92 results about "Modal testing" patented technology

The invention discloses a large-span bridge vibration response prediction method based on data driving, and relates to the technical field of bridge vibration response prediction, and the method comprises the following steps: arranging a plurality of sensors at a plurality of key structure parts of a bridge, collecting vibration response data of the bridge during operation in real time based on an initial sampling frequency set based on the inherent frequency of the bridge structure; performing frequency domain analysis on the collected vibration response data, extracting a main excitation frequency component under the current working condition, and constructing a current excitation frequency spectrum; the method comprises the following steps: calling structural modal parameters obtained in a design stage, a static load test or a modal test of a bridge, extracting the natural vibration frequency of each order of structure, and constructing a bridge inherent frequency feature library; according to the method, the resonance state is dynamically identified through frequency domain analysis and the fuzzy risk index, the sampling frequency is intelligently adjusted, high-frequency response accurate capture and resource efficiency optimization are realized, and the sensitivity, the real-time performance and the safety of a bridge health monitoring system are remarkably improved.

The embodiment of the invention provides a structure optimization method and device, electronic equipment and a storage medium, and the method comprises the steps: obtaining the test vibration response data of a CT rack under a static modal test, obtaining the test work vibration response data of the CT rack under a dynamic work modal test, and obtaining a simulation model of the CT rack based on a simulation digital model of the CT rack; simulation vibration response data of the CT rack under the simulation static mode test are obtained, and simulation working vibration response data of the CT rack under the simulation dynamic working mode test are obtained based on the simulation digital model of the CT rack; the resonance danger frequency of the CT rack is determined based on the motor rotating speed of the CT rack, the test vibration response data, the simulation vibration response data, the test work vibration response data and the simulation work vibration response data, and the structure optimization strategy of the CT rack is determined based on the resonance danger frequency. The resonance danger frequency of the CT rack can be accurately positioned, so that the structure is improved based on the resonance danger frequency, and the stability and reliability of the CT rack are improved.

The invention provides a bearing outer ring fault diagnosis test parameter setting optimization method, which comprises the following steps of: firstly, accurately acquiring structural parameters of a bearing by utilizing a measuring tool; secondly, testing and calculating the inherent frequency and the damping ratio of the bearing in the installed state through a modal experiment; selecting test working condition parameters according to the actual operation environment of the bearing, and calculating the fault characteristic frequency of the bearing; bearing fault simulation signal band-pass filtering processing is constructed; meanwhile, constructing a fault signal equivalent model; carrying out resonance demodulation analysis on the equivalent model, extracting an envelope spectrum and evaluating a fault diagnosis effect; and finally, circularly adjusting working condition parameters, iteratively optimizing the test working conditions, and selecting the working condition with the maximum fault characteristic frequency amplitude and the minimum noise interference as the optimal test condition. According to the invention, the accuracy and reliability of bearing outer ring fault detection are effectively improved, and powerful support is provided for fault diagnosis of mechanical equipment.

The invention discloses a vehicle part inertial parameter detection method based on modal parameters, and relates to the technical field of modalities, and the method comprises the steps: obtaining part modal test data; modal analysis is carried out according to data of the modal test of the part, and a six-order rigid body modal is extracted; based on the six-order rigid body mode, reconstructing a frequency response function HOI of the part; acquiring a rigid body origin acceleration conversion matrix To based on setting of a rigid body by a part; based on the setting that the part is a rigid body, obtaining a conversion matrix TI of the measurement point excitation FI of the part; converting the frequency response function HOI of the part into a frequency response function based on an original point of a coordinate system; constructing a part inertial parameter based on the origin frequency response function of the coordinate system, and obtaining coefficient matrixes Ta and Tb; aiming at the pre-selected frequency band, obtaining inertia parameters of the part; through the scheme, free boundary conditions are simulated, modal test accuracy is ensured, rigid body motion test parameters are screened out, rigid body measurement accuracy is improved, excitation system design is simplified, and inertial parameter identification precision is improved.

