the results of the simulations, and the difference result at least includes one or more of the following: residual velocity difference, perforation size difference, debris cloud shape difference; S4, using a preset abnormal evaluation rule to determine whether the difference result is abnormal. If so, record the difference result as an abnormal result, otherwise execute S7; Wherein, the abnormal evaluation rule requires that when the residual velocity difference is greater than a preset velocity difference value, it is determined that the residual velocity value is abnormal; when the perforation size difference is greater than a preset size difference value, it is determined that the perforation size is abnormal; when the debris cloud shape difference is greater than a preset shape difference value, it is determined that the debris cloud shape is abnormal; S5, determining the correction category of the initial simulation model according to the number of abnormalities in the abnormal result; Wherein, when the number of abnormalities is greater than or equal to L, the correction category is selected as a first-class correction; when the number of abnormalities is less than or equal to H, the correction category is selected as a second-class correction, and L is greater than H; Wherein, the correction object of the first-class correction is at least one of the first-class correction objects, and the correction object of the second-class correction is at least one of the second-class correction objects; the first-class correction objects include the material model of the component and the material model of the space debris; the second-class correction objects include 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; S6, correcting the initial simulation model according to the correction category; S7, calculating multiple groups of simulation results according to the initial simulation model, and each group of simulation results corresponds to a group of test conditions; S8, fitting a damage effect model according to the multiple groups of simulation results and the test conditions.

[0010] As an improvement, when determining the correction category of the initial simulation model according to the number of anomalies in the anomaly result in S5, when the number of anomalies is greater than H and less than L, the correction category is selected as the three-category correction; Correspondingly, the steps of performing correction according to the three-category correction in S6 include: S601, obtain the first-category correction object and the second-category correction object input by the user, and construct a first simulation model according to the first-category correction object and the second-category correction object; at the same time, adopt a pre-constructed adjustment system to automatically adjust one of the second-category correction objects in the initial simulation model according to the difference result obtained in S3, so as to adjust the initial simulation model to a second simulation model; S602, input the test conditions into the first simulation model and the second simulation model respectively, and obtain a first simulation result and a second simulation result; S603, calculate a first change trend according to the result of the test and the first simulation result, and calculate a second change trend according to the result of the test and the second simulation result; S604, obtain the trend difference between the first change trend and the second change 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 model as the initial simulation model in S7.

[0011] 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, execute the steps: S605, prompt the user to adjust one of the second-category correction objects in the first simulation model, and the adjustment system synchronously adjusts the second simulation model according to the user's operation; and repeat the execution of S602 - S605 until the initial simulation model is determined.

[0012] As an improvement, the damage effect model is: ; where is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, is the model parameter.

[0013] As an improvement, the component is one of a storage tank, an integrated electronic chassis, and a main structure board.

[0014] In a second aspect of the present invention, there is provided a collision effect test system combining ground tests and simulation, including: Equivalent test module: configured to construct an equivalent test system on the ground and perform tests under at least two different test conditions through the equivalent test system to correspondingly obtain the results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting components; Initial simulation module: configured to construct an initial simulation model and input the test conditions into the initial simulation model respectively to correspondingly obtain the results of at least two groups of simulations; wherein, the results at least include the following parameter types: residual velocity value, perforation size, and debris cloud shape; Difference result calculation module: configured to calculate a difference result based on the test results and the simulation results, and the difference result at least includes one or more of the following: residual velocity difference, perforation size difference, and debris cloud shape difference; Difference result processing module: configured to determine whether the difference result is abnormal by using a preset abnormal evaluation rule, and if so, record the difference result as an abnormal result; Among them, the abnormal evaluation rule requires that when the residual velocity difference is greater than a preset velocity difference value, the residual velocity value is determined to be abnormal; when the perforation size difference is greater than a preset size difference value, the perforation size is determined to be abnormal; 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 according to the number of abnormalities in the abnormal results; Among them, when the number of abnormalities is greater than or equal to L, the correction category is selected as a first-class correction; when the number of abnormalities is less than or equal to H, the correction category is selected as a second-class correction, and L is greater than H; Among them, the correction object of the first-class correction is at least one of the first-class correction objects, and the correction object of the second-class correction is at least one of the second-class correction objects; the first-class correction objects include the material model of the component and the material model of the space debris; the second-class correction 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 used to correct the initial simulation model according to the correction category; Damage effect model construction module: Configured to calculate multiple groups of simulation results according to the initial simulation model, each group of simulation results corresponding to a group of test conditions; and fitting a damage effect model according to the multiple groups of simulation results and the test conditions.

