185 results about "Conceptual design" patented technology

A method for planning the clock distribution network in the conceptual design phase of an ASIC device is provided herein that comprises partitioning the technology-independent description of the device into partitioned groups based on the clocking time of the clock recipients in each of the partitioned groups. In addition, a clock budgeting plan is generated by creating target timing groups and assigning each of the partitioned groups to one of the target timing groups based on the clocking time of the clock recipients in each of the partitioned groups. The clock recipients in each of the target timing groups clock at a substantially same time and clock recipients in different target groups clock at different times. The clock distribution network is created based on the clock budgeting plan such that the clock distribution network provides a clock signal to clock recipients in each of the target timing groups in a manner that the clock recipients in each of the target timing groups are clocked together at a substantially same time.

The invention discloses a premixing and pre-evaporating combustion chamber, which has a single annular chamber structure and adopts a conceptual design of fractional combustion. In the combustion chamber, the total combustion gas volume is supplied by a pre-combustion fraction and a main combustion fraction, the pre-combustion fraction adopts a swirl-flow stable diffusion flame combustion organization mode and the main combustion fraction adopts a premixing and pre-evaporating combustion organization mode. The combustion chamber mainly comprises a shunting diffuser, a combustion chamber outer casing, a combustion chamber inner casing, a fuel oil nozzle, the pre-combustion fraction, the main combustion fraction, a combustion liner outer wall and a combustion liner inner wall. The pre-combustion fraction stabilizes flame by using a low-speed refluxing zone generated by swirl air entering the combustion chamber from a pre-combustion fraction swirler; and after being sprayed out by a main combustion fraction nozzle, the fuel oil needed by the main combustion fraction first form an oil-gas mixed gas through atomization under the action of an air flow in a prefilming air ring in the main combustion fraction nozzle and then flows to the premixing and pre-evaporating fraction to be evaporated and further blended with the air, so a uniform oil-gas mixed gas jet flow is formed at the position of the outlet of the premixing and pre-evaporating fraction and enters the combustion liner to be ignited by flame in the pre-combustion fraction to combust. The combustion chamber is simple in structure and can effectively reduce pollutant discharge while ensuring an aeroengine works normally.

The invention relates to a main combustion stage tangential oil supply premix and pre-evaporation combustion chamber. The combustion chamber is in a single-ring chamber structure and is designed by adopting the conceptual design of staging combustion, and all the used amount of gas for combustion is supplied by the precombustion stage and the main combustion stage. The combustion chamber mainly comprises a flow-dividing type diffuser, a combustion chamber outer case, a combustion chamber inner case, a fuel nozzle, the precombustion stage, the main combustion stage, a flame tube outer wall and a flame tube inner wall. The precombustion stage utilizes a low-speed flow returning zone generated by swirl air entering the combustion chamber by a precombustion stage swirler component; the fuel needed by the main combustion stage is ejected by the tangential main combustion stage nozzle, is atomized under the air flow effect generated by entering of atomized air of the main combustion stage nozzle into a pipe, then flows into a premix and pre-evaporation ring pipe for evaporation, and is further blended with air; and even oil-gas mixed gas formed at the outlet of the premix and pre-evaporation ring pipe enters a flame tube and combusts under the pilot combustion of the precombustion stage flame. The combustion chamber has simple structure, and can effectively reduce the discharge of pollution simultaneously while guaranteeing that an aeroengine is in normal working state.

An integrated evaluation and simulation system interactively evaluates concept design decisions and design requirements in the context of an operational weapon system. The combat effectiveness of a weapon system may also be concurrently tested by virtual simulation. A computer system is programmed to implement a causal network model comprising an integrated collection of analysis models for creating a virtual representation of a weapon system. The integrated evaluation and simulation system includes a user interface operably coupled to at least the computer system to selectively input data into the causal network model and receive information from the causal network model and at least one virtual simulation system. The system further includes either a virtual simulation system operably coupled to the causal network model or, as part of the computer system, a virtual simulation system interface to communicate with a virtual simulation system.

