3761results about "Aerodynamic testing" patented technology

The invention discloses a small-size rotor test bed, a parameter matching method and a control angle resolving method, belongs to the technical field of aviation aerodynamic wind tunnel tests, and aims to solve the problems of an existing small-size rotor test bed. The test bench comprises a main shaft tilting system, the main shaft tilting system comprises a base, a tilting electric cylinder, two rotating shaft seats, a tilting table and a tilt angle sensor, the two rotating shaft seats are arranged on the left side and the right side of the base respectively, shaft heads are arranged on the left side and the right side of the tilting table respectively, and the two coaxial shaft heads are in corresponding rotating fit with the two rotating shaft seats respectively. A rear cylinder cover of the tilting electric cylinder is hinged to the front side of the base, a piston rod of the tilting electric cylinder is arranged upwards and hinged to the front side of the tilting table, and a tilt angle sensor is arranged on the tilting table. The test rotor wing is connected with the power transmission system, the power transmission system is connected with the tilting table, and technical support can be provided for measurement of rotor wing performance, blade surface pressure and blade bending moment load of the small unmanned aerial vehicle.

The invention discloses a full-state wind field simulation system and method for wind resistance detection of an unmanned aerial vehicle. The system comprises a system base, a distribution box, a system control cabinet, a modular wind wall, a protective net and a wind speed and direction sensor. The wind field simulation system is of a cuboid structure, independent fan arrays are embedded in modular wind walls, the three modular wind walls independently generate three single-direction wind fields forming 90-degree included angles, and wind fields of any size and any direction can be generated through space wind field vector superposition. The distribution box provides power support for the ventilation wall to work, and the system control cabinet can independently control the fan arrays. The protective net is fixed on the system base bracket, so that the unmanned aerial vehicle is prevented from causing system damage in the testing process; the wind speed and direction sensor senses wind speed and direction information of a wind field in a test area and quantitatively represents the simulated wind field. According to the invention, a wind field with any size and direction can be generated for an unmanned aerial vehicle wind resistance test, and necessary test platform support is provided for unmanned aerial vehicle wind resistance detection.

The invention belongs to the technical field of wind tunnel tests, and particularly relates to a precession simulation device for a spiral flutter wind tunnel test. According to the invention, the design problem of the rotor craft spiral flutter wind tunnel test device is solved, and the key influence parameters and influence rules of the spiral flutter of the aircraft are researched by designing the precession motion simulation device of the rotor craft. Rotation of the rotor wings can be realized in the wind tunnel, and the rotating speed of the rotor wings is adjusted through the motor. Meanwhile, pitching and deflection modal decoupling of the rotating shaft of the rotating system is achieved, and pitching and deflection modal frequencies are independently adjustable; meanwhile, the axis of the pitch axis and the axis of the yaw axis coincide, so that pitching and yaw freedom degree coupling precession motion can be achieved under the effect of gyroscopic moment. Meanwhile, nacelle rotating mass rotational inertia, nacelle weight and mass center position adjustment can be achieved; and finally, the rotating speed of the rotating mass such as the rotor wing and the propeller hub can be adjusted through a speed adjusting motor, matching of the rotating speed and the incoming flow speed is guaranteed, and the spiral flutter state is achieved.

The invention discloses a method for measuring an attitude angle of a free throwing object in a wind tunnel test through a binocular system, and belongs to the field of aerodynamics tests based on a photogrammetry technology. Comprising the steps that a binocular system is arranged in a wind tunnel, and internal and external parameters of the binocular system are calibrated through a cross scale; reconstructing the surface mark points of the calibration plate by photogrammetry outside the wind tunnel and establishing a local coordinate system; placing a calibration plate in the wind tunnel, wherein each vector of a local coordinate system is parallel or vertical to an incoming vector, and calibrating a wind tunnel coordinate system by adopting a resection method; carrying out photogrammetry and initial pose installation on mark points on the surface of a thrown object; acquiring each state image of the thrown object and reconstructing the three-dimensional coordinates of the surface mark points; taking the attitude angle of the thrown object as 0 degree as a reference state, and comparing the rigid body transformation relationship between the blowing state point cloud and the reference state point cloud to obtain attitude angle data. Alignment of a wind tunnel coordinate system and a binocular system coordinate system can be achieved, limitation of the appearance of the thrown object is avoided, and attitude angle data of the thrown object are calculated in a non-contact and high-precision mode.

