1805results about How to "Shorten the design cycle" patented technology

The invention provides a neural network processor oriented automatic design method, device and optimization method. The automatic design method includes: a first step, acquiring a neural network model description file and a hardware resource constraint parameter, wherein the hardware resource constraint parameter includes the hardware resource size and the target operation speed; a second step, searching a unit library from an established neural network assembly library according to the neural network model description file and the hardware resource constraint parameter, and generating a hardware description language code corresponding to a neural network processor of the neural network model according to the unit library; and a step 3, converting the hardware description language code into a hardware circuit of the neural network processor.

The invention discloses a laser radar road reconstruction and expansion exploratory survey design method. The method comprises the steps of A designing a result coordinate benchmark, measuring basic control and measuring pavement control points; B determining parameters including the data density, acquisition route and the like, and acquiring vehicle laser radar data along a main road and a ramp; C determining parameters including the data density, flight design and the like, and acquiring airborne laser radar data according to a designed flight strip; D realizing laser radar data fusion by refining laser point cloud plane coordinates and elevation coordinates and refining track line data; E acquiring characteristics of road traffic lane lines by using point cloud intensity information, and realizing extraction of characteristic lines of road pavements, protection and the like by adopting a method of projecting three-dimensional point clouds to a two-dimensional plane; F recovering planar elements and longitudinal surface elements of an existing road; G producing a DEM (digital elevation model), a DOM (digital orthophoto map) and a DLG (digital line graphic); H collaboratively designing laser radar measurement and road reconstruction and expansion CAD (computer-aided design), designing flat, longitudinal and transverse cross sections of a road, comparing and selecting schemes, and outputting final design drawings and charts.

There is provided a printed circuit board having a differential signal transmission line composed of non-skew-adjusting portions and skew-adjusting portions. The non-skew-adjusting portion consists of parallel conductive traces spaced apart by a spacing. The skew-adjusting portion consists of a pair of meander traces for the skew adjustment. The skew-adjusting portion include convex transmission line segments and concave transmission line segments. The convex transmission line segment has parallel traces having a differential trace pair spacing greater than the differential trace pair spacing in the non-skew-adjusting portion. The concave transmission line segment has parallel traces having a differential trace pair spacing smaller than the differential trace pair spacing in the non-skew-adjusting portion.

A lightweight forward design method and system of automobile structure based on multi-performance constraints is disclosed. The finite element analysis model of automobile body structure is established by using finite element modeling technology. The typical force transfer path of automobile structure is identified by using topology optimization technology and the bending / torsional rigidity performance of automobile body is taken as constrained working condition, and lightweight design in conceptual stage is carried out. Then the strain energy analysis and the material thickness sensitivity analysis are carried out by using the sensitivity analysis technology, and the weak links and the critical design area of the vehicle body are found. Topography optimization is used to improve vehicle performance; Finally, based on business integration optimization software, The multi-performance target of automobile body is analyzed by integrated simulation, and the correlation between design parameters and performance, performance and performance is studied by using DOE sampling and data mining technology, and then the lightweight design of automobile body structure considering multi-disciplinary performance is carried out, which reduces the quality of automobile body structure, improves product performance, shortens R D and manufacturing cycle, and saves cost.

A technique to design deep sub-micron (DSM) integrated circuits is disclosed, in which global wire delays are minimized first, before performing logic synthesis. According to the present method, a designer performs layout of physical blocks by estimating an area for each block. After connecting the pins of the blocks with no timing constraints, each wire is assigned to a metal layer, based on length. The delay of each wire is minimized by inserting buffers at optimal distances. The blocks are then partitioned into “cores” and “shells.” The shells and cores are synthesized, and then recombined. This procedure greatly reduces the number of design iterations required to complete a design.

The invention discloses a general signal processing board card based on a multi-core DSP (digital signal processor). An FPGA (field programmable gate array) serves as a master control core, and two multi-core DSP chips are connected through a high-speed serial bus and supportable to SRIO (serial rapid input / output) and PCIE (peripheral component interconnect express) protocols. Each DSP is connected with an expandable external memory and a gigabit Ethernet interface, and the DSPs are connected mutually through the high-speed serial bus and supportable to Hyperlink, SRIO and PCIE protocols. The FPGA and a VPX connector are mutually connected through a gigabit transceiver and supportable to SRIO, PCIE and Ethernet protocols. Mounting positions of an external memory chip, a DSP chip and an FPGA chip on a printed board of the general signal processing board card are compatible positions allowing placement of other chips in the series respectively and accord with 6U standards in size. The problems of poor universality, small data throughput, low storing rate and low processing speed of existing signal processing board cards are solved, and the general signal processing board card has the advantages of quickness in processing, high storing rate, large data throughput and high universality and can be widely applied to fields of communication, radar, guided missiles, remote sensing, image processing and the like.