The invention provides a vehicle road load simulation method which comprises the following steps of: 1) complete vehicle modular modeling; 2) complete vehicle modular model validation; 3) complete vehicle model assembly; 4) complete vehicle model validation; 5) establishment of finite element models of enhanced durable roads; 6) model initialization; 7) obtaining of virtual road load result; and 8) comparative validation with physical road load. The invention has the advantages of shortening development time and reducing costs, which is of great significance to vehicle development during the conceptual design phase. During the conceptual design phase of new models, fatigue analysis can be carried out before the design and manufacture process by using a virtual prototype to predict road load so as to truly predict the life of the product, thus greatly reducing great expenses caused by producing prototype machines and testing the fatigue life.

The invention relates to a method for designing automobile body structure layout. The method comprises the following steps of: 1) initially setting the parameters of a new type automobile, 2) choosing the white automobile body finite element models having similar structures and sizes, or directly building a white automobile body finite element model, 3) generating a grid enveloped model according to the white automobile body finite element model, 4) generating a body grid model according to the grid enveloped model, 5) topologically optimizing and analyzing according to a target parameter based on the body grid model, 6) according to an analyzed result and drawing an automobile body material layout diagram, 7) designing conception according to the layout diagram, and 8) designing the layout structure in detail according to the data of the conception design, performing simulating analysis of strength, NVH and impact performance CAE and formability process analysis according to the data of the detailed design of the layout structure, and modifying so as to acquire a three-dimensional digitized product model fit for volume production. The automobile body structure layout has the advantages of shortened developing period and lowered researching and developing cost.

The present invention discloses a helicopter aerodynamic layout optimization method capable of reducing the adverse effect of aerodynamic interference. According to the method, aiming at the defects of a wind tunnel test and a CFD method and based on a discrete vortex method and a surface element method, a coupled aerodynamic interference high-precision analysis model for a helicopter is set up, so that the influence of aerodynamic interference on the helicopter can be considered only by simulating calculation without carrying out the wind tunnel test; compared with the CFD method, the method has the advantages of greatly reducing the requirements of a simulation model for computing resources and shortening computing time. In order to further reduce calculated amount and a optimization region, a helicopter fuselage shape parameter model is set up by a parametric method and a combined optimization method based on an agent model is adopted, so that the optimal helicopter aerodynamic outline and layout are obtained and the purpose of reducing aerodynamic interference to improve the flight characteristics of the helicopter is achieved. The helicopter aerodynamic layout optimization method can be applied to the conceptual design phase of the helicopter so as to improve the flight characteristics, the balancing characteristic, stability and manoeuvrability of the helicopter.

The invention provides a 3D (three-dimensional) printing based processing technique of an automobile styling concept model and belongs to the field of automobile styling concept design. The technique includes the steps of 1, performing three-dimensional model reconstruction based on an image/draft; 2, performing 3D printing oriented model structural optimization; 3, performing 3D printing oriented solid modeling; 4, generating a support structure; and 5, performing 3D printing. The technique has the advantages that quick expression of an automobile solid model from an automobile image/draft is achieved, model processing cost is lowered at the premise of quickly implementing a personalized solid model, processing efficiency is improved, operating is simple, and the technique is reliably applied to the automobile concept design phase for automobile styling engineers.

The invention discloses a structural finite-element parametric modeling method applicable to a grating-configuration rudder surface. According to the method, a mapping transformation method based on a finite element model and a parametric approach to achieving conversion from two-dimensional mesh parameterization division to three-dimensional appearance expansion are adopted. The method includes the steps of specifically conducting two-dimensional plane projection on the grating-configuration rudder surface, extracting characteristic parameters, and conducting two-dimensional parameterization division; building a mapping relation between a two-dimensional finite element mesh and a three-dimensional finite element mesh, designing a numbering rule for finite element mesh points, and achieving conversion from the two-dimensional mesh to the three-dimensional appearance expansion; by means of a high-level computer language program, implementing the structural finite-element parametric modeling procedures for the grating-configuration rudder surface. By using the method, in a conceptual design phase or a preliminary design phase, the structural modeling efficiency can be greatly increased, the costs of time and manpower are low, parameters of self-compiled programs can be adjusted quickly, analysis applicability is high, the obtained model is applicable to analytical calculation of structural vibration, structural dynamics and the like, and the method is applicable to grating-configuration rudder surfaces and grating-configuration airfoils.

