CN109000868B - Method for formulating concave condition of spacecraft sinusoidal vibration test - Google Patents
Method for formulating concave condition of spacecraft sinusoidal vibration test Download PDFInfo
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Abstract
The invention discloses a method for formulating a concave condition of a spacecraft sinusoidal vibration test, which is a programming method for formulating the concave condition of the spacecraft sinusoidal vibration test with rigor and accuracy. The method comprises the following steps: before the test, determining and summarizing all the measuring points to be analyzed, directions and amplitude limiting conditions of corresponding measuring point channels of the spacecraft; on a test site, obtaining a characteristic-level frequency sweep test result, and linearly calculating to obtain a theoretical response curve of a specified large-scale sinusoidal vibration test; comparing theoretical response curves of a large-scale sinusoidal vibration test with amplitude limiting conditions of channels of corresponding measuring points one by one, finding all frequency points needing to be recessed, and storing lower recessed magnitude values of all frequency points and corresponding channel names; the analysis and comparison are completed for all the measuring point channels, and finally a concave condition prediction curve is obtained; and (3) comprehensively considering nonlinear factors, and making a concave condition for controlling the sinusoidal vibration test of the spacecraft between the response envelope curve of the rocket interface and the concave condition prediction curve.
Description
Technical Field
The invention relates to the technical field of spacecrafts, in particular to a method for formulating a concave condition in a spacecraft sinusoidal vibration test.
Background
The spacecraft is required to perform a sinusoidal vibration test in each development stage so as to check the rigidity and strength design of the structure and obtain the response data of a measuring point channel on the spacecraft. In the test, because the resonance frequency of the spacecraft is generally in the test frequency range, the test condition is usually required to be recessed to avoid overlarge response. The on-site establishment of the concave condition is a tedious and time-consuming process, generally, characteristic-level frequency sweep test results are judged and read one by one manually so as to determine the maximum response which possibly occurs in measuring point channels at the positions during large-magnitude (a large number of levels refer to identification level, acceptance level or standard identification level) tests and determine the concave condition according to the principle that the maximum response does not exceed the upper limit of the bearing capacity of the structure or the single-machine equipment, and meanwhile, the carrier rocket side requires that the concave condition is not lower than the coupling analysis result of the spacecraft and the carrier rocket.
The dip control criteria for the spacecraft sinusoidal vibration test are generally three as follows:
criterion one is as follows: in a sinusoidal vibration test of the spacecraft, the stress of a main structure of the spacecraft is not greater than the stress under static load, namely the maximum strain response is not greater than the maximum strain value of the main structure of the spacecraft in the static test; the criterion one indicates that the formulation of the dip condition should ensure that the structure of the spacecraft cannot be over-tested.
Criterion two: acceleration response at the installation position of the key single-machine equipment on the spacecraft does not exceed component-level sinusoidal vibration test conditions specified by environmental test specifications; the second criterion indicates that the formulation of the concave condition should ensure that the key single-machine equipment of the spacecraft cannot be over-tested.
Criterion three: the input vibration value of the whole spacecraft after the sinking is not lower than the response value of the rocket interface in the coupling analysis result of the rocket, and the spacecraft has enough safety margin which can meet the requirement of a carrier rocket; the criterion three indicates that the formulation of the dip condition cannot be undertested.
In specific implementation, the first criterion is taken as an upper limit, the third criterion is taken as a lower limit, then the second criterion is considered, values are reasonably taken in the middle area, and finally, concave conditions which can be accepted by all parties are worked out, so that the test is ensured not to be overloaded or underloaded.
The whole process relates to interpretation, calculation, estimation and analysis of a large amount of test data, the previous process is completed only by manpower, the workload is huge, the phenomena of overtime and waiting of personnel at each department of a test field test team are caused, the conditions of overnight dadan and fatigue operation often occur, and the method is particularly suitable for large-scale spacecrafts which concern a large number of measuring point channels; in the conventional method, a plurality of maximum response points are usually compared, full-band comparison cannot be achieved, secondary large response, local response and the like are easily omitted, determination of the concerned part or the single-machine equipment depends on some artificial subjective judgment or experience factors, and the measurement point channel, the non-maximum response frequency point and the like which are not determined as the concerned part or the single-machine equipment are selectively ignored.
