19results about How to "Has engineering practical value" patented technology

The invention belongs to the technical field of hypersonic wind tunnel tests, and discloses a test evaluation device and method for a slender body appearance attitude control jet flow aerodynamic interference effect. The test evaluation device comprises a spray pipe bracket, a sieve-shaped core pipe and a balance which are sequentially connected from front to back; the balance adopts an annular structure, a semiconductor strain gauge is pasted on a sensitive element of the balance, the rear end of the balance is connected with a jet-flow supporting rod, and the jet-flow supporting rod is provided with a jet-flow air inlet; a spray pipe is fixed on the spray pipe bracket; a spray pipe outlet penetrates out of the aircraft model; a jet flow pipeline which sequentially penetrates through the jet pipe support, the sieve-shaped core pipe, the aerodynamic force measuring balance and the jet flow supporting rod is arranged on the central axis of the aircraft model. The test evaluation method comprises the steps of conventional force measurement test, jet flow force measurement test, determination of influence quantity of jet flow interference, jet flow supplementary force measurement test, determination of jet flow medium parameters, and establishment of a jet flow state table of the attitude control jet flow engine of the slender aircraft. And technical support is provided for design and installation of the attitude control jet engine of the slender aircraft.

The invention belongs to the technical field of wind tunnel tests, and discloses a dual-body track capturing wind tunnel test method considering an unsteady effect of a disturbing flow field. The invention discloses a dual-body capture trajectory wind tunnel test method considering an unsteady effect of a disturbing flow field. The method comprises the following steps: determining a dynamic derivative needing to be simulated; calculating a dynamic derivative under the disturbing flow field by adopting a numerical forced oscillation method; designing and manufacturing a test device; installing a test device; starting the separated body model jet flow simulation device; starting a wind tunnel, and performing a double-body track capturing wind tunnel test; and analyzing and processing dual-body capture track wind tunnel test data. According to the dual-body capture track wind tunnel test method considering the unsteady effect of the disturbing flow field, dynamic characteristic influence quantity taking a key dynamic derivative as a characterization parameter is coupled in a capture track test process with relatively high precision, so that dual-body dynamic aerodynamic characteristics and separation tracks which are closer to a real separation process are obtained; the test simulation accuracy is improved, and the engineering practical value is achieved.

The invention belongs to the technical field of wind tunnel tests, and discloses a double-body track capturing wind tunnel test method suitable for multi-jet interference. The invention discloses a double-body track capturing wind tunnel test method suitable for multi-jet interference. The method comprises the following steps: determining a segmented continuous simulation test scheme; designing and manufacturing a test device; installing a test device; carrying out a double-jet-flow capture track wind tunnel test; carrying out a three-jet-flow capture track wind tunnel test; carrying out a single jet flow capture track wind tunnel test; and analyzing and processing segmented test data. According to the double-body capture track wind tunnel test method suitable for the multi-jet-flow interference, segmented continuing is carried out according to the jet flow opening time in a multi-jet-flow complex interference scene, whole-process simulation of a double-body complex separation process with the multi-jet-flow interference is achieved, and the method has engineering practical value.

The invention discloses a decoupling design method and system for reliability optimization of an angular contact ball bearing. The method comprises the following steps: determining initial design parameters of the angular contact ball bearing; constructing a reliability optimization design model which takes maximization of the rated dynamic load as a target and comprises probability reliability constraint processed by a penalty function; constructing a design variable and failure probability mapping agent model, specifically, identifying and quantifying uncertainty parameters, constructing a quasi-statics model and a limit state function, calculating the failure probability of a sample point through a probability reliability method, and training the agent model taking the design variable as input and the failure probability as output; and based on the proxy model, solving the reliability optimization design model by using an optimization algorithm, and outputting optimal bearing design parameters. According to the method, the reliability analysis process and the optimization iteration process are decoupled, so that the optimization efficiency is greatly improved while the design robustness is ensured.

The invention belongs to the technical field of high-speed wind tunnel tests, and discloses a high-speed jet flow wind tunnel large-scale model velocity pressure simulation test method, which comprises the following steps: installing a model at an initial state position; calculating the total pressure P0 of the wind tunnel; the injection pressure P0p is calculated; starting a high-speed free jet wind tunnel; transforming the model to a second state; performing flow field parameter adjustment according to the model state, and performing static pressure matching fine adjustment; continuing to transform the model state until all data are collected; and closing the high-speed free jet wind tunnel. According to the high-speed jet flow wind tunnel large-scale model velocity pressure simulation test method, under the condition that the Mach number M is determined, the wind tunnel total pressure P0 and the injection pressure P0P are selected, accurate simulation of the Mach number M and the velocity pressure is achieved, and the method has engineering practical value.

