Satellite sampling inspection method and device, storage medium and computer program product

Abstract

The invention discloses a satellite sampling inspection method and device, a storage medium and a computer program product. The method comprises the following steps: in a preset test environment, first test data of a spot check satellite is obtained, and the preset test environment is used for simulating a vibration environment in a satellite launching process; evaluating the structural state of the sampling inspection satellite based on the first test data to obtain a first evaluation result; judging that the structural state of the casual inspection satellite is good based on the first evaluation result, and performing mechanical property evaluation on the casual inspection satellite by adopting the evaluation model to obtain a second evaluation result; and determining the casual inspection satellite as a qualified satellite product in response to determining that the casual inspection satellite meets a first requirement based on the second evaluation result, and determining that the casual inspection satellite is a consistency requirement of the mechanical properties of the satellite. The technical problem that the test efficiency is low when a traditional mechanical test method is used for carrying out comprehensive tests on large-scale batch production satellites is solved.

Description

Technical Field

[0001] This invention relates to the field of spacecraft manufacturing and testing, and more specifically, to a satellite sampling inspection method, equipment, storage medium, and computer program product. Background Technology

[0002] In the context of mass production of commercial internet satellites, and facing the business demand of producing dozens to thousands of satellites at a time, rocket fairings often employ multi-satellite stacking for assembly. However, conducting comprehensive testing of large-scale stacked satellites using traditional spacecraft mechanical testing methods is not only difficult and risky, but also time-consuming and costly.

[0003] There is currently no effective solution to the above problems. Summary of the Invention

[0004] This invention provides a satellite sampling inspection method, equipment, storage medium, and computer program product to at least solve the technical problem of low testing efficiency when using traditional mechanical testing methods to conduct comprehensive testing on large-scale mass-produced satellites.

[0005] According to one aspect of the present invention, a satellite sampling inspection method is provided, comprising: acquiring first test data of a sampled satellite under a preset test environment, wherein the preset test environment is used to simulate the vibration environment during satellite launch; evaluating the structural state of the sampled satellite based on the first test data to obtain a first evaluation result; determining that the structural state of the sampled satellite is good based on the first evaluation result, and using an evaluation model to evaluate the mechanical performance of the sampled satellite to obtain a second evaluation result; determining that the sampled satellite meets a first requirement based on the second evaluation result, and identifying the sampled satellite as a qualified satellite product, wherein the first requirement is a consistency requirement for the mechanical performance of the satellite.

[0006] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: responding to a determination based on a first evaluation result that the structural state of the sampled satellite is abnormal, and identifying the sampled satellite as a non-conforming satellite product.

[0007] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: responding to a second evaluation result determining that the sampled satellite does not meet the first requirement, using a first modified test model to perform a design margin assessment on the stacked structure of multiple satellites to obtain a third evaluation result; responding to a third evaluation result determining that the stacked structure meets the second requirement, and determining that the sampled satellite is a qualified satellite product, wherein the second requirement is a design margin requirement.

[0008] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: determining that the stacking structure does not meet the second requirement based on the third evaluation result, and identifying the sampled satellite as a non-conforming satellite product.

[0009] Optionally, an evaluation model is used to assess the mechanical performance of the sampled satellites to obtain a second evaluation result, including: using the evaluation model to perform resonant frequency offset comparison, peak response offset comparison, and / or response curve coherence analysis on the sampled satellites to obtain a second evaluation result; wherein, the resonant frequency offset comparison is used to determine whether the natural frequencies of different satellites are consistent at the same measuring point, the peak response offset comparison is used to determine whether the structural strength and stiffness of each satellite are consistent by comparing the maximum acceleration response of different satellites at the same measuring point, and the response curve coherence analysis is used to determine the degree of consistency between different satellites in vibration transmission characteristics and structural integrity characteristics.

[0010] Optionally, the coherence analysis of the response curves of the sampled satellites includes: obtaining the autospectrum of a single satellite; obtaining the cross-spectrum of the mechanical performance parameters of different satellites at the same measurement point; obtaining multiple coherence coefficients between different satellites based on the autospectrum and cross-spectrum, wherein the multiple coherence coefficients are used to evaluate the consistency of the satellite's mechanical behavior from multiple dimensions; and evaluating the mechanical performance of the sampled satellites based on the multiple coherence coefficients.

[0011] Optionally, the satellite sampling method in this embodiment of the invention further includes: acquiring second test data of multiple satellites under a preset test environment; and modifying the first initial test model based on the second test data and the second modified test model to obtain the first modified test model.

[0012] Optionally, the satellite sampling method in this embodiment of the invention further includes: acquiring third test data of a single satellite under a preset test environment; and correcting the second initial test model based on the third test data to obtain a second corrected test model.

[0013] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: in response to the sampled satellite being a qualified satellite product, updating the model parameters of the evaluation model based on the first test data to obtain an updated evaluation model.

[0014] Optionally, the satellite sampling method in this embodiment of the invention further includes: under a preset test environment, conducting mechanical tests on multiple satellites in multiple different directions to obtain mechanical performance parameters of multiple satellites at different positions, thus obtaining fourth test data; performing feature-level test data comparison on the fourth test data to obtain comparison results; in response to the comparison results indicating that the feature-level test data comparison is good, constructing a basic database based on the fourth test data; and in response to the comparison results indicating that the feature-level test data comparison is abnormal, removing the fourth test data, wherein the basic database provides data support for the evaluation model.

[0015] According to another aspect of the present invention, a satellite sampling inspection device is also provided, comprising: a first acquisition module, configured to acquire first test data of a sampled satellite under a preset test environment, wherein the preset test environment is used to simulate the vibration environment during satellite launch; a first evaluation module, configured to evaluate the structural state of the sampled satellite based on the first test data to obtain a first evaluation result; a second evaluation module, configured to, in response to the determination that the structural state of the sampled satellite is good based on the first evaluation result, use an evaluation model to evaluate the mechanical performance of the sampled satellite to obtain a second evaluation result; and a first determination module, configured to, in response to the determination that the sampled satellite meets a first requirement based on the second evaluation result, determine that the sampled satellite is a qualified satellite product, wherein the first requirement is a consistency requirement for the mechanical performance of the satellite.

[0016] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: a second determining module, used to determine that the sampled satellite is a non-conforming satellite product in response to a determination based on the first evaluation result that the structural state of the sampled satellite is abnormal.

[0017] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: a third evaluation module, used to respond to a second evaluation result indicating that the sampled satellite does not meet the first requirement, and to use a first modified test model to perform a design margin evaluation on the stacked structure of multiple satellites to obtain a third evaluation result; and a third determination module, used to respond to a third evaluation result indicating that the stacked structure meets the second requirement, and to determine that the sampled satellite is a qualified satellite product, wherein the second requirement is a design margin requirement.

