9 results about "Mockup" patented technology

The application discloses a model box for vibration test of a stepped reinforced soil retaining wall and belongs to the technical field of vibration test model boxes, which comprises a bottom plate, a side plate detachably installed on the bottom plate, a plurality of U-shaped plates slidably installed on the side plate, two arms of the U-shaped plate slidably installed on two opposite side walls of the side plate, a stepped cavity formed by splicing the plurality of U-shaped plates and the side plate, an upper cavity and a lower cavity of the stepped cavity, a cover plate slidably installed on the U-shaped plate at the top of the lower cavity and used for closing the lower cavity, a threaded hole arranged on one arm of the U-shaped plate, a screw threadedly connected in the threaded hole, an accelerometer detachably installed on the screw, and the U-shaped plate comprising a U-shaped part and a connecting part connected with two arms of the U-shaped part. The model box for making a model and the vibration test model box are integrated, so that the stability of the model in the vibration test and the accuracy of the vibration test result are ensured.

This invention relates to the field of computer-aided design technology, and discloses a method and system for replicating printed materials using augmented reality technology. The method includes: reconstructing a dynamic scene encompassing geometric, material, and environmental dimensions through multimodal perception of the physical scene and using physically based rendering material inverse calculation technology; constructing a dynamic parametric design space to achieve real-time binding of virtual elements and reconstructed data, as well as dynamic topology adaptive adjustment; generating a closed loop based on dynamic parameters, and outputting intelligent design units conforming to CAD standards. The system consists of modules for multimodal perception, dynamic scene reconstruction, dynamic parametric design, and closed-loop generation and output. This invention improves design fidelity in non-rigid form carriers and produces digital assets that can be directly used in intelligent manufacturing.

The invention discloses a design method of a turbine disc characteristic simulation piece with bolt hole induced end tooth crack propagation, and belongs to the technical field of aero-engine fatigue fracture tests. The method comprises the following steps: designing an initial shape of a simulation piece dominated by arc end teeth; through double-stage static strength analysis, the characteristic sizes of bolt holes and the like are preferentially and alternately adjusted so as to be matched with a crack-free stress field of a real turbine disc; introducing a surface crack at a dangerous point, and optimizing the crack size by taking J integral of a crack tip and a correction stress gradient from a bolt hole to the crack tip as double standards; an initial defect with the controllable size is machined through the electric spark technology; and finally, on the basis of direct-current potential drop technology monitoring, the crack is prefabricated to the target size from the defect through the fatigue load. According to the invention, high-fidelity simulation of the crack propagation behavior under the structure coupling effect is realized, and a low-cost and high-reliability test means is provided for life prediction and safety evaluation of the turbine disc.

The utility model discloses a ventilation smoke prevention and exhaust core unit hoisting bulk sample structure, which relates to the technical field of smoke prevention and exhaust unit hoisting, and comprises a suspension mechanism, the suspension mechanism comprises a plurality of suspension rods and a supporting plate used for installing a core unit, every two suspension rods form a group, and the two suspension rods in the same group are distributed left and right; the lifting rods are arranged along the central longitudinal section of the same lifting rod, each lifting rod is of a variable-length structure and provided with an adjusting assembly, lifting rings are movably connected to the upper ends of the lifting rods, locking assemblies used for limiting shaking between the lifting rings and the lifting rods are arranged at the upper ends of the lifting rods, and each lifting rod in the same set corresponds to one supporting plate. The lower end of the hanging rod is slidably connected to the supporting plate, the end of the hanging rod is rotationally connected with a cylindrical sliding block, the core unit is installed on the supporting plate, the supporting plate is provided with a sliding groove for the sliding block to slide, and limiting assemblies are arranged in front of and behind a sliding path of the sliding block. The core unit hoisting structure has the effects of prolonging the service life and reducing potential safety hazards.