The application belongs to the technical field of wind tunnel test, and discloses a semi-mould loading device control system and a control method thereof. The semi-mould loading device control system is used for controlling four electric cylinders of the semi-mould loading device, and realizes Fx, Fy, Mx, My and Mz value loading of the semi-mould balance through the four electric cylinders. The semi-mould loading device control system takes a main control computer and an embedded ARM controller as a core control unit, is responsible for collection and processing of all signals, controls a running position of the electric cylinder, and has a prompt function of motion and state. The semi-mould loading device control system comprises the main control computer, the embedded ARM controller and control circuits corresponding to the electric cylinders. The control method comprises power-on self-checking of the control system, load rationality inspection, calculation of a tensile and compressive force sensor target value, current loading direction loading, current loading direction unloading, loading direction replacement and completion of all load group loading. Through automatic control, simple and convenient operation is realized.

The utility model discloses a kind of inclined plane embedded part auxiliary positioning device, belong to building construction technical field, including support, angle height adjusting unit and auxiliary frame;The support is fixed in the preset position of inclined plane embedded part;The angle height adjusting unit is set on support, including several groups of adjusting assembly along front-back direction distribution;The adjusting assembly includes the bracket of height and front-back position adjustable;The auxiliary frame is used for fixed inclined plane embedded part;Auxiliary frame is set on the bracket of several groups of adjusting assembly, and the position and horizontal inclination angle of auxiliary frame change with the height and front-back position adjustment of each bracket.The utility model can realize height and angle adjustment, and can be reused, improve construction quality and efficiency.

The application provides a low-profile duplex filter antenna and belongs to the technical field of wireless energy transmission.The low-profile duplex filter antenna comprises an upper metal floor, a dielectric substrate, a lower metal floor, a cavity column, a perturbation via and a suppression via; the lower metal floor is arranged on the lower surface of the lower dielectric substrate; the upper metal floor is arranged on the upper surface of the dielectric substrate; the cavity column penetrates through the upper metal floor, the dielectric substrate and the lower metal floor and surrounds a substrate integrated waveguide cavity; the perturbation via and the suppression via penetrate through the upper metal floor, the dielectric substrate and the lower metal floor; a cross-shaped groove is etched in the center of the upper metal floor; two complementary split ring resonator grooves with different diameters are etched at the connection between the circular cavity and the two side rectangular cavities of the upper metal floor; two feed lines are led out from the two ends of the upper metal floor. The antenna has the characteristics of low profile, is easy to integrate, and simultaneously reduces the manufacturing cost of the antenna and facilitates processing and manufacturing.

The present application belongs to the technical field of high-speed wind tunnel test, and discloses a high-speed transverse gas jet test device and test method. The test device comprises a test model located in the test section of a high-speed wind tunnel, the inner cavity of the test model is sequentially fixed with a balance and a support rod from front to back, the rear section of the balance is sleeved with a heat insulation sleeve, a gas generator is installed on the support rod, and the rear section of the support rod is connected with a high-speed wind tunnel support mechanism. The test device further comprises a fuel storage tank and an air storage tank which are placed outside the high-speed wind tunnel and provide fuel and air for the gas generator, and an ignition controller of the gas generator. The test method establishes a safety interlocking test timing, ensures the reliability and safety of the high-speed transverse gas jet test, provides a stable time of the hot jet of 10s order, a stable chamber pressure, non-toxic and harmless gas, can simulate the specific impulse, temperature, specific heat ratio and secondary combustion effect of the real high-speed aircraft jet gas, and has engineering practical value.

The application belongs to the technical field of wind tunnel test, and discloses a three-axis force loading device for flexibility coefficient test of an elastic model. The device is a square frame body, comprising a base assembly, a support section assembly and a mounting plate assembly which are stacked in sequence from bottom to top, and a Y-direction sliding frame and an X-direction sliding frame which are vertically crossed and are installed on the inner wall of the mounting plate assembly; the loading assembly is a cylindrical rod body which is located on the vertical central axis of the device, and the lower end of the loading assembly is fixed on the base assembly, and the upper end of the loading assembly extends out of the mounting plate assembly at the intersection of the X-direction and Y-direction sliding frames; the X-direction and Y-direction driving assemblies respectively drive the X-direction sliding frame to slide along the X-direction and the Y-direction sliding frame to slide along the Y-direction through linear guide rails, and drive the upper end of the loading assembly to perform a conical column movement to adjust the loading direction, and meanwhile, the top end of the loading assembly is driven by a driving motor installed on the base assembly to extend upward to increase the loading force value. The device can achieve the measurement target of nine-component flexibility coefficients of the elastic model, and has engineering practical value.

