66 results about "Elastic analysis" patented technology

The invention provides a hypersonic speed guided missile multi-field coupling dynamics integrated simulation analysis method, which comprises the following steps of: establishing a coupled structural motion equation; improving an aerodynamic heating calculation method; improving an unsteady aerodynamics calculation method; establishing an integrated simulation analysis technique process; designing a relationship between an integrated simulation analysis operation model and data; and realizing an integrated simulation analysis system. Compared with the prior art, the aerodynamic heating calculation method and the unsteady aerodynamics calculation method are improved; various techniques of flutter analysis, thermal flutter analysis, pneumatic servo elastic analysis and thermal pneumatic servo elastic analysis are integrated; and an effective integration method for integrally solving and optimally designing a high-speed winged missile all-missile combination body coupling dynamics problem is provided.

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 structure reduced-order model-based geometric nonlinear static aeroelastic full-aircraft trim method. The method comprises the steps of firstly building a full-aircraft finiteelement model of an aircraft, giving a follow-up test load and solving corresponding test deformation through finite element software; secondly solving a nonlinear stiffness coefficient by performingregression analysis on the follow-up test load and the test deformation in a given nonlinear stiffness coefficient form to build a structure reduced-order model; and finally applying the model to thegeometric nonlinear static aeroelastic full-aircraft trim analysis of the aircraft, and establishing wing geometric nonlinear static aeroelastic deformation calculation and full-aircraft geometric nonlinear static aeroelastic trim analysis processes. The nonlinear stiffness coefficient in a cubic polynomial form is given, and the aerodynamic follow-up effect and the spanwise deformation under thewing geometric nonlinear large deformation are considered, so that the reasonability and accuracy of geometric nonlinear static aeroelastic analysis are improved and the efficient analysis calculation of geometric nonlinear aeroelastic deformation and trim is facilitated.

Computational aeroelastic analyses typically use a mathematical model for the structural modes of a flexible structure and a nonlinear aerodynamic model that can generate a plurality of unsteady aerodynamic responses based on the structural modes for conditions defining an aerodynamic condition of the flexible structure. In the present invention, a linear state-space model is generated using a single execution of the nonlinear aerodynamic model for all of the structural modes where a family of orthogonal functions is used as the inputs. Then, static and dynamic aeroelastic solutions are generated using computational interaction between the mathematical model and the linear state-space model for a plurality of periodic points in time.

The invention discloses an elastic-plastic buckling bearing capacity calculation method which comprises the following steps: S1, carrying out linear elasticity analysis on a truss structure under a stress load condition, and determining the most unfavorable rod piece of the truss structure under the load condition; S2, calculating and acquiring the linear elastic buckling bearing capacity and the elastic-plastic buckling bearing capacity of the most unfavorable rod piece of the truss structure; S3, calculating the elastic-plastic buckling bearing capacity of the truss structure according to the elastic-plastic buckling bearing capacity of the most unfavorable rod piece of the truss structure; S4, respectively calculating the elastic-plastic buckling bearing capacity of the truss structure by adopting a characteristic value buckling analysis method and a riks analysis method in finite element software Abaqus, comparing and analyzing the obtained elastic-plastic buckling bearing capacity result of the truss structure and the calculated elastic-plastic buckling bearing capacity result of the truss structure so as to verify the correctness and feasibility of the elastic-plastic buckling bearing capacity of the truss structure.

The invention discloses a thermoset coupling structure dynamics order reduction model method suitable for thermodynamic elasticity analysis and belongs to the technical field of aerodynamics. The method comprises the steps of S1, performing order reduction on a structure temperature field, constructing a structure temperature field order reduction model, and obtaining a structure temperature fieldlow-order vector after order reduction of the structure temperature field at any moment; S2, selecting a modal shape of a reference structure as a reference modal shape phi ref, and performing orderreduction on a deformation field to obtain a low-dimensional vector q based on phi ref; s3, establishing a kinetic equation of the heated structure; s4, establishing a thermosetting coupling kinetic model of the heated structure; sampling is carried out in the q and the formed L + N-dimensional space; a series of sample working conditions with different deformation field and temperature field loads are obtained, M, D and K (1) in a formula (7) are identified through a system, and nonlinear structure dynamics analysis under a time-varying temperature load is carried out after training is completed, so that a thermosetting coupling dynamics model based on a neural network is a nonlinear model and has generality.