A BIM-based assembly building forward deepening design method is provided. The method comprises the following steps: determining design parameters of an assembly building according to design requirements of construction engineering, structural engineering, HVAC engineering, and electromechanical engineering, and generating an editable geometry and data information model; performing assembly component disassembling on the geometry and data information model generated in the deepening design software, and checking component parameters, so that the component size and weight meet the requirementsfor production, transportation, and installation; performing modeling on the protruding bar, the component bracing, the formwork, and the protective frame of the assembly component, and performing dynamic collision inspection on the installation of the assembly component; performing new collision inspection, and performing non-extension rib modeling of the component after there is no collision conflict; automatically generating an assembly building construction drawing and a component drawing by using a BIM drawing output module, and generating a component production material list; and finally, deriving a deeply designed BIM model to assist the mold design. According to the method provided by the present invention, the design cycle is shortened, and coordination of various professions is facilitated.

The invention relates to a variable-frequency power source based on the control of a digital signal processor, which comprises a switch power source module, a control circuit, a circuit for isolating and shaping pulse-width modulating signal, IPM inverting circuits, a circuit for detecting and protecting busbar voltage, a rectification input slow-start circuit, a communication circuit, an interface circuit for isolating and inputting parallel signals and an human-computer interface circuit for displaying the key. The invention adopts the structure of a single digital signal processor (DSP) coupled with the double IPM inverting circuits, provides two paths of independent variable-frequency power sources for two sets of asynchronous motors at the same time and carries out independent speed regulations to the two sets of asynchronous motors. The variable-frequency power source of the invention has the advantages of small volume, low power consumption, high reliability and being convenient for bulk production, etc., and adopts an appropriate switch frequency and an advanced voltage space vector pulse width modulation algorithm (SVPWM), thereby lowering the noise during the operation of the asynchronous motors and increasing the voltage utilization rate, with obvious effect on energy saving.

The invention belongs to the technical field of aircraft simulation, and particularly relates to a simulation analysis method and system for gust response of an elastic aircraft. The method comprisesthe steps of according to the dynamics and the structure correspondence of the elastic aircraft under gust excitation, firstly, modeling an aircraft six-degree-of-freedom system, the atmospheric turbulence, the gust excitation and the aerodynamic force data according to the flight state; secondly, under the condition of static elasticity, analyzing the deformation of the aircraft wing under the aerodynamic force load and the change of an angle of attack and the influence of the angle of attack on an aerodynamic coefficient, correcting the aerodynamic coefficient to enable the aerodynamic coefficient to better conform to the real flight state of the elastic aircraft, and finally, connecting all the modules into a system to realize the corresponding analysis under the excitation of gust of the elastic aircraft. The system achieves a good effect in cases of a general aircraft and a civil large-scale passenger plane.

The invention discloses an optimization design method of a composite material wing panel. The optimization design method comprises the following steps: (1) carrying out finite element simulation modeling on the main structure of a wing; (2) applying a load and boundary condition to a finite element wing box section model; (3) calculating an integral wing box finite element model, and extracting the internal load of a structure; (4) designing a layup library, and calculating the laminate attributes of all layers in the layup library to obtain a rigidity matrix and an equivalent elastic modulus; (5) aiming at the calculation requirements of different structural unit initial dimensions and different failure modes of a skin stringer to carry out secondary distribution calculation on the load; (6) calculating the design allowable value of each structure failure mode of the panel; (7) calculating the safety margin of each BAY of a panel structure; (8) setting a maximum slope rate of panel layup arrangement and an adjacent area laminate throwing layer, setting the Poisson ratio difference value coefficient and the stiffness ratio of the stringer and the skin, and regulating the layer if a design range is not met; (9) if the design does not meet weight requirements, requiring to circularly carrying out the steps (1) to (8) to regulate the lay and the dimension until structure weight requirements are met. According to the method, the design and optimization working efficiency of the integral panel of the composite material is improved, and research and development cost is saved.