Therefore, the two previous criteria are difficult to meet strictly, the method has large workload and is easy to omit, great risk hidden danger is brought to the test, and the quality problems of damage of structures or single equipment caused by over-test and the like in some spacecraft sinusoidal vibration tests are just caused by the defects and disadvantages of the method.
Disclosure of Invention
In view of the above, the invention provides a method for formulating the concave-down condition of the spacecraft sinusoidal vibration test, which overcomes the defects of the conventional method, is a strict and accurate programming method for formulating the concave-down condition of the spacecraft sinusoidal vibration test, and greatly improves the intuitiveness of the process for formulating the concave-down condition of the spacecraft sinusoidal vibration test and the accuracy and credibility of the formulated result.
In order to achieve the purpose, the technical scheme of the invention is as follows: a concave-down condition making method for a spacecraft sinusoidal vibration test is characterized in that a concave-down condition making method utilizes a concave-down condition prediction curve to complete concave-down condition making.
The method for formulating the concave condition comprises the following steps:
step (1) -before the sinusoidal vibration test, determining and summarizing all the measuring points to be analyzed in the spacecraft, the directions and the amplitude limiting conditions of corresponding measuring point channels, and compiling into a test input file.
The stations to be analyzed include: and strain response measuring points and acceleration response measuring points on the spacecraft.
Each measuring point has 1-3 directions, and each direction corresponds to 1 measuring point channel.
And if the measuring point to be analyzed is a strain response measuring point, the amplitude limiting condition of the measuring point channel is the maximum strain value of the strain response measuring point in the static test.
And if the measuring point to be analyzed is an acceleration response measuring point, the amplitude limiting condition of the measuring point channel is a component-level sinusoidal vibration test condition specified by the corresponding environment test specification of the acceleration response measuring point.
Step (2), executing a characteristic-level frequency sweep test on a spacecraft sinusoidal vibration test site to obtain a characteristic-level frequency sweep test result; obtaining a theoretical response curve of a specified large-scale sinusoidal vibration test by linear calculation according to the characteristic-scale frequency sweep test result; the large magnitude is acceptance level, quasi-identification level or identification level.
Step (3), reading a test input file, and comparing theoretical response curves of a large-scale sinusoidal vibration test with specified measuring points and specified directions with amplitude limiting conditions of channels of corresponding measuring points one by one; if the value in the theoretical response curve is larger than the amplitude limiting condition at one frequency point, marking the frequency point as a concave frequency point, and estimating the concave value of the concave frequency point through linear calculation; storing the concave magnitude of the concave frequency point and the corresponding measuring point channel name; the lower concave value enables a theoretical response value obtained through linear calculation to be equal to the amplitude limiting condition at the lower concave frequency point when the spacecraft inputs the lower concave value at the lower concave frequency point.
Step (4) -executing step (3) aiming at all measuring point channels in the test input file; if the same concave frequency point has a plurality of concave values, the concave frequency point only keeps the minimum value of the concave values and the corresponding measuring point channel name; if there is no concave value at a frequency point, setting the frequency point as an original value; the original value is the original test condition of a large-scale sine vibration test; and drawing the concave quantity value or the original quantity value corresponding to each frequency point into a curve to obtain a concave condition prediction curve, and marking the name of the measuring point channel leading to each concave valley bottom.
And (5) obtaining a spacecraft-rocket coupling analysis result of the spacecraft, multiplying the spacecraft-rocket interface response quantity value in the spacecraft-rocket coupling analysis result by a specified safety factor, obtaining a spacecraft-rocket interface response envelope curve after envelope taking, and making a concave condition for controlling the spacecraft sinusoidal vibration test between the spacecraft-rocket interface response envelope curve and the concave condition prediction curve by comprehensively considering the nonlinear factor.
Further, in the step (2), a theoretical response curve of a specified large-scale sinusoidal vibration test is obtained through linear calculation by using a characteristic-scale frequency sweep test result, and the method specifically comprises the following steps:
and extracting a response curve of the characteristic-level sinusoidal vibration test from the characteristic-level frequency sweep test result.
The spacecraft system is a linear system, the theoretical response curve of the large-scale sinusoidal vibration test and the response curve of the characteristic-scale sinusoidal vibration test have a linear relationship, and the theoretical response curve of the specified large-scale sinusoidal vibration test is directly obtained through linear calculation by utilizing the response curve of the characteristic-scale sinusoidal vibration test extracted from the characteristic-scale frequency sweep test result.