The invention provides a force thermal load impact test method and device for a turbine blade feature simulation piece, and belongs to the technical field of turbine blades, the method is used for the turbine blade feature simulation piece with a through hole, a first clamping part of the feature simulation piece is fixed to a first support, and a second clamping part is connected with a load displacement assembly; the clamping assembly jointly clamps the two ends of the feature simulation piece, the flame heater faces the feature simulation piece clamped by the clamping assembly, the first temperature measurement assembly measures the surface temperature of the feature simulation piece, and the temperature sensor of the second temperature measurement assembly is located in a through hole of the feature simulation piece and measures the inner wall temperature of the feature simulation piece. The cooling assembly is used for conveying cooling gas into the through hole of the feature simulation piece through the first gas pipeline, and external heating and internal cooling can be performed on the feature simulation piece at the same time through cooperative work of the heating assembly and the cooling assembly, so that a real temperature gradient is simulated, and the accuracy and reliability of a test result are improved.

The application discloses a wheel disc feature structure simulation part design method based on an additive manufacturing idea, and comprises the following steps: firstly, a parameterized model of a wheel disc is established, and stress field data of the wheel disc feature structure is obtained by using finite element analysis means; then, based on the stress field data of the wheel disc feature structure, a MATLAB program is written to obtain a stress gradient space curve; finally, initial cross-sectional dimensions of the simulation part are determined based on test conditions of a testing machine, and a size iteration formula is determined based on the additive manufacturing idea, so that the contour curve of the simulation part is iteratively calculated according to the stress gradient space curve, and the simulation part configuration is determined in combination with the test conditions of the testing machine; compared with the prior art, the method does not need to select a stress gradient path, design an initial configuration of the simulation part and optimize the size of the initial configuration in the whole design process, greatly improves the standardization and normalization of the wheel disc feature structure simulation part design, fundamentally avoids repeated design processes, shortens a design period and improves design efficiency.

The application discloses a turbine blade profile simulation piece design method and a simulation piece test piece, and belongs to the technical field of aerospace engines. According to the method, the turbine blade is divided into sections, the temperature and stress of each section dangerous point are obtained, and the strength reserve coefficient is calculated. The section corresponding to the minimum strength reserve coefficient is selected as the dangerous section. The selected dangerous section is the weakest section in the section division, so that the designed simulation piece can fail under the same physical mechanism as the real blade. Therefore, the creep life and fracture data obtained from the simulation piece test can truly reflect the creep performance of the turbine blade, greatly improving the accuracy of life prediction. Meanwhile, the worst "strength-stress" matching section can be directly pointed out, and targeted measures can be taken in the subsequent iterative design process.

The invention discloses an anti-deformation casting method for an evanescent mode deep and long hole casting, and relates to the technical field of casting of evanescent mode castings. S1, simulation prediction; s2, simulation optimization is carried out; s3, making a model; s4, coating the model; s5, sand filling and vibration compaction are carried out; s6, sand pressing and negative pressure sealing are conducted; s7, pouring forming is conducted; and S8, detecting and correcting. According to the anti-deformation casting method for the evanescent mode deep and long hole casting, the steps of simulation prediction and simulation optimization are added, the accuracy of deformation prevention and control can be greatly improved, distribution of a temperature field and a stress field is simulated in combination with professional software, a temperature difference peak value area and a stress concentration part can be accurately positioned, and shrinkage deformation data can be quantified; therefore, iterative optimization of the casting head layout based on the simulation result is facilitated, the deformation risk caused by uneven solidification is avoided in advance, scientific data support is provided for the subsequent process, and in the subsequent detection and correction process, through combination of initial detection and fine detection, unqualified parts can be precisely processed.

This invention discloses a superconducting magnet and simulation device for plasma confinement. The superconducting magnet includes: a frame on which superconducting coils are mounted, the superconducting coils including a central coil and end coils; a cooling medium tank, a cold shield, and a vacuum Dewar inner cylinder are sequentially arranged outside the frame; a superconducting power supply, including a first superconducting power supply and a second superconducting power supply, the first superconducting power supply simultaneously supplies power to the central coil and end coils, and the second superconducting power supply supplies power to the end coils when needed; a protection diode connected in parallel across the two ends of the central coil and the two ends of the end coils; a radial lifting rod disposed on the outside of the frame; and an axial lifting rod parallel to the axis of the frame. This invention not only achieves adjustable magnetic field uniformity but also effectively ensures the safety of the superconducting magnet in the event of magnet quenching, while reducing the impact of heat leakage while meeting the protection requirements for lifting and transportation.