414 results about "Aerodynamic load" patented technology

The invention discloses a pitch angle dynamic compensation method based on multi-radar space-time synchronization, and relates to the technical field of wind power generation. In order to solve the problem that the pitch angle control precision is insufficient due to the fact that three-dimensional wind field space-time characteristics cannot be captured in traditional single-point wind speed measurement, a wind wheel plane three-dimensional space-time speed field is synchronously constructed through a horizontal-vertical radar array, and blade segmented aerodynamic load distribution is calculated in real time in combination with a flow field-structure coupling model; establishing a vorticity transport equation under a rotating coordinate system based on a vorticity-shearing force transfer function, mapping dynamic load deviation through a neural network to generate a reference variable pitch instruction, and fusing the tower shadow interference feature vector to perform pre-compensation; a quadratic programming algorithm is adopted to resist saturation optimization, so that the variable pitch rate strictly follows a dynamic constraint curve of a hydraulic system. According to the method, the problem of aerodynamic load phase delay is effectively solved, periodic load fluctuation caused by the tower shadow effect is reduced, and technical guarantee is provided for stable operation of a large wind turbine generator under the complex wind condition.

The invention relates to the technical field of wind turbine generators, particularly provides a blade load evaluation method, electronic equipment and a storage medium, and aims to solve the problem of load evaluation after elastic deformation of blades of a wind turbine generator. Therefore, the blade load evaluation method provided by the invention comprises the following steps: acquiring a pre-constructed aeroelastic model and a blade tip loss coefficient database; based on the aeroelastic model and the blade tip loss coefficient database, iteratively calculating and determining the final deformation quantity of the blade; and determining at least one of an aerodynamic load, a centrifugal force load, a rotation load and a gravity load of the blade based on the final deformation quantity of the blade. According to the method, the final deformation quantity of the blade is determined through the pre-constructed aeroelastic model and the blade tip loss coefficient database, the deformation state of the blade can be accurately predicted, the aerodynamic load, the centrifugal force load, the rotation load and the gravity load are calculated based on the final deformation quantity of the blade, and high-precision data support is provided for design, operation and maintenance of the blade.

The invention provides a wind power blade aeroelastic coupling modeling method considering a pre-bending shape, which comprises the following steps of: establishing a finite element kinetic equation of a geometric precise beam structure of a pre-bending blade and solving to obtain the section speed of the blade; calculating the inflow velocity according to the section velocity of the blade; calculating a lift coefficient after dynamic stall of the blade; establishing an unsteady aerodynamic load calculation equation according to the inflow velocity and the lift coefficient after dynamic stall of the blade; and constructing a pre-bent blade aeroelastic coupling model according to the unsteady aerodynamic load calculation equation. The method can solve the technical problems that a modeling method in the prior art cannot accurately describe nonlinear deformation of the blade, the continuity of a blade model is poor, the number of calculation units is too large, the calculation efficiency is low, and the modeling method is not suitable for the long flexible blade.

The invention provides a vertical axis wind turbine power prediction method based on multi-dimensional environment data, and relates to the technical field of vertical axis wind turbine power based on the multi-dimensional environment data. Multi-dimensional data are collected in real time based on a sensor network, and the multi-dimensional data comprise environment parameters such as wind speed, turbulence intensity and temperature and humidity, and operation states such as rotor rotating speed and pitch angle; secondly, performing empirical mode decomposition on a vibration acceleration signal, constructing a physical information neural network, taking environmental data and an aerodynamic load frequency domain energy spectrum as input, outputting a real-time wind energy utilization coefficient and an aerodynamic coefficient, and finally, determining the aerodynamic load based on an aerodynamic load time domain signal. A load cyclic spectrum is extracted by adopting online rain flow counting of dynamic window length, an accumulated damage value is calculated in combination with a fatigue damage model of humidity correction, and when the residual life is lower than a threshold value, load peak suppression and power generation efficiency balance are realized through cooperative control of magnetic resistance torque linear attenuation and flap fuzzy PID (Proportion Integration Differentiation).