[0015] As an improvement, the correction module is further configured to: When determining the correction category of the initial simulation model according to the number of abnormalities in the abnormality results, when the number of abnormalities is greater than H and less than L, select the correction category as the three-category correction; Correspondingly, when performing correction according to the three-category correction, it is specifically configured to: Obtain a first-category correction object and a second-category correction object input by the user, and construct a first simulation model according to the first-category correction object and the second-category correction object; at the same time, use a pre-constructed adjustment system to automatically adjust one of the second-category correction objects in the initial simulation model according to the difference result obtained in S3 to adjust the initial simulation model to a second simulation model; Input the test conditions into the first simulation model and the second simulation model respectively to obtain a first simulation result and a second simulation result; Calculate a first change trend according to the result of the test and the first simulation result, and calculate a second change trend according to the result of the test and the second simulation result; Obtain the trend difference between the first change trend and the second change 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 model as the initial simulation model.

[0016] As an improvement, the correction module is further 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, prompt the user to adjust one of the second-category correction objects in the first simulation model, and the adjustment system synchronously adjusts the second simulation model according to the user's operation.

[0017] As an improvement, the damage effect model is: ; Wherein, is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, is the model parameter.

[0018] As an improvement, the component is one of a storage tank, an integrated electronic chassis, and a main structure board.

[0019] The principle and beneficial technical effects of the present invention are as follows: In the complex space environment, the collision effects of different space debris on different aerospace components (components) are different. If a large number of tests and analyses are carried out separately for each situation, the workload will be very large. Therefore, it is particularly important to provide a solution that can facilitate users to quickly find the corresponding relationship between the current space debris and the components.

[0020] For the case of hypervelocity collision in the aerospace orbit, the present invention integrates the finite parameter results (only considering the residual velocity value, the perforation size, and the debris cloud shape, that is, the dominant parameters strongly related to the damage result), and first makes a fuzzy judgment and correction of the model according to the number of abnormal results; further, for the unclear results, a semi-automatic testability correction scheme is introduced, and at the same time, the selection of the correction object is restricted, and a "semi-automatic correction scheme based on finite data and hierarchical levels" is comprehensively provided, effectively improving the correction efficiency of the simulation model while ensuring the accuracy of the damage effect model.

[0021] Specifically, first, the present invention makes a fuzzy qualitative analysis of the model based on the number of abnormal results, and matches two completely different correction categories for it according to the qualitative results (correcting the material model or correcting the parameters of the model).

[0022] Further, for the situation where it is difficult to make a qualitative judgment between the two correction categories, a restrictive semi-automatic correction scheme is introduced. Specifically, a scheme combining manual intervention and machine recommendation is adopted to comprehensively determine a correction scheme with better result trends. In this process, on the one hand, the object of machine correction is restricted (only correcting one of the two types of objects). Further, when the difference between the two schemes is not large, a small-scale correction is further made to the finite object (such as a type of object), so as to select a more reliable correction scheme. Description of the Drawings

[0023] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. In all the drawings, similar elements or parts are generally identified by similar reference numerals. In the drawings, the elements or parts do not necessarily draw according to the actual scale. Obviously, the following-described drawings are some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained according to these drawings without creative efforts.

[0024] Figure 1 It is a flowchart of the collision effect test method combining ground test and simulation in the embodiment of the present invention; Figure 2 It is a modular structure diagram of the collision effect test system combining ground test and simulation in the embodiment of the present invention. Detailed implementation manners

[0025] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the drawings in the embodiments of the present invention. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0026] In this article, suffixes such as "module", "component" or "unit" used to represent elements are only for the convenience of the description of the present invention, and they have no specific meaning themselves. Therefore, "module", "component" or "unit" can be used interchangeably. In this article, the terms "upper", "lower", "inner", "outer", "front", "rear", "one end", "the other end", etc. indicate the orientation or position relationship based on the orientation or position relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be construed as a limitation to the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance.

[0027] In this article, unless otherwise clearly specified and defined, terms such as "installation", "equipped with", "connection", etc. should be understood in a broad sense. For example, "connection" 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, and it can be the communication inside two components. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations. In this article, "a plurality of" means two or more, that is, it includes two, three, four, five, etc.

