24 results about "Sinusoidal vibration" patented technology

The application provides a ship structure fatigue strength analysis method and system, which calculates the main engine vibration load and the wave load received by the ship structure based on the ship data, the characteristic data of the ship structure and the global sea state data, then calculates the stress response process under the combined action of the wave load and the main engine vibration load, the spectral density function of the stress response process, each order spectral moment of the stress response process and the zero-crossing rate of the stress response process, then calculates the stress response and the stress response peak of the ship structure under the action of the sinusoidal vibration load, calculates the stress cycle number of the ship structure based on the stress response and in combination with the fatigue life S-N curve, further calculates the fatigue damage under the action of the main engine vibration load, and finally calculates the total coupling fatigue damage under the long-term sea state, and further calculates the fatigue damage of the ship structure under the combined action of the high and low frequency loads, which effectively improves the accuracy and reliability of the ship structure fatigue strength calculation.

A control method for a non-sinusoidal hydraulic vibration curve of a mold, relating to the technical field of automation in metallurgical continuous casting. A three-segment linear-sinusoidal composite function is used, wherein one vibration cycle of a position curve thereof comprises three stages: the first stage is a sine-like curve obtained by superimposing a standard sinusoidal function having an angular velocity ω1 with a linear function having a slope (I), the second stage is a sine-like curve obtained by superimposing a standard sinusoidal function having an angular velocity ω2 with a linear function having a slope (II) and an offset (III), and the third stage is a sine-like curve obtained by superimposing a standard sinusoidal function having an angular velocity ω1 and a linear function having a slope (IV) and an offset (V) and connected to the sine-like curve of the first stage at different sampling moments. The method optimizes a non-sinusoidal vibration curve, and achieves a smooth and stable velocity curve for hydraulic cylinder motion, a small peak value, and continuous and smooth acceleration transitions without sudden changes. The control method is simple and easy to implement, has few control parameters, and is convenient to operate.

The invention belongs to the technical field of fiber-optic gyroscopes, and particularly relates to an acceleration-based fiber-optic gyroscope vibration error compensation method and an inertial measurement unit. Based on normal strain, optical fiber dielectric impermeability tensor variable quantity, refractive index variable quantity of light in the fast axis direction and phase variable quantity corresponding to a sensitive axis of an optical fiber gyroscope, quantitative relations between the phase variable quantity and the fast axis direction of the optical fiber and between the phase variable quantity and the length of a micro-section optical fiber are established, and the equivalent value of the stress borne by the optical fiber and the phase difference of an optical fiber ring is obtained; the linear relation between the phase difference equivalent value and the angular velocity to be compensated of the fiber-optic gyroscope is determined, the relation of converting the vibration acceleration to the phase to be compensated is established, and the required compensation coefficient is calibrated by combining a sinusoidal vibration test to compensate the vibration error of the fiber-optic gyroscope. According to the invention, vibration error compensation of the fiber-optic gyroscope can be realized without adding extra devices, and the real-time performance and accuracy of error compensation are improved.

The invention discloses a multifunctional light and simplified tree mover which comprises a frame, a torsional vibration excavating mechanism, a hoisting mechanism, a backfill soil paving mechanism and a traveling mechanism, the traveling mechanism is arranged at the bottom of the frame, the torsional vibration excavating mechanism is movably hinged to the head of the frame, and the backfill soil paving mechanism is movably hinged to the tail of the frame; the torsional vibration excavating mechanism comprises a torsional vibration unit and a scraper knife assembly, the torsional vibration unit comprises a vibration excitation device and a rotary excavating device, the scraper knife assembly comprises a knife shaft and a U-shaped scraper knife fixedly arranged on the knife shaft, the rotary excavating device drives the knife shaft to rotate, and the vibration excitation device is connected with the rotary excavating device and provides sinusoidal vibration for the knife shaft. By arranging the torsional vibration digging mechanism, the hoisting mechanism, the backfilling and soil paving mechanism and the walking mechanism, the whole-process mechanical operation of digging seedlings, hoisting the seedlings, transporting the seedlings, filling and leveling soil holes and compacting the soil holes can be realized, and the operation efficiency is high.