The invention discloses a flexible photovoltaic support aeroelastic response wind tunnel test platform and method, and the platform comprises a platform body which comprises a wind field simulation region and an experiment test region. A wind tunnel wedge is arranged at the front section of the incoming flow wind direction in the wind field simulation area; a flexible photovoltaic support model is arranged in the experimental test area; the flexible photovoltaic support model comprises a photovoltaic panel, a flexible photovoltaic panel support and a flexible photovoltaic panel base; the flexible photovoltaic panel base is fixed on the wind tunnel turntable; the photovoltaic panel is fixed on the flexible photovoltaic panel base through the flexible photovoltaic panel bracket; steel cables penetrate through the interior of the photovoltaic panel, and the steel cables on the two sides are connected with an electronic tension meter and a tightening device. Through the platform and the method, a real complex wind field environment can be simulated, dynamic response data of the support under different working conditions can be obtained, and a scientific basis is provided for design optimization and wind resistance improvement of the flexible photovoltaic support.

The invention provides a wind tunnel health monitoring data mining method, medium and system, and belongs to the technical field of wind tunnel health monitoring data mining and processing, and the method comprises the steps: collecting a plurality of sensing signals to construct a monitoring data stream, and carrying out the filtering and noise reduction processing to obtain preprocessed data and an abnormal data set; and starting a GPU and CPU processing stream to receive the preprocessed data and the abnormal data set, performing component decomposition to obtain a steady-state data matrix, a dynamic data matrix, an abnormal feature matrix, a parameter data vector and an abnormal parameter vector, establishing a data mining feature equation set, and calculating a wind tunnel operation state evaluation result by using the wind tunnel operation state evaluation equation set. And generating a wind tunnel operation characteristic matrix and a wind tunnel state early warning index, and outputting an early warning signal according to a comparison result of the early warning index and a preset health threshold value. The technical problem that potential fault symptoms cannot be better found due to the fact that wind tunnel health detection data cannot be rapidly and efficiently mined and analyzed from the two aspects of steady state and dynamic state at present is solved.

The invention discloses a model wide-range attack angle change tail and web support device suitable for an airplane wind tunnel test, which comprises two support modes, namely a curved knife support rod and a web support support rod, an attack angle change mechanism, a lifting compensation mechanism and a mounting base, and is characterized in that a wind tunnel airplane model is arranged at the end part of the support rod, and the support rod is in screw connection with the attack angle change mechanism; the attack angle changing mechanism is connected to the lifting compensation mechanism through the mounting base, and the lifting compensation mechanism is mounted in wind tunnel test equipment. According to the invention, the large-range attack angle change of the airplane model in the wind tunnel test can be realized, and the center is kept unchanged at the height of the wind tunnel test.

The invention belongs to the technical field of hypersonic flight vehicle design, and discloses a design method for a thermal experiment model of a front body and an air inlet channel of a high-speed wind tunnel. The design verification method comprises the following steps: determining an overall structure and design requirements; determining a heating structure; determining a pressure measuring point and a temperature measuring point; determining an independent temperature control adjusting device; verifying the influence of the heat insulation groove on temperature gradient distribution; verifying the heat insulation effect of the heat insulation measures; model structure deformation generated by temperature is investigated; obtaining a heat flux density and surface temperature relation curve; the influence of model structure deformation on the flow field is studied. The design verification method proves that the precursor of the high-speed wind tunnel and the air inlet duct thermal experiment model have accurate temperature control and thermal insulation protection capabilities, and verifies the obvious influence of wall temperature change on the flow field structure; the aerodynamic thermal coupling effect can be effectively reproduced, a hypersonic air inlet heat-flow coupling experimental platform is established, and the experimental platform has engineering practical value.