[0028] Embodiment 1 The present invention provides a collision effect test method combining ground test and simulation, including: S1, constructing an equivalent test system on the ground, and testing through the equivalent test system under at least two different test conditions to correspondingly obtain the results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting on components.

[0029] In some embodiments, the test conditions at least include the damage parameters of space debris (impact initial velocity , incident angle , first attitude angle , second attitude angle , third attitude angle ). The results at least include the following parameter types: residual velocity value, perforation size, debris cloud shape.

[0030] In some embodiments, the first attitude angle, the second attitude angle, and the third attitude angle are respectively the yaw angle, the pitch angle, and the roll angle.

[0031] In some embodiments, the equivalent test system is composed of a space environment simulation platform, a parameter test platform, a launching device, and components (also known as the target), etc.

[0032] Among them, the space environment simulation platform mainly includes a vacuum target track test system and its related measurement and monitoring equipment, which is mainly used to provide a simulated high-vacuum environment for the test, and at the same time provide a bearing platform and a flight target track for the space debris high-speed launching device and the target. It is mainly divided into three parts: an equipment room, a flight monitoring section, and a damage assessment room. The launching device is placed in the equipment room, and the power supply cable and the data cable are connected to it through the tank wall flange to provide power supply and communication interaction for it. The components are placed in the effect assessment room, and the high-speed camera device is placed outside the effect assessment room to measure the space debris hitting position on the target through the observation window and monitor the collision effect; the double-light screen high-precision laser velocity measurement device is placed in the flight monitoring section to monitor the flight speed of the space debris.

[0033] The parameter test platform is mainly used to measure and record the velocity of space debris, the process of hitting the collision target, and the degree of damage to the target. It mainly includes a double-light curtain laser velocity measurement device and a high-speed camera device.

[0034] The double-light curtain laser velocity measurement device is mainly used to measure the flight velocity of high-speed moving objects (space debris) in a vacuum environment. Two light curtain detection sensors are placed along the ballistic direction in the vacuum chamber. The signals output when the space debris passes through the two detection light curtains are collected by a data acquisition instrument, and the time interval between the two signals and the flight velocity of the space debris are calculated using the space debris signal recognition algorithm.

[0035] The high-speed camera device controls its trigger moment through a remote interface and is triggered in a post-trigger form. It can take corresponding pictures within several seconds before and after the moment when the space debris hits the target, obtaining images of the attitude of the space debris, the damage effect, etc.

[0036] The launch device mainly consists of an integrated control subsystem, a launch subsystem, a charging subsystem, a pulse power supply subsystem, an integrated installation structure, etc.

[0037] The components mainly include the main vulnerable components of the satellite such as the storage tank, the integrated electronic chassis, the main structure board, and the solar panel.

[0038] Exemplarily, the usage method of the equivalent test system is as follows: The launch device is integrally fixed in the equipment room of the vacuum test target track through a structural tooling, and the fire line calibration is completed through a laser rangefinder to ensure that its fire line is coaxial with the center of the components. The components are fixed in the effect evaluation room of the vacuum test target track through a structural assembly platform. The double-light curtain high-precision laser velocity measurement device is placed in the flight monitoring section of the vacuum test target track to measure the initial velocity of the space debris launched in each test. Two orthogonal high-speed camera devices are respectively placed on the side and top of the effect evaluation room, and the real-time monitoring of the debris cloud and the state of the space debris during the collision process is realized through the observation window. Other measurement devices are respectively deployed at corresponding positions on the side of the vacuum test target track to monitor the corresponding states of the launch device and the vacuum environment during the test process.

[0039] The test data measured by each measurement device are all transmitted to the corresponding industrial control computer in the integrated control room through the corresponding data transmission. The corresponding operators can monitor the states of each participating device before, during, and after the test in real time through the industrial control computer, and after the test, the remaining velocity value, the hole size, the shape of the debris cloud and other key parameters are quantitatively analyzed by playing back the monitoring video of the high-speed camera device, and the corresponding parameters of the launch device are statistically recorded.

[0040] 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 correspondingly. Among them, the results at least include the following parameter types: remaining speed value, perforation size, and fragment cloud shape. Among them, the initial simulation model is a meshless simulation model, which is constructed by using the material point meshless method.

[0041] S3. Calculate a difference result based on the results of the test and the results of the simulation, and the difference result at least includes one or more of the following: remaining speed difference, perforation size difference, and fragment cloud shape difference.