A first linear elastic estimation method for analyzing ultimate bearing capacity of a planar circular tube structure comprises the steps of (1) establishing a planar circular tube structure analyzing model; (2) determining a failure unit; (3) calculating ultimate bearing capacity of the planar circular tube structure by means of first linear elastic estimation; the method allows the ultimate bearing capacity of the planar circular tube structure to be solved accurately and quickly through first linear elastic analysis; the defect is overcome that a universal elastoplasticity incremental analysis method for analyzing structural ultimate bearing capacity is insufficient due to the need for setting a complex loading process and carrying out multiple incremental iterative analysis; the efficient method for estimating the overall safety of the planar circular tube structure is provided.

The invention discloses a three-dimensional acousto-elastic analysis method of a ship for arbitrary damping processing of a structure and relates to the technical field of acoustics. The method comprises the steps of performing modal analysis on a finite element model of a ship structure with an initial damping laying layer to obtain a modal damping ratio of modalities at various orders of the ship structure; substituting the modal damping ratio of the modalities at various orders of the ship structure into an acousto-elastic coupling dynamic equation of the ship structure to obtain a composite structure dynamic equation of the ship structure; and performing vibration noise analysis on the coupling dynamic equations by use of a three-dimensional acousto-elastic theory of the ship. A damping laying optimization design scheme for the ship structure with structural acoustic radiation as an optimization objective is provided. According to the three-dimensional acousto-elastic analysis method of the ship for arbitrary damping processing of the structure, the direct vibration noise analysis for the laying-damped ship structure is implemented, and the method can be widely used for processing of the damping structure when the vibration noise of the ship is calculated and can provide a technical support for the damping laying design of the ship.

The present invention discloses a combination method for a demand response based time-of-use power price strategy suitable for smart grid development. The combination method comprises the following steps: estimating electricity price affordability of enterprises with changes in multiple factors; according to a system load situation in conjunction with user demand-side analysis with seasonal attributes, carrying out period optimization that takes the seasonal attributes into account; and based on analysis of demand price elasticity in industries, differentiating application of the time-of-use power price in different situations, thereby forming a demand response based time-of-use power price strategy. According to the combination method for the time-of-use power price strategy, for different seasons, valley and peak power prices suitable for the seasons are set according to differences in demand price elasticity, so as to finally form a time-of-use power price strategy that combines peak and valley power prices, time-of-use power prices, and season-differentiated power prices.

The invention relates to a numerical method for analyzing ultimate bearing capacity of bends and in particular relates to an estimation method for analyzing ultimate bearing capacity of bends. The method comprises the following steps: (1) establishing a bend structure analysis model; (2) performing primary linear elastic analysis; (3) performing secondary linear elastic analysis; and (4) calculating the ultimate bearing capacity of the bends according to the estimation method. According to the method disclosed by the invention, only the linear elastic analysis twice is needed, and rapid estimation of the ultimate bearing capacity of the bends is realized. The defects that a complicated loading process needs to be set in an elastic-plastic incremental method for analyzing the ultimate bearing capacity of the bends, repeated incremental iterative analysis is performed and the like are overcome, and a high-efficiency pathway is provided for rapidly and reasonably determining the ultimatebearing capacity of the bends at a primary design stage of the bends.

