9results about How to "Has engineering practical value" patented technology

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 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 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.