The invention provides an automobile suspension key structure element optimization design method, which comprises the following steps of: building a suspension system kinetic model according to a pre-determined suspension system development scheme, and obtaining an equivalent load of a suspension structure element connecting point under a typical work condition; building a suspension system mechanism kinetic model, and determining an initial design domain of a development structure element; building a limited element analysis model of the initial design domain of the development structure element; obtaining the material distribution of the development structure element and determining a basic topological configuration of the development structure element; obtaining a conceptual design model of the development structure element; and obtaining each parameter optimum scheme of the conceptual design model of the development structure element and an optimization design model. When the embodiment of the invention is implemented, the development period of the suspension key structure element can be effectively shortened; and the reference can be provided for the optimization design of other system parts of an automobile.

The invention concerns an apparatus and a computer software product for the conceptioneering, predesign and configuration of a machine object represented by an object data model. Component objects are stored in an object database, wherein a component object contains at least one parameter object. In addition the database contains functional objects. The modeling approach implemented by the separation according to the invention of component objects and functional objects permits a distinction to be drawn between constraints within a component object and constraints which exist between component objects. The former are embraced by the component objects themselves and the latter by the functional objects. That encapsulation has in particular the advantage that the modeling process can be substantially clearer. In addition encapsulation permits re-use of the component objects in various systems.

The present invention relates to an example-based concept-orietned data extraction method. In an example labeling phase, the exemplary data string is converted into an exemplary token sequence, in which the target concepts and filler concepts are labeled to be tuples for use as an example, and thus an exemplary concept graph is constructed. In the data extraction phase, the untested data string is converted into an untested token sequence to be processed, and, based on the associated concept recognizers defined by the tuples in the example labeling phase, it is able to detect the concept candidates and establish the composite concepts and aggregate concepts, thereby constructing a hypothetical concept graph. After comparing the exemplary concept graph with the hypothetical concept graph, the optimal hypothetical concept sequence in the hypothetical graph is determined, so as to extract the targeted data from the matched target concepts.

The invention discloses an automobile hub lightweight design method. The method comprises the steps of S1, establishing an automobile hub three-dimensional geometrical model and filling the spoke area of the geometrical model with materials; S2, establishing a hub topology optimization mathematical model and obtaining the optimal material distribution structure of a hub by means of topology optimization; S3, conducting secondary design and strength analysis in CAD software according to the hub structure subjected to topology optimization; S4, establishing an approximation model by means of the Latin square test sampling method and the response surface technology, and conducting size optimization on the hub subjected to secondary design by means of the evolution algorithm; S5, conducting strength verification on the optimized model. According to the method, conceptual design is conducted on the automobile hub firstly through topology optimization to obtain optimal material structure distribution of the automobile hub, then the approximation model is established by means of the Latin square testing method and the response surface technology with the strength of the hub as the restraint condition, detailed size optimization is conducted on the hub subjected to secondary design by means of the evolution algorithm, and then lightweight of the hub is realized.

Embodiments of the present invention provide a Streamline Traced External Compression Inlet (STECI) that represents a new solution to external compression inlet integration issues. STECI utilizes a Computational Fluid Dynamics (CFD) solution produced by a shock-generating shape which is defined by a conceptual design trade study. The shock generating shape may be created by single or multiple surfaces depending on number of upstream oblique shocks required to produce desired flow characteristics at the throat of the inlet. An aperture is then defined according to shaping requirements. This desired aperture is projected onto the forward-most, and aft-most oblique shocks of the flow field. The projected cowl portion of the aperture is then offset downstream from the aft-most oblique shock to allow for air to be “spilled” by the inlet. The resultant shape of the projected/offset cowl and the projected compression surface leading edge is the STECI aperture. Streamline seeds are placed along the STECI aperture and are used to produce streamlines through the CFD solution (which represents a physical flow field). These streamlines provide the basis for the surfaces that make up the portion of the STECI from the leading edge of the bump surface to the inlet throat and the tangencies for surfaces that will exist downstream of the throat. Traditional methods are used to define and loft the subsonic diffuser from the inlet aperture to the engine face.