The invention discloses an AFM (atomic force microscope) and a piezoelectric ceramic driving method applied to high-speed feedback of an AFM (atomic force microscope) system, interaction force borne by a probe is enabled to be the same as preset interaction force by controlling the motion depth of piezoelectric ceramic, and the motion depth change of hardness detection piezoelectric ceramic is controlled to accord with a sine curve. Therefore, the movement depth change of the probe is a superposition waveform curve of the movement depth change of the two piezoelectric ceramics. Therefore, surface fluctuation detection and hardness detection of the to-be-detected surface are realized. According to the invention, the motion depth changes of the two piezoelectric ceramics are controlled to be non-interfering motion depth changes, so that the motion depth change (i.e., sinusoidal vibration) for detecting the viscosity of the surface to be detected and the motion depth change for feedback tracking of the appearance of the surface to be detected are two non-interfering motion depth changes. And the stroke of feedback tracking of the to-be-measured surface topography is ensured. Therefore, under the condition that the scanning speed of the atomic force microscope is high, a sample with large surface fluctuation can be measured.

The invention relates to a very-low-frequency sinusoidal vibration mechanism and a water sound pressure calibration device, and the mechanism comprises a servo motor which is used for providing rotation power; the harmonic reducer is connected with an output shaft of the servo motor and is used for reducing the rotating speed and improving the output torque; the driving shaft is connected with the output end of the harmonic reducer, and a sine curve guide groove is formed in the driving shaft; and the guide crank is provided with a tip part matched with the sine curve guide groove in the driving shaft, and the tip part is matched with the sine curve guide groove to enable the rotary motion of the driving shaft to be converted into the linear motion of the guide crank. According to the sine vibration mechanism, lower vibration frequency and higher stability can be generated, the harmonic reducer and the servo motor are introduced into the sine vibration mechanism for driving for the first time, lower frequency can be generated, and the influence of waveform distortion degree introduced by the sine vibration mechanism is reduced.

The invention discloses an optical material defect identification method for vibration deformation measurement through a time average holographic method, and relates to the technical field of digital holographic measurement, the optical material defect identification method specifically comprises the following steps: simplifying an optical material into a circular thin plate, and obtaining the influence of the surface defect of the circular thin plate on the amplitude; obtaining the influence relation of the exposure time change of the circular thin plate under sinusoidal vibration excitation on the reconstruction effect of the time-averaged hologram; constructing a digital holographic reflective optical path; respectively shooting time average holograms before and after vibration deformation of the to-be-detected sample; extracting interference information of the to-be-detected sample; inverse Fourier transform is carried out to obtain complex amplitude distribution, phase extraction is carried out, and the phase difference before and after vibration deformation is calculated; and based on the phase difference before and after the vibration deformation, obtaining the occurrence position of the surface defect of the to-be-detected sample to realize defect identification. According to the invention, the identification of different types of defects is realized by positioning the areas with obviously abnormal phase difference stripes.

The application provides an aero-engine accessory sine vibration endurance test time calculation method, and belongs to the technical field of aero-engines. The method comprises the following steps: determining the structural parameters of an aero-engine and the range of high and low pressure rotating speeds; determining the load profile and vibration value of the engine vibration environment; determining the sine vibration fatigue frequency of the aero-engine accessory; determining the resonance frequency of the accessory product; obtaining the fixed frequency acceleration total equivalent test time of the resonance frequency point; obtaining the acceleration vibration scanning cycle test time; and determining the vibration endurance test time according to the fixed frequency acceleration total equivalent test time and the acceleration vibration scanning cycle test time. The method provided by the application solves the problem that the current sine vibration endurance time determination is not scientific and reasonable, and improves the effectiveness and accuracy of the vibration endurance test of the engine accessory.

The application provides a whole-satellite vibration reduction device based on a vibration absorption plate and a crab claw truss structure, which is composed of a bottom plate, a crab claw truss and a vibration absorption plate. The crab claw truss is connected with light-weight joints through hollow carbon fiber square tubes (containing inclined upper rods, horizontal rods, vertical rods and the like), and bears a 100L large-capacity storage tank through a storage tank flange. The vibration absorption plate is connected with the inclined upper rods of the truss through a single-point connection of an in-plate embedded part and a connection joint in a non-stiffener structure of a 20mm-thick honeycomb plate and a 0.3mm aluminum skin, forms a minimum rigidity point in the axial direction of the storage tank, and concentrates the absorption of sinusoidal vibration energy through the "drum skin effect". The bottom plate serves as a basic support and is rigidly connected with the main load-bearing rods of the truss through joints to ensure the stability of mechanical conduction.