[0042] That is to say, the types of the results of the test and the simulation are consistent, and the two can be corresponding one by one. For example, there is a remaining speed value of the test in the results of the test, and correspondingly, there is a remaining speed value of the simulation in the results of the simulation. The above remaining speed difference is the difference between the remaining speed value of the test and the remaining speed value of the simulation. Similarly, the perforation size difference and the fragment cloud shape difference can also be calculated in the same way.

[0043] S4. Use a preset abnormal evaluation rule to judge whether the difference result is abnormal. If so, record the difference result as an abnormal result; otherwise, execute S7. Among them, the abnormal evaluation rule requires that when the remaining speed difference is greater than a preset speed difference value, judge that the remaining speed value is abnormal; when the perforation size difference is greater than a preset size difference value, judge that the perforation size is abnormal; when the fragment cloud shape difference is greater than a preset shape difference value, judge that the fragment cloud shape is abnormal.

[0044] In other words, when at least one of the remaining speed difference, perforation size difference, and fragment cloud shape difference is abnormal, record the difference result as an abnormal result. At this time, it means that the initial simulation model needs to be corrected. If the remaining speed difference, perforation size difference, and fragment cloud shape difference are not abnormal, record the difference result as a normal result. At this time, it means that the initial simulation model is basically accurate, and the model can be directly used for subsequent processing.

[0045] S5. Determine the correction category of the initial simulation model according to the number of abnormal results in the abnormal results. The number of abnormal results is the type of abnormal data in the abnormal results. For example, when it is judged that the remaining speed difference is abnormal and the perforation size difference and the fragment cloud shape difference are both normal, the number of abnormal results is 1 at this time.

[0046] Among them, when the number of abnormalities is greater than or equal to L, the correction category is selected as the first type of correction; when the number of abnormalities is less than or equal to H, the correction category is selected as the second type of correction, where L is greater than H; the values of L and H are obtained based on a large number of tests. Of course, they can also be set by the user according to experience. Moreover, the values of L and H are restricted by the number of parameter types in the result. When the number of parameter types is larger, the value of L may increase correspondingly, while the value of H may decrease correspondingly.

[0047] Among them, 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 objects include the material models of the middle components and the material models of the space debris in the initial simulation model; the second type of correction includes the failure thresholds of the space debris, the failure thresholds of the components, the opening and closing states of the close-contact algorithm, and the failure handling methods.

[0048] In some embodiments, when the close-contact algorithm is selected to be enabled, the second type of correction object further includes the minimum spacing calculation coefficient. By adjusting the minimum spacing calculation coefficient, the calculation of the contact force can be changed, so that the simulation results are closer to the test results.

[0049] In some embodiments, the failure threshold can be the maximum principal stress, equivalent plastic strain, maximum shear strain, or maximum principal strain. The material model can be an ideal elastoplastic model, a kinematic hardening model, or a Johnson Cook model. The failure handling method is also the handling method after the component particles fail (including the cases where the particles can be both tensile and compressive, can only be tensile and not compressive, or can only be compressive and not tensile after failure).

[0050] S6. Correct the initial simulation model according to the correction category.

[0051] S7. Calculate multiple groups of simulation results based on the initial simulation model, and each group of simulation results corresponds to a group of test conditions.

[0052] S8. Fit a damage effect model based on the multiple groups of simulation results and the test conditions. Among them, the fitting method uses a second-order response surface model without interaction terms to fit the test conditions and the product of the long and short axes of the holes (obtained by analyzing the hole size).

[0053] In some embodiments, the damage effect model is: ; Among them, is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, is the model parameter.

[0054] The above damage effect model is only affected by the test conditions (i.e., the initial attitude of the space debris), that is, the results expressed by the above model are only related to the initial collision velocity , the incident angle , the first attitude angle , the second attitude angle , the third attitude angle and are not related to the launch device, etc. That is to say, the damage effect model in this application only targets the terminal effect and is not affected by other factors.

[0055] In some embodiments, after S8, it further includes the steps of: S9, verifying the model parameters. If the iteration conditions are met, the current model parameters are adopted; otherwise, the model parameters are adjusted; The iteration conditions require meeting the minimum error: , ; where is the th simulation, is the value of the hole size in the th simulation result, and are the major axis and minor axis of the hole generated by the space debris on the component respectively; is the function value calculated under the th simulation conditions through the damage effect model.