The invention discloses a rod type six-component high-precision trace rolling moment wind tunnel balance and a measurement method, and belongs to the technical field of aerospace force measurement test power measurement. According to the invention, the problems of large processing difficulty, long processing period and incapability of meeting aviation tests in research and development of micro rolling moment balances at present are solved. A longitudinal column beam, a transverse column beam and a roll-on *-shaped beam are connected between a front cone and a combined element and between a rear cone and the combined element respectively, a resistance beam is arranged on the combined element, the thickness range of sheet beams of a multi-sheet structure of the longitudinal column beam is 0.5 mm-0. 8mm, the gap range of the sheet beams is 0.5 mm-1mm, the thickness range of sheet beams of a multi-sheet structure of the transverse column beam is 0.5 mm-0. 8mm, and the gap range of the sheet beams is 0.5 mm-1mm. According to the rod type six-component high-precision trace rolling moment wind tunnel balance and the measurement method, rolling output is effectively increased, and matching output of small rolling moment and loads in other directions is achieved.

The invention discloses an evtol tilt rotor aerodynamic noise wind tunnel test method, and belongs to the technical field of wind tunnel tests. In order to establish an evtol tilt rotor aerodynamic noise wind tunnel test method, the method comprises the following steps: carrying out a hovering empty propeller hub background noise test: rotating a rotor table, enabling the axis of a rotor to be perpendicular to the axis of a wind tunnel, carrying out an empty propeller hub aerodynamic and noise test, and then carrying out aerodynamic data acquisition and noise data acquisition at each rotating speed to obtain hovering empty propeller hub background noise data; performing a tilt rotor hovering noise test: installing blades, setting a rotor axis to be perpendicular to a wind tunnel axis, then performing pneumatic data acquisition and noise data acquisition at each total pitch and rotating speed, and correcting the obtained tilt rotor hovering noise data by using hovering empty propeller hub background noise data to obtain a tilt rotor hovering noise test result; obtaining static tension and static power under each total pitch and rotating speed of tilt rotor hovering; carrying out a transition state and axial flow forward flight empty propeller hub noise characteristic test; and carrying out a transition state and axial flow forward flight tilt rotor noise characteristic test.

The invention discloses a high-temperature and high-pressure multifunctional integrated shock tube test system, belongs to the technical field of explosion and impact dynamics tests, and aims at solving the problem that an existing shock tube is usually single in function and is only used for a simulation test of a certain function. The high-pressure section and the low-pressure section of the shock tube are both made of high-temperature-resistant nickel-based alloy, an induction heater is adopted for heating, high-pressure inert gas is filled into the high-pressure section through pressure gradients of diaphragm sets with different layers of diaphragm clamping sections, high temperature and high pressure of the high-pressure section at the temperature of 20-900 DEG C and the pressure of 0.1-50 MPa are obtained, and the high-pressure shock tube has the advantages that the high-pressure shock tube is compact in structure and low in cost. The multifunctional integrated shock tube test system can be used for researching the crushing characteristics of rock materials under the conditions of different pressures, temperatures, water contents and the like, the damage characteristics of explosion shock waves in the air to a target piece and the impact damage characteristics of a high-speed projectile body. Effective methods and means are provided for related research, and the shock tube test technology and engineering application capability are expanded. The test system is easy to implement, low in cost and multipurpose.

The invention discloses a multifunctional experimental device capable of realizing a wind wave coupling effect, which comprises a deep water experimental area, a transition experimental area and a shallow water experimental area, and is characterized in that a lifting floating bottom mounted at the bottom of a water tank can simulate the elevation change from a deep sea to a shallow sea seabed; a wind generating system is assembled above the water tank and is matched with the flow guide arrays on the two sides to provide a high-quality wind field for the experimental water tank; the L-shaped wave maker can make multi-directional irregular waves, the wave flow experiment water tank and the wind making system are used for constructing a target joint field required by an experiment, and the whole process that the waves are gradually propagated from deep sea to shallow sea under the wind wave coupling effect can be achieved. The device has multiple functions of wind generation, wave generation, current generation and the like, has the function of simulating various load factors which mainly influence ocean engineering structures, and compared with an existing experimental device, the device can achieve the real wind and wave coupling effect, more truly and completely simulate the whole process of ocean wave propagation, and the experimental device has the advantages of being simple in structure and convenient to use. And a more accurate marine simulation environment is provided for experiments.