The application discloses a motor haptic vibration generation method and device based on a second-order damping model and a storage medium. A vibration parameter structure body and a motor vibration operation state structure body are predefined; a vibration triggering instruction for a target motor is received, vibration parameters corresponding to the triggering instruction are loaded to the vibration parameter structure body of the target motor, and a vibration activation flag is set; if it is detected that the vibration activation flag of the target motor is in a set state, a sinusoidal vibration signal with an exponential decay envelope is calculated and generated based on a second-order under-damped vibration model; the sinusoidal vibration signal is discretized, updated and amplitude-limited to obtain a q-axis current vibration component; the q-axis current vibration component is superimposed on an original torque current instruction in FOC vector control to generate a q-axis current reference value of a current loop, so as to drive the target motor to output corresponding haptic vibration. The scheme has the advantages of reproducibility, configurable parameters, more natural vibration feeling and better system friendliness.

The invention provides a method for stably controlling the surface quality of a low-carbon high-nitrogen steel continuous casting round billet, and belongs to the technical field of ferrous metallurgy, the method comprises the following steps: (1) controlling the degree of superheat of a first furnace for casting of low-carbon high-nitrogen steel refined molten steel to be 25-35 DEG C, controlling the temperature of a continuous furnace to be 15-25 DEG C, and controlling the ratio of V / Ti to be 2.5-3.5; (2) full-hydraulic non-sinusoidal vibration is carried out, and As is 0.30-0.45; (3) the consumption of the nano TiO2-ZrO2 composite casting powder is 0.85-0.95 kg / t, and the thickness of a liquid slag layer is 9-11 mm; (4) secondary cooling reference specific water flow is 0.30-0.31 L / kg, and an online nitrogen saturation model is gt; when the temperature is 0.95, the temperature is automatically reduced by 5-10%; (5) the pulling speed is 1.40-1.50 m / min; and (6) the pit entering temperature of a round billet with the diameter phi being 220 mm is larger than or equal to 550 DEG C, and slow cooling is conducted for 20 h or longer. The first-pass yield of the obtained casting blank is greater than or equal to 99.9%, and high-strength structural steel can be directly rolled.

The present application relates to a kind of control methods of protecting slag and 210 square high-carbon steel continuous casting billet surface slag groove, control method includes: before replacing crystallizer copper pipe, arc is carried out to the roll of enough;Crystallizer is vibrated and debugged, crystallizer uses sinusoidal vibration mode, the negative slip displacement amount of crystallizer vibration is set to 3-4mm, negative slip time is set to 0.12-0.18s, ensure that the vibration offset of crystallizer in X, Y, Z three directions is in the preset range;Enter continuous casting production link, add protecting slag, its binary basicity is set to 0.5-0.8, melting point is set to 960 ℃±30 ℃, viscosity is set to 0.20±0.05Pa·s, when the superheat of molten steel <20 ℃, set the pulling speed to 1.15m / min, when the superheat of molten steel is in 20-40 ℃ interval, set the pulling speed to 1.10m / min, when the superheat of molten steel >40 ℃, set the pulling speed to 1.05m / min.The present application can reduce or eliminate the detection rate of bearing steel, grinding ball steel and other high-carbon steel species continuous casting billet slag groove.

The invention provides a construction method and a prediction method for a formant prediction model of a spacecraft component, and the construction method comprises the steps: obtaining the measurement point acceleration response data of the spacecraft component in a sinusoidal vibration test, and constructing a multi-task learning model for predicting a formant, and training the multi-task learning model by using the time-frequency domain feature vector. According to the scheme provided by the invention, the formant deviation condition of the response curve can be predicted in advance in the test process, and the abnormal condition of the product can be judged in time.

The invention provides a multi-split conductor vibration excitation device which is fixedly connected with a split spacer frame body, and the vibration excitation device comprises a housing assembly, the outside of which is fixed with the split spacer frame body; the servo motor 2 is fixed on one side in the shell assembly, and a main shaft of the servo motor 2 is perpendicular to the split spacer frame body; bearings at the two ends of the first gear shaft 4-1 are fixed to the shell assembly, and the first gear shaft 4-1 is parallel to a main shaft of the servo motor; the first pinion 5-1 is fixed on a main shaft of the servo motor 2; the second pinion (5-2) is fixed at one end, close to the servo motor (2), of the first gear shaft (4-1) and is meshed with the first pinion (5-1); the first eccentric wheel 7-1 is fixed at the other end of the first gear shaft 4-1; the energy supply control assembly is electrically connected with the servo motor; the excitation device generates excitation force peak value and sinusoidal vibration with adjustable frequency by changing the rotating speed of the servo motor, and is used for gentle breeze vibration simulation test, vibration suppression and line deicing operation of a multi-split conductor of a real-type line.