The invention discloses a three-dimensional design method and system for a nuclear powder support hanger. The three-dimensional design method and system are operated under a PDMS (Plant Design Management System); a nuclear powder support hanger database consisting of a support hanger composition table is hung below a main menu of the PDMS system; the support hanger composition table comprises support hanger types, type description and inner codes; the inner codes are formed according to part types and the part shut sequence forming the support hanger; each support hanger type is in respective one-to-one correspondence to a style picture and the inner code of the support hanger; the design method comprises the following steps of: establishing the support hanger composition table at a first phase according to the type code, the type description and the inner code; generating a preliminary mode of the support hanger at a second phase according to the support hanger description and a corresponding picture; adding a connecting point and a rooting point by setting parameters; and finally, generating a corresponding a support hanger three-dimensional mode, wherein the first phase and the second phase can be continuously and alternatively carried out, or a novel type support hanger in the support hanger composition table during execution at the second phase can be added and modified.

The invention discloses a method for hydraulically optimizing a centrifugal pump under a plurality of working conditions based on loss, which comprises the following steps of: establishing a multi-working condition hydraulic optimization model of the centrifugal pump based on various loss formulae; establishing relationships among various loss coefficients, specific speeds and flows of the centrifugal pump at different specific speeds under the different working conditions by external characteristic experiments; compiling multi-working condition hydraulic optimization programs PCC.exe of the centrifugal pump by adopting Visual C++; integrating the PCC.exe by adopting iSIGHT, taking parameter values of single-point design as initial values, taking heads and power under the plurality of working conditions as constraint conditions, taking maximum efficiency under the plurality of working conditions as a target, and optimizing the centrifugal pump by adopting a global optimization algorithm or combination; and designing a multi-working condition hydraulic model by adopting PCAD according to an optimal solution set obtained in the optimization. The method has the advantages of not only performing multi-working condition hydraulic design on the centrifugal pump according to performance requirements under the plurality of working conditions, but also performing energy-saving alternation on the conventional centrifugal pump.

The invention discloses a modular full direct current photovoltaic system and a control method thereof. The system comprises n DC (direct current)-DC converter modules and an MMC (Multi Media Card) centralized inverter, and every DC-DC converter module is connected with an independent control loop and a maximum power tracking control function so as to ensure that a photovoltaic battery pack connected with every DC-DC converter works on the highest point of the output power. According to the modular full direct current photovoltaic system and a control method thereof, a direct current bus is formed by connecting the output ends of a plurality of DC-DC converter modules in series, and the high-power grid-connected power generation function is achieved through the centralized MMC inverter. The direct current bus can effectively reduce the operating loss of the entire system and structurally improve the operating efficiency of the system.

The invention discloses an aircraft multi-objective optimization method based on a self-adaptive agent model, relates to a multi-objective optimization method for treating complex aircraft design, and belongs to the field of aircraft design optimization. According to the aircraft multi-objective optimization method, an integrated preference function is constructed by use of a physical planning method to realize the conversion of the multi-objective optimization problem into a single-objective optimization problem reflecting design preference; next, the self-adaptive agent model is constructed from the integrated preference function and constraint conditions to take the place of a high-accuracy analysis model, and therefore, the problem of great time taken in calculation of optimization design is solved; finally, the constraint problem is converted into a non-constraint problem by use of an augmentation Lagrange multiplier method, and the non-constraint problem is solved by use of a genetic algorithm. The aircraft multi-objective optimization method has the advantages that the solving process of the aircraft multi-objective optimization method taking much time in calculation is simple and efficient, and therefore, a Pareto noninferior solution meeting the requirements of a user can be obtained quickly to shorten the design period of the aircraft, and the design cost is reduced. Besides, the aircraft multi-objective optimization method is high in universality and convenient for program development.

The invention relates to a multi-layer co-extrusion die head intelligent temperature control system including a temperature acquisition module, an FPGA temperature control module, a drive heating module and a control panel. The temperature acquisition module includes N temperature acquisition units; the FPGA temperature control module includes an AD switching circuit, an FPGA control chip for realizing a fuzzy PID control algorithm, and a PWM output circuit; the drive heating module includes N drive heating units corresponding to heaters in a control partition; temperature signals of the control partition are acquired by the temperature acquisition units and are inputted into the FPGA temperature control module, and after treatment, N paths of PWM control variables are outputted and are respectively outputted to the drive heating units by the PWM output circuit in a single path mode. According to the control method, double-parameter input of a deviation e and a deviation change rate e[c] is adopted, correction values of a PID parameter value obtained by fuzzy inference are corrected, final PID input parameter values are obtained, and thus heating coil temperature intelligent control is realized.

