23 results about "Mockup" patented technology

The invention relates to the technical field of engines, and discloses a clamping device and a test method for a composite material casing installation edge simulation piece, the clamping device for the composite material casing installation edge simulation piece comprises a supporting piece, the surface of the supporting piece is used for placing a simulation piece; the first limiting piece is located on the simulation piece, the first limiting piece is connected with the supporting piece through a first fixing piece, a limiting space is formed between the first limiting piece and the supporting piece, and the first side edge of the simulation piece is located in the limiting space; the second limiting piece is located on the supporting piece, one end of the second limiting piece is connected with the supporting piece, the other end of the second limiting piece abuts against the second side edge of the simulation piece, and the length of the second side edge is larger than that of the first side edge. According to the invention, precise fixation of the simulation piece is realized, the operation process is simplified, the simulation piece is protected, the reliability and efficiency of the test are improved, and the problems of poor clamping precision and complex operation of a clamping device in the prior art are solved.

A ground-based wing mockup station is provided. The mockup station comprises a primary support structure removably coupled to a floor and a wing mockup coupled to the primary support structure. A secondary support structure configured to suspend the wing mockup over the floor from the primary support structure. A payload pylon mockup is coupled to the wing mockup, wherein the payload pylon mockup is configured to hold an apparatus. The primary support structure, secondary support structure, wing mockup, and payload pylon mockup are configured to support a weight at least equal to the apparatus.

The utility model belongs to the field of aircraft landing gear structural strength tests, and particularly relates to a landing gear wheel fake part for a strength test of an integrated lever loading system. The wheel fake part comprises a lever wheel fake part body which comprises a wheel fake part body middle section, a wheel fake part body left section and a wheel fake part body right section, wherein the wheel fake part body left section and the wheel fake part body right section are symmetrically arranged on the left side and the right side of the wheel fake part body middle section. The two vertical loading joints are respectively hinged to lug holes in the end parts of the left section and the right section of the airplane wheel fake piece main body through bolts; the two lateral loading connectors are fixed to the upper ends of the front side and the rear side of the middle section of the airplane wheel fake part body through bolts respectively. The fake wheel main shaft sleeve is welded to the lower end of the middle section of the airplane wheel fake piece main body, the fake wheel main shaft sleeve is sleeved with a course loading shaft sleeve, and double-lug connectors are arranged at the two ends of the course loading shaft sleeve; the two ends of each course loading pull rod are provided with single-lug connectors, and the single-lug connectors of the two course loading pull rods are hinged to the double-lug connectors at the two ends of the course loading shaft sleeve.

The application discloses a design method of a thin-walled structure feature simulation piece considering a load transmission path, and comprises the following steps: extracting geometric features and load transmission path features of a thin-walled structure, so as to facilitate subsequent construction of a preliminary simulation piece and provide a prerequisite for realizing mechanical equivalence of the feature simulation piece and the actual thin-walled structure at a fatigue key position; constructing a preliminary simulation piece based on the geometric features and the load transmission path features of the thin-walled structure; establishing a parameterized geometric model based on the preliminary simulation piece, so as to facilitate subsequent iteration; taking stress distribution at an examination position and original structure equivalence as a target, iteratively optimizing geometric parameters of the geometric model, so as to output a feature simulation piece, so that the stress distribution of the feature simulation piece is equivalent to the original structure and is closer to the stress state of the original structure.

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.

The application discloses an aero-engine CMC turbine guide vane simulation piece design and test method, comprising the following steps: S1: establishing a turbine guide vane assembly finite element model; S2: setting the interaction boundary conditions between each part in the turbine guide vane assembly, and applying temperature and pressure boundary conditions according to the specified working condition; S3: setting the lay-up scheme and material parameters of the CMC turbine guide vane; S4: performing finite element simulation solving of the model, obtaining the stress distribution in the model, and determining the stress concentration area; S5: calculating the stress concentration coefficient one of the stress concentration area; S6: performing feature simplification and stress analysis of the stress concentration area, designing the simulation piece according to the feature simplification result, and then performing tool design and simulation piece test according to the stress analysis result, so as to obtain the stress distribution of the simulation piece; and S7: confirming whether the design consistency of the simulation piece and the CMC turbine guide vane meets the design requirement.

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 provides an APU fake part and a design method thereof. The front right column body and the front left column body, the front left column body and the rear column body, and the front right column body and the rear column body are connected through a front horizontal rod, an outer horizontal rod and an inner horizontal rod respectively, a triangular connector is arranged above a triangle and connected with a course rod, and the course rod is connected with the rear column body, the front right column body and the front left column body through a rear inclined supporting rod, a front inner inclined supporting rod and a front outer inclined supporting rod respectively. A course rod front joint and a course rod rear joint are respectively arranged at the front end and the rear end of the course rod; the bottom ends of the front left column body, the front right column body and the rear column body are respectively provided with a front left column body connecting interface, a front right column body connecting interface and a rear column body connecting interface which are correspondingly identical with the APU real part interface in structure and position; the triangular connector is located at the gravity center position of the APU real part. The APU fake part has the advantages of being simple in connecting structure, unique in connecting process, wide in obtaining channel of manufacturing materials, low in manufacturing cost, convenient to store and manage, and convenient to load and measure static force.

The invention relates to a turbine blade simulation piece, a clamp and a test system. Wherein the simulation piece is used for simulating the characteristic structure of the double-wall high-pressure turbine blade and comprises a test section and a clamping section, and the test section comprises a first wall plate and a second wall plate; the cavity is surrounded and limited by the first wall plate and the second wall plate; the turbulent flow column is connected between the first wall plate and the second wall plate, the turbulent flow column is an inclined cylinder, and the height of the turbulent flow column ranges from 0.5 mm to 1.2 mm; the inclination angle alpha ranges from 0 degree to 90 degrees; the first wall plate and the second wall plate are integrally connected through the two ends, in the length direction, of the clamping section.