Further, in the step (5), the non-linear factors are comprehensively considered, and the method comprises the following steps:
in the step (2), performing a plurality of different magnitude characteristic level frequency sweep tests to obtain a plurality of different magnitude characteristic level frequency sweep test results, continuing to perform the step (3) and the step (4) to obtain a plurality of concave condition prediction curves corresponding to different magnitudes, and comparing differences of the concave condition prediction curves corresponding to different magnitudes:
and if the difference of the concave condition prediction curves corresponding to the different magnitudes is within a set allowable range, taking the current concave condition prediction curve, and making a concave condition for controlling the spacecraft sinusoidal vibration test between the current concave condition prediction curve and the rocket interface response envelope curve.
If the difference of the concave condition prediction curves corresponding to the different magnitudes exceeds the set allowable range, obtaining a nonlinear polynomial through polynomial fitting according to the magnitudes of the concave condition prediction curves corresponding to the different magnitudes and the corresponding magnitudes, obtaining a concave condition prediction curve correction value by using an extrapolation method according to the nonlinear polynomial, correcting the concave condition prediction curve, and making a concave condition for spacecraft sinusoidal vibration test control between the rocket interface response envelope curve and the concave condition prediction curve after correction.
Has the advantages that:
the invention provides the concept of the concave condition prediction curve, so that the making process of the concave condition is more visual, the general testers do not need to determine the concerned parts or the single-machine equipment in a manual mode any more, the selective omission is avoided, and the risk of damage of the spacecraft structure or the single-machine equipment due to over-test caused by human negligence, insufficient experience and other factors is reduced to the minimum; a measuring point channel, an amplitude limiting condition and the like used in the process of indicating the recessed condition are completely and accurately written into a test input file before the test, which is equivalent to that a part of work of a test field is carried out before the test, so that the waiting time of various test equipment and personnel on the test field is greatly saved, and the test work flow is optimized; by utilizing the rigidness of the programming method and the high efficiency of computer operation, testers are liberated from a large amount of repeated data interpretation and analysis work with low added value, the concave condition analysis prediction of the spacecraft sinusoidal vibration test can be comprehensively, accurately and quickly carried out, and the concave condition formulation result is more accurate and credible.
Drawings
Fig. 1 is a flowchart of a method for making a concave condition in a sinusoidal vibration test of a spacecraft according to an embodiment of the present invention;
FIG. 2 is an exemplary illustration of a prediction curve of a dip condition obtained by an embodiment of the present invention;
FIG. 3 is an exemplary diagram of a concave condition for a spacecraft sinusoidal vibration test control formulated by using a rocket coupling analysis result and a concave condition prediction curve according to an embodiment of the present invention.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a method for formulating a concave condition of a spacecraft sinusoidal vibration test, which is used for formulating the concave condition by a program strictly according to a concave control rule of the spacecraft sinusoidal vibration test.
The sinking control criterion of the spacecraft sinusoidal vibration test comprises the following steps:
criterion one is as follows: in a sinusoidal vibration test of the spacecraft, the maximum strain response of the main structure of the spacecraft is not larger than the maximum strain value of the main structure of the spacecraft in a static test.
Criterion two: acceleration response at the installation position of the key single-machine equipment on the spacecraft does not exceed component-level sinusoidal vibration test conditions specified by environmental test specifications.
Criterion three: and the input vibration value of the whole spacecraft after the sinking is not lower than the response value of the rocket interface in the coupling analysis result of the spacecraft and the rocket, and the spacecraft has enough safety margin.
The principle of the technical scheme of the invention is as follows: the first criterion and the second criterion are converted into computer programs which can be executed quantitatively, an exhaustion method is adopted to ensure that the inspection and analysis of each measuring point, each direction and each frequency point are not omitted, a concave condition prediction curve is obtained by utilizing a specific program algorithm, the concave condition prediction curve concept is adopted to replace the artificial determination of an attention part or a single-machine device, a concave condition prediction curve of a sine vibration test of a specified magnitude can be calculated according to the characteristic level frequency sweep test result, measuring point channel information leading to each concave valley bottom is obtained, and then a reasonable concave condition is worked out by combining the arrow coupling analysis result in the third criterion.