[0056] Exemplarily, when the difference results include the residual velocity difference, the hole size difference, and the debris cloud shape difference, and the number of abnormalities is less than or equal to H (preferably 1), for example, the residual velocity difference is abnormal and the other two are normal. At this time, it indicates that the selection of the basic model (including the material models of the space debris and the component) is correct. Only the failure threshold of the space debris needs to be reduced so that the residual velocity difference is less than or equal to the preset velocity difference value, and at the same time, the failure threshold of the component is slightly adjusted to ensure that the hole size and the debris cloud shape remain basically unchanged.

[0057] For another example, when the number of anomalies is greater than or equal to L (preferably 2), for example, the remaining speed difference, the perforation size difference, and the debris cloud shape difference are all abnormal, indicating a qualitative difference (that is, there is a problem with the selection of the material model of the space debris and / or the components). At this time, the material model of the component is changed from the current ideal elastoplastic model to the Johnson Cook model; and, the second correction object can be synchronously selected for adjustment. For example, the close-contact algorithm is enabled to increase the contact force, so that the remaining speed value increases, while the failure threshold of the space debris is reduced, so that the perforation size is reduced, and finally the failure handling method of the mass point is finely adjusted to adjust the debris cloud shape.

[0058] In some embodiments, when determining the correction category of the initial simulation model according to the number of anomalies in the anomaly result in S5, when the number of anomalies is greater than H and less than L, the correction category is selected as the three-category correction; Correspondingly, the steps of correction according to the three-category correction in S6 include: S601, obtain the first-category correction object and the second-category correction object input by the user, and construct the first simulation model according to the first-category correction object and the second-category correction object; at the same time, use the pre-constructed adjustment system to automatically adjust one of the second-category correction objects in the initial simulation model according to the difference result obtained in S3, so as to adjust the initial simulation model to the second simulation model.

[0059] Among them, the adjustment system can be set in advance, and the adjustment system includes various adjustment methods in different situations.

[0060] 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.

[0061] 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.

[0062] S603, calculate the first change trend according to the result of the test and the first simulation result, and calculate the second change trend according to the result of the test and the second simulation result.

[0063] In some embodiments, the change trend can be represented by dividing the difference result (which can be simply referred to as the current difference result) between the current simulation result (the first simulation result or the second simulation result) and the result of the test, by the difference result in S3, and then multiplying by 100%.

[0064] Among them, when calculating the difference of the difference result, the remaining velocity difference, the perforation size difference, and the debris cloud shape difference in the current difference result can be subtracted from the remaining velocity difference, the perforation size difference, and the debris cloud shape difference in the difference result in S3 respectively to obtain it.

[0065] S604. Obtain the trend difference between the first change trend and the second change trend, and determine whether the trend difference is greater than a first preset trend difference. If so, it indicates that the first simulation model is significantly better than the second simulation model, and the result simulated according to the first simulation model is more reliable. At this time, 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, it indicates that the second simulation model is better. At this time, determine the second model as the initial simulation model in S7.

[0066] 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 very different. At this time, execute the steps: S605. Prompt the user to adjust one of the secondary correction objects in the first simulation model, and the adjustment system synchronously adjusts the second simulation model according to the user's operation; and repeat the execution of S602 - S605 until the initial simulation model is determined.

[0067] In some embodiments, the secondary correction objects at least include a first type of object, a second type of object, and a third type of object. Among them, the first type of object is the failure threshold of space debris and the failure threshold of components, the second type of correction object is the opening and closing state of the close - range contact algorithm, and the third type of correction object is the failure handling method. Correspondingly, the object adjusted in S605 is limited to the first type of object. The correction objects are classified according to the influence degree of different correction objects on the simulation result, and the adjustment is restricted according to the level during the adjustment process, which can ensure the correction efficiency and will not excessively increase the calculation amount.

[0068] When the user actively adjusts one of the secondary correction objects in the first simulation model (preferably the first type of object), similarly, the adjustment system also adjusts the first type of object. That is to say, the present application provides a parallel test solution for the model with respect to a single factor. By restricting the correction objects, that is, focusing the variable on one type (such as the first type of object), and the other unselected correction objects are in a "locked state", and the factors related to these unselected correction objects will not affect the result, thereby making the influencing factors of the comparison result fewer and the result more reliable.

[0069] That is to say, when the number of anomalies is significantly large, it is very likely that there is a problem with the material model itself. When the number of anomalies is significantly small, it is very likely that only some parameter settings in the material model are not accurate enough. The present application first qualitatively analyzes the initial simulation model based on the number of anomalies.