The invention relates to the technical field of life evaluation, in particular to a turbine blade life evaluation method which comprises the following steps: acquiring surface temperature gradient data of a turbine blade of a gas turbine, extracting the temperature change rate of each area of the blade, analyzing the influence of the temperature change rate on the local stress of the blade, and evaluating the life of the turbine blade. And calculating a thermal stress synthetic effect by combining the blade rotation inertia force and the aerodynamic load to obtain blade thermal stress distribution data. According to the method, the thermal stress synthesis effect is calculated by acquiring the temperature gradient data of the surface of the blade and combining the rotary inertia force and the aerodynamic load, the thermal stress distribution characteristics of the blade in different operation states can be accurately reflected, and the life attenuation rate is calculated by combining the current working condition, so that life prediction can be adjusted along with the operation states; the service life offset is calculated by analyzing the influence of the start-stop load of the gas turbine and comparing creep fatigue joint distribution, so that the influence of the running state of the gas turbine on the service life prediction can be dynamically updated in real time.

The invention relates to the technical field of blade monitoring, in particular to a long flexible blade real-time monitoring and fault early warning method which comprises the steps that vibration signals of a long flexible blade in the running state are collected, and the vibration signals are subjected to the aerodynamic load, gravity and centrifugal force multi-factor coupling effect; constructing an overdetermined equation set containing a multi-source excitation characteristic based on the blade dynamic model; decomposing the vibration signal by adopting a sparse decomposition algorithm to obtain a signal decomposition result; based on the signal decomposition result, solving the overdetermined equation set to obtain modal parameters of each coupling vibration source; and determining a state monitoring result of the long flexible blade according to the modal parameters of the coupling vibration sources.

The invention belongs to the technical field of multi-component aerodynamic load measurement sensors, and discloses a method for applying a constant force to a half-mode balance calibration system. The method for applying the constant force comprises the following steps: installing the constant force value loading device; accurate force value loading is carried out; carrying out displacement real-time compensation; constant force value output is kept at all the force application device point positions; and completing the ground static calibration of the half-mode balance. According to the method for applying constant force, the displacement of the electric cylinder is calculated according to the value of the applied force, after the corresponding displacement of the electric cylinder is completed through closed-loop control of the driving electric cylinder, the steel spring inevitably generates creep displacement in the process of waiting for arrival of a plurality of force application device point positions, and the creep displacement is changed into the creep displacement. The applied force value corresponding to the creep deformation is synchronously measured by the high-precision force sensor, the compensation displacement of the piezoelectric ceramic is correspondingly calculated, the creep deformation displacement is dynamically compensated in real time, the constant force value loading device is ensured to be always at the required constant force value, and the high-precision calibration of the half-mode balance is realized.

The invention relates to the technical field of turbomachinery monitoring, and discloses a cross-dimension turbomachinery dynamic risk prediction and visualization system. A dynamic data acquisition module of the system acquires multi-source heterogeneous sensing data such as a vibration spectrum sequence, an aerodynamic load distribution matrix, a rotor axial displacement time sequence and a surface temperature field thermodynamic diagram in real time; the service degradation evaluation module extracts a vibration characteristic spectrum based on a historical degradation mode library, calculates an instability risk level in combination with an aerodynamic load deviation value, and fuses a displacement sudden change gradient and a temperature difference abnormal area to generate a service degradation track matrix; the multi-dimensional risk prediction module inputs the degradation track matrix into a space-time coupling prediction network, and outputs a dynamic risk assessment vector including time-varying fault probability distribution, a residual life prediction value and a risk propagation path set; and the risk visualization engine module constructs a three-dimensional risk thermal field model and generates a dynamic thermal grid layer superposed on the digital twinborn body.

The invention relates to the technical field of motor current limiting, and discloses a cooling fan motor starting current limiting method, device and equipment, and the method comprises the steps: carrying out the starting power calculation of a radiator, and obtaining a drive power prediction value; rotor angle position detection and blade aerodynamic resistance calculation are carried out, and aerodynamic load distribution parameters of all phase change points are obtained; performing starting current limitation to obtain a current limitation control instruction; performing motor commutation time sequence control to obtain a basic commutation control signal, and meanwhile, monitoring a starting torque abnormal increment to obtain a reverse airflow recognition result; according to the method, the current limit value is increased in the emergency mode to accelerate the starting response, the current limit is reduced in the energy-saving mode to reduce the energy consumption, and the starting current phase difference compensation is carried out to obtain a reverse airflow compensation control parameter and fuse the reverse airflow compensation control parameter with the basic phase-change control signal to obtain a target phase-change control signal. And the intelligent balance between the starting performance and the energy efficiency is realized.