The invention discloses a method for checking electric fitting data of a printed circuit board, which mainly solves the problem that the electric fitting data of the printed circuit board cannot be automatically checked in the prior art. The method comprises the following steps of: converting automatic design files of electronic design of different structures into normalized files; digitalizing the assembled design specifications of the printed circuit board into process rules for checking, establishing a surface mounting process rule database and storing the process rules; recovering geometric shapes of a substrate and components of the printed circuit board by using visualization technology, and three-dimensionally and dynamically displaying the mounting process of the printed circuit board; checking the assembly properties of the components to be mounted by using the surface mounting process rule database as a drive, and recording the checking results; and classifying the checking results, and outputting the checking results in a figure or graph mode. By the method, the data for the automatic design files of the electronic design of different structures can be automatically checked, and the checking results can be intuitively displayed; moreover, the method can be used for surface mounting production preparation of the electric fitting industry.

The invention provides a coaxial rigid rotor coupling pneumatic elastic response analysis method, and belongs to a helicopter kinetic analysis technology. The method is characterized in that according to the operation and control characteristics of a coaxial rigid rotor helicopter, a balance equation optimization solution method is built, and an optimization solution is found according to the given target and constraint conditions. According to the characteristic of complicated coaxial rigid rotor flow field environment, a rotor flow field is calculated by using a computational fluid dynamic method based on an Euler / N-S equation; and then, the coupling pneumatic elastic response is calculated by using a computational fluid dynamic / computational structural dynamic loose coupling analysis method. The coaxial rigid rotor coupling pneumatic elastic analysis method has the advantage that when the analysis method is used, balance operation and control parameters, blade response, rotor loads and the like of the coaxial rigid rotor helicopter can be calculated. The method has good analysis precision and engineering applicability; the relying of the development process on the test can be reduced; and the design period and the development cost can be greatly reduced.

The invention provides a manufacture method for an ultra-fine grain and high-intensity alloy blade forged piece. The manufacture method for the ultra-fine grain and high-intensity alloy blade forged piece comprises the following manufacture processes of extruding, finally forging, cutting burrs and carrying out thermal treatment and is characterized in that a barium salt furnace is adopted to heat before the extrusion process; an extrusion die is a ''rhombic blade body and rabbet'' split-type square frustum structure; and the throat part of the extrusion die is strengthened. According to the manufacture method for the ultra-fine grain and high-intensity alloy blade forged piece, which is disclosed by the invention, the die design period and the product technology flow are shortened, the material consumption is lowered, and the cost is saved. Meanwhile, the mean grain size of the prepared forged piece performance tissue is less than the tenth grade, and the performance achieves the level of a high-strength forged piece.

The invention provides a method in the field of automobile computer aided design, particularly a vehicle frontal collision finite element model rapid-matching method. In the method, based on the conventional method, a process of establishing a reverse finite element model is added, and reverse and positive related parameters in a simulation process are compared to rapidly determine a critical area determining matching accuracy in the model; and then a conventional modeling method is performed, and a positive model is regulated by utilizing parameter values of the critical area obtained by the comparison between the reverse and positive related parameters so as to be rapidly matched well. By the method, the designing period of a vehicle frontal collision finite element model is effectively shortened, and the designing accuracy is relatively higher.

The invention discloses a CFD (Computational Fluid Dynamics)-based modeling design method for a nuclear main pump and a designed million-kilowatt-grade nuclear main pump impeller, belonging to the technical fields of design and manufacture of pumps. The CFD-based modeling design method for the nuclear main pump is characterized by comprising four steps of: 1, selecting a model pump impeller satisfying similar conditions with a pre-designed pump impeller according to the design parameters of a million-kilowatt-grade nuclear main pump; 2, calculating size conversion coefficients by utilizing a conventional modeling design formula, and selecting 3-4 different size coefficients within a certain range to convert the model pump impeller; 3, carrying out numerical simulation respectively on the 3-4 pump impellers obtained in the step 2, and carrying out logarithm fitting on a relation between the size coefficients and delivery lift to obtain the nuclear main pump impeller meeting requirements; and 4, optimizing the nuclear main pump impeller obtained in the step 3 to complete the design. The invention has the advantages that the design problem of the high-temperature and high-pressure large-flow million-kilowatt-grade nuclear main pump is solved, and a design process is concise, efficient and controllable.