The invention discloses a low-impact development multi-objective interval optimal configuration method based on an SWMM model, and the method comprises the steps: building a current situation model ofan urban research region based on the SWMM model, and carrying out the current situation simulation and elastic analysis of a drainage pipe network system in the urban research region; establishing amulti-objective optimization system, and determining an optimization variable and an objective function of the optimization system; and enabling the objective function to take the minimum LID facility cost and the minimum drainage pipe network system elastic index as optimization objectives, and optimizing by combining a multi-objective interval optimization algorithm. A formula for calculating the elasticity index U-Res of the drainage pipe network system is provided to comprehensively evaluate the elasticity of the drainage pipe network system, and water quantity and water environment indexes are comprehensively considered; the minimum LID facility cost and the minimum pipe network system elasticity index U-Res are used as optimization objectives for solving by adopting an intelligent algorithm; the optimization model taking the runoff reduction rate as the constraint condition effectively overcomes the subjectivity of the traditional weight method and reduces the artificial noise influence.

The invention relates to a static aeroelasticity analysis method, device and apparatus of an aircraft and a storage medium. The static aeroelasticity analysis method, device and apparatus are appliedto high-lift aircraft configuration in a climbing or landing scene. The method comprises the following steps: generating a three-dimensional skin grid of each component in a target component; carryingout steady flow field analysis on each component to obtain an aerodynamic load generated on each component; determining the structural deformation of each component according to the aerodynamic loadon each component; and according to the structural deformation amount of each component, deforming the aerodynamic surface grid and the aerodynamic space grid of each component, and outputting an analysis result of each component when it is determined that static aerodynamic elasticity analysis of each component reaches a preset convergence condition. According to the method, the static aeroelasticity analysis of the low-speed high-lift aircraft configuration can be automatically realized in the whole process, the complexity of the static aeroelasticity analysis of the low-speed high-lift aircraft configuration is simplified, and the analysis efficiency is improved. Meanwhile, the accuracy of an analysis result is also improved.

A machine learning system determines an estimate of elasticity of an insurance policy. The system includes one or more processors in communication with at least one memory device, the one or more processors programmed to store an insurance policy model including a plurality of characteristics for the insurance policy and historical insurance policy data including a plurality of individual insurance policies. The one or more processors are further programmed to execute the insurance policy model to calculate an estimate of elasticity of the insurance policy based upon analyzing the historical data to detect a change to a characteristic of the insurance policy. The one or more processors are further programmed to modify a characteristic based upon the calculated elasticity. The processors are further programmed to receive a user insurance application, generate an individualized insurance policy based upon the application and the modified characteristic, and transmit the individualized insurance policy.

A job matching algorithm improves matching a job opening profile to a job-seeker with accuracy and efficiency by breaking down the job opening profile into a data model of standard codes. Job criteria are abstracted as attributes into at least categories of qualifications and characteristics, having an associated assigned weight. Job-seeker profile's corresponding attributes in qualifications and characteristics are multi-dimensionally mapped to those in the job opening profile to calculate an overall score against a threshold score for successful matching. The job-seeker's profile and the job opening's profile may also be re-matched using an elastic analysis to model job seeker's strengths and growth potential for a same or a different job, through adjusting individual weights of each attribute of the qualifications and characteristics of one or both of the job-seeker's profile and the job opening profile to predict risks or successes for the job-seeker in taking the job opening.

The invention provides an atrium cross-floor frame column design method based on rigidity equivalence. The method includes respectively establishing a floor slab non-holing model (a first model) and afloor slab holing model (a second model), and carrying out the static and seismic response spectrum analysis; based on a first model meeting specification requirements and an elastic analysis resultof the first model, respectively extracting the floor lateral stiffness of the two models, according to the principle that the floor lateral stiffness of the first model is equivalent to the floor lateral stiffness of the second model, amplifying the earthquake action of a cross-floor frame column (namely a frame column within a floor holing range) in the second model, and carrying out component reinforcement design to achieve the effect that the earthquake resistance indexes of the first model and the second model are similar. According to the method, aiming at the problem that earthquake shearing force distributed to the cross-floor frame column is small due to the fact that a large hole is formed in a floor slab, the amplification coefficient based on floor lateral stiffness equivalenceis provided, the anti-seismic contribution of the cross-floor frame column is improved, the anti-seismic performance of the whole structure is improved, and reference is provided for similar engineering projects.