According to the test case level-to-level management system provided by the invention, a dynamic perception-intelligent decision-accurate execution closed-loop system is constructed through cooperative operation of the intelligent arrangement center module, the multi-modal test fusion module and the heterogeneous execution environment adaptation module. Real-time dynamic allocation of test resources is realized based on a bidirectional sensing mechanism, and the resource utilization rate is improved; a data feedback channel of five-dimensional linkage of interface testing, function testing, UI testing, performance testing and safety testing is established through a multi-modal testing fusion module, and cross-modal conversion and multiplexing are carried out on key testing elements such as boundary value cases and safety injection points, so that the coverage rate of a testing scene is increased, and the defect escape rate is reduced; the heterogeneous execution environment adaptation module realizes automatic identification and accurate matching of a virtual machine, a container and a physical machine environment based on a feature fingerprint database, manual configuration errors are eliminated, environment adaptation time consumption is reduced, the test period is greatly shortened, and the defect positioning efficiency is greatly improved.

The invention discloses a method for identifying a micro-vibration source of a reaction wheel, which comprises the following steps of: firstly, testing micro-vibration signals of the reaction wheel under a plurality of rotating speed working conditions, then carrying out noise reduction processing on the micro-vibration signals under each rotating speed working condition, converting the micro-vibration signals into frequency domain signals, and identifying the micro-vibration source of the reaction wheel on the basis of amplitude-frequency response under each rotating speed working condition. The method comprises the steps that firstly, a three-dimensional frequency spectrum waterfall plot with micro-vibration changing along with the rotating speed is formed, then, based on theoretical values and test values of modal frequency characteristics, a characteristic peak value is extracted, modal characteristics in the three-dimensional frequency spectrum waterfall plot are recognized and verified, and finally, a vibration source is positioned based on the characteristic peak value, the modal characteristics and rotor-bearing vibration frequency characteristics. According to the recognition method, theoretical calculation and operation modal testing are fused, so that the modal frequency of the reaction wheel system can be more comprehensively obtained, damage of a force measurement method to the reaction wheel and modal distortion in simulation are avoided, the recognition error of a harmonic coefficient is reduced, the fitting precision of high-order harmonics is improved according to multi-order resonance response characteristics, and the recognition accuracy of the reaction wheel system is improved. Therefore, the contribution of the reaction wheel vibration source component and the structure thereof under transmission can be effectively evaluated.

The invention provides an automatic calibration method and system for an inertial measurement unit, and electronic equipment, and relates to the technical field of sensors, the method comprises the following steps: building an IMU multi-modal calibration environment, and deploying multiple groups of reference sensors; designing a working environment test parameter table, performing simulation test on the to-be-calibrated IMU, and synchronously recording IMU multi-modal test data and multi-modal reference data; establishing an error parameter model; and constructing a calibration multi-objective function, performing minimization solution on the error parameter model, and performing closed-loop optimization correction on the to-be-calibrated IMU. According to the method and the device, the technical problems that in the prior art, as IMU error calibration is usually carried out in an ideal environment state, complex coupling errors caused by a multi-factor coupling effect are neglected, the compensation precision of calibration parameters under complex actual working conditions is seriously reduced, and IMU output drift is remarkably increased are solved; and the output precision of the IMU in a full working condition environment and the robustness of calibration parameters are improved.

The invention provides an acoustic modal test method and device, electronic equipment and a storage medium, and the method comprises the steps: controlling at least one sound source device to output a preset audio signal at the same time; acquiring response signals detected by the plurality of sensors; the plurality of sensors are used for respectively executing sound detection at a plurality of detection positions in a compartment area; establishing a geometric model based on the audio signal, the detection position and a response signal detected by the sensor; and analyzing the geometric model to obtain an acoustic modal test result. According to the embodiment of the invention, the acoustic modal test result measured by the method is beneficial to improving the riding experience of passengers.

The high-efficiency low-deformation machining method suitable for the aviation blade disc comprises the following steps that S1, a cutting force model is constructed based on a ball-head spiral conical milling cutter, a cutting test is carried out, and therefore a cutting force coefficient is determined; s2, performing numerical control simulation on the milling cutter by adopting special software, determining a machining path according to a principle of maximum rigidity of a cutting system, extracting a cutting area and a cutting edge length through the special software on the basis of the machining path so as to calculate real-time cutting force in the machining path, and then constructing a finite element model of the blade disc, carrying out transient mechanical analysis in the blade curved surface coordinate system, adjusting cutting parameters and the inclination angle of a workbench when cutting deformation exceeds a set range, and determining a parameter interval I of the feeding amount and the cutting depth; and S3, modal testing is carried out to obtain modal parameters, then calculation software is adopted to sequentially calculate parameter intervals of different machining parameters and the rotating speed of the main shaft, and effective machining parameters are obtained.