The invention relates to a turbine disk probability failure physical life predicting method based on Bayes information update, which comprises the following steps that 1, failure physical information of a turbine disk is determined in a reliability analyzing method based on physics of failure according to the structural characteristics of the aircraft engine turbine disk; 2, the failure physical information of the aircraft engine turbine disk obtained in step 1 and the existing failure information obtained by maintenance data statistics are analyzed in an FTA (failure tree analysis) / FMECA (failure mode, effects & criticality analysis) method to obtain the main failure mode and the failure position of the turbine disk, and uncertain factors and inaccurate data of the turbine disk facing whole life cycle are collected and cleared up; and 3, a failure physical life predicting model of the aircraft engine turbine disk is established according to the main failure mode and the failure position of the turbine disk obtained in step 2. The method disclosed by the invention has the beneficial effects that the design cycle of the aircraft engine turbine disk can be obviously shortened, the development cost is reduced, and the life reliability of the aircraft engine turbine disk can be obviously improved.

The invention relates to a POD (proper orthogonal decomposition) and surrogate model based order reduction method for hypersonic aerodynamic thermal models and belongs to the technical field of aerospace. A hypersonic aircraft aerodynamic thermal environment is predicted and obtained by the aid of a POD and surrogate model method, nonlinear characteristics of real gas effect, turbulence viscosity and the like of high-precision numerical calculation are reserved, the hypersonic aircraft aerodynamic thermal environment can be provided for design of the hypersonic aerocraft by the aid of model order reduction method which is high in precision and efficiency, related thermal boundary conditions are provided for aerodynamic thermal elastic design, the thermal environment is provided for thermal protection design of the hypersonic aerocraft, design efficiency can be greatly improved, design circle is shortened, and design cost is reduced.

Methods and apparatus are described for making a placement sensitive engineering change to meet design for test requirements. One of the methods includes placing a set of new flops in an already placed chip design to meet functional requirements of an engineering change. The already placed chip design is pruned to create a set of valid flops and valid scan chains based on a set of pruning rules. A unified flop database is generated containing physical location and connection information for the new flops and the set of valid flops. A change file for the new flops, selected valid flops, and valid scan chains associated with the selected valid flops is generated meeting allocation and placement sensitive signal connection rules. The new flops are connected to the selected valid flops allowing design for test requirements to be met

The invention relates to the technical field of agricultural machinery, in particular to an automatic whole-row grafting device for grafted seedlings. The device comprises a rack (1), an electric control cabinet (3), a scion conveying mechanism I (5), a scion conveying mechanism II (8), a grafted seedling conveying mechanism (6), a scion clamping mechanism (87), a rootstock clamping mechanism (88), a scion seedling cutting mechanism (17), a rootstock seedling cutting mechanism (11), a scion seedling gathering mechanism (2), a rootstock seedling gathering mechanism (12) and an automatic whole-row grafting clamp conveying mechanism (89). According to the automatic whole-row grafting device for the grafted seedlings, plug seedling supply, whole-row seedling grabbing, seedling cutting, fixing and grafting of plug rootstock seedlings and plug scion seedlings are realized, and the whole operation process is automatically completed by a machine; the plug seedlings are rapidly grafted, the labor efficiency of grafting operation is improved, and the labor force is saved.

The invention provides a simulation and demonstration system for design and validation of an AFDX (Avionics Full Duplex Switched Ethernet) network and a simulation and demonstration method thereof, which are used for guiding the design of the AFDX network. The simulation and demonstration system mainly comprises an integrated avionics network design module, a loaded avionics communication task module, a plausibility check and validation module, a simulation module, a loadable configuration file output module, a network demonstration system module, and the like and has the functions of designing the avionics interconnection structure, simulating communication tasks of the AFDX network and validating the designed network topology in the network demonstration system module. The simulation and demonstration method is used for designing the network topology, simulating the avionics communication tasks and demonstrating and validating the designed network to obtain related technical parameters and provide the reference for the design of the AFDX network. The invention provides a more reliable scheme for the design of the AFDX network, shortens the design time, saves the cost, and improves the design efficiency.

The invention discloses an intelligent pipeline arrangement optimization method and system based on a differential evolution algorithm. The method includes the steps of conducting mathematical modeling on a pipeline to be arranged and arrangement space so as to determine an arrangement object, the constraint condition and the evaluation criteria, coding the arrangement object through polar coordinates and posture vectors, conducting optimization solution on a pipeline arrangement optimization mathematical model according to the differential evolution algorithm, and conducting constraint condition verification and arrangement adjustment on the arrangement optimization scheme obtained through the solution so as to obtain a final arrangement scheme. By means of the intelligent pipeline arrangement optimization method and system based on the differential evolution algorithm, the design cycle can be greatly shortened, optimization performance can be enhanced, the purpose of arranging pipelines on a large scale within limited time can be achieved, and the method and the system have the advantages of being short in arrangement design time, high in optimization accuracy, capable of quantitatively evaluating the arrangement scheme and the like.