The present invention belongs to the technical field of structural health monitoring and the field of machine learning, and discloses a real-time monitoring method for bolt tensile damage based on acoustic emission technology, including conducting a bolt tensile damage experiment; drawing a load curve of a bolt tensile damage experiment; processing acoustic emission signal data; establishing a bolt tensile damage prediction model; and predicting the stage of bolt tensile damage. The real-time monitoring method for bolt tensile damage uses acoustic emission technology to ensure the real-time nature of the monitoring signal, and can check the damage of the bolt even when large equipment is in working condition; multiple tensile tests are conducted on the same type of bolt material, and experimental parameters of different tensile stages are extracted, and the experimental parameters are averaged by grouping, normalizing, and secondary grouping, and the mean, standard deviation, skewness, and kurtosis of the secondary grouping are calculated to obtain the trend of the monitoring signal changing over time within a period of time, and the trend is used to predict whether the bolt has the risk of breaking and falling off, which has practical engineering value.

The invention belongs to the technical field of shaft part positioning, and particularly relates to a shaft phase cam positioning structure. The shaft type phase cam positioning structure comprises a female cam and a male cam, a first cam hole is formed in the female cam, the male cam is inserted into the first cam hole, and a plurality of arc-shaped positioning grooves which are eccentrically formed are evenly distributed in the inner wall of the first cam hole according to the circumference; a plurality of eccentric arc-shaped positioning protrusions are evenly distributed on the outer wall of the male cam in the circumferential direction, and the arc-shaped positioning grooves and the arc-shaped positioning protrusions are the same in number and matched in a one-to-one mode. According to the shaft type phase cam positioning structure, the arc-shaped positioning groove and the arc-shaped positioning protrusion which are provided with the multiple positioning points are matched for positioning, the arc-shaped positioning groove and the arc-shaped positioning protrusion are eccentrically arranged, circumferential positioning and axial positioning of paired shaft type parts are achieved in a manner of machining eccentric circles, and the shaft type phase cam positioning structure has engineering practical value.

The invention belongs to the technical field of planetary roller screw testing, and discloses a heavy-load planetary roller screw traction loading method and device. According to the loading method, the planetary roller screw and the hydraulic cylinder are arranged on the upper side and the lower side of the test bed respectively; a driving motor is arranged on the same side of the planetary roller screw; the driving motor is connected with the ball screw through the pulley block and a steel rope arranged on the pulley block in a sleeving manner, so that pulling force is only provided for the planetary roller screw; a simulation instruction is output to a console to control a driving motor to drive a steel rope to simulate different stress conditions of the planetary roller screw; a test bed of the loading device is of a central symmetry structure, a driving motor and a planetary roller lead screw are symmetrically arranged on the test bed along the center, steel ropes are symmetrically distributed on the two sides of a nut to simulate the stress conditions of lug plates on the two sides, and a hydraulic cylinder is used for balancing loads on the two sides. According to the loading method and device, the total length and moment arm of the testboard are reduced, the transverse flexibility and total deformation are reduced, and the total rigidity of the testboard is improved.

A method for identifying meshing faults of axle gearboxes of rail engineering vehicles is disclosed. In the method, a monitoring signal X of the axle gearbox of a rail engineering vehicle is collected, and a sparse dictionary Φ is constructed by using Q-switched wavelet transform. * The harmonic signal and the impulse signal in the monitoring signal X are sparsely represented, and the objective function of sparse decomposition is established and the objective function is solved by the Lagrangian contraction algorithm to decompose the monitoring signal X into the harmonic signal and the impulse signal. H The pulse index and the skewness index are extracted from the axle gearbox. When the pulse index is within the first range and the skewness index is within the second range, the axle gearbox is considered to be normal. Otherwise, a meshing fault occurs.

The present application belongs to the technical field of model test, and discloses a large low-temperature equipment test model transfer device and a transfer method. The model transport vehicle of the transfer device drives the test section and the model through a lifting tool, and translates back and forth between the chamber and the temperature adjusting room along the track to perform low-temperature state transfer and normal-temperature environment operation. The transfer method comprises adjusting the environmental dew point, performing transfer, replacing the test model condition, and returning the test model. The transfer device and the transfer method can transfer the test model from the chamber to the temperature adjusting room through the drying hall in a low-temperature state, and after completing the replacement of the test model condition in the temperature adjusting room, the test model is transferred back to the chamber of the equipment. On the basis of maintaining the low-temperature environment of the large low-temperature equipment, the transfer device and the transfer method realize the normal-temperature replacement of the test model condition, improve the test efficiency of the large low-temperature equipment, reduce the energy loss of liquid nitrogen, and can be applied to other large low-temperature equipment which needs to carry out internal condition replacement.