The invention belongs to the technical field of robots, and discloses a milling force simulation and feed rate optimization method considering a robot pose dependence dynamics effect, and the method comprises the steps: firstly carrying out modal testing under different poses of a robot milling area; then, a kinetic model is established in a robot cutting area; and meanwhile, the surface of the workpiece is dynamically updated based on the dynamic sweeping track of the blade and the workpiece model, so that the calculation precision of the instantaneous cutting thickness and the cutting force is guaranteed. And finally, based on the simulated accurate cutting force, feed rate segmented self-adaptive planning under the cutting force peak value constraint is carried out, and robot curved surface part milling and machining error measurement experiments are carried out. The milling efficiency and precision of the curved surface part robot are effectively improved, and the cutting force in the machining process is more stable. And the method is of great significance to improvement of the stability and the machining performance in the robot machining process.

The invention relates to the technical field of modal tests, and discloses a modal test method and system based on environment control, and the system comprises an environment simulation module which is configured to set environment scene parameters according to experiment requirements; the test platform module is configured to limit and fix the tested structural member; the excitation module is configured to switch excitation modes according to the environment scene parameters and the structural characteristics of the tested structural component and excite the tested structural component; the data acquisition module is configured to acquire test data of the tested structural member; the data processing module is configured to pre-process the test data and perform modal analysis based on the pre-processed test data; and the evaluation module is configured to visually display the modal analysis result and perform structure evaluation based on the modal analysis result. According to the invention, the modal test automation and intelligence of the tested structural member in various environment scenes are realized.

This application proposes a small-scale universal modal testing device for rockets, comprising a suspension mechanism for suspending the rocket body and a testing mechanism with an impact end, wherein the impact end can impact the rocket body around a first axis. It also includes a drive mechanism for driving the impact end to impact the rocket body, and a testing platform for mounting the suspension mechanism and the testing mechanism. In use, the impact end is rotated around the rocket body with the first axis as the center and stopped at a suitable position. At this point, the drive mechanism drives the impact end to impact the rocket body. Compared to existing technologies that only include four impact points (left, right, top, and bottom), the impact end that can surround the rocket body has more impact positions, allowing for more flexible adjustment and facilitating the simulation of multi-position impact tests.

The invention provides a modal test method and device, a readable storage medium and a modal test component. The modal testing method is applied to a modal testing assembly, the modal testing assembly comprises a laser target and a laser tracking device, the laser target is arranged on a to-be-tested object, the laser tracking device and the laser target are correspondingly arranged, and the modal testing method comprises the steps that under the condition that the to-be-tested object is subjected to impact excitation, a force signal of impact excitation is obtained; performing laser tracking on the laser target through a laser tracking device, and determining a first displacement signal of the laser target; and determining a modal test result of the to-be-tested object according to the force signal and the first displacement signal. According to the embodiment of the invention, the detection efficiency and accuracy of modal testing are improved.

The process adaptability pilot test verification evaluation method and system for the aviation structural part machining machine tool comprises the steps that the comprehensive geometric error, the motion linkage error and the machining process dynamic error of the machine tool are obtained, and a comprehensive precision evaluation model of the machine tool is established; based on a comprehensive precision evaluation model, processing efficiency adaptability evaluation is carried out on the machine tool; establishing a thermal characteristic model of the machine tool through heat source analysis, temperature field monitoring and thermally induced error modeling; establishing a resonance characteristic model of the machine tool through modal test of the whole machine and key parts and resonance characteristic evolution analysis in a processing space; and performing comprehensive process adaptability evaluation on the machine tool by combining the comprehensive precision evaluation model, the thermal characteristic model of the machine tool and the resonance characteristic model of the machine tool, and performing process adaptability pilot test verification on the machine tool based on an evaluation result.

This invention discloses a combustion chamber nozzle modal testing fixture device. The device includes a test platform (3), a first clamping unit (1), and a second clamping unit (2). The first clamping unit (1) and the second clamping unit (2) are disposed on the test platform (3). The device is characterized in that the first clamping unit (1) is provided with a cavity for accommodating the end (18) of the workpiece to be tested and a fuel supply assembly. This clamping device can stably support the workpiece to be tested, and the cavity can accommodate the protrusion of the product. Simultaneously, the clamping method is the same as the actual assembly method of the workpiece to be tested, thereby obtaining parameters of the finite element model that better match the test results, thus improving the accuracy of the finite element method calculation, thereby saving test costs and improving R&D efficiency.