The invention discloses a device and a method for a low-speed wind tunnel gust or flutter half-mode test, belongs to the field of wind tunnel tests, and aims to solve the problems that an existing gust or flutter half-mode test device cannot realize complete release of heaving and pitching degrees of freedom and is difficult to share the two tests. The device comprises an overall frame, the overall frame is installed in a wind tunnel test section, two sliding rails are vertically arranged on the front end face of the overall frame, two sliding block sets are arranged on the left side and the right side of the rear end face of a tackle, the two sliding block sets are in sliding fit with the two sliding rails in a one-to-one correspondence mode, two spring seats are arranged at the top end of the overall frame, and horizontal shafts are arranged on the spring seats. The inner ring ends of the two clockwork springs are connected with the horizontal shafts of the two spring seats in a one-to-one correspondence manner, the outer ring ends of the two clockwork springs respectively droop to be connected with the pulley, and the model mounting seat is cylindrical and is in running fit with the pulley; the device can be used for a gust load retarding test and a body degree of freedom flutter test, and can be shared by the two tests.

The invention belongs to the technical field of integrated test of airplanes and engines, and discloses a flow measurement method for coupling test of an airframe air inlet duct fan. The flow measuring method for the engine body air inlet duct fan coupling test comprises the steps that the pressure value of a pressure measuring point is calculated through CFD; calculating slope screening pressure measuring points; carrying out an air inlet channel wind tunnel test; training a neural network; carrying out an engine body air inlet duct fan integrated wind tunnel test; calculating a pressure correction coefficient; calculating a predicted flow coefficient; and correcting the flow coefficient. According to the flow measurement method for the engine body air inlet duct fan coupling test, the flow coefficient-surface pressure distribution matching characteristic of an air inlet duct is obtained through a wind tunnel test, and then the flow coefficient is obtained through the matching characteristic and the engine body surface and air inlet duct inner surface pressure distribution in an engine body air inlet duct fan integrated model; the method can accurately predict the air inlet flow and has engineering practical value.

The invention discloses a speed measurement method based on single-frame multiple exposure, and belongs to the field of hypersonic velocity field measurement. The implementation method comprises the following steps: recording equal time interval change of molecular marking in a flow field along with movement of the flow field through single-frame multi-time exposure imaging of an image enhancement camera, and realizing continuous and rapid acquisition of speed information within a short time after single-time marking. The morphological position after the time interval is determined according to the molecular marker, and the velocity field with spatial resolution in the flow field is extracted by mapping the marker before and after displacement, so that the velocity measurement precision is improved. Compared with other two-dimensional velocity field acquisition methods based on femtosecond laser molecular marker tracing velocity measurement, the method provided by the invention does not need a complex focusing lens combination, can obtain spatial positions of molecular markers at different moments only through isochronous continuous triggering exposure of a camera, thereby obtaining velocity flow field displacement information. And corresponding acceleration information can be further deduced according to the obtained velocity field. The method is especially suitable for hypersonic velocity field measurement.

The invention discloses a shock wave heat loading high-temperature wind tunnel and a test method, and relates to the technical field of high-temperature wind tunnel test equipment. The shock wave heat loading high-temperature wind tunnel comprises a shock tube, a wind tunnel test system, a pressure acquisition system and an air intake and exhaust system; a high-temperature and high-pressure gas source is obtained in a secondary shock wave reflection heating mode, and the total temperature of the obtained heating gas source is higher; the high-temperature wind tunnel realizes gas heating and pressurization completely through shock wave flow, extra electric power and gas requirements are not needed, and the cost of a single test is lower; the high-temperature wind tunnel test gas is premixed, so that the components of the test gas can be accurately controlled, and the purity of the components of the test gas is ensured; the device can obtain a high-temperature high-pressure subsonic flow field and even a supersonic flow field covering wide-range working conditions, can be used for visualization test diagnosis of spray fuel atomization and spontaneous combustion processes under high-temperature crosswind, accurately characterizes physical and chemical characteristic parameters such as fuel atomization characteristics, self-ignition characteristics, flame propagation characteristics and the like, and has a wide application prospect. And test data support is provided for engine combustion chamber spray atomization combustion organization.