And converting the first sinking control criterion and the second sinking control criterion into a program algorithm in the full frequency band range.
The specific process is shown in fig. 1, and comprises the following steps:
step (1) -before the sinusoidal vibration test, determining and summarizing all the measuring points to be analyzed in the spacecraft, the directions and the amplitude limiting conditions of corresponding measuring point channels, and compiling into a test input file.
The stations to be analyzed include: strain response measuring points and acceleration response measuring points on the spacecraft; wherein the strain response measurement is associated with criterion one; the acceleration response measurement is associated with criterion two.
Each measuring point has 1-3 directions, and each direction corresponds to 1 measuring point channel.
And if the measuring point to be analyzed is a strain response measuring point, the amplitude limiting condition of the measuring point channel is the maximum strain value of the strain response measuring point in the static test.
And if the measuring point to be analyzed is an acceleration response measuring point, the amplitude limiting condition of the measuring point channel is a component-level sinusoidal vibration test condition specified by the corresponding environment test specification of the acceleration response measuring point.
The amplitude limiting condition used here is the key for determining the predictive correctness, and needs to be written into a test input file completely and accurately before the test, which is equivalent to lifting a part of work of a sinusoidal vibration test field to be carried out before the test, thereby greatly saving the waiting time of various test equipment and personnel on the test field and optimizing the test work flow.
Step (2), acquiring a characteristic-level frequency sweep test result on a spacecraft sinusoidal vibration test site; and obtaining a theoretical response curve of the specified large-scale sinusoidal vibration test by linear calculation according to the characteristic-scale frequency sweep test result.
The large scale referred to in the embodiments of the present invention is acceptance, quasi-authentication or authentication.
The method mainly comprises the steps of extracting a response curve of a characteristic-level sine vibration test from a characteristic-level frequency sweep test result; assuming that the spacecraft vibration system is a linear system, the theoretical response curve of the large-scale sinusoidal vibration test and the response curve of the characteristic-scale sinusoidal vibration test have a linear relationship, and the theoretical response curve of the specified large-scale sinusoidal vibration test is directly obtained through linear calculation by utilizing the response curve of the characteristic-scale sinusoidal vibration test extracted from the characteristic-scale frequency sweep test result.
Step (3), comparing theoretical response curves of a large-scale sinusoidal vibration test with a specified measuring point and a specified direction with amplitude limiting conditions of channels of corresponding measuring points one by one; if the value in the theoretical response curve is larger than the amplitude limiting condition at one frequency point, marking the frequency point as a concave frequency point, and estimating the concave value of the concave frequency point through linear calculation; and storing the concave magnitude of the concave frequency point and the corresponding measuring point channel name.
The lower concave magnitude value in the embodiment of the invention enables the theoretical response value obtained by linear calculation to be equal to the amplitude limiting condition at the lower concave frequency point when the spacecraft inputs the lower concave magnitude value at the lower concave frequency point.
Step (4) -executing step (3) aiming at all measuring point channels; if the same concave frequency point has a plurality of concave values, the concave frequency point only keeps the minimum value of the concave values and the corresponding measuring point channel name; if there is no concave value at a frequency point, setting the frequency point as an original value (the original value is the original test condition of a large-scale sinusoidal vibration test); and drawing the concave quantity value or the original quantity value corresponding to each frequency point into a curve to obtain a concave condition prediction curve, and marking the name of the measuring point channel leading to each concave valley bottom. Wherein the bottom of the concave valley refers to the corresponding position of the minimum value in the concave condition pre-curve.
The embodiment of the invention provides a possible embodiment of a dip condition prediction curve, which is shown in fig. 2. The physical significance of the dip condition prediction curve is: the input magnitude is controlled according to the concave condition prediction curve under the premise that the whole spacecraft vibration system is completely linear, and the maximum value in the response of all measuring point channels can be ensured not to exceed the corresponding amplitude limiting condition.
The concave condition prediction curve concept obtained in the step replaces artificial determination of a concerned position or a single machine device, and a concave condition prediction curve of a sinusoidal vibration test of a specified magnitude can be rapidly calculated according to a characteristic-level frequency sweeping test result and measuring point channel information of each concave valley bottom is obtained, so that the intuitiveness of the concave condition formulation process of the sinusoidal vibration test of the spacecraft and the accuracy and the credibility of the formulated result are greatly improved.