The invention discloses a floating type offshore wind turbine aerodynamic load calculation method based on a frequency domain method. The method comprises the steps that a state derivative is determined based on a blade element momentum theory quasi-steady-state assumption, and a dynamic inflow model is used for correction; establishing a pneumatic-elastic coupling two-degree-of-freedom linear dynamic model; establishing a wind wheel kinetic model; establishing a control model according to a floating type offshore wind turbine pitch angle control strategy, a torque control strategy and a floating body motion feedback control strategy; based on the pneumatic-elastic coupling two-degree-of-freedom linear dynamic model, the wind wheel dynamic model and the control model, pneumatic additional mass and pneumatic additional damping are obtained; pneumatic exciting force acting on the hub when the position of the cabin is fixed is obtained; and based on the pneumatic additional mass, the pneumatic additional damping and the pneumatic exciting force, an overall linear dynamic model of the fan is established and solved, and overall response is obtained. According to the method, the calculation result precision can be improved while the calculation efficiency is ensured, and a technical support is provided for accelerating the simulation efficiency of the offshore wind turbine.

The invention discloses a wind turbine blade semi-coupling aeroelastic modeling method considering nonlinear deformation, and belongs to the technical field of fan simulation calculation. In combination with calculation parameters used by three-party software, establishing a blade structured load model and a blade correction aerodynamic model, calculating an aerodynamic load and a structural load, and superposing: superposing the aerodynamic load, the gravity load and the centrifugal force load of the blade as an external load of a nonlinear structure control equation of the blade, and taking the external load as a calculation parameter; according to the method, the blade nonlinear structure model and the semi-coupling simulation process of the three-party wind turbine simulation software are constructed, and under the same simulation environment and load conditions, the blade nonlinear structure model and the three-party wind turbine simulation software can be subjected to semi-coupling simulation, so that the blade nonlinear structure model and the three-party wind turbine simulation software can be subjected to semi-coupling simulation calculation. The higher-precision non-linear motion response characteristics of the super-long flexible wind turbine blade are calculated, and a good effect can be achieved in the aspects of initial structure design and response evaluation of the large wind turbine blade.

The invention discloses an integrated coupling calculation method and system for a floating type wind wave combined power generation device based on Modelica-AeroDyn-MoorDyn, and relates to the technical field of offshore wind power generation, and the method comprises the steps: constructing a floating type fan model and a wave energy floater model which are highly matched with the actual operation of the floating type wind wave combined power generation device through Modelica; the aerodynamic load can be accurately loaded to the floating fan in an omnibearing mode, meanwhile, the attachment mode between the wave energy floater and the floating fan is established, the freedom degree of the floater can be freely released, enough precision is provided for reliability and stability evaluation of mooring based on the concentrated mass method by combining MoorDyn, and based on collaborative simulation of Modelica-AeroDyn-MoorDyn, the reliability and stability of the floating fan can be evaluated. The simulation result of the multi-floating-body coupling response obtained on the whole can truly reflect the operation state of the floating type wind and wave combined power generation device, and the coupling reliability is improved.

The invention provides a strong nonlinear simulation method and device suitable for a large floating fan, and the method comprises the steps: dividing a target floating fan into a plurality of body structures according to the model parameters of the target floating fan, so as to construct a multi-body model containing a plurality of degrees of freedom, and building a whole machine load and a motion transmission path; the aerodynamic load input of each body structure is calculated, and the nonlinear dynamic response of the blade is calculated according to the aerodynamic load input of each body structure; according to the coordinate transformation relation, the nonlinear dynamic response of the blade is converted into a whole coordinate system and input into a multi-body dynamic model of the whole machine, generalized active force and generalized inertia force of each body structure in the target floating type draught fan are obtained through calculation, and the motion response of each body structure of the target floating type draught fan is obtained through simultaneous solution. According to the scheme, the motion response of each body structure of the target floating fan can be accurately determined, so that the running state of the floating fan in the deep and far sea complex environment can be accurately evaluated.