The invention relates to an efficient parallel algorithm for a three-dimensional acoustic elastic generalized hydrodynamic coefficient. The efficient parallel algorithm comprises the following steps:obtaining a vibration mode displacement matrix of a ship dry mode based on finite element software; respectively distributing the total frequency number and the total process number into each frequency group; obtaining a Green function matrix and a partial derivative matrix of the Green function matrix for each frequency in each frequency group; constructing a wet surface element source intensitymatrix equation for a single frequency, performing two-dimensional parallel division on a Green function partial derivative matrix and a vibration mode displacement normal component matrix in the equation, and performing calculation to obtain a wet surface element source intensity matrix; and calculating the dry-mode attached water mass and the attached water damping in the generalized hydrodynamic coefficient. Aiming at a ship three-dimensional acoustic elasticity analysis method, the efficient parallel algorithm distributes the total frequency number to the frequency groups for parallel calculation, and performs two-dimensional parallel division on the Green function partial derivative matrix and the vibration mode displacement normal component matrix, so that the bottleneck problem of large calculation amount is effectively solved, and the large-scale engineering calculation applicability of the ship three-dimensional acoustic elasticity analysis method is greatly improved.

The invention discloses an aeroelastic structure coupling optimization method based on a self-adaptive point adding proxy model, and the method comprises the steps: firstly considering the parameter uncertainty and the model uncertainty, carrying out the quantification of the uncertainty, and providing a self-adaptive intelligent point adding criterion based on a Kriging proxy model, the maximum stress of the aircraft structure and the upper and lower boundaries of the flutter speed are obtained, and then the aircraft structure is optimally designed by considering the structural strength constraint condition and the aeroelasticity constraint condition based on the self-adaptive point adding agent model. According to the method, the number of times of finite element analysis and aeroelasticity analysis in the aircraft structure optimization process is reduced, the calculation amount is reduced, the optimization efficiency is improved, and a new thought is provided for aircraft structure optimization design.

The invention belongs to an aircraft aeroelasticity analysis technology, and particularly relates to an aeroelasticity analysis method considering internal fluid dynamic characteristics. According tothe method, firstly, an additional mass matrix considering internal fluid is generated, then a motion equation considering the additional mass matrix is assembled, and then aeroelasticity analysis considering the influence of the internal fluid is carried out. According to the method provided by the invention, the influence of internal fluid dynamic characteristics can be considered in the dynamicsimulation model of the aircraft with a large number of internal fluid, so that the aeroelasticity analysis precision of the whole aircraft can be improved, and the aeroelasticity design can be better guided. And the provided analysis method is simple and convenient to operate and has a relatively high engineering application value.

The invention relates to a nonlinear gasket-based flange bolt pre-tightening load design method. The compression resilience performance of a gasket is analyzed; a relationship between unloading performance and bolt pre-tightening force of the gasket is discussed; a flange connection system is subjected to elastic analysis, and the nonlinear performance of a gasket material can enable the bolt pre-tightening force to be nonlinearly changed; a flange connection is subjected to coordination analysis of axial displacement; a law of change of gasket pressing force along with a working pressure and the bolt pre-tightening force is solved; a law of change of a flange deflection angle along with the working pressure and the bolt pre-tightening force is solved; the tightness of the bolt flange connection system is subjected to safety assessment; and a safety region of the nonlinear bolt pre-tightening force of a flange under the condition of a certain nominal pressure is given by integrating two aspects of the gasket pressing force and the flange deflection angle, so that the tightness of the bolt flange system reaches the best. According to the method, a simple and effective quantitative assessment method is given for the tightness of the normal-temperature flange connection system; a basis is provided for design and tightness assessment of the bolt flange connection system; and the safety is improved.