[0070] Specifically, first integrate the finite parameter results (only considering the residual velocity value, the perforation size, and the debris cloud shape, that is, the dominant parameters strongly related to the damage result), and first make a fuzzy judgment on the model according to the number of anomaly results to qualitatively analyze the initial simulation model. When the qualitative analysis is clear, specifically select whether to correct the first correction object. If so, further determine whether to synchronously adjust the second correction object. Otherwise, directly adjust the second correction object.

[0071] Furthermore, for the case where the qualitative analysis is not clear, introduce a semi-automatic testability correction scheme. Specifically, first manually intervene to determine whether it is a problem with the parameter model, and then manually provide a set of correction schemes. At the same time, according to the above results, the system automatically matches a testability correction scheme with the opposite quality to the manual correction scheme to obtain two sets of corrected simulation results. Then, compare the change trends of the two sets of results, and determine the better-trending scheme as the new initial simulation scheme. In this way, if the user continues to correct the initial simulation scheme based on this scheme, the obtained results will be more reliable.

[0072] Even further, when the results obtained from the manual correction scheme and the testability scheme automatically matched by the system are not very different, further restrictively correct (or perform secondary correction) some of the secondary correction objects in the two sets, and then obtain two sets of results after the second correction, and then screen out a reliable correction scheme. In the above process, by restricting the secondary correction objects to be corrected, even when two correction schemes are provided in parallel, the data processing volume is within a controllable range.

[0073] In summary, for the case of ultra-high-speed collision in the aviation orbit, the present invention integrates the finite parameter results (only considering the residual velocity value, the perforation size, and the debris cloud shape, that is, the dominant parameters strongly related to the damage result), and first makes a fuzzy judgment and correction on the model according to the number of anomaly results. Furthermore, for the unclear results, introduce a semi-automatic testability correction scheme and at the same time restrict the selection of the correction object, comprehensively providing a "semi-automatic correction scheme based on finite data and hierarchical levels", effectively improving the correction efficiency of the simulation model while ensuring the accuracy of the damage effect model.

[0074] In other words, the high-speed collision process involves the strong non-linear physical and mechanical behaviors of the medium under extreme conditions such as high speed, high temperature, and high pressure. By modifying the key parameters (material models and their parameters), this application can reduce the influence of extreme conditions such as high speed, high temperature, and high pressure, and greatly improve the confidence level of the simulation results.

[0075] Embodiment 2 This application also provides a collision effect test system combining ground tests and simulation, including: Equivalent test module: configured to construct an equivalent test system on the ground and perform tests under at least two different test conditions through the equivalent test system to correspondingly obtain the results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting components; Initial simulation module: configured to construct an initial simulation model and input the test conditions into the initial simulation model respectively to correspondingly obtain the results of at least two groups of simulations; where the results at least include the following parameter types: residual velocity value, perforation size, and debris cloud shape; Difference result calculation module: configured to calculate the difference result based on the test results and the simulation results, and the difference result at least includes one or more of the following: residual velocity difference, perforation size difference, and debris cloud shape difference; Difference result processing module: configured to use a preset abnormal evaluation rule to determine whether the difference result is abnormal, and if so, record the difference result as an abnormal result; Among them, the abnormal evaluation rule requires that when the residual velocity difference is greater than the preset velocity difference value, the residual velocity value is determined to be abnormal; when the perforation size difference is greater than the preset size difference value, the perforation size is determined to be abnormal; when the debris cloud shape difference is greater than the 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 according to the number of abnormalities in the abnormal results; Among them, when the number of abnormalities is greater than or equal to L, the correction category is selected as a first-class correction; when the number of abnormalities is less than or equal to H, the correction category is selected as a second-class correction, and L is greater than H; Among them, the correction object of the first-class correction is at least one of the first-class correction objects, and the correction object of the second-class correction is at least one of the second-class correction objects; the first-class correction objects include the material models of components and the material models of space debris; the second-class correction objects include the failure thresholds of space debris, the failure thresholds of components, the opening and closing states of the close-contact algorithm, and the failure handling methods; And used to correct the initial simulation model according to the correction category; Damage effect model construction module: configured to calculate multiple sets of simulation results according to the initial simulation model, each set of the simulation results corresponding to a set of test conditions; and fit a damage effect model according to the multiple sets of simulation results and the test conditions.