[0018] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: a fourth determining module, used to determine that the sampled satellite is a non-conforming satellite product in response to a judgment based on the third evaluation result that the stacking structure does not meet the second requirement.

[0019] Optionally, the second evaluation module is further used to: perform resonant frequency offset comparison, peak response offset comparison, and / or response curve coherence analysis on the sampled satellites using an evaluation model to obtain a second evaluation result; wherein, the resonant frequency offset comparison is used to determine whether the natural frequencies of different satellites are consistent at the same measuring point, the peak response offset comparison is used to determine whether the structural strength and stiffness of each satellite are consistent by comparing the maximum acceleration responses of different satellites at the same measuring point, and the response curve coherence analysis is used to determine the degree of consistency between different satellites in vibration transmission characteristics and structural integrity characteristics.

[0020] Optionally, the second evaluation module is also used to: obtain the autospectrum of a single satellite; obtain the cross-spectrum of the mechanical performance parameters of different satellites at the same measurement point; obtain multiple coherence coefficients between different satellites based on the autospectrum and cross-spectrum, wherein the multiple coherence coefficients are used to evaluate the consistency of the satellite's mechanical behavior from multiple dimensions; and evaluate the mechanical performance of the sampled satellites based on the multiple coherence coefficients.

[0021] Optionally, the satellite sampling device in this embodiment of the invention further includes: a second acquisition module, used to acquire second test data of multiple satellites under a preset test environment; and a first correction module, used to correct the first initial test model based on the second test data and the second corrected test model to obtain the first corrected test model.

[0022] Optionally, the satellite sampling device in this embodiment of the invention further includes: a third acquisition module, used to acquire third test data of a single satellite under a preset test environment; and a second correction module, used to correct the second initial test model based on the third test data to obtain a second corrected test model.

[0023] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: an update module, used to update the model parameters of the evaluation model based on the first test data in response to the sampled satellite being a qualified satellite product, so as to obtain an updated evaluation model.

[0024] Optionally, the satellite sampling device in this embodiment of the invention further includes: a fourth acquisition module, used to acquire the mechanical performance parameters of multiple satellites at different positions by conducting mechanical tests on multiple satellites in multiple different directions under a preset test environment, and obtain fourth test data; and a comparison module, used to perform feature-level test data comparison on the fourth test data and obtain comparison results.

[0025] The processing module is used to construct a basic database based on the fourth experimental data in response to the comparison results indicating that the feature-level experimental data are well matched; and to remove the fourth experimental data in response to the comparison results indicating that the feature-level experimental data are abnormal. The basic database provides data support for the evaluation model.

[0026] According to another aspect of the present invention, a satellite sampling inspection device is also provided, comprising: a memory storing an executable program; and a processor for running the program, wherein the program executes the satellite sampling inspection method of the present invention during runtime.

[0027] According to another aspect of the present invention, a computer-readable storage medium is also provided, the computer-readable storage medium including a stored executable program, wherein, when the executable program is executed, it controls the device where the storage medium is located to execute the satellite sampling method of the present invention.

[0028] According to another aspect of the present invention, a computer program product is also provided, including a computer program that, when executed by a processor, implements the satellite sampling method of the present invention.

[0029] According to another aspect of the present invention, a chip system is also provided, comprising: a processor for calling and running a computer program from a memory, such that a communication device equipped with the chip system performs the satellite sampling method of the present invention.

[0030] In this embodiment of the invention, first test data of a sampled satellite is acquired under a preset test environment, and the structural state of the sampled satellite is evaluated based on the first test data to obtain a first evaluation result. Then, when the structural state of the sampled satellite is determined to be good based on the first evaluation result, an evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain a second evaluation result. Finally, when the sampled satellite is determined to meet the first requirement based on the second evaluation result, the sampled satellite is determined to be a qualified satellite product. This achieves the goal of rapid, accurate, and low-cost mechanical performance evaluation of mass-produced satellites, thereby improving the efficiency of mechanical testing of mass-produced satellites, reducing testing costs, and shortening the testing cycle. This solves the technical problem of low testing efficiency when using traditional mechanical testing methods to conduct comprehensive testing of mass-produced satellites. Attached Figure Description

[0031] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0032] Figure 1 This is a flowchart of a satellite sampling method according to one embodiment of the present invention;

[0033] Figure 2 This is a schematic diagram of a first initial experimental model according to one embodiment of the present invention;

[0034] Figure 3 This is a schematic diagram of a second initial experimental model according to one embodiment of the present invention;

[0035] Figure 4 This is a schematic diagram of a satellite sampling method according to one embodiment of the present invention;

[0036] Figure 5 This is a structural block diagram of a satellite sampling device according to one embodiment of the present invention. Detailed Implementation

[0037] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0038] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0039] In the context of mass production of commercial internet satellites, and facing the business demand of producing dozens to thousands of satellites at a time, rocket fairings often employ multi-satellite stacking for assembly. However, conducting comprehensive testing of large-scale stacked satellites using traditional spacecraft mechanical testing methods is not only difficult and risky, but also time-consuming and costly.

[0040] Specifically, although the existing "Test Requirements for Launch Vehicles, Upper Stages and Spacecraft" (GJB 1027A-2020) and the national standard "Test Methods for Vibration of Spacecraft" (GB / T 34516-2017) have formulated detailed technical requirements and specifications for spacecraft mechanical tests, there is currently no complete, efficient and cost-effective sampling mechanical test scheme for handling mass-produced stacked satellites.

[0041] Figure 1 This is a flowchart of a satellite sampling method according to one embodiment of the present invention, such as... Figure 1 As shown, the method includes the following steps:

[0042] Step S11: Under a preset test environment, acquire the first test data of the sampled satellites, wherein the preset test environment is used to simulate the vibration environment during satellite launch;

[0043] Specifically, acquiring the first test data of the randomly selected satellites under a pre-set test environment refers to conducting mechanical environment tests on randomly selected satellite samples under controlled laboratory conditions to collect their response data under specific mechanical loads. The aforementioned pre-set test environment refers to simulated tests set according to the satellite's design specifications and expected operating environment, including but not limited to sinusoidal vibration tests or random vibration tests, as well as temperature cycling tests.

[0044] The aforementioned sample satellites refer to satellite samples randomly selected from mass-produced satellites of the same model or batch for mechanical performance testing. The selection of sample satellites aims to evaluate the mechanical strength and vibration response characteristics of the entire mass-produced satellite constellation through a limited number of tests, ensuring that the entire mass-produced satellite constellation can withstand the harsh vibration environment during actual launches.