And (5) obtaining a spacecraft and rocket coupling analysis result of the spacecraft, multiplying the spacecraft and rocket interface response quantity value in the spacecraft and rocket coupling analysis result by a specified safety factor (generally more than or equal to 1.25), obtaining a spacecraft and rocket interface response envelope curve after envelope, comprehensively considering nonlinear factors, and making a concave condition for controlling a spacecraft sinusoidal vibration test between the spacecraft and rocket interface response envelope curve and a concave condition prediction curve.
The actual spacecraft vibration system cannot be completely linear, so that the nonlinear phenomenon occurring in the test needs to be comprehensively analyzed by considering the nonlinear factor, namely in the step (2), a plurality of different magnitude characteristic level frequency sweep tests are executed to obtain a plurality of different magnitude characteristic level frequency sweep test results, the steps (3) and (4) are continuously executed to obtain a plurality of concave condition prediction curves corresponding to different magnitudes, and the difference of the concave condition prediction curves corresponding to different magnitudes is compared: if the difference of the concave condition prediction curves corresponding to the different magnitudes is within the set allowable range, taking the current concave condition prediction curve, and making a concave condition for controlling the spacecraft sinusoidal vibration test between the current concave condition prediction curve and the rocket interface response envelope curve;
if the difference of the concave condition prediction curves corresponding to the different magnitudes exceeds the set allowable range, obtaining a nonlinear polynomial through polynomial fitting according to the magnitudes of the concave condition prediction curves corresponding to the different magnitudes and the corresponding magnitudes, obtaining a concave condition prediction curve correction value by using an extrapolation method according to the nonlinear polynomial, correcting the concave condition prediction curve, and making a concave condition for spacecraft sinusoidal vibration test control between the rocket interface response envelope curve and the concave condition prediction curve after correction.
Generally, the judgment is assisted by adding one or more low-order frequency sweep tests, for example, by comparing the results of the 0.1g frequency sweep test and the 0.2g frequency sweep test, whether the linear relation of each channel and each frequency point is good or not is analyzed. In the analysis process, the method can also play a beneficial role, can respectively calculate the concave condition prediction curves deduced from the two different magnitude frequency sweep test results, and then compares the difference of the two prediction curves, the frequency band with small difference has small nonlinear influence, and the frequency band with large difference has large nonlinear influence, so that the analysis process of the nonlinear influence is more visual, and the final concave condition is guided to be formulated according to the nonlinear change trend.
FIG. 3 is a drawing example of a concave condition of a sinusoidal vibration test in a certain direction, wherein a thick dotted line is a concave condition prediction curve, a thin solid line is a tool-arrow interface response envelope curve of a tool-arrow coupling analysis result, and a thick solid line is a concave condition which is made between the two curves by comprehensively considering factors such as nonlinearity.
The method is convenient for programming realization, the rigidness of the programming method and the high efficiency of computer operation liberate testers from the work of interpreting and analyzing a large amount of repetitive data with low added value, can comprehensively, accurately and quickly analyze and predict the concave condition of the spacecraft sinusoidal vibration test, directly guides the formulation of the concave condition, and ensures that the analysis process of linear calculation and nonlinear influence is more visual and the formulated result is more accurate and reliable.