The application provides a kind of accumulator membrane box sine vibration test condition design method and device, comprising: obtaining the low-frequency vibration acceleration flight telemetry time domain data of accumulator membrane box and accumulator shell installation interface;Select typical transient time domain data segment to carry out low-frequency band-pass filtering, and the filtered data is processed by impact response spectrum equivalent sine;The data is processed by maximum envelope;According to the impact response spectrum equivalent sine envelope data of typical transient time, design acceptance level sine vibration test condition;Based on acceptance level sine vibration test condition, determine the identification level sine vibration test condition, complete accumulator membrane box sine vibration test condition design.The sine vibration test condition of the accumulator membrane box is obtained by the design when the ground vibration test is carried out alone, which can improve the over-test condition of the accumulator membrane box caused by the ground vibration test of the accumulator as a whole, and reduce the structure design difficulty and ground over-test risk of the accumulator membrane box.

The invention belongs to the technical field of metallurgical machinery, and particularly relates to a crystallizer non-sinusoidal vibration method, device and equipment, a medium and application. A speed curve in each period comprises a horizontal straight line AB, an oblique straight line BC, an oblique straight line CD and a horizontal straight line DE which are sequentially connected, and a driving device of the crystallizer is controlled through a curve function to only impact twice in one vibration period. A non-sinusoidal vibration mode is constructed through a four-section function, and a crystallizer driving device is controlled. The non-sinusoidal vibration curve constructed by the method has the characteristics of small vibration acceleration, relatively constant vibration acceleration and small impact on equipment at the same pulling speed; only two times of impact are carried out in one vibration period, so that the number of times of impact is reduced to the minimum, and the method is finally used for design guidance of a non-sinusoidal vibration mode of the crystallizer. The four-section non-sinusoidal vibration curve function constructed by the invention is simple in form and easy to realize, and can meet different vibration requirements.

The application discloses a kind of reuse spacecraft sinusoidal vibration test scanning rate calculation method and system, comprising: selecting observation point on spacecraft, obtaining scanning rate and frequency domain sinusoidal vibration condition;The frequency domain sinusoidal vibration condition is converted into time domain sinusoidal vibration condition;Time history analysis is carried out to observation point, and stress time domain response is obtained;The rainflow counting is carried out to the stress time domain response, and rainflow counting result is obtained;Single fatigue damage of observation point is calculated;M fatigue damage of observation point is calculated;The scanning rate of the observation point is adjusted, and the scanning rate when single test fatigue damage is equal to M fatigue damage of the observation point is calculated;The relationship between scanning rate and spacecraft reuse frequency is obtained, for calculating the test scanning rate corresponding to any reuse frequency.The application realizes once test to check multiple flights, avoids the damage risk of multiple tests to product, and can provide support for the development of reusable spacecraft.

The invention relates to the technical field of vibration measurement and metering, and discloses a digital metering system and method for monocular vision multi-parameter vibration measurement, and the system comprises a display screen which is connected with a digital video library and is used for outputting a sinusoidal vibration video in the digital video library. The visual imaging unit is fixed to the digital video library through a fixing frame, the visual imaging unit is connected with the processing display unit and sends collected motion sequence images to the processing display unit, and the processing display unit establishes an uncertainty evaluation model according to the motion sequence images and evaluates the measurement uncertainty of the motion sequence images. And comparing the output standard quantity value with the measurement quantity value, establishing an uncertainty propagation chain according to each uncertainty component, obtaining a measurement error and expansion uncertainty of monocular vision, and storing and displaying a traceability result. The method can be applied to performance verification and metering of monocular vision measurement systems formed by visible light imaging units of different models and manufacturers; metering is simple, flexible and efficient, and the system cost is low.

A device for mixing and / or conditioning powdered materials by fluid-free fluidization comprises a movable container that defines a first processing chamber for receiving powdered material; a vibration generator by which, during operation, a powdered material located in the processing chamber can be subjected to a vibration, in particular a sinusoidal vibration; and a control unit that controls the vibration generator.