[0045] The aforementioned first test data refers to the data collected on the satellite's structural response after testing the randomly selected satellite under a preset test environment, simulating the vibration environment experienced during satellite launch. Specifically, the first test data includes, but is not limited to, information such as the acceleration response, frequency response, and modal characteristics of the randomly selected satellite during the vibration test, used to analyze the structural state and mechanical performance of the randomly selected satellite, and to assess its ability to withstand the load during launch.

[0046] Specifically, by obtaining the first test data of the sampled satellites under a preset test environment, the structural performance and response of the sampled satellites in a simulated launch vibration environment can be analyzed, thereby inferring whether the entire batch of satellites meets the mechanical performance requirements, which can reduce test costs and shorten the test cycle.

[0047] For example, the aforementioned sampled satellite can be a single satellite in a batch-produced satellite constellation. Specifically, a characteristic-level frequency sweep test can be performed on the sampled satellite first to preliminarily identify its modal characteristics, including but not limited to natural frequencies and mode shapes. Subsequently, a high-scale sinusoidal vibration test is conducted to verify the performance of the sampled satellite structure under higher loads. Finally, a characteristic-level frequency sweep test is performed again to verify the state of the sampled satellite structure after the high-scale test, and whether there is any potential structural damage or performance degradation.

[0048] Step S12: Evaluate the structural status of the sampled satellites based on the first test data to obtain the first evaluation result;

[0049] For example, based on the first test data, the characteristic level curves and transfer function curves of the sampled satellite before and after the test can be obtained. Furthermore, by comparing the aforementioned characteristic level curves and transfer function curves, the structural state of the sampled satellite can be preliminarily determined.

[0050] Specifically, the aforementioned characteristic level curves refer to the dynamic response characteristic curves of the satellite structure at lower vibration levels. These curves can intuitively reflect the resonance behavior of the satellite structure at key frequency points, including but not limited to the position, shape, and height of resonance peaks. The aforementioned transfer function curves refer to the relationship between input excitation and output response in vibration tests, typically expressed as the ratio of output acceleration to input force, or the gain and phase change of acceleration with respect to frequency. The transfer function reveals the satellite structure's ability to respond to external vibration stimuli, including the structure's amplification factor and phase hysteresis. By comparing the transfer function curves before and after the test, it is possible to check whether the satellite's structural integrity has been affected by high-level vibration tests, whether there are abnormal response enhancements or attenuations, and whether the phase characteristics have changed.

[0051] For example, the structural state assessment based on the first test data first requires analyzing the data before and after the characteristic-level frequency sweep test to check for the appearance of new resonance points, the disappearance of existing resonance points or significant frequency shifts, and whether there are abnormal peak changes in the structural response. This helps identify whether the sampled satellite structure has been damaged or altered due to the high-magnitude sinusoidal vibration test. Furthermore, a detailed comparison of the transfer function curves is needed to assess whether the curve shapes are consistent, especially whether the amplification factor and phase changes near the resonance points are within the expected tolerance range. If the curve changes exceed the tolerance, it can be determined that certain parts of the sampled satellite structure have experienced unexpected stress accumulation or material fatigue, affecting its dynamic response characteristics.

[0052] Step S13: Based on the first evaluation result, the structural condition of the sampled satellite is determined to be good. The evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain the second evaluation result.

[0053] Specifically, when the first assessment results indicate that the structural condition of the sampled satellite is good, that is, after the sampled satellite has undergone a preset vibration environment test, the changes in its characteristic level curve and transfer function curve are within the allowable range, and there are no signs of structural damage or performance degradation, the evaluation model can be used to further evaluate the mechanical performance of the satellite in detail.

[0054] For example, historical mechanical response data from at least three qualified satellites can be obtained through experiments, including but not limited to acceleration responses at different locations, forming the basic database for an evaluation model. This allows the model to capture the modal and frequency response characteristics of the satellites within a specific frequency range (e.g., 5-100Hz). Based on this database, the mechanical consistency of the satellites can be assessed by analyzing parameters such as the autospectrum, cross-spectrum, and coherence coefficient corresponding to each set of historical mechanical response data. This includes the proximity of resonant frequencies, the similarity of peak responses, and the coherence of acceleration response curves, thereby constructing an evaluation model. Furthermore, the mechanical performance of relevant parameters of the currently sampled satellites can be evaluated based on the evaluation model to obtain a second evaluation result.

[0055] Step S14: Based on the second evaluation result, the sampled satellite is determined to meet the first requirement and is identified as a qualified satellite product. The first requirement is the consistency requirement of the satellite's mechanical performance.

[0056] The aforementioned requirement for consistency in satellite mechanical performance refers to the fact that during mass production, all satellites exhibit similar mechanical response characteristics under the same testing conditions, including but not limited to the proximity of resonant frequencies, the similarity of peak responses, and the high coherence of acceleration response curves. This ensures that the structural strength, stiffness, and dynamic characteristics of each satellite remain consistent in a statistical sense, thereby meeting the requirements of the ability of mass-produced stacked satellites to jointly withstand mechanical loads and the expected safety performance indicators in the launch and operation environment.

[0057] Specifically, based on the second assessment results, if the sampled satellite is determined to meet the consistency requirements of satellite mechanical performance, that is, its mechanical response characteristics are consistent with the historical satellite data in the basic database in a statistical sense, then the sampled satellite can be determined to be a qualified satellite product.

[0058] Based on steps S11 to S14 above, by acquiring first test data of the sampled satellite under a preset test environment, and evaluating the structural state of the sampled satellite based on the first test data, a first evaluation result is obtained. Then, when the structural state of the sampled satellite is determined to be good based on the first evaluation result, an evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain a second evaluation result. Finally, when the sampled satellite is determined to meet the first requirement based on the second evaluation result, the sampled satellite is determined to be a qualified satellite product. This achieves the goal of rapid, accurate, and low-cost mechanical performance evaluation of mass-produced satellites, thereby improving the efficiency of mechanical testing of mass-produced satellites, reducing testing costs, and shortening the testing cycle. This solves the technical problem of low testing efficiency when using traditional mechanical testing methods to conduct comprehensive testing of mass-produced satellites.

[0059] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: responding to a determination based on a first evaluation result that the structural state of the sampled satellite is abnormal, and identifying the sampled satellite as a non-conforming satellite product.