The invention relates to a multi-dimensional high-resolution turbine blade heat-flow coupling field synchronous measurement method and system, and the method comprises the steps: obtaining a target spot image of known space distribution in a measurement space, and building a three-dimensional space mapping function; carrying out particle matching on the velocity field measurement original image based on a three-dimensional space mapping function, and reconstructing a three-dimensional particle trajectory by adopting a self-adaptive grid algorithm combined with machine learning to obtain a high-resolution three-dimensional velocity vector field; acquiring a temperature field measurement original image, performing three-dimensional space registration according to a three-dimensional space mapping function, further calculating voxel-level temperature distribution, and inverting a three-dimensional temperature field; and carrying out coupling analysis on the three-dimensional velocity vector field and the three-dimensional temperature field, and outputting a three-dimensional heat-flow coupling cloud picture. According to the invention, multi-dimensional and high-precision synchronous measurement of the temperature field and the velocity field in the complex flow field of the turbine blade is realized, the spatial resolution and dynamic response capabilities are remarkably improved, and a reliable experimental basis is provided for analysis and optimization of the cooling performance of the blade.

The invention discloses a rod type six-component optical fiber balance and an FBG grating installation method, and belongs to the technical field of optical fiber balances. The problems that an existing optical fiber balance is low in sensitivity, the measuring capacity of the existing optical fiber balance is affected, and wiring is not convenient are solved. A first group of four-column strain beams, a resistance element supporting sheet, a second group of four-column strain beams and an equal straight section are sequentially arranged between a model end conical surface and a fixed end conical surface, a resistance element elastic element is arranged on the resistance element supporting sheet, and the equal straight section is connected with the fixed end conical surface through an M42 left-hand thread; the first set of four-column strain beams, the second set of four-column strain beams and the resistance element supporting piece are all provided with optical fiber wiring grooves machined along the centers of the beams, and optical fibers are arranged in the optical fiber wiring grooves. According to the rod type six-component optical fiber balance and the FBG grating installation method, the measurement capability of the optical fiber balance and the wiring convenience are improved, on the other hand, a sensitization structure is optimized to a certain degree, and the sensitivity of the optical fiber balance is improved.

The invention discloses an L-shaped wind wave flow-earthquake simulation system and method suitable for a high gravity field, the simulation system comprises a model box, a wind generation system, an L-shaped wave generation system, a flow generation system and a vibration seabed model, and the model box is used for accommodating and installing each system and is arranged on a rotating arm of a centrifugal machine in an up-and-down swinging manner; the wind generation system is used for forming horizontal airflow circulation, the L-shaped wave generation system is used for generating waves, the flow generation system is used for generating flow, and the vibration seabed model is used for researching interaction between a maritime work structure and seabed soil under various sea conditions. The simulation system can reproduce sea wind, wave, ocean current and earthquake scenes in a high gravity field.

The invention provides a sound wave generator soot blowing test method and system. The method comprises the steps that an experiment platform for simulating the working environment of a low-low-temperature economizer is built, and a test sample and sensing equipment are installed; setting power output parameters including a fixed power level and pulse power modulation parameter, a soot blowing frequency and phase control parameter, a time period and adaptive adjustment parameter, a sound wave frequency and an airflow velocity and vector control parameter; soot blowing operation is carried out, data are collected through sensing equipment, the soot coverage rate and particle information are obtained through an optical imaging sensor, and the pressure intensity generated by sound waves at the position where soot particles are located is obtained through an acoustic sensor array; calculating cleaning efficiency, and performing adjustment and iterative experiment on parameters according to the cleaning efficiency and data feedback; comprehensive optimization of the soot blowing process of the sound wave generator is achieved, the soot blowing effect of the low-low-temperature economizer is improved, then the overall operation efficiency of energy equipment is improved, the service life of the equipment is prolonged, and the requirements for environmental protection and energy saving are met.