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 invention discloses a thrust chamber inner wall simulation piece fatigue test method and test system, and relates to a liquid rocket engine simulation piece test technology. Aiming at the optimization design of the liquid rocket engine, the invention proposes that the actual thermal protection requirement of the inner wall of the thrust chamber can be met and the thermal protection working state of the inner wall of the thrust chamber can be really simulated and reflected by applying the refrigerant to the heated simulation piece of the inner wall of the thrust chamber and regulating and controlling the pressure and the flow of the refrigerant in real time. The thrust chamber inner wall simulation piece fatigue test system provides a refrigerant for a medium channel of a thrust chamber inner wall simulation piece through the refrigerant supply assembly, and through control of the control system, the flow and pressure of the refrigerant entering the simulation piece from the outside are regulated and controlled in real time through the pressure and flow regulation and control assembly, the actual thrust chamber inner wall thermal protection requirement can be met, and the reliability of the thrust chamber inner wall simulation piece is improved. The convective heat transfer working state during thermal protection of the inner wall of the thrust chamber is truly simulated and reflected, and reliable and comprehensive data support can be provided for actual optimization implementation of thermal protection of the thrust chamber and optimization design of a liquid rocket engine.

The application discloses a vehicle simulation chassis, which comprises a bottom plate, front and rear chassis fixed on the front and rear ends of the bottom plate, a front transverse driving module arranged on the bottom plate, two front crossbeams, two front longitudinal beams arranged between the front crossbeams, front longitudinal sliding blocks arranged on the front longitudinal beams, front support plates arranged on the front longitudinal sliding blocks, a longitudinal driving module arranged on the front chassis, a rear transverse driving module arranged at the rear of the bottom plate, two rear crossbeams, two rear longitudinal beams arranged between the rear crossbeams, rear longitudinal sliding blocks arranged on the rear longitudinal beams, rear support plates arranged on the rear longitudinal sliding blocks and a simulation table fixed on the front and rear support plates. Compared with the prior art, the application has the advantages of low gravity center, low installation difficulty, high safety coefficient and high precision.

The invention belongs to the technical field of electric data processing, and particularly relates to a method for establishing a three-dimensional rigidity prototype, which comprises the following steps: S1, establishing a finite element model of a target structure, and obtaining original finite element node coordinates of the target structure; s2, rigidity simulation analysis is conducted on the target structure, and node displacement information under the specific working condition is obtained; s3, generating a deformed node coordinate according to the original finite element node coordinate and the node displacement information; s4, reconstructing the finite element model of the target structure based on the deformed node coordinates to obtain a deformed structure finite element model; and S5, generating a deformed three-dimensional structure model from the deformed structure finite element model through a grid mapping function. The three-dimensional rigidity model machine generated by the scheme can be synchronously displayed with an original structure and a peripheral structure, the deformation amount can be intuitively known, and whether a structure interference problem occurs or not is judged as a structure design constraint.

The application relates to a kind of engineering project real model consistency checking methods, comprising the following steps: scanning engineering project entity, and obtaining entity scanning data;The entity scanning data is preprocessed;Reverse modeling is carried out using the preprocessed entity scanning data, and scanning model is obtained;The scanning model is aligned with the BIM model constructed in advance in the same coordinate system;The geometric properties of the two models after alignment are compared, and the overall deviation distance between the two models is obtained;Consistency evaluation is carried out according to the overall deviation distance.The application can accurately check and mark the deviation between the two models by scanning the entity and carrying out reverse modeling, and comparing the entity model with the pre-created BIM model by combining algorithm.

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.

The invention provides a gradient bead-glue ratio pseudo-shaped glass cover plate, which is used in the technical field of packaging and protection of spacecraft energy components. The component of the gradient bead-glue ratio pseudo-shaped glass cover plate comprises glass beads and an adhesive, and the mass ratio of the glass beads to the adhesive is changed along the thickness direction of the gradient bead-glue ratio pseudo-shaped glass cover plate. According to the invention, the cooperative requirements of radiation resistance, high light transmittance and high flexibility of the cover plate can be met at the same time; the design of the cover plate in different use environments is facilitated, the research and development period is obviously shortened, and the research and development cost is reduced; and meanwhile, through the design of multiple structural layers and multiple bead-to-glue ratios, a better thermal expansion coefficient can be realized while the anti-radiation performance and high flexibility are met, and the interface performance of the solar cell array is effectively improved.

The invention discloses a CMC gas turbine outer ring simulation piece and a design method thereof.The design method comprises the following steps that S1, fiber orientation distribution and porosity distribution of a real component are obtained, and a thermal-mechanical-oxidation multi-field coupled real component finite element model is established based on the fiber orientation distribution and porosity distribution of the real component and material parameters in a service environment; s2, determining a damaged part of the real component and a damage parameter distribution curve of the damaged part by adopting a multi-scale analysis means; s3, designing a simulation part based on the damaged part of the real component; s4, verifying the consistency of the simulation part and the real component, if the consistency meets the design requirement, outputting a design result, if the consistency does not meet the requirement, performing size correction on the simulation part by adopting the damage parameter distribution curve, and repeating the step S4; compared with the prior art, according to the scheme, the simulation piece achieves accurate simulation of the service performance of a real component, and the test cost and the test period of the CMC gas turbine outer ring are greatly reduced.