[0060] For example, when a satellite exhibits significant differences in its characteristic level curves and transfer function curves before and after a test—such as a significant shift in the resonance peak frequency, a significant increase or decrease in the peak response amplitude, or an unexpected change in the curve shape—it can be determined that the satellite's structural state is abnormal. Specifically, during vibration testing, if the satellite's structure is damaged or its internal components are displaced, causing changes in its dynamic characteristics, this will be directly reflected in the characteristic level curves and transfer function curves. If, after a high-order sinusoidal vibration test, the resonance frequency of a satellite shifts significantly compared to the frequency before the test, it may mean that some components or connection points in the satellite structure have suffered irreversible damage during the test, or that their inherent characteristics have changed, thus affecting the overall structural performance of the satellite. Similarly, if the peak response amplitude increases or decreases significantly after the test, it may also indicate a change in the strength or stiffness of the satellite structure. Furthermore, unexpected changes in the curve shape, such as the appearance of new resonance peaks or changes in the shape of existing resonance peaks, may also indicate nonlinear responses or damage states of the satellite's internal structure or components. Once any of the above anomalies are found, the structural state of the satellite can be determined to be abnormal, thus identifying the satellite as a non-conforming satellite product.

[0061] Based on the above optional embodiments, when the structural condition of the sampled satellite is determined to be abnormal based on the first evaluation result, the sampled satellite is identified as a non-conforming satellite product. This can identify problems with the structural integrity or vibration resistance of the sampled satellite, avoiding subsequent more time-consuming testing processes. Simultaneously, it also helps to adjust the manufacturing process in a timely manner, preventing potential design or manufacturing defects from continuously affecting subsequent satellite production, thereby improving production efficiency and reducing overall costs.

[0062] Optionally, the satellite sampling method in this embodiment of the invention further includes:

[0063] Step S21: Based on the second evaluation result, if the sampled satellite does not meet the first requirement, the design margin of the stacked structure of multiple satellites is evaluated using the first modified test model to obtain the third evaluation result.

[0064] Step S22: Based on the third evaluation result, the stacking structure is determined to meet the second requirement, and the sampled satellite is determined to be a qualified satellite product. The second requirement is the design margin requirement.

[0065] Specifically, if the second evaluation results show that the sampled satellite fails to meet the first requirement, i.e., it fails to meet the consistency requirement of satellite mechanical performance, it indicates that some mechanical performance parameters of the sampled satellite deviate significantly from the performance parameters of the previously established qualified satellites. In this case, to further verify the structural reliability and safety of the sampled satellite in a stacked state, a first modified test model can be used to evaluate the design margin of the stacked structure of multiple satellites to determine whether the sampled satellite can withstand the expected mechanical loads in an actual stacked launch environment without structural failure.

[0066] The aforementioned first revised experimental model refers to the finite element model that has undergone iterative revision. Specifically, the first revised experimental model is the result of revision and optimization based on the finite element model of a single satellite, combined with mechanical test data from multiple satellite stacks. During the revision process, factors such as the influence of the interaction forces between satellites during satellite stacking, small changes in actual material properties, and minor errors in processing and manufacturing can be taken into account, thereby making the model closer to the mechanical behavior of a real satellite stack structure.

[0067] The aforementioned design margin assessment refers to the evaluation of the structural strength and stiffness safety margin of a stacked structure of multiple satellites under specific load conditions, after the establishment of the first revised experimental model. Design margin refers to the portion exceeding the required load-bearing capacity reserved during the design phase to ensure structural safety. Through design margin assessment, the maximum mechanical load that satellites can withstand during stacked launch can be determined, thus providing safety assurance for mass production and rapid launch of satellites. During the design margin assessment process, a series of preset mechanical loads (such as vibration and impact during launch) can be applied, and simulation calculations can be used to determine whether the actual response of the stacked structure of multiple satellites is within the expected safety range.

[0068] If the design margin assessment shows that the stacked structure of multiple satellites can meet the second requirement, that is, to ensure that the satellite structure still has sufficient safety margin even under extreme conditions, even if the initially sampled satellite has deviations in individual mechanical performance indicators, the structural design of the sampled satellite in the stacked state can be considered reliable, and therefore the sampled satellite can be determined to be a qualified satellite product.

[0069] Based on steps S21 and S22 above, when the second evaluation result determines that the sampled satellite does not meet the consistency requirements of satellite mechanical performance, a first modified test model is used to evaluate the design margin of the stacked structure of multiple satellites, resulting in a third evaluation result. If the third evaluation result determines that the stacked structure meets the design margin requirements, the sampled satellite is determined to be a qualified satellite product, further verifying the reliability and safety of the satellite structure in the stacked state. If the third evaluation result shows that the stacked structure of multiple satellites meets the design margin requirements, it indicates that while the mechanical performance of individual satellites may have slight differences, the overall structural design in the stacked state still has sufficient margin to withstand the mechanical environment during launch without damage. Therefore, determining that the sampled satellite is a qualified satellite product ensures that even with a certain degree of performance fluctuation in batch-produced satellites, the entire satellite stacking launch scheme remains highly feasible and safe. This allows for optimization of the test process while ensuring launch success rate, reducing unnecessary full-stack tests, and ultimately lowering test costs and time.

[0070] Optionally, the satellite sampling method in this embodiment of the invention further includes:

[0071] Based on the results of the third assessment, the stacking structure was determined to be non-compliant with the second requirement, and the sampled satellite was identified as a non-compliant satellite product.

[0072] For example, when the stacking structure of multiple satellites is determined to fail to meet design margin requirements based on the results of a third assessment, the sampled satellites can be identified as non-conforming satellite products. For non-conforming satellite products, further inspection and correction can be carried out, including design modifications, material replacements, or structural reinforcement, to ensure that all satellites meet the mechanical consistency performance requirements and design margin standards.

[0073] Based on the above optional embodiments, when the stacked structure is determined not to meet the design margin requirements based on the third evaluation results, the sampled satellite is identified as a non-conforming satellite product. This can promptly identify satellite products with insufficient structural strength or stiffness in the stacked state, thereby avoiding potential launch accidents.

[0074] Optionally, in step S13, the mechanical performance of the sampled satellites is evaluated using an evaluation model, and the second evaluation result includes:

[0075] Step S131: The evaluation model is used to perform resonant frequency offset comparison, peak response offset comparison and / or response curve coherence analysis on the sampled satellites to obtain the second evaluation result.

[0076] Among them, the resonant frequency offset comparison is used to determine whether the natural frequencies of different satellites are consistent at the same measuring point; the peak response offset comparison is used to determine whether the structural strength and stiffness of each satellite are consistent by comparing the maximum acceleration response of different satellites at the same measuring point; and the coherence analysis of the response curve is used to determine the degree of consistency between different satellites in vibration transmission characteristics and structural integrity characteristics.