The invention belongs to the technical field of numerical simulation and analysis of unmanned aerial vehicles, and relates to a rigid-flexible coupled variable-camber-range deformable wing optimization design method, which comprises the following steps of: obtaining working conditions of an aircraft, determining wing types and basic parameters of wings of the aircraft, and establishing a three-dimensional aerodynamic model of the wings; variable-attack-angle pneumatic simulation is carried out on working conditions of the aircraft in take-off and cruise, optimal camber values and corresponding pneumatic loads of wings under multiple working conditions are determined, and the positions of rotating joints of the deformed wing ribs are adjusted to obtain the deformed wing ribs after primary optimization; dividing the optimization range of the deformed wing rib after primary optimization into a fixed area and an optimizable area, loading an aerodynamic load under the optimal camber value in the optimizable area to perform aerodynamic simulation to obtain a deformed wing rib after secondary optimization, and optimizing the structure; and a deformed wing rib sample is made, performance testing is conducted, and the optimizable area is adjusted till the wing performance meets the preset requirement. The aerodynamic efficiency of the full flight envelope can be improved.

The invention discloses a floating fan aerodynamic load real-time mixing test method and system based on AI enhancement, and the method comprises the steps: calculating the six-degree-of-freedom motion information of a floating foundation through a numerical calculation model based on a real-time floating foundation kinetic equation; the method comprises the following steps: carrying a reduced-scale fan model on a six-degree-of-freedom motion platform, placing the six-degree-of-freedom motion platform on a wind tunnel atmospheric boundary layer, controlling the six-degree-of-freedom motion platform based on floating foundation six-degree-of-freedom motion information, driving the reduced-scale fan model to move, generating an aerodynamic load in a simulated wind environment, measuring an original load signal, and correcting the original load signal. Synchronously recording the actual pose of the six-degree-of-freedom platform; and AI correction is carried out on the corrected load signal and the actual pose of the six-degree-of-freedom platform to obtain a net aerodynamic load, the net aerodynamic load is fed back to the numerical calculation model, and closed-loop updating is carried out to realize coupling circulation. According to the method, the problem of interaction between numerical values and physical boundaries is solved, and the test precision of the large floating fan under the complex environment load can be remarkably improved.

The invention provides an impeller unbalance monitoring method based on fusion of wind speed and blade root load, which comprises the following steps of: firstly, constructing a dynamic synthesis model of local effective wind speed of a blade, and establishing a dynamic effective wind speed model of each point of the blade by combining wind shear, a pitch angle, a rotation effect and an incoming flow wind direction so as to provide high-precision input for theoretical aerodynamic load calculation; then, a multi-sensor dynamic data fusion method is fully adopted, real-time wind speed field data and direct measurement data of a blade root load sensor are dynamically fused, a real-time correction algorithm based on a physical model is constructed, interference of wind speed fluctuation on load judgment is eliminated, and unbalance detection precision is improved. And finally, based on a dynamic threshold early warning mechanism adopted by theoretical-actual load deviation, a sliding window standard deviation analysis and machine learning algorithm is introduced to set a dynamic abnormal threshold of the load deviation. Therefore, the unbalance state of the impeller is recognized in real time, and real-time monitoring, analysis and early warning of pneumatic unbalance of the fan are achieved.

The invention discloses a wind power plant active yaw optimization method and system considering a fatigue load of a wind turbine, and relates to the technical field of wind turbine power generation, and the method comprises the steps: obtaining a wake flow model for calculating the equivalent inflow wind speed of a wind wheel surface of the wind turbine; determining a wind wheel surface equivalent inflow wind speed-yaw angle-thrust coefficient two-dimensional lookup table and a wind wheel surface equivalent inflow wind speed-yaw angle-power two-dimensional lookup table of each wind turbine in the wind power plant; constructing an equivalent fatigue load proxy model of the wind turbine based on a blade aerodynamic load and blade gravity coupling effect; and constructing an optimized objective function by taking power maximization and equivalent fatigue load minimization as objectives, solving the optimized objective function through an optimization algorithm according to the actually measured wind turbine-wind measurement data, the wake flow model, each two-dimensional query table and the equivalent fatigue load proxy model, and determining a target yaw angle combination. On the basis of the scheme, the fatigue load caused by the wake effect is reduced while the power improvement is guaranteed, and the active yaw optimization reliability is improved on the whole.