The whole sinking condition making process is completed manually by two or three hours or even longer according to the conventional method, and only the information of part of concerned parts and the sinking lowest point of the single-machine equipment can be obtained; the linear calculation can be completed within one minute by adopting the method and the application program compiled according to the method, the concave condition prediction curve of the full frequency band can be obtained, the time consumed by nonlinear and other factors is considered, and the whole concave condition making process can be shortened to within half an hour.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. A concave-down condition making method for a spacecraft sinusoidal vibration test is characterized in that a concave-down condition making method utilizes a concave-down condition prediction curve to complete making of a concave-down condition;
the method for formulating the concave condition comprises the following steps:
step (1) -before a sinusoidal vibration test, determining and summarizing all the measuring points to be analyzed in the spacecraft, directions and amplitude limiting conditions of corresponding measuring point channels, and compiling into a test input file;
the station to be analyzed comprises: strain response measuring points and acceleration response measuring points on the spacecraft;
each measuring point has 1-3 directions, and each direction corresponds to 1 measuring point channel;
if the measuring point to be analyzed is a strain response measuring point, the amplitude limiting condition of the measuring point channel is the maximum strain value of the strain response measuring point in the static test;
if the measuring point to be analyzed is an acceleration response measuring point, the amplitude limiting condition of the measuring point channel is a component-level sinusoidal vibration test condition specified by the corresponding environment test specification at the acceleration response measuring point;
step (2), executing a characteristic-level frequency sweep test on the spacecraft sinusoidal vibration test site to obtain a characteristic-level frequency sweep test result; obtaining a theoretical response curve of a specified large-scale sinusoidal vibration test by linear calculation according to the characteristic-scale frequency sweep test result; the large magnitude is an acceptance level, a quasi-identification level or an identification level;
step (3), reading the test input file, and comparing the theoretical response curves of a large-scale sinusoidal vibration test with the specified measuring points and the specified direction with the amplitude limiting conditions of the channels of the corresponding measuring points one by one; if the value in the theoretical response curve is larger than the amplitude limiting condition at a frequency point, marking the frequency point as a concave frequency point, and estimating the concave magnitude of the concave frequency point through linear calculation; storing the concave quantity values of the concave frequency points and corresponding measuring point channel names; the lower concave magnitude value enables a theoretical response value obtained through linear calculation to be equal to an amplitude limiting condition at the lower concave frequency point when the spacecraft inputs the lower concave magnitude value at the lower concave frequency point;
step (4) -executing the step (3) aiming at all measuring point channels in the test input file; if the same concave frequency point has a plurality of concave values, the concave frequency point only keeps the minimum value of the concave values and the corresponding measuring point channel name; if there is no concave value at a frequency point, setting the frequency point as an original value; the original value is the original test condition of a large-scale sine vibration test; drawing the concave quantity value or the original quantity value corresponding to each frequency point into a curve to obtain a concave condition prediction curve, and marking the name of a measuring point channel leading to each concave valley bottom;
step (5), obtaining a spacecraft-rocket coupling analysis result of the spacecraft, multiplying a spacecraft-rocket interface response quantity value in the spacecraft-rocket coupling analysis result by a specified safety factor, obtaining a spacecraft-rocket interface response envelope curve after envelope taking, and making a concave condition for controlling a spacecraft sinusoidal vibration test between the spacecraft-rocket interface response envelope curve and a concave condition prediction curve by comprehensively considering a nonlinear factor;
the comprehensive consideration of non-linear factors includes:
in the step (2), performing a plurality of different magnitude characteristic level frequency sweep tests to obtain a plurality of different magnitude characteristic level frequency sweep test results, continuing to perform the steps (3) and (4) to obtain a plurality of concave condition prediction curves corresponding to different magnitudes, and comparing differences of the concave condition prediction curves corresponding to different magnitudes:
if the difference of the concave condition prediction curves corresponding to the different magnitudes is within a set allowable range, taking a current concave condition prediction curve, and making a concave condition for controlling the spacecraft sinusoidal vibration test between the current concave condition prediction curve and a rocket interface response envelope curve;
if the difference of the concave condition prediction curves corresponding to the different magnitudes exceeds the set allowable range, obtaining a nonlinear polynomial through polynomial fitting according to the magnitudes of the concave condition prediction curves corresponding to the different magnitudes and the corresponding magnitudes, obtaining a concave condition prediction curve correction value by using an extrapolation mode according to the nonlinear polynomial, correcting the concave condition prediction curve, and making a concave condition for spacecraft sinusoidal vibration test control between a rocket interface response envelope curve and the concave condition prediction curve after correction.
2. The method as claimed in claim 1, wherein in the step (2), the theoretical response curve of the specified large-scale sinusoidal vibration test is obtained by linear estimation using the result of the characteristic-scale frequency sweep test, specifically:
extracting a response curve of a characteristic-level sinusoidal vibration test from the characteristic-level frequency sweep test result;
and the spacecraft system is a linear system, the theoretical response curve of the large-scale sinusoidal vibration test and the response curve of the characteristic-scale sinusoidal vibration test have a linear relationship, and the theoretical response curve of the specified large-scale sinusoidal vibration test is directly obtained through linear calculation by utilizing the response curve of the characteristic-scale sinusoidal vibration test extracted from the characteristic-scale frequency sweep test result.
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