[0077] Specifically, the resonant frequency offset comparison is mainly used to check whether the natural frequencies of different satellites are consistent at the same measurement point. A natural frequency is the frequency at which a satellite structure vibrates freely without external excitation. For stacked satellites, the consistency of natural frequencies reflects the similarity of the structural design between satellites; that is, the vibration response of satellites under the same excitation should be similar in frequency. By using natural frequencies, the structural consistency of satellites can be assessed, thereby determining whether there are design or manufacturing deviations.

[0078] Peak response offset comparison is used to assess whether the maximum acceleration response of different satellites is consistent at the same measurement point. Peak acceleration response reflects the maximum force a satellite experiences during vibration testing. If the peak responses of multiple satellites differ significantly, it indicates a significant difference in the structural strength or stiffness of the satellites, which could reduce the safety of the satellites during launch and the stability after stacking.

[0079] Coherence analysis of response curves is used to assess the degree of consistency in vibration transmission characteristics and structural integrity among different satellites. Coherence analysis is a statistical method used to measure the linear correlation between two signals. In satellite mechanical testing, coherence analysis of response curves can determine whether the vibration responses of different satellites exhibit similar patterns, thus indirectly reflecting the consistency and integrity of the satellite structure. Higher coherence indicates a closer relationship between the signals and better structural consistency among satellites.

[0080] Based on the above optional embodiments, the evaluation model is used to quantitatively assess the dynamic response characteristics of different satellites at the same measurement point. This can promptly identify and eliminate potential manufacturing defects or structural variations, ensuring the reliability and safety of the satellite during launch and operation, while reducing overall testing costs and time.

[0081] Optionally, in step S131, the coherence analysis of the response curves of the sampled satellites includes:

[0082] Step S1311: Obtain the autospectrum of a single satellite;

[0083] Step S1312: Obtain the cross spectrum of mechanical performance parameters of different satellites at the same measurement point in the same direction;

[0084] Step S1313: Based on the self-spectrum and cross-spectrum, obtain multiple coherence coefficients between different satellites. These multiple coherence coefficients are used to evaluate the consistency of satellite mechanical behavior from multiple dimensions.

[0085] Step S1314: Evaluate the mechanical performance of the sampled satellites based on multiple coherence coefficients.

[0086] The self-spectrum of a single satellite refers to the energy distribution of the acceleration response at different frequencies of a specific measurement point (e.g., measurement point n) of satellite m over time. For measurement point n of satellite m, the spectrum of its acceleration response signal can be obtained by performing a Fourier transform, and then the self-spectrum of the single satellite can be calculated. For example, the self-spectrum of the single satellite can be expressed as:

[0087]

[0088] in, This represents the autospectral of the acceleration response of measuring point n on satellite m in the X direction. This represents the response of satellite m at measurement point n in the X direction.

[0089] The cross-spectrum described above is used to analyze the relationship between the vibration responses of different satellites at the same measuring point and in the same direction. For example, the cross-spectrum can be expressed as:

[0090]

[0091] in, This represents the cross spectrum of measurement point n of satellites m and p in the X direction.

[0092] The aforementioned coherence coefficients include a first coherence coefficient, a second coherence coefficient, and a third coherence coefficient.

[0093] Specifically, the first coherence coefficient is used to reflect the linear relationship between the vibration responses of two different satellites at the same measuring point and direction. The closer the first coherence coefficient is to 1, the more similar the mechanical behavior of the two satellites at that measuring point and direction, and the higher the consistency in the structural design and manufacturing process. For example, the first coherence coefficient can be expressed as:

[0094]

[0095] in, This represents the correlation coefficient of satellite n with respect to satellite 1 in the X direction at measurement point 1, i.e., the first coherence coefficient.

[0096] Specifically, similar to the first coherence coefficient, the closer the second coherence coefficient between different satellites is to 1, the higher the consistency. For example, the aforementioned second coherence coefficient can be expressed as:

[0097]

[0098] in, This represents the correlation coefficient of measurement point 1 in the X direction relative to satellite 1 and satellite n, i.e., the second coherence function.

[0099] Specifically, the third coherence coefficient is used to represent the overall correlation of the vibration response of satellite n with all other previously tested satellites (satellite 1 to satellite (n-1)) at the same measurement point and in the same direction. For example, the above third coherence coefficient can be expressed as:

[0100]

[0101] in, This represents the correlation coefficient of satellite n with respect to satellite 1~(n-1) in the X direction at measurement point 1, which is the third coherence function.

[0102] Based on steps S1311 to S1314 above, multiple coherence coefficients between different satellites are obtained based on the autospectrum and cross-spectrum. Then, the mechanical performance of the sampled satellites is evaluated based on these multiple coherence coefficients. This allows for precise quantification and analysis of the consistency of mechanical behavior among different satellites under vibration environments from multiple dimensions. By using coherence coefficients, it is possible to more meticulously identify and evaluate whether the mechanical performance of a single satellite is abnormal or deviating compared to other satellites in the stack group. This provides a scientific basis for the rapid and accurate screening of batch-produced satellites, thereby avoiding full-sample mechanical testing of all satellites, thus improving testing efficiency and reducing testing costs.

[0103] Optionally, the satellite sampling method in this embodiment of the invention further includes:

[0104] Step S31: Under a preset test environment, acquire second test data from multiple satellites;

[0105] Step S32: Based on the second experimental data and the second modified experimental model, the first initial experimental model is modified to obtain the first modified experimental model.

[0106] The aforementioned second test data refers to the response data generated when multiple satellites are subjected to mechanical tests under a preset test environment. Unlike the first test data, the second test data includes not only the response data of a single satellite, but also the response data of multiple satellites in a stacked state, which is used to evaluate the mechanical behavior and structural state of multiple satellites under actual launch configuration.

[0107] For example, the second experimental data mentioned above can be sinusoidal vibration experimental data of multi-star stacks. The second modified experimental model can be obtained by modifying the single-star finite element model.

[0108] Figure 2 This is a schematic diagram of a first initial experimental model according to one embodiment of the present invention. The first initial experimental model can be created based on finite element analysis of multiple satellites to predict the structural response of multiple satellites under specific mechanical conditions. However, due to the influence of satellite stacking on structural dynamic performance and minor variations in the manufacturing process, the first initial experimental model may not accurately reflect the actual mechanical behavior of multiple satellites stacked. Therefore, parameters in the first initial experimental model, such as material properties, connection details, and mass distribution, can be adjusted based on second experimental data and a second modified experimental model to make it closer to the mechanical behavior of actual stacked satellites.