The invention provides a method for determining the working load environment of an aero-engine rotor connection structure, belongs to the field of dynamic analysis and design of aero-engine rotors, and aims at a rotor structure system with a connection structure in an advanced aero-engine to determine the type of a load possibly borne by the connection structure. Based on a rotor finite element model and aerodynamic thermodynamic parameter input of an engine, aerodynamic load analysis, temperature distribution simulation, rotor dynamic characteristic simulation and the like are carried out respectively, and working load amplitudes of a connection structure under different working conditions are obtained. The energy differential method is innovatively adopted to obtain the bending moment at the connecting structure, and the accuracy of bending moment calculation is improved. According to the method, the working load environment of the rotor connection structure can be accurately obtained, accurate load boundary conditions are provided for mechanical property simulation of the rotor connection structure, so that the simulation analysis precision is improved, and meanwhile, reliable data support can be provided for the mechanical property of the connection structure and rotor dynamics optimization design.

The invention discloses an intelligent variable pitch control method, system and equipment for a wind generating set, and relates to the technical field of wind generating set control, and the method comprises the steps: synchronously collecting multi-source data in real time through a multi-source heterogeneous sensor array, constructing a dynamic load spectrum matrix, and carrying out nonlinear optimization; an optimal pitch angle sequence is generated to drive a variable pitch execution mechanism, meanwhile, the blade stress change rate is monitored in real time, and an aerodynamic load-structure response coupling factor is calculated; when the factor exceeds a safety threshold, the pitch angle command is reconstructed and the pitch angle is forcibly adjusted to a preset safety angle. The technical problems that the power generation efficiency and the structure safety are difficult to consider under the complex turbulence condition and a safety protection mechanism under the over-limit working condition is lacked in the variable pitch control of the existing wind generating set are solved, and the aim that the power generation efficiency and the structure safety are effectively improved through nonlinear optimization control and introduction of an over-limit triggered standby control path is achieved. And the technical effect of dynamic unification of power generation efficiency and structural safety in a complex turbulence environment is achieved.

An intelligent unmanned aerial vehicle pneumatic structure reduced-order analysis model comprises a pneumatic reduced-order model and a structure reduced-order model. The aerodynamic structure order reduction analysis process comprises the steps that an aerodynamic order reduction model and a structure order reduction model are initialized; under the given calculation working condition, the aerodynamic load acting on the intelligent unmanned aerial vehicle structure is obtained through calculation of the aerodynamic reduced-order model; transmitting the load on the pneumatic grid to the structural grid through a force interpolation algorithm; solving deformation response by the structure order reduction model under the action of aerodynamic load; the structural deformation is fed back to the pneumatic grid through displacement interpolation, and the pneumatic configuration is updated; and performing iterative calculation until a convergence criterion is met, finally obtaining a pneumatic structure analysis result in an equilibrium state, and outputting a pneumatic coefficient and structural deformation and stress. According to the method, the CFD / CSD model is replaced by the equivalent model, so that the calculation efficiency is remarkably improved on the premise of ensuring the calculation precision.

The invention discloses an operation control method and device for a vertical axis wind turbine generator, and belongs to the technical field of wind power generation. The method comprises the steps that a pitch angle of a lower blade is driven to be gradually increased to a preset angle at a preset angular speed through a variable pitch controller; when the rotating speed of the wind wheel reaches the cut-in rotating speed, the optimal tip speed ratio is tracked until the rotating speed of the wind wheel rises to the rated rotating speed; when the rotating speed of the wind wheel reaches the rated rotating speed, the rotating speed of the wind wheel is stabilized at the rated rotating speed; when the driving torque under the action of the aerodynamic load continuously exceeds the rated torque of the generator and the rotating speed of the generator reaches an early-warning rotating speed threshold value, a shutdown control strategy is triggered; and under the shutdown control strategy, the connection between the generator and the power grid is cut off, and mechanical braking is applied, so that the wind wheel stops rotating. According to the technical scheme, smooth starting of the wind wheel, stable operation at the rated rotating speed and safe shutdown in the fault state are achieved, the starting and stopping capacity and power stability of the unit are effectively improved, the wind speed application range is expanded, and it is guaranteed that the whole-process operation of the unit is safe and reliable.

The invention discloses a large flexible wing static aeroelasticity analysis method based on a physical information neural network, and belongs to the field of aircraft design. The method comprises the following steps: for the wing with the super-high aspect ratio, firstly, dispersing the wing into n spanwise sections based on a strip theory, and initializing a reference angle-of-attack parameter of each spanwise section; then, a physical information neural network (PINN) is built, unsteady flow field solving is carried out on each section, for the current ith iteration, the physical information neural network is used for sequentially traversing and extracting pressure distribution of the airfoil surface of each section, respective aerodynamic load distribution is calculated, and the generalized force of the airfoil is obtained; and solving a structural dynamics equation based on the generalized force and structural information of the wing, calculating the deformation of the large-deformation wing by using a modal rotation method, and finally, carrying out solving iterative circulation on aerodynamic force and structural deformation until the attack angle is converged, so as to obtain the actual lift force L of the wing. According to the method, the calculation precision and efficiency are remarkably improved, and different flight conditions and wing design can be adapted.