The invention discloses a high-precision modal test method and related equipment, and belongs to the technical field of structural dynamics tests.The method comprises the steps that spring design parameters are obtained, and spring design variables are initialized and generated; calculating stress field characteristic parameters based on the spring design parameters and the spring design variables; evaluating stress field characteristic parameters based on preset stress field constraint conditions; under the condition that the stress field characteristic parameters meet the stress field constraint conditions, spring design variables are output to serve as spring design results; and preparing a spring based on a spring design result, and completing a modal test. According to the method, the stress field quantification constraint condition is introduced in the modal test instrument spring design stage, the characteristic parameters of the modal test instrument spring are evaluated, the modal test instrument spring design precision and reliability can be effectively improved, the spring design iteration period is remarkably shortened, the modal test precision and stability are improved, and the modal test efficiency is improved. And the design requirement of the high-reliability spring is effectively met.

The invention belongs to the field of spacecraft modal testing, and particularly relates to a modal testing method based on dynamic modal decomposition in an unfolded state of a large flexible solar wing, which comprises the following steps of: S1, exciting the solar wing by adopting a pre-tightening force release method, and synchronously acquiring displacement attenuation data of different positions of the solar wing through a plurality of laser displacement sensors in a testing device; s2, performing fast Fourier transform calculation on each group of displacement attenuation data, and processing all fast Fourier transform calculation results to generate an average frequency response curve; s3, processing the displacement data by adopting a Monte Carlo delay embedding dynamic mode decomposition algorithm to obtain Q groups of fundamental frequencies, damping ratios and vibration mode results; and S4, arithmetic average is carried out on Q groups of results, and a final fundamental frequency, a modal damping ratio and a vibration mode are output. According to the method, the modal parameters are identified by adopting the Monte Carlo dynamic modal decomposition method, the fundamental frequency, the modal damping ratio and the vibration mode of the unfolded state of the large flexible solar wing can be identified, and meanwhile, the reliability of an identification result is ensured.

The invention relates to the technical field of selenium drum circulation, and particularly discloses a selenium drum recycling and replacing system and a control method.The method comprises the steps that firstly, quantitative characterization of subsurface defects and local mechanical properties is conducted on waste metal core base materials through microwave resonance and nanoindentation multi-source fusion detection, and a base material state quantitative data set is generated; performing multi-physical field transient simulation by taking the data set and target coating parameters as input, and predicting an interface residual stress score in a regeneration process; based on a prediction result, reversely solving a dynamic temperature control sequence and gradient material matching scheme; in a vacuum coating environment, active stress compensation coating is realized, transient thermal excitation modal testing is performed on the regenerated toner cartridge, high-frequency dynamic characteristics of the regenerated toner cartridge are extracted and compared with a simulation predicted value, simulation model parameters are optimized according to deviation data feedback, closed-loop control is formed, and the interface bonding strength and long-term imaging reliability of the regenerated toner cartridge are improved.

The application discloses a sensor position selection method, device and medium in a modal test process, which is characterized by the following steps: establishing a correlation matrix MAC 12 , MAC 13 ,..., MAC ij , calculating the contribution degree value of a preselected sensor preselected position point to each order modal, deleting the preselected sensor position point with a negative contribution degree, and continuously adjusting the correlation matrix so that the remaining preselected sensor position points meet the different order modal vibration mode requirements, thereby realizing automatic matching of the preselected sensor position points to the measurement requirements, improving the sensor positioning accuracy, and eliminating the need for manual repeated intervention for modal measurement of the sensor arrangement position.

The invention provides a method for synchronously measuring the vibration mode slope of a rocket by using a plurality of high-definition cameras. Belongs to the technical field of spaceflight structure vibration testing. According to the method, a plurality of high-definition cameras are arranged outside a rocket structure, image information of different local areas of the structure is collected respectively, and each camera is calibrated in advance so as to establish a corresponding relation between an angle in an image and an actual physical rotation angle. In the vibration process, the instantaneous rotation angle of each local area is extracted through an image processing means, phase comparison is carried out on the instantaneous rotation angle and a reference camera signal arranged at the tail of the rocket, and finally the vibration mode slope change condition in the structure direction is obtained through calculation. The method avoids high cost and high complexity of a traditional high-precision rate gyroscope, has the advantages of being non-contact, low in cost, easy to deploy and the like, and is suitable for rocket structure ground modal testing and flight vibration analysis.