[0109] Based on steps S31 to S32 above, by using the second experimental data and the second revised experimental model, the first initial experimental model is revised, and the resulting first revised experimental model can more accurately simulate and predict the mechanical performance of multiple satellites under actual launch configuration.

[0110] Optionally, the satellite sampling method in this embodiment of the invention further includes:

[0111] Step S41: Under a preset test environment, acquire the third test data of a single satellite;

[0112] Step S42: Based on the third experimental data, the second initial experimental model is modified to obtain the second modified experimental model.

[0113] The aforementioned third test data refers to the data collected from mechanical tests on a single satellite under a preset test environment, including but not limited to acceleration response data, displacement response data, and stress response data of a single satellite during vibration tests. These data are used to analyze the performance and changes of a single satellite structure under vibration conditions in order to assess the integrity and reliability of the single satellite structure.

[0114] Figure 3 This is a schematic diagram of a second initial experimental model according to one embodiment of the present invention. The second initial experimental model refers to a single-satellite finite element simulation model established in the early stage of satellite design based on theoretical assumptions and known parameters.

[0115] For example, after collecting the third experimental data, the deviations between the third experimental data and the second initial experimental model can be compared and analyzed. Based on the third experimental data, necessary adjustments and corrections can be made to the second initial experimental model to improve its reliability. The corrected model is the second corrected experimental model, which can more accurately reflect the true mechanical behavior of a single satellite.

[0116] Based on steps S41 to S42 above, by using the third test data of a single satellite to correct the second initial test model, it can be ensured that the simulation analysis results are closer to the actual satellite performance, thereby improving the accuracy of satellite mechanical performance evaluation, optimizing satellite design, reducing the number of subsequent tests, and lowering development costs.

[0117] Optionally, the satellite sampling inspection method in this embodiment of the invention further includes: in response to the sampled satellite being a qualified satellite product, updating the model parameters of the evaluation model based on the first test data to obtain an updated evaluation model.

[0118] Specifically, when a sampled satellite is found to be a qualified satellite product, the model parameters of the evaluation model are updated based on the first test data. This can be understood as using the mechanical test data of the qualified satellite product to optimize and calibrate the evaluation model in order to improve its accuracy in assessing the mechanical performance of subsequent satellites.

[0119] For example, by comparing the first experimental data with the expected performance indicators in the evaluation model, the structural state of a satellite performing well and its specific mechanical performance parameters can be identified. Furthermore, these mechanical performance parameters can be used to verify and correct the expected performance indicators in the evaluation model, thereby continuously iteratively optimizing the evaluation model.

[0120] Based on the above optional embodiments, by accumulating test data from qualified satellite products, the evaluation model's ability to consistently assess the structural characteristics and mechanical performance of satellites can be enhanced. Simultaneously, continuous improvement of the evaluation model helps to identify manufacturing or assembly variations that may affect structural consistency in advance, allowing for timely adjustments to the process and ensuring that the entire batch of satellites meets the mechanical performance requirements.

[0121] Optionally, the satellite sampling method in this embodiment of the invention further includes:

[0122] Step S51: Under a preset test environment, mechanical tests are conducted on multiple satellites in multiple different directions to obtain the mechanical performance parameters of multiple satellites at different positions, thus obtaining the fourth test data;

[0123] Step S52: Perform feature-level experimental data comparison on the fourth experimental data to obtain the comparison results;

[0124] Step S53: In response to the comparison results indicating that the feature-level experimental data are well matched, a basic database is constructed based on the fourth experimental data; and in response to the comparison results indicating that the feature-level experimental data are abnormally matched, the fourth experimental data is removed. The basic database provides data support for the evaluation model.

[0125] For example, under a preset test environment, mechanical performance parameters of multiple satellites at different positions can be obtained by conducting mechanical tests on multiple satellites in three axes (i.e., the pitch, yaw, and roll directions of the satellites), thus obtaining a fourth set of test data. Specifically, the aforementioned multiple satellites include at least three satellites.

[0126] Specifically, the purpose of comparing the acquired fourth test data with the characteristic-level test data is to check whether different satellites exhibit similar mechanical properties under the same mechanical test conditions.

[0127] For example, comparison results can be obtained by comparing multiple indicators such as resonant frequency, peak response, and coherence of response curves in the fourth experimental data. If the comparison results show good data consistency, it can be determined that the multiple satellites tested exhibited similar mechanical performance under the same experimental conditions. In this case, a basic database can be constructed based on the fourth experimental data to provide data support for the evaluation model. Conversely, if the comparison results show anomalies in the characteristic-level experimental data comparison, i.e., significant performance differences exist, the fourth experimental data needs to be removed to ensure the accuracy and reliability of the basic database.

[0128] Based on steps S51 to S53 above, by comparing and screening feature-level experimental data, it can be ensured that the establishment of the basic database is based on satellite data with consistent performance, thereby providing accurate and reliable data support for the evaluation model.

[0129] Figure 4 This is a schematic diagram of a satellite sampling method according to one embodiment of the present invention, as shown below. Figure 4 As shown, in the satellite sampling inspection process, the first step is to select satellites for inspection and conduct sinusoidal vibration tests on them, followed by a comparison of their characteristic levels. If the measurement point curves show good comparison, the satellite can be determined to be a qualified satellite, and further judgment can be made based on the single-satellite experimental data evaluation model. Conversely, if there are anomalies in the measurement point curve comparison, the satellite can be determined to be unqualified. The single-satellite experimental data evaluation model can be obtained by conducting sinusoidal vibration tests on a single satellite in three directions, comparing the single-satellite characteristic level test data, and finally conducting sinusoidal vibration tests on multiple single satellites. When further judging based on the single-satellite experimental data evaluation model, if the data of the sampled satellite compares well with the evaluation model, the satellite can be determined to be a qualified satellite. Otherwise, a multi-satellite stacking design margin analysis is required. If the multi-satellite stacking margin analysis results are within the design margin, the satellite can be determined to be a qualified satellite, and the sampled satellite data can then be incorporated into the evaluation model to improve it.

[0130] Through the above description of the embodiments, those skilled in the art can clearly understand that the methods according to the above embodiments can be implemented by means of software plus necessary general-purpose hardware platforms. Of course, they can also be implemented by hardware, but in many cases the former is a better implementation method. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, can be embodied in the form of a software product. This computer software product is stored in a storage medium (such as ROM / RAM, magnetic disk, optical disk) and includes several instructions to cause a terminal device (which may be a mobile phone, computer, server, or network device, etc.) to execute the methods described in the various embodiments of the present invention.