The invention discloses a wind vibration actual measurement analysis method for a large-span steel structure roof, and belongs to the field of steel structure engineering monitoring, and the actual measurement analysis method comprises the following specific steps: I, based on the geometric and dynamic characteristics of a large-span steel structure roof structure, optimizing the arrangement of each sensor, and constructing a multi-modal heterogeneous sensing network; iI, acquiring wind speed and wind direction time sequence data according to the multi-mode heterogeneous sensing network, establishing a reconstruction model of a non-stationary wind field, and predicting time-varying distribution of wind pressure on the surface of the structure; according to the method, high-fidelity dynamic reconstruction of the wind field is realized, the authenticity of wind load input is improved, the data quality and information diversity are improved, the prediction precision and timeliness of the wind pressure field are improved, and the scientificity and the monitoring effect of an overall layout strategy are enhanced; according to the method, the accuracy of long-term performance evaluation can be improved, environment coupling simulation of structural response is achieved, the dynamic adaptive capacity of analysis is enhanced, the structural rigidity evolution rule is depicted finely, and the robustness and local recognition capacity of the model under uncertain data are enhanced.

The invention discloses a dynamic turbulence measurement method. A hot-wire anemometer with two hot-wire probes is adopted to measure the wind speed of two points in a space; then setting the sampling frequency fc of the hot-wire anemometer, and counting the average time ts and the space length r; obtaining voltage data output by the hot-wire anemometer, judging whether the voltage data is normal or not, and removing abnormal data; corrected correction voltage data is obtained; calculating the wind speed u according to the corrected voltage data; determining a time interval td according to a preset sampling frequency fc, calculating a speed structure constant # imgabs0 # by combining the wind speeds measured by the two hot-wire probes, and calculating second-order and third-order turbulence dissipation rates; and calculating the kinematic viscosity coefficient v2 at the in-situ measurement position, the internal scale 10 of the atmospheric turbulence and the turbulence I in sequence. The dynamic turbulence measuring method overcomes the defects that a temperature pulsation instrument cannot measure dynamic turbulence and an ultrasonic anemometer platform is poor in applicability, and has the advantages of being easy and convenient to operate, suitable for being carried on a sounding balloon for high-altitude turbulence measurement in a severe environment and the like.

The invention provides a wind tunnel structure sensitive reflection settlement position intelligent identification method, and belongs to the technical field of wind tunnels. Vibration sensors and displacement sensors are arranged at key positions of a wind tunnel structure to form a monitoring network, collected signals are preprocessed, and a settlement factor matrix is established; a dynamic load matrix is constructed to describe composite load distribution, a vibration burr identification matrix is established, real signals and noise are separated by adopting wavelet transformation, a slow settlement trend matrix is constructed to extract a long-term change rule, and a least square optimization algorithm is adopted to jointly solve each matrix parameter to establish a settlement position identification function. The settlement three-dimensional position coordinate is determined according to the multi-sensor data fusion result, the structure safety state is evaluated through the settlement risk coefficient, and the technical problems that the wind tunnel structure settlement position recognition precision is insufficient, and a real settlement signal and a noise interference signal cannot be effectively distinguished are solved.

The invention discloses a flow field velocity measurement and visualization device and method, and relates to the technical field of flow field display measurement, and the device comprises a two-color laser emission system, a surface dielectric barrier discharge system, a Cassegrain light path shaping system, a fluorescence signal detection system and a data processing system. Wherein the two-color laser emission system is used for generating femtosecond pulse laser and first laser, and the femtosecond pulse laser and the first laser are converged and collimated by the Cassegrain light path shaping system and then are focused to a detection area to cooperatively excite nitrogen molecules; the surface dielectric barrier discharge system forms a plasma environment in the detection area; the fluorescence signal detection system is used for collecting nitrogen molecule fluorescence signals in the detection area; and the data processing system is used for controlling a time sequence, realizing visual representation of a flow field structure in a detection area and realizing speed measurement of a flow field in the detection area, and the device and the method can realize synchronous acquisition of a speed vector and flow field structure parameters near a wall surface under a millimeter-level spatial resolution and a microsecond-level time scale.

The invention relates to the technical field of flow field temperature testing, in particular to a gas phase temperature measuring probe for a high-speed low-temperature cloud field and a design method and application of the gas phase temperature measuring probe. The design method of the gas phase temperature measurement probe for the high-speed low-temperature cloud field comprises the following steps: designing a temperature measurement probe configuration on the basis of a backward temperature measurement probe configuration in combination with a backward step two-phase flow theory in the backward temperature measurement probe configuration and working conditions of the high-speed low-temperature cloud field; secondly, two-phase flow simulation and suction flow simulation are carried out based on the temperature measurement probe configuration, and suction flow is designed; thirdly, icing numerical simulation is carried out, and two-phase flow simulation is carried out; and finally, analyzing the simulation result of the near-wall flow field change of the iced temperature measurement probe configuration and the simulation result of the gas-liquid flow characteristics, and if no liquid drop is monitored at the detection position of the temperature sensing element in the iced temperature measurement probe configuration, completing the design; otherwise, repeating the above steps until no liquid drop is monitored at the detection position of the temperature sensing element in the frozen temperature measurement probe configuration.