The invention belongs to the technical field of mechatronics, and discloses a rail type transmission mechanism and a transmission method thereof. The transmission mechanism comprises a rotating workpiece and a supporting workpiece which are sequentially connected through a rotating shaft, and the rotating workpiece and the supporting workpiece are in cambered surface fit; a linear rail workpiece is arranged on the side face of the supporting workpiece. A linear rail I is arranged on the linear rail workpiece. A linear track II is arranged in the rotary workpiece; an actuating rod is inserted into the intersection of the linear track I and the linear track II; and a driving rod of the linear stepping motor is fixedly connected with the actuating rod. According to the transmission method, a driving rod of a linear stepping motor drives a moving rod to linearly move along a linear rail I, a rotating workpiece is forced to deflect around a rotating shaft, and linear motion of the linear stepping motor is converted into rotating motion of the rotating workpiece. According to the rail type transmission mechanism and the transmission method thereof, the mechanical transmission efficiency and precision are improved, the machining and manufacturing difficulty is lowered, the requirement of transmission for installation space is lowered, and the rail type transmission mechanism and the transmission method have engineering practical value.

The application discloses a kind of blade disc structure connecting interface in-situ relationship measurement method, mainly including electric cylinder driving system, support frame, blade, displacement measuring interferometer and data processing system;Electric cylinder driving system is composed of high-precision straight electric cylinder, force sensor and elastic rope etc., according to actual situation, the installation quantity of electric cylinder system is adjusted, position, to ensure that when restoring real working condition connecting interface contact state, as far as possible adapt to the complex measurement needs of different blade shapes, whether with blade crown / shoulder etc.;Displacement measuring interferometer is used to obtain the displacement value of multiple calibration points at blade root end at nanometer level precision, and the translation and torsion angle of blade root are calculated accordingly, finally the in-situ relationship of blade disc connecting interface is obtained by combining force sensor and the motion amount of blade root.The application can simulate the complex contact state of connecting interface under real working condition of blade disc structure in static environment, and can provide more real situation boundary conditions for vibration test etc..

This invention belongs to the field of hypersonic aerodynamics and discloses a method for predicting hypersonic boundary layer transition based on the numerical solution of the frequency domain Navier-Stokes equations. This method, through the assumption of small perturbations, linearly decomposes the hypersonic flow field into a steady flow field and a perturbed flow field. It eliminates the time differential terms in the time-domain Navier-Stokes equations using complex decomposition, transforming the time-domain Navier-Stokes equations into linear algebraic equations in complex space, thereby simplifying the solution and analysis of the time-domain Navier-Stokes equations. Specifically, it includes three stages: preprocessing, solver, and post-processing. The iterative solution of the frequency-domain Navier-Stokes equations in the solver is the core, including spatial discretization of the frequency-domain Navier-Stokes equations, iterative progression, implementation of boundary conditions, parallel data exchange, convergence judgment, and result output. The hypersonic boundary layer transition prediction method based on the numerical solution of the frequency-domain Navier-Stokes equations of this invention can balance computational efficiency and accuracy, and has practical engineering value.

The present application belongs to the technical field of high-speed wind tunnel test, and discloses a stress deformation compression wedge wind tunnel test model for teaching and a test method thereof. The base of the test model is a stepped base, which is embedded into a high-speed wind tunnel from outside to inside through a stepped matching mode, and the top surface of the base is flush with the wall surface of the test section of the high-speed wind tunnel. An inclined stress deformation panel is fixed on the top surface of the base, and the stress deformation panel faces the high-speed wind tunnel flow. A plurality of pressure measuring holes are formed on the top surface of the base in front of the stress deformation panel to measure the surface pressure distribution of the top surface of the base. The test method comprises determining test related parameters, installing the base, installing pressure sensors, conducting a teaching test, and closing the high-speed wind tunnel. The test model and the test method thereof provide hardware conditions and measurement interfaces for directly displaying flow phenomena caused by shock waves in a high-speed wind tunnel, quickly adjusting shock wave forms, and evaluating boundary layer control strategies, and have engineering practical value.