[0131] This invention also provides a satellite sampling inspection device for implementing the above embodiments and preferred embodiments; details already described will not be repeated. As used below, the term "module" can refer to a combination of software and / or hardware that performs a predetermined function. Although the device described in the following embodiments is preferably implemented in software, hardware implementation, or a combination of software and hardware, is also possible and contemplated.

[0132] Figure 5 This is a structural block diagram of a satellite sampling device according to one embodiment of the present invention, such as... Figure 5 As shown, the device includes:

[0133] The first acquisition module 501 is used to acquire the first test data of the sampled satellite under a preset test environment, wherein the preset test environment is used to simulate the vibration environment during the satellite launch process;

[0134] The first evaluation module 502 is used to evaluate the structural status of the sampled satellites based on the first test data and obtain the first evaluation result;

[0135] The second evaluation module 503 is used to respond to the first evaluation result, which determines that the structural condition of the sampled satellite is good. It then uses an evaluation model to evaluate the mechanical performance of the sampled satellite and obtains the second evaluation result.

[0136] The first determining module 504 is used to respond to the determination that the sampled satellite meets the first requirement based on the second evaluation result, and to determine that the sampled satellite is a qualified satellite product, wherein the first requirement is the consistency requirement of the satellite's mechanical performance.

[0137] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: a second determining module 505, used to determine that the sampled satellite is a non-conforming satellite product in response to a determination based on the first evaluation result that the structural state of the sampled satellite is abnormal.

[0138] Optionally, the satellite sampling device in this embodiment of the invention further includes:

[0139] The third evaluation module 506 is used to respond to the second evaluation result that the sampled satellites do not meet the first requirement, and to use the first modified test model to evaluate the design margin of the stacked structure of multiple satellites to obtain the third evaluation result.

[0140] The third determination module 507 is used to respond to the determination that the stacking structure meets the second requirement based on the third evaluation result, and to determine that the sampled satellite is a qualified satellite product, wherein the second requirement is the design margin requirement.

[0141] Optionally, the satellite sampling device in this embodiment of the invention further includes:

[0142] The fourth determination module 508 is used to respond to the judgment based on the third evaluation result that the stacking structure does not meet the second requirement and to determine that the sampled satellite is a non-conforming satellite product.

[0143] Optionally, the second evaluation module 503 is further configured to: use an evaluation model to perform resonant frequency offset comparison, peak response offset comparison, and / or response curve coherence analysis on the sampled satellites to obtain a second evaluation result; wherein, the resonant frequency offset comparison is used to determine whether the natural frequencies of different satellites are consistent at the same measuring point, the peak response offset comparison is used to determine whether the structural strength and stiffness of each satellite are consistent by comparing the maximum acceleration responses of different satellites at the same measuring point, and the response curve coherence analysis is used to determine the degree of consistency between different satellites in vibration transmission characteristics and structural integrity characteristics.

[0144] Optionally, the second evaluation module 503 is also used to: obtain the autospectrum of a single satellite; obtain the cross-spectrum of the mechanical performance parameters of different satellites at the same measurement point; obtain multiple coherence coefficients between different satellites based on the autospectrum and cross-spectrum, wherein the multiple coherence coefficients are used to evaluate the consistency of the satellite's mechanical behavior from multiple dimensions; and evaluate the mechanical performance of the sampled satellites based on the multiple coherence coefficients.

[0145] Optionally, the satellite sampling device in this embodiment of the invention further includes:

[0146] The second acquisition module 509 is used to acquire second test data from multiple satellites under a preset test environment;

[0147] The first correction module 510 is used to correct the first initial test model based on the second test data and the second corrected test model to obtain the first corrected test model.

[0148] Optionally, the satellite sampling device in this embodiment of the invention further includes:

[0149] The third acquisition module 511 is used to acquire third test data of a single satellite under a preset test environment;

[0150] The second correction module 512 is used to correct the second initial test model based on the third test data to obtain the second corrected test model.

[0151] Optionally, the satellite sampling inspection device in this embodiment of the invention further includes: an update module 513, used to update the model parameters of the evaluation model based on the first test data in response to the sampled satellite being a qualified satellite product, so as to obtain an updated evaluation model.

[0152] Optionally, the satellite sampling device in this embodiment of the invention further includes:

[0153] The fourth acquisition module 514 is used to acquire the mechanical performance parameters of multiple satellites at different positions by conducting mechanical tests on multiple satellites in multiple different directions under a preset test environment, and obtain the fourth test data.

[0154] The comparison module 515 is used to perform feature-level experimental data comparison on the fourth experimental data to obtain the comparison results;

[0155] The processing module 516 is used to construct a basic database based on the fourth experimental data in response to the comparison result indicating that the feature-level experimental data is well matched; and to remove the fourth experimental data in response to the comparison result indicating that the feature-level experimental data is abnormally matched. The basic database provides data support for the evaluation model.

[0156] It should be noted that the above modules can be implemented by software or hardware. For the latter, they can be implemented in the following ways, but are not limited to: all the above modules are located in the same processor; or, the above modules are located in different processors in any combination.

[0157] According to another aspect of the present invention, a satellite sampling inspection device is also provided, comprising: a memory storing an executable program; and a processor for running the program, wherein the program executes the satellite sampling inspection method of the present invention during runtime.

[0158] According to another aspect of the present invention, a computer-readable storage medium is also provided, the computer-readable storage medium including a stored executable program, wherein, when the executable program is executed, it controls the device where the storage medium is located to execute the satellite sampling method of the present invention.

[0159] Optionally, in this embodiment, the storage medium may be configured to store a computer program for performing the following steps:

[0160] Step S11: Under a preset test environment, acquire the first test data of the sampled satellites, wherein the preset test environment is used to simulate the vibration environment during satellite launch;

[0161] Step S12: Evaluate the structural status of the sampled satellites based on the first test data to obtain the first evaluation result;

[0162] Step S13: Based on the first evaluation result, the structural condition of the sampled satellite is determined to be good. The evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain the second evaluation result.

[0163] Step S14: Based on the second evaluation result, the sampled satellite is determined to meet the first requirement and is identified as a qualified satellite product. The first requirement is the consistency requirement of the satellite's mechanical performance.

[0164] Optionally, in this embodiment, the storage medium may include, but is not limited to, various media capable of storing computer programs, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0165] According to another aspect of the present invention, a computer program product is also provided, including a computer program that, when executed by a processor, implements the satellite sampling method of the present invention.

[0166] Optionally, in this embodiment, the above-mentioned computer program product can be configured as a computer program that performs the following steps:

[0167] Step S11: Under a preset test environment, acquire the first test data of the sampled satellites, wherein the preset test environment is used to simulate the vibration environment during satellite launch;

[0168] Step S12: Evaluate the structural status of the sampled satellites based on the first test data to obtain the first evaluation result;

[0169] Step S13: Based on the first evaluation result, the structural condition of the sampled satellite is determined to be good. The evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain the second evaluation result.