This invention belongs to the field of structural dynamics testing and modal analysis technology, and provides a physical / mathematical integrated experimental modal analysis method, system, equipment, and medium. The method includes: applying preliminary excitation and using the phase separation method to obtain preliminary modal parameters containing mode shapes; constructing a mode shape matrix based on the mode shapes and optimizing the position and number of exciters to ensure that the modal participation values ​​of all modes of interest are not lower than a preset threshold; performing refined excitation according to the optimized scheme, locking the resonance state using the phase resonance method, and obtaining the final modal parameters. This invention effectively solves the problems of blind excitation point placement, modal confusion, and mode omission by coordinating three stages: phase separation initial screening, mode shape-driven excitation optimization, and phase resonance fine measurement. It significantly improves the integrity, accuracy, and efficiency of modal testing of large structures and reduces experimental safety risks. It is applicable to ground vibration tests of complex structures such as aircraft, spacecraft, and bridges.

The invention provides an automatic verification test method and system for a recording system, and belongs to the technical field of software testing, and the method comprises the steps: constructing a multi-modal test scene library, and configuring multi-dimensional test parameters for each test scene in the scene library; responding to the test triggering instruction, calling a target test scene, automatically generating multi-modal test data according to multi-dimensional test parameters in the target test scene, and injecting the multi-modal test data into the recording system to trigger the recording system to run; in the operation process of the recording system, collecting multi-modal response data of the recording system for the multi-modal test data in real time; and according to the expected result of the target test scene and the multi-modal response data, carrying out automatic verification analysis, and generating a test result. According to the method, the test scene library containing the multi-dimensional parameters is constructed, the multi-modal test data is automatically generated and injected to drive the system to run, and the multi-modal response data is collected in real time for verification, so that the test accuracy of the recording system is remarkably improved.

The application discloses a kind of for vehicle tire static load modal test excitation loading mechanism, including work type base and sample piece fixed pedestal, the top main shaft end of sample piece fixed pedestal is equipped with wheel hub adapter, the back of fixed plate is provided with Z direction stiffness measurement scale, horizontal excitation platform is provided on main loading platform, the bottom end surface central place of horizontal excitation platform is equipped with rolling bearing, the bottom of main loading platform is supported by two groups of air spring, and horizontal excitation platform is fixedly assembled with exciter by the exciter mounting seat of the outside of main loading platform.The method of Z direction static load loading and X, Y, Z direction excitation on static load loading surface to the tire piece to be measured can be realized simultaneously in the application;The structural design of main loading platform and horizontal excitation platform satisfies the demand of structural strength, first-order natural frequency, self-weight light weight, realizes the demand of "loading surface is excitation surface", so that the test result of test rig is closer to the vibration transmission characteristics under actual working condition.

The utility model relates to the technical field of liquid shaking testing equipment, and discloses a storage tank liquid modal testing device, which is characterized in that a support frame is arranged in the middle of a device base, a vibration exciter and a liquid adding and discharging device are respectively arranged on two sides of the support frame, a mobile platform is arranged below the support frame, and a flexible pull rod is arranged at each of four corners of the mobile platform. The upper and lower ends of the flexible pull rod are fixedly connected with the support frame and the mobile platform respectively; the shaft vibration exciter is fixedly connected with the movable platform through a push-pull rod; and an experiment storage box is arranged on the mobile platform and is fixedly connected with the mobile platform through a storage box clamp. The device can achieve diversified simulation of different liquid working conditions and modal characteristics, is compact in size, can be used for various scenes such as laboratories and industrial sites, and has high applicability.

The invention relates to a modeling method and a modeling system for modal calculation of a stator assembly of a motor. The modeling method comprises the following steps: S1, carrying out modal test on a sample piece of a stator assembly of a motor to obtain a modal shape of the stator assembly and a corresponding modal inherent frequency test value; s2, establishing an actual three-dimensional geometric model of the stator assembly according to the sample piece, and determining characteristic parameters and size parameters of the actual three-dimensional geometric model; s3, based on the characteristic parameters and the size parameters of the actual three-dimensional geometric model, a finite element model of the stator assembly is established, and the stator assembly is modeled into a circular ring cylinder through the finite element model, and S4, material attribute setting is conducted on the finite element model; s5, performing modal calculation on the finite element model subjected to material attribute setting to obtain a corresponding modal inherent frequency calculation value, and S6, comparing the modal inherent frequency calculation value with a modal inherent frequency test value, and adjusting a rigidity correction coefficient according to a comparison result until a difference value between the two values is smaller than a preset threshold value.