The invention relates to the technical field of wind power generation. The invention provides an emergency yaw and automatic crosswind method and system for a wind turbine generator. The method comprises the following steps: monitoring the on-off state of a safety chain in real time, and activating an emergency power supply switching module when detecting that the safety chain is disconnected; synchronously acquiring unit vibration spectrum, impeller rotating speed, environment wind speed and cabin load distribution data, and generating dynamic risk assessment parameters based on a multi-source signal fusion algorithm; inputting a hierarchical control instruction to a yaw driver according to a comparison result of the risk assessment parameter and a preset threshold value; and in the automatic crosswind control stage, the yaw rate and the angle offset are dynamically adjusted based on the blade root bending moment real-time feedback and the wind speed change rate, so that the unit maintains the aerodynamic load balance in the non-windward state. The problems that after a safety chain of an existing wind turbine generator is disconnected, yaw capacity is completely lost, emergency crosswind protection or fault recovery cannot be achieved, and a traditional emergency yaw scheme is high in cost, complex in maintenance, slow in response, difficult to adapt to complex working conditions and the like are solved.

The invention provides a high aspect ratio wing topological optimization method considering pneumatic-structure coupling. The method comprises the following steps: establishing a pneumatic-structure strong coupling topological optimization model; performing finite element analysis to obtain an original variable field of the high aspect ratio wing; generating a filtering variable field and a projection variable field; deformation displacement of each finite element unit is obtained based on a UMMI material interpolation model; establishing information transmission, structure displacement response, aerodynamic load transmission and aerodynamic load updating strategies under pneumatic-structure coupling, and analyzing and updating the aerodynamic load; according to the method, manufacturing constraints such as geometric nonlinearity, multi-material layout and wing rib orientation size are comprehensively considered, design variables in an original variable field are subjected to iterative optimization solution, a wing optimization configuration is obtained, the three core problems of calculation distortion, performance deviation and manufacturing difficulty in lightweight design of the high aspect ratio wing are successfully solved, and the method is suitable for the lightweight design of the high aspect ratio wing. And the comprehensive performance and economical efficiency of the aircraft are remarkably improved.

The invention discloses a brush type sealing fluid-solid-heat-grinding multi-physics field efficient coupling method, and particularly relates to the field of aero-engine sealing. Comprising the following steps: establishing an interdigitated tube bundle solid model, taking the interdigitated tube bundle solid model as a first model, and executing a division step; cFD simulation is carried out on the first model after grid division, and flow field distribution is obtained; determining a three-dimensional aerodynamic load of the brush wires based on the flow field distribution; determining the three-dimensional pneumatic deformation result of the brush wires according to the three-dimensional pneumatic load, and determining the wear volume of each brush wire; according to the pneumatic deformation result of the brush wires and the abrasion volume of each brush wire, the forked row tube bundle solid model is updated, and a deformation geometric model under aerodynamic force is obtained; and taking the deformation geometric model as a first model, starting to execute a division step, and stopping iteration until a brush wire three-dimensional pneumatic deformation result reaches a first condition, so as to finish accurate simulation of a fluid-solid-heat-grinding coupling effect.

A total-degrees-of-freedom movement-based wind tunnel test device for a vehicle on a bridge, comprising a model body (1), a force measuring assembly, a longitudinal moving assembly, and a transverse moving assembly. The longitudinal moving assembly comprises longitudinal movement wheels (2) arranged at two ends of the model body (1) and a longitudinal conveyor belt (3) sleeved on the two longitudinal movement wheels (2). The upper surface of the longitudinal conveyor belt (3) is flush with a bridge surface of the model body (1). The transverse moving assembly comprises a follow-up part and a transverse moving part arranged on the follow-up part. The follow-up part is connected to the longitudinal conveyor belt (3) so that the longitudinal conveyor belt (3) drives the follow-up part to move in the longitudinal direction of the model body (1). The transverse moving part is connected to the follow-up part. The transverse moving part can move in the transverse direction of the model body (1), and the top surface of the transverse moving part is flush with the surface of the longitudinal conveying belt (3). The force measuring assembly comprises a force measuring balance (4) and a model vehicle (5). The force measuring balance (4) is connected to the top surface of the transverse moving part. The model vehicle (5) is connected to the force measuring balance (4). The present invention can simulate and measure the aerodynamic load when a vehicle moves along a bridge and changes the lane. The results of wind tunnel tests are more referenceable.