[0170] Step S14: Based on the second evaluation result, the sampled satellite is determined to meet the first requirement and is identified as a qualified satellite product. The first requirement is the consistency requirement of the satellite's mechanical performance.

[0171] According to another aspect of the present invention, a chip system is also provided, comprising: a processor for calling and running a computer program from a memory, such that a communication device equipped with the chip system performs the satellite sampling method of the present invention.

[0172] Optionally, in this embodiment, the processor can be configured to perform the following steps via a computer program:

[0173] Step S11: Under a preset test environment, acquire the first test data of the sampled satellites, wherein the preset test environment is used to simulate the vibration environment during satellite launch;

[0174] Step S12: Evaluate the structural status of the sampled satellites based on the first test data to obtain the first evaluation result;

[0175] Step S13: Based on the first evaluation result, the structural condition of the sampled satellite is determined to be good. The evaluation model is used to evaluate the mechanical performance of the sampled satellite to obtain the second evaluation result.

[0176] Step S14: Based on the second evaluation result, the sampled satellite is determined to meet the first requirement and is identified as a qualified satellite product. The first requirement is the consistency requirement of the satellite's mechanical performance.

[0177] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0178] In the above embodiments of the present invention, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0179] In the several embodiments provided by this invention, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units can be a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual coupling, direct coupling, or communication connection can be through some interfaces; the indirect coupling or communication connection of units or modules can be electrical or other forms.

[0180] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0181] Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0182] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0183] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A satellite sampling inspection method, characterized in that, include: Under a preset test environment, the first test data of the sampled satellites are obtained, wherein the preset test environment is used to simulate the vibration environment during the satellite launch process; The structural status of the sampled satellites is evaluated based on the first test data to obtain a first evaluation result; Based on the first evaluation result, the system determines that the structural condition of the sampled satellite is good, and uses an evaluation model to evaluate the mechanical performance of the sampled satellite to obtain a second evaluation result. The response determines that the sampled satellite meets the first requirement based on the second evaluation result, and identifies the sampled satellite as a qualified satellite product, wherein the first requirement is the consistency requirement of the satellite's mechanical performance.

2. The satellite sampling inspection method according to claim 1, characterized in that, The satellite sampling method also includes: Based on the first evaluation result, the system determines that the structural state of the sampled satellite is abnormal and identifies the sampled satellite as a non-conforming satellite product.

3. The satellite sampling inspection method according to claim 1, characterized in that, The satellite sampling method also includes: Based on the second evaluation result, if the sampled satellite does not meet the first requirement, the first modified test model is used to evaluate the design margin of the stacked structure of multiple satellites to obtain the third evaluation result. Based on the third evaluation result, the response determines that the stacking structure meets the second requirement and identifies the sampled satellite as a qualified satellite product, wherein the second requirement is a design margin requirement.

4. The satellite sampling inspection method according to claim 3, characterized in that, The satellite sampling method also includes: Based on the third evaluation result, the response determines that the stacking structure does not meet the second requirement, and identifies the sampled satellite as a non-conforming satellite product.

5. The satellite sampling inspection method according to claim 3, characterized in that, The mechanical performance of the sampled satellites was evaluated using the evaluation model described above, and the second evaluation results obtained include: The evaluation model is used to perform resonance frequency offset comparison, peak response offset comparison, and / or response curve coherence analysis on the sampled satellites to obtain the second evaluation result; The resonant frequency offset comparison is used to determine whether the natural frequencies of different satellites are consistent at the same measuring point. The peak response offset comparison is used to determine whether the structural strength and stiffness of each satellite are consistent by comparing the maximum acceleration response of different satellites at the same measuring point. The coherence analysis of the response curve is used to determine the degree of consistency between different satellites in vibration transmission characteristics and structural integrity characteristics.

6. The satellite sampling inspection method according to claim 5, characterized in that, The coherence analysis of the response curves of the sampled satellites includes: Obtain the autospectrum of a single satellite; Obtain the cross spectrum of mechanical performance parameters of different satellites at the same measurement point in the same direction; Based on the self-spectrum and the cross-spectrum, multiple coherence coefficients are obtained between different satellites, wherein the multiple coherence coefficients are used to evaluate the consistency of satellite mechanical behavior from multiple dimensions; The mechanical performance of the sampled satellites is evaluated based on the multiple coherence coefficients.

7. The satellite sampling inspection method according to claim 3, characterized in that, The satellite sampling method also includes: Under the preset test environment, second test data of the multiple satellites are acquired; Based on the second experimental data and the second revised experimental model, the first initial experimental model is revised to obtain the first revised experimental model.

8. The satellite sampling inspection method according to claim 7, characterized in that, The satellite sampling method also includes: Under the preset test environment, third test data for a single satellite is acquired; The second initial experimental model is modified based on the third experimental data to obtain the second modified experimental model.

9. The satellite sampling inspection method according to claim 7, characterized in that, The satellite sampling method also includes: In response to the fact that the sampled satellite is a qualified satellite product, the model parameters of the evaluation model are updated based on the first test data to obtain an updated evaluation model.

10. The satellite sampling inspection method according to claim 1, characterized in that, The satellite sampling method also includes: Under the preset test environment, mechanical tests are conducted on multiple satellites in multiple different directions to obtain the mechanical performance parameters of the multiple satellites at different positions, thus obtaining the fourth test data; The fourth set of experimental data was compared with the feature-level experimental data to obtain the comparison results; In response to the comparison result indicating that the feature-level experimental data comparison is good, a basic database is constructed based on the fourth experimental data; and in response to the comparison result indicating that the feature-level experimental data comparison is abnormal, the fourth experimental data is removed, wherein the basic database provides data support for the evaluation model.

11. A satellite sampling inspection device, characterized in that, include: Memory, which stores executable programs; A processor for running the program, wherein the program executes the satellite sampling method according to any one of claims 1 to 10 when it runs.

12. A computer-readable storage medium, characterized in that, The computer-readable storage medium includes a stored executable program, wherein, when the executable program is executed, it controls the device on which the storage medium is located to perform the satellite sampling method according to any one of claims 1 to 10.

13. A computer program product, characterized in that, It includes a computer program that, when executed by a processor, implements the satellite sampling method according to any one of claims 1 to 10.

14. A chip system, characterized in that, include: A processor for retrieving and running a computer program from memory, causing a communication device equipped with the chip system to perform the satellite sampling method as described in any one of claims 1 to 10.

Images