The invention relates to a factory building internal load identification method and system, belongs to the technical field of vibration testing, and solves the problem of low measurement precision of weak and coupled multi-power loads in a factory building process area in the prior art. The method comprises the following steps: determining a modal excitation point and a modal test point, collecting an excitation signal and an excitation vibration response signal when a plant is in a non-operation state, and identifying modal parameters of the plant; building a finite element model of the factory building, obtaining a finite element simulation result, and updating the finite element model according to the finite element simulation result and the modal parameters; determining a vibration response measuring point, collecting a vibration response signal of the equipment when the plant is in an operation state, and determining a real spectral response; according to the updated finite element model, obtaining a simulation response corresponding to the vibration response measuring point; and determining the internal load of the plant according to the simulation response, the equipment vibration response signal and the real spectral response. And high-precision and strong-anti-interference weak dynamic load identification in a complex vibration source environment is realized.

The invention discloses an industrial robot modal test measuring point selection method based on a modal kinetic energy method, and relates to the technical field of industrial robot modal test. On the basis of a traditional modal kinetic energy method, a comprehensive modal kinetic energy weight index is introduced, the index comprises a modal kinetic energy weight factor and a direction effectiveness coefficient, and therefore the problems that in industrial robot application of a traditional method, local modals are ignored, sensor direction matching is insufficient, and modals of different parts are processed in an equal weight mode are solved; nodes with large modal kinetic energy are screened out through iterative updating, an optimal measuring point is selected, and finally an acceleration sensor is arranged to complete experimental modal testing; according to the method, the local modality can be effectively identified, the rationality of measuring point arrangement and the accuracy of modal parameter identification are improved, modal loss is avoided, and reliable data support is provided for structural optimization and dynamic performance improvement of the industrial robot.

The invention discloses a contact parameter calculation method for improving case random vibration simulation precision based on modal testing. The contact parameter calculation method comprises the following steps: S1, providing a plate part, a frame part and an assembly thereof; s2, performing part modal simulation and part modal testing on the plate part and the frame part respectively to determine material parameters of the plate part and the frame part; and S3, performing assembly body modal simulation and part modal test on the assembly body to determine the contact type and the stiffness parameter of the assembly body, and obtaining contact stiffness parameters under different connection distances in combination with an interpolation algorithm. The method has the beneficial effects that the calculated contact parameters can improve the precision of a simulation model and the accuracy of a random vibration result, and the product reliability is guaranteed while the weight is reduced.

The invention provides a lifting structure modal test method and system. The invention discloses a lifting structure modal test method. The method comprises the following steps: mounting a detection mechanism and a locking mechanism on each lifting tower of a lifting structure; the lifting tower of the lifting structure is lifted; the lifting tower is locked and excited through the locking mechanism; and the modal information of the lifting structure is detected through the detection mechanism. The locking mechanisms are designed between the lifting tower sections for restraining and supporting, when the lifting structure is lifted in place, self-excited vibration generated when the locking mechanisms of the tower sections are locked serves as excitation, the detection mechanism is used for collecting signals, and modal testing of the heavy-load high lifting structure can be completed.

The invention provides an adjustable suspension device for a modal test of a solid rocket engine. The adjustable suspension device comprises a suspension belt, an adjustable suspension beam assembly, two chain blocks and two groups of adjustable suspension rope assemblies, the adjustable lifting beam assembly comprises a supporting cross beam and two adjustable connecting assemblies, and each adjustable connecting assembly is hinged to one lifting lug; the supporting cross beam is provided with a sliding groove used for sliding of the adjustable connecting assembly. The adjustable lifting rope assembly comprises an upper supporting plate, a lower supporting plate and an elastic lifting rope. The upper supporting plate and the lower supporting plate are connected into a whole through the elastic lifting rope. A solid rocket engine test piece is hung at the lower end of the adjustable lifting rope assembly; and the adjustable suspension device is suspended on a crane by the suspension belt. According to the adjustable hanging beam assembly designed by the invention, the problem that a traditional hanging device cannot realize distance adjustment below 3m is solved, the number of stressed elastic hanging ropes is quickly adjusted according to parameters of different solid rocket engine test pieces, the rigidity and the bearing strength of the adjustable hanging device are changed, and the modal test efficiency and the test accuracy are improved.