The present invention provides a response surface based optimization method for a single reed structure in a novel space deployable hinge. The method comprises: according to an actual operating environment of the single reed structure in the novel space deployable hinge, establishing a simplified mechanical model; performing equivalent processing on constraint and loading modes of the single reed structure; obtaining a first-five-order buckling mode and a buckling load of the structure based on ABAQUS; introducing an initial geometric defect to obtain a load-displacement curve, a critical buckling load and a stress distribution cloud chart of the structure; obtaining an optimization model with the maximum buckling bearing capacity under stress constraint of the structure; realizing explicit expressions of a constraint and an objective function based on a response surface method, checking the precision of fitting and updating the model; and simplifying the optimization model into a standard quadratic programming model, and then solving the model by a sequential quadratic programming method to obtain an optimal result. The present invention provides a reliable stability analysis method for the single reed structure, thereby shortening design cycle of the novel space deployable hinge, improving work efficiency and reducing design costs.

The invention discloses a broadband micro-perforated board sound absorber, a sound absorber performance prediction method and a sound absorber structure design method. The sound absorber comprises a surface micro-perforated board and a back chamber with unequal periodicity depth, and the back chamber is used for expanding sound absorption bandwidth of the sound absorber. The performance prediction method is used for predicting a sound absorption coefficient frequency spectrum of the sound absorber, through finite element simulation and experiment measurement verification, the performance prediction method is accurate and reliable; the structure design method used for effectively realizing the broadband micro-perforated board sound absorber comprises steps that (1), a depth matrix of the periodic back chamber is designed on the basis of the secondary residual sequence combination arrangement theory; and (2), evaluation is realized on the basis of the performance prediction method, combination of parameters of the sound absorber are sequentially determined, including total sound absorber width of the periodic back chamber, depth of each sub back chamber, board thickness of the micro-perforated board, aperture and perforated percentage. Through the sound absorber performance prediction method and the sound absorber structure design method, the micro-perforated board sound absorber having the broadband sound absorption performance can be accurately, reliably and simply designed.

The invention provides a calculating method for short-circuit current on the direct current side of an MMC-MTDC (modular multi-level converter-based multi-terminal direct-current transmission system). The calculating method comprises the steps of (1) calculating an MMC-MTDC direct-current network, and taking calculated steady-state operation current as a steady-state component of the short-circuit current; (2) performing equivalent conversion to obtain an equivalent passive circuit corresponding to an MMC; (3) calculating a fault component of the short-circuit current according to the MMC equivalent passive circuit, a direct-current power transmission line and a fault point direct-current voltage source equivalent calculating network; (4) adding the steady-state component and the fault component to obtain a final short-circuit current calculated result. Therefore, on the premise of guaranteeing the effectiveness, the efficiency for calculating the short-circuit current on the direct current side of the MMC-MTDC is obviously improved; due to the use of the method disclosed by the invention, the time for checking the requirement on the performance of a direct-current circuit breaker can be obviously shortened, so that the period for planning and designing the whole MMC-MTDC engineering is shortened; the calculating method has an important engineering practical value.

The invention discloses a method for analyzing static strength characteristics of a turbomachinery blade based on CPU+GPU heterogeneous parallel computing. The method comprises the following steps of firstly, establishing a finite element model, computing the total stiffness matrix of the model, then, computing the centrifugal load vector and the pneumatic load vector of the turbomachinery blade, performing displacement constraint and coupling of a node, and correcting the total stiffness matrix; and then, solving an equation set formed by the total stiffness matrix and the load vector in parallel by using CPU+GPU, obtaining a node displacement vector, then, computing the principal strain and the VonMises equivalent stress, drawing a distribution cloud picture, and finally, performing safety check. By means of the method disclosed by the invention, for static strength analysis and design of the turbomachinery blade, project planners can perform operation conveniently; simultaneously, due to an adopted CPU+GPU parallel algorithm, the computing speed of a finite element method can be effectively increased; an accurate and rapid blade static strength characteristic analysis result is provided for design of the turbomachinery blade; and the design period of the turbomachinery blade is greatly shortened.