[0076] In some embodiments, the correction module is further configured to: When determining the correction category of the initial simulation model according to the number of abnormalities in the abnormality results, when the number of abnormalities is greater than H and less than L, select the correction category as the three-category correction; Correspondingly, when performing correction according to the three-category correction, it is specifically configured to: Obtain a first type of correction object and a second type of correction object input by the user, and construct a first simulation model according to the first type of correction object and the second type of correction object; at the same time, adopt a pre-constructed adjustment system to automatically adjust one of the second type of correction objects in the initial simulation model according to the difference result obtained in S3 to adjust the initial simulation model to a second simulation model; Input the test conditions into the first simulation model and the second simulation model respectively to obtain a first simulation result and a second simulation result; Calculate a first change trend according to the result of the test and the first simulation result, and calculate a second change trend according to the result of the test and the second simulation result; Obtain the trend difference between the first change trend and the second change 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 model as the initial simulation model.

[0077] In some embodiments, the correction module is further 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 difference, prompt the user to adjust one of the second type of correction objects in the first simulation model, and the adjustment system synchronously adjusts the second simulation model according to the user's operation.

[0078] In some embodiments, the damage effect model is: ; Wherein, is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, are model parameters.

[0079] In some embodiments, the component is one of a storage tank, an integrated electronic chassis, and a main structural board.

[0080] It should be noted that in this article, the term "including", "comprising", or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article, or device including a series of elements not only includes those elements but also includes other elements not explicitly listed, or further includes elements inherent to such a process, method, article, or device. Without further limitation, an element defined by the statement "including one..." does not exclude the existence of additional identical elements in the process, method, article, or device including that element.

[0081] The embodiments of the present invention have been described above in conjunction with the accompanying drawings. However, the present invention is not limited to the above specific embodiments. The above specific embodiments are merely illustrative and not restrictive. Under the inspiration of the present invention, those of ordinary skill in the art can also make many forms without departing from the spirit and scope protected by the claims of the present invention. These all fall within the protection scope of the present invention.

Claims

1. A collision effect test method combining ground test and simulation, characterized in that: include: S1, constructing a ground equivalent test system, and performing tests under at least two different test conditions through the equivalent test system to obtain corresponding results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting the component; S2, constructing an initial simulation model, and inputting the test conditions into the initial simulation model respectively, so as to obtain at least two sets of simulation results correspondingly; wherein the results at least include the following parameter types: residual velocity value, hole size, and debris cloud shape; S3, calculating a difference result according to the test result and the simulation result, wherein the difference result includes at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference; S4, using a preset abnormality assessment rule to determine whether the difference result is abnormal, if so, recording the difference result as an abnormal result, otherwise executing S7; The abnormality assessment rule requires that when the residual speed difference is greater than a preset speed difference value, the residual speed value is judged to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is judged to be abnormal; when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is judged to be abnormal; S5, determining a correction category of the initial simulation model according to the number of abnormalities in the abnormal results; When the number of abnormalities is greater than or equal to L, the correction category is selected as a first-class correction; when the number of abnormalities is less than or equal to H, the correction category is selected as a second-class correction, and L is greater than H; 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 objects include material models of components and material models of space debris; the second type of correction objects include failure thresholds of space debris, failure thresholds of components, on / off states of close contact algorithms, and failure handling methods; S6, modifying the initial simulation model according to the modification category; S7, obtaining multiple groups of simulation results according to the initial simulation model, each group of simulation results corresponding to a group of test conditions; S8, obtaining a damage effect model by fitting according to the multiple groups of simulation results and the test conditions.

2. The collision effect test method combining ground test and simulation according to claim 1 is characterized in that: In S5, when determining the correction category of the initial simulation model according to the number of abnormalities in the abnormal result, when the number of abnormalities is greater than H and less than L, the correction category is selected as the third type correction; Accordingly, the step of performing correction according to the three types of corrections in S6 includes: S601, obtaining a first type of correction object and a second type of correction object input by a user, and constructing a first simulation model according to the first type of correction object and the second type of correction object; and simultaneously using a pre-constructed adjustment system to automatically adjust one of the two types of correction objects in the initial simulation model according to the difference result obtained in S3, so as to adjust the initial simulation model to a second simulation model; S602, inputting the test conditions into the first simulation model and the second simulation model respectively to obtain a first simulation result and a second simulation result; S603, calculating a first change trend according to the result of the test and the first simulation result, and calculating a second change trend according to the result of the test and the second simulation result; S604, obtaining the trend difference between the first change trend and the second change trend, and determining whether the trend difference is greater than a first preset trend difference. If so, determining the first simulation model as the initial simulation model in S7; otherwise, determining whether the trend difference is less than a second preset trend difference. If so, determining the second model as the initial simulation model in S7.