The invention discloses a multifunctional wind wave and flow coupling experiment platform, and belongs to the technical field of bridge engineering. The experimental platform comprises a wind power system and a water power system, the wind power system is of a two-layer structure, the upper layer is an unsteady wind tunnel, and the lower layer is a steady wind tunnel; the hydrodynamic system is located below the steady wind tunnel; the steady wind tunnel is of a sealed annular structure, and a fan, a first experimental section and a second experimental section are arranged in the steady wind tunnel; the unsteady wind tunnel is arranged above the second experiment section, and interaction windows A which are communicated with each other are formed between the unsteady wind tunnel and the steady wind tunnel; the hydrodynamic system is located below the second experiment section, and an interaction window B which is communicated with the steady wind tunnel is formed between the hydrodynamic system and the steady wind tunnel; the unsteady wind tunnel, the steady wind tunnel and the hydrodynamic system are communicated with one another through the two interactive windows. The experimental platform can simulate different coupling action environments of wind, waves and flows, and is used for testing the stability, reliability and durability of various ocean engineering structures and equipment.

The invention relates to the technical field of wind tunnel tests, in particular to a segment model system for a wind tunnel test, which comprises two groups of inner elastic suspension systems, a segment model is connected between the inner elastic suspension systems, and an outer elastic suspension system is arranged on the outer side of each group of inner elastic suspension systems. The inner elastic suspension system can twist relative to the outer elastic suspension system and drive the outer elastic suspension system to vertically move; the vertical damping adjusting devices are arranged at the two ends of the outer elastic suspension system and used for providing adjustable vertical damping for the outer elastic suspension system; the torsional damping adjusting device is arranged between the inner elastic suspension system and the outer elastic suspension system and used for providing adjustable torsional damping for the inner elastic suspension system; the end connecting device is used for connecting the inner elastic suspension system and the outer elastic suspension system; and the limiting device is used for limiting the vertical movement of the outer elastic suspension system, so that the separation and combination of a vertical mode and a torsional mode and the independent adjustment of vertical damping and torsional damping are realized.

The invention belongs to the technical field of hypersonic flight vehicle test, and relates to a hypersonic flight vehicle simulation flight test system based on a multi-modal large model, which comprises a data acquisition and fusion system and a control system. Through a data acquisition and fusion system and a cross-modal attention mechanism, efficient alignment and feature representation of time sequence data, environmental data and a historical case library acquired by a ground test system are realized, and the data acquisition and analysis precision is remarkably improved. In combination with a hardware system, effectiveness of test parameters is ensured, and the aircraft design and verification period is shortened. The control system dynamically adjusts test parameters through a natural language instruction, the model generates a structured control parameter vector through semantic understanding, the performance and stability of the aircraft control system are improved, the test operation complexity is reduced, and the user experience is improved.

The invention relates to the technical field of wind tunnel experiment equipment, in particular to an adjustable multipurpose wind tunnel simulation device which comprises an adjusting structure, a wind tunnel body and an auxiliary module. The wind tunnel body is fixedly arranged on the adjusting structure, and the auxiliary module is detachably installed in the wind tunnel body. The height and angle of the wind tunnel body are flexibly adjusted through the adjusting structure, the flow guide plate set and the sensor array in the wind tunnel body work cooperatively, the airflow direction and speed are accurately controlled, and experimental data are monitored in real time. The auxiliary module is suitable for various experiment scenes through combination of a filter screen and a test model. After the electromagnetic lock is powered off, the limiting block is released, the filter screen is quickly popped out by means of the acting force of the elastic buckle, and replacement or cleaning is convenient. The flexibility and the application range of experimental equipment are improved, the operation convenience is optimized, and the experimental efficiency and the result accuracy are improved.

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.