The invention belongs to the technical field of metallurgy, and particularly relates to an efficient and energy-saving intelligent control method for slab continuous casting. Comprising the following steps that S1, secondary cooling control is conducted, specifically, casting blank surface temperature field information is collected in real time, and partition cooling control is conducted on a casting blank based on a dynamic water distribution model; s2, vibration control is conducted, specifically, according to the real-time pulling speed, a crystallizer is controlled to conduct non-sinusoidal vibration through an online vibration parameter adjusting model; s3, multi-mode electromagnetic field control, wherein electromagnetic fields of different modes are applied to the crystallizer area, the secondary cooling area and the tail end area correspondingly; s4, multi-parameter breakout early warning is conducted, specifically, real-time diagnosis and early warning are conducted on breakout based on the multi-source signal fusion and early warning model; and S5, dynamically matching the performance of the casting powder: dynamically matching the viscosity of the casting powder according to the real-time pulling speed. According to the method, a fixed water distribution model in the prior art is corrected through the dynamic water distribution model, and the secondary cooling area is independently controlled in a partitioned mode, so that the cooling effect and uniformity are improved, and the temperature difference is reduced.

This invention discloses a design method for an inertial navigation system (INS) vibration isolation system for helicopter vibration environments, belonging to the technical field of INS vibration isolation system design for helicopter vibration environments. The method includes the following steps: Step 1, based on the differential equation of motion of a single-degree-of-freedom isolation system under basic acceleration excitation, constructing an analytical model of the root-mean-square acceleration (RMS) of the INS vibration isolation system under SOR excitation; Step 2, based on this model, analyzing the variation of the RMS acceleration and response power of the system with the natural frequency of the isolation system under sinusoidal vibration, broadband random vibration, and both superimposed excitation conditions, and determining the optimal natural frequency of the isolation system according to the principle of minimizing response. This invention can effectively reduce the maximum error and standard deviation of the yaw, pitch, and roll angles of the INS, verifying the effectiveness of the design method.

This invention provides a non-destructive and rapid vibration characteristic testing method for automobiles that can detect structural differences from a standard automobile structure. [Solution] The automobile vibration characteristic test method according to the present invention involves inputting sinusoidal vibrations with the same frequency but a phase difference to two vibration input points 111a and 111b on the automobile body 100 to be tested, and measuring the response waveform of the vibration generated in the excited automobile body 100 in synchronization with the input waveform of the vibration input to the vibration input points 111a and 111b. The amplitude of the measured response waveform and the phase difference of the input waveform of the vibration input to the vibration input points 111a and 111b are determined as the response characteristics of the excited automobile body. The response characteristics obtained for the automobile body 100 to be tested are compared with the response characteristics when a standard structure automobile body 100 is excited with a phase difference, thereby detecting the structural differences between the automobile body 100 to be tested and the standard structure automobile body 100.

The invention belongs to the technical field of aero-engines, and discloses a compilation method and system for an environment vibration test spectrum of an aviation auxiliary power plant, and the method comprises the steps: compiling the vibration test spectrum of the auxiliary power plant, and superposing the random excitation of an airplane and the sine excitation of the auxiliary power plant in the vibration test spectrum of the auxiliary power plant, obtaining an initial environment vibration test spectrum; and correcting the initial environment vibration test spectrum according to the maximum unbalance test data of the auxiliary power device to obtain a random superposition sinusoidal vibration test spectrum. The stochastic superposition sinusoidal vibration test spectrum compiled by the method comprises the stochastic excitation of the airplane and the sinusoidal excitation of the auxiliary power device, so that during the vibration test, the auxiliary power device can be in a non-working state, and the real vibration environment of the auxiliary power device can be fully and accurately simulated when the auxiliary power device is installed.

The application belongs to the technical field of fiber-optic gyroscope, and particularly relates to a fiber-optic gyroscope vibration error compensation method and an inertial measurement unit based on acceleration. A model of vibration acceleration and fiber-optic gyroscope output error under vibration conditions is established. The model is based on normal strain, a variation amount of a fiber dielectric impermeability tensor, a variation amount of the refractive index of light in the fast axis direction, a variation amount of the phase corresponding to the sensitive axis of the fiber-optic gyroscope, and a quantitative relationship between the variation amount of the phase and the fiber fast axis direction and the micro-section fiber length. The stress received by the fiber and the phase difference equivalent value of the fiber ring are obtained, and a linear relationship between the phase difference equivalent value and the fiber-optic gyroscope to-be-compensated angular velocity is determined. A relationship of converting the vibration acceleration to the to-be-compensated phase is established. The required compensation coefficient is calibrated in combination with a sinusoidal vibration test to compensate for the fiber-optic gyroscope vibration error. The application can realize the vibration error compensation of the fiber-optic gyroscope without adding additional devices, and improves the real-time performance and accuracy of the error compensation.