3. The collision effect test method combining ground test and simulation according to claim 2 is 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 steps are executed: S605, prompting the user to adjust one of the two types of correction objects in the first simulation model, and the adjustment system synchronously adjusts the second simulation model according to the user's operation; and repeatedly executing S602-S605 until the initial simulation model is determined.

4. The collision effect test method combining ground test and simulation according to claim 1 is characterized in that: The damage effect model for: ； in, is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, is the model parameter.

5. The collision effect test method combining ground test and simulation according to claim 1 is characterized in that: The component is one of a storage tank, an integrated electronic chassis, and a main structural plate.

6. A collision effect test system combining ground test and simulation, characterized in that: include: Equivalent test module: configured to construct an equivalent test system on the ground, and to perform tests under at least two different test conditions through the equivalent test system to obtain corresponding results of at least two groups of tests; the equivalent test system is used to simulate the process of space debris impacting the components; Initial simulation module: configured to 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; A difference result calculation module is configured to calculate a difference result according to the test result and the simulation result, and the difference result includes at least one or more of the following: residual velocity difference, hole size difference, and debris cloud shape difference; A difference result processing module is configured to use a preset abnormality assessment rule to determine whether the difference result is abnormal, and if so, record the difference result as an abnormal result; The abnormality assessment rule requires that when the residual speed difference is greater than a preset speed difference value, the residual speed value is judged to be abnormal; when the hole size difference is greater than a preset size difference value, the hole size is judged to be abnormal; when the debris cloud shape difference is greater than a preset shape difference value, the debris cloud shape is judged to be abnormal; A correction module: configured to determine a correction category of the initial simulation model according to the number of abnormalities in the abnormal results; When the number of abnormalities is greater than or equal to L, the correction category is selected as a first-class correction; when the number of abnormalities is less than or equal to H, the correction category is selected as a second-class correction, and L is greater than H; 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 objects include material models of components and material models of space debris; the second type of correction includes failure thresholds of space debris, failure thresholds of components, on / off states of close contact algorithms, and failure handling methods; and for modifying the initial simulation model according to the modification category; A damage effect model building module is configured to calculate a plurality of groups of simulation results according to the initial simulation model, each group of simulation results corresponds to a group of test conditions; and to fit the damage effect model according to the plurality of groups of simulation results and the test conditions.

7. The collision effect test system combining ground test and simulation according to claim 6 is characterized in that: The correction module is further configured to: When determining the correction category of the initial simulation model according to the number of abnormalities in the abnormal result, when the number of abnormalities is greater than H and less than L, the correction category is selected as the third type correction; Accordingly, when performing correction according to the three types of corrections, it is specifically configured to: Obtaining a first type of correction object and a second type of correction object input by a user, and constructing a first simulation model according to the first type of correction object and the second type of correction object; and simultaneously using a pre-constructed adjustment system to automatically adjust one of the two types of correction objects in the initial simulation model according to the difference result obtained in S3, so as to adjust the initial simulation model to a second simulation model; Inputting the test conditions into the first simulation model and the second simulation model respectively to obtain a first simulation result and a second simulation result; A first change trend is calculated based on the result of the test and the first simulation result, and a second change trend is calculated based on the result of the test and the second simulation result; Obtaining a trend difference between the first change trend and the second change trend, and determining whether the trend difference is greater than a first preset trend difference, and if so, determining the first simulation model as the initial simulation model; Otherwise, it is determined whether the trend difference is less than a second preset trend difference, and if so, the second model is determined as the initial simulation model.

8. The collision effect test system combining ground test and simulation according to claim 7 is characterized in that: The correction module is further 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, and the adjustment system synchronously adjusts the second simulation model according to the user's operation.

9. The collision effect test system combining ground test and simulation according to claim 6, characterized in that: The damage effect model for: ； in, is the initial collision velocity, is the incident angle, is the first attitude angle, is the second attitude angle, is the third attitude angle, is the model parameter.

10. The collision effect test system combining ground test and simulation according to claim 6, characterized in that: The component is one of a storage tank, an integrated electronic chassis, and a main structural plate.

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