The invention discloses a method for realizing multidisciplinary and multi-objective optimization of a structural system of an automobile instrument panel, which is used in conceptual design and detailed design stages of the automobile instrument panel. In the method, the constitutive relation of a material is obtained based on a high-speed tensile test for a test specimen; on the basis of the constitutive relation, NVH (noise, vibration and harshness) performance analysis, service life prediction, head impact, knee pad impact and other discipline simulation analysis on the instrument panel structure are completed; based on a multidisciplinary coordinated optimization strategy, multidisciplinary cross analysis is carried out on the instrument panel system; and based on a radial basis function, a response surface method, a concurrent subspace method and a multi-objective genetic algorithm, multidisciplinary and multi-objective optimization design is carried out to obtain the Pareto optimal solution set of the instrument panel system, thus comprehensive optimization of performances of the automobile instrument panel such as structural lightweight, NVH performances, life prediction, passive safety and the like is realized so as to guide and realize efficient development and improved design of the instrument panel product.

The invention aims to provide a method for optimizing overall performance of an aero-engine. The method comprises two rounds of optimization processes; and second optimization calculation comprises optimization of nacelle resistance, so that an aero-engine design scheme obtained by optimization is more comprehensive. An optimization platform takes an optimization result of first optimization calculation as an input of the second optimization calculation to reduce convergence time of the second optimization calculation. According to the method for optimizing the overall performance of the aero-engine, the optimization calculation speed can be increased; the research and development cycle can be shortened; and the optimization of the nacelle resistance is introduced in an engine concept design stage, so that the scheme is more reasonable in design.

A method for developing a conceptual design for a product or service involves defining conceptual design project goals and parameters and then creating a project team representing several diverse types of intelligences. The team is directed to generate multi-faceted ideas embodying brand, product or service, and marketing communications concepts in accordance with the project goals and parameters. The diverse intelligences represented on the team results in a greater variety, freshness and depth of ideas generated by the team for use in marketing and advertising the product or service. Better quality and more innovative concepts can be developed faster and more completely that have broader appeal to diverse intelligences than by using conventional methods.

The invention puts forward a quick design optimization method of power assembly suspension decoupling. MATLAB (matrix laboratory) programming and a computing platform are adopted to realize the computation of the modal frequency and the decoupling rate of a power assembly six-degree-of-freedom rigid body; on the premise that a plurality of targets are fully considered, a modal frequency target model, a modal decoupling target model and a suspension rigidity manufacture target model are established; and finally, a target function is defined and optimized, and meanwhile, the installation position, the rigidity and the installation angle of a suspension system can be subjected to optimal design. The quick design optimization method does not depend on traditional commercial software, analyzes the power assembly suspension decoupling and greatly improves analysis efficiency. In addition, the quick design optimization method fully considers the installation position, the rigidity and the installation angle in a suspension optimization design process, enriches an optimal design variable, and provides rich solving resources for the power assembly design of a finished automobile concept design stage. Meanwhile, frequency avoidance and suspension manufacture constraints in a design process are considered, and the mismatching of a later period power assembly under the working situation of the finished automobile is avoided.

The invention discloses a simplified analysis method for the bending property of a box-section thin-wall beam, belonging to the field of car body design. The simplified analysis method for the bending property of the box-section thin-wall beam is mainly used for analyzing the bending deformation of the box-section thin-wall beam during car body collision in a concept car body finite element modelfor anti-collision researches at the concept design stage of a car. The simplified analysis method for the bending property of the box-section thin-wall beam mainly comprises four steps, i.e. classifying plastic hinge lines according to whether the lengths of the plastic hinge lines are changed or not, calculating rate of energy dissipated by the plastic hinge lines, calculating rate of energy dissipated by convex annular surfaces and calculating the bending property of the entire structure. The simplified analysis method for the bending property of the box-section thin-wall beam has the advantages that the requirements on the modeling of the simplified frame structure and the anti-collision analysis of the car body can be satisfied very well, designers can be assisted to rapidly extract the bending properties of the thin-wall beams, the cockamamie work for traditional finite element analysis and tests is avoided, the rapid performance assessment and the rapid modification of a preliminary design plan are realized, and the design cycle is shortened.