The invention relates to the technical field of fatigue testing, and discloses a blade fatigue testing device and method based on a vortex-induced vibration principle, the blade fatigue testing device based on the vortex-induced vibration principle comprises a test bench foundation and at least one excitation unit, the test bench foundation is suitable for fixing a blade root of a tested blade; the excitation unit comprises a blade cover body and a pneumatic loading module, the blade cover body is of an annular structure fixedly arranged on the periphery of a test blade in a sleeving mode, the pneumatic loading module is arranged below the blade cover body, and the pneumatic loading module comprises a frame and at least one air blowing piece installed on the frame; wherein the air blowing piece is configured to blow air to the blade cover body, and turbulent flow is formed at the blade cover body. Non-contact excitation is achieved through aerodynamic coupling, the additional mass influence caused by mechanical connection is avoided, and full-size fatigue verification of the blade is completed under the condition that the natural vibration characteristic is kept.

The invention discloses an aerodynamic load determination method and device of a train and the train, and relates to the field of aerodynamics. The method comprises the steps that geometric shape data of the train with the load to be determined are obtained; inputting the geometric shape data of the train with the to-be-determined load into the prediction model to obtain the pressure and shear stress of the train with the to-be-determined load, which are output by the prediction model; and according to the pressure and the shear stress of the train with the to-be-determined load, determining the resistance, the lift force and the lateral force of the train with the to-be-determined load. The prediction model is trained through the data of the train with the known load, the trained prediction model only needs to input the geometric file of the train object to be calculated, the pressure and the shear stress can be obtained, the threshold in the professional field is not involved, and therefore all workers have the operable ability. Simulation calculation is replaced by the prediction model, the prediction model does not need to be subjected to simulation calculation again, the pressure and the shear stress are directly output, the calculation time is shortened, and the calculation efficiency is improved.

The invention discloses a full-coupling numerical simulation system and method for a wind and wave hybrid energy obtaining system, and relates to the field of data analysis, and the method comprises the steps: generating an aerodynamic load of a current period based on incoming flow wind speed and coupling dynamics response data of a previous simulation period; based on preset mooring system parameters and the coupling dynamics response data of the previous simulation period, generating a mooring load of the current period; in the random wave field, determining the hydrodynamic force of the floating foundation entity and the wave energy power generation entity, and generating a wave load; determining a PTO force based on the relative motion between the power generation platform and the wave energy power generation entity; and taking the aerodynamic load, the mooring load, the wave load and the PTO force as external force terms in the same time domain kinetic equation for unified solution, and obtaining a coupling kinetic response of the current simulation period. According to the full-coupling numerical simulation system and method for the wind and wave hybrid energy obtaining system, the simulation precision of the simulation system can be improved, and the overall calculation efficiency of the system is improved.

The invention discloses a system-level coupling modeling method, system, equipment and medium for a multi-wind-wheel multi-tower-drum floating type wind turbine generator set, and relates to the field of simulation modeling, and the method comprises the steps that parameter information of the multi-wind-wheel multi-tower-drum floating type wind turbine generator set is obtained, and a multi-system structural dynamics model is obtained based on the parameter information of the multi-wind-wheel multi-tower-drum floating type wind turbine generator set; the unsteady aerodynamic model, the hydrodynamic model and the mooring structure dynamic model are used for outputting aerodynamic loads, hydrodynamic loads and mooring cable tension, the aerodynamic loads, the hydrodynamic loads and the mooring cable tension are fed back to the multi-system structure dynamic model, and based on a Lagrange framework, the models are subjected to joint simulation operation through a joint simulation interface, so that the mooring cable tension is obtained. And the multi-wind-wheel and multi-tower-drum floating type wind turbine generator is designed. According to the method, a complete system dynamics model can be established, and complete machine level rapid evaluation and engineering iteration under multiple working conditions can be supported.