The invention discloses a method for designing blade sections of helicopter rotors, and belongs to the technical field of helicopters. The method comprises determining appearance parameters according to pneumatic requirements, designating optimization objective functions and constraint functions, and establishing optimization models; utilizing finite element software to establish blade geometric models and dividing grids, importing node, grid and material information into matrix laboratory (MATLAB) software, and utilizing an implicit method for pressure linked equations (SIMP), wherein the SIMP uses every cell density as a design variable; calculating rotor blade sensitivity information in a current design state again, utilizing a sensitivity filter method to avoid checkerboard problems, and updating density information of blade section units; and calculating density differences before and after update, ending optimization if convergence conditions are met, otherwise, continuing iterative computations with updated densities as initial design parameters till convergence is achieved, and outputting blade structural styles. The method for designing blade sections of helicopter rotors can be applied to initial designs of blade structures of conceptual phases.

The invention relates to the field of optimal designing of engineering structures, and provides a structure topology optimization method for implementing diversified designs. The method comprises the following steps: implementing a structural concept design by virtue of structure topology optimization; proposing diversified design solution methods to obtain a plurality of concept design configurations meeting initial design requirements, comprising: introducing a weighted objective function and proposing diversity constraints, wherein the diversity constraints can be used for describing differences among the topology configurations and driving optimization to obtain a plurality of diversified configurations; evaluating the performance of each concept configuration under detailed design requirements, screening the concept design configurations meeting the design requirements, and performing detailed designing on the concept design configurations by shape optimization and parameter optimization. According to the method, a plurality of diversified initial designs can be obtained, the risk that an initial design solution which cannot meet a subsequent design requirement is forced to be abandoned is reduced, and design iteration times and design time are greatly reduced.

A system and method for using design specification and measurements on manufactured products in conceptual design model are provided. In one aspect, a conceptual model is extended to map one or more model elements to corresponding external reference values. The corresponding external reference values include at least design specification values and manufacturing properties associated with one or more model elements. The model elements mapped to corresponding external reference values are presented, for example, for identification and consistency checks of attributes at various stages of product life cycle.

The invention discloses a design method of an automobile control arm, which belongs to the technical field of automobile design. The method comprises the steps of obtaining key stressed working conditions according to the road spectra load in a control arm position of benchmarking vehicle or platform vehicle of a developed vehicle type and dynamics simulation analysis of the developed vehicle type, establishing a finite element grid envelopment model of the control arm of the developed vehicle type, performing topological optimization on the finite element grid envelopment model according to the key stressed working conditions and preset performance requirement, obtaining a control arm material distribution drawing according to topological optimization results, performing conceptual design according to the control arm material distribution drawing, so as to obtain a control arm geometrical model, obtaining a finite element model meeting design requirements according to the control arm geometrical model, and performing structure design according to the finite element model meeting the design requirements so as to obtain final design. The automobile control arm meeting the design requirements is obtained through CAE simulation, the development cycle of the control arm is effectively shortened, and the research and development cost is reduced.

The invention discloses a bionic slat design method based on owl wings and belongs to the field of air vehicle wing design. The bionic slat design method mainly includes the steps of extracting three-dimensional geometric structures of the owl wings; constructing bionic wing profiles; determining bionic slat profile curves; determining fixed wing front edge profile curves; determining starting points E of internal and external profile curves of bionic slats; determining starting points F of the fixed wing front edge profile curves; determining ending points C of the internal and external profile curves of the bionic slats; determining ending points H of the fixed wing front edge profile curves. The bionic slat design method based on the owl wings has the advantages that design efficiency is improved substantially, continuity of internal profiles of the slats and fixed wing configuration curved surfaces is guaranteed, design quality of the profiles and the curved surfaces of the slats is improved, and lift augmentation effect of the bionic slats is remarkable, so that the requirements of designing and analyzing on improvement in wing profile aerodynamic force in an air vehicle conceptual design stage can be met; limitations of a traditional design method are avoided, rapid assessment and modification on performance in a preliminary design scheme are achieved, and a design period is shortened.