406 results about "Aerodynamics" patented technology

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 an aircraft aerodynamic parameter prediction method based on multi-view airfoil profile concept correlation learning, and belongs to the technical field of aerodynamics, deep learning and computer vision crossing, and the method comprises the steps: converting a three-dimensional model into a multi-view image sequence through a hybrid projection strategy combining orthogonality and surround view; utilizing an optimal transmission theory to map visual features to a learnable airfoil profile concept space to realize semantization and discretization of the features; in combination with flow field working condition coding, aerodynamic parameters are regressed under the constraint of aerodynamic physical laws; and finally, by displaying the matching relationship between the input sample and the airfoil profile concept, the inherent interpretability based on the instance is provided.

The invention discloses an explainable appearance feature learning and quantitative representation method for aerodynamic parameter prediction, and belongs to the technical field of aerodynamics and artificial intelligence crossing. The method comprises the following steps: constructing a collaborative network architecture comprising an aerodynamic prediction module, an airfoil concept learning module and a quantitative distillation agent module; while high-precision and high-efficiency aerodynamic parameter prediction is realized, a prediction result can be decomposed into the sum of quantitative contributions of different airfoil profile concepts, so that a direct explainable basis is provided for the prediction result, and expert users are assisted in understanding and verifying the prediction process of the model.

The invention relates to a multi-target aerodynamic-structure optimization method based on a deep neural network proxy model, and solves the problem that an existing method is insufficient in efficiency, feasibility and credibility, and the method comprises the steps: firstly, carrying out the sampling in a parameterized design target, building an aerodynamic-structure database through CFD / FEA high-fidelity simulation; the method comprises the steps that firstly, a multi-task neural network is used for predicting the lift-drag ratio, quality and stress at the same time, uncertainty is output, then, in NSGA-III multi-target optimization, a proxy model is used for rapidly evaluating and searching out a Pareto leading edge meeting constraints, finally, the precision of the model is gradually improved through high-fidelity checking and incremental updating, and an optimal design scheme is output. According to the method, sub-optimization and repeated iteration caused by'pneumatic first and then structure 'are avoided; the design universality and robustness are improved; a compromise scheme set of the system is directly obtained; and the optimization cost and the optimization period can be obviously reduced.

The invention discloses a boundary layer cushion block leveling method suitable for a wind tunnel half-mode test, relates to the field of experimental aerodynamics, and aims to reduce interference of wind tunnel wallboards in the half-mode test and improve assembly efficiency. The method comprises the following steps: S1, measuring corresponding data according to an established three-dimensional model of a boundary layer cushion block and a balance adapter; s2, based on the data in the step S1, the sizes of the first tool, the second tool, the third tool and the fourth tool are determined; s3, a corresponding first tool, a second tool, a third tool and a fourth tool are manufactured; s4, a balance adapter is installed in the wind tunnel test section, and a balance is measured; and S5, a leveling tool is used for assisting in leveling of the boundary layer cushion block. By adopting the method, the leveling tool is simple and convenient to apply, measurement parameters are few, and the mounting and leveling operation of the boundary layer base plate is effectively simplified; meanwhile, the leveling precision is high enough, the requirement for the installation precision of the boundary layer cushion block of the half-mold test can be met, and labyrinth groove collision is avoided.

The invention discloses a calibration board and wind tunnel feature point-based binocular system wind tunnel coordinate system calibration method, and belongs to the field of aerodynamic tests. Comprising the following steps: reconstructing surface mark points of a calibration plate by photogrammetry outside a hole and establishing a local coordinate system to obtain coordinates under the local coordinate system; a binocular system is arranged in the hole, and binocular internal and external parameters are calibrated through a special cross calibration ruler; arranging a plurality of circular feature mark points on the surface of the hole wall with overlapped visual fields of the binocular system; the calibration plate is correctly placed according to the geometrical relationship, so that each vector of the local coordinate system is parallel or perpendicular to an incoming vector, and the binocular system reconstructs global points of the calibration plate and registers the global points to achieve alignment of a measurement coordinate system of the binocular system and a wind tunnel coordinate system; reconstructing a three-dimensional coordinate of the fixed point in a wind tunnel coordinate system through a binocular system; and in a subsequent test, adopting resection to realize the recalibration of the wind tunnel coordinate system. According to the invention, high-precision and high-efficiency alignment requirements of a measurement coordinate system and a wind tunnel coordinate system of a binocular system can be met.

The invention discloses a multi-vortex system space energy evolution process analysis method, belongs to the field of fluid mechanics and aerodynamics, and aims to solve the problem of energy analysis errors caused by integral radius dependence and single-vortex hypothesis limitation in a traditional method. According to the method, a vortex core is positioned through a Liutex method, a vortex to be analyzed is translated to an original point, a pseudo time sequence is generated in combination with evolution direction slices, and a first modal energy distribution and evolution law is extracted through eigen-orthogonal modal decomposition. According to the method, the integral radius does not need to be manually set, the adaptability is high, the vortex global energy space change process can be comprehensively reflected, the method is particularly suitable for energy evolution analysis in complex vortex system scenes such as bird flight and complex aircraft wake flow, a brand new view angle is provided for vortex energy evolution, and the method has certain engineering practical value. The method can be used for quantitative analysis of complex vortex field scenes such as aircraft design, biological bionics and wind energy engineering, and has important engineering application value.

The invention belongs to the technical field of flight control, particularly relates to a simulation control method and device for a control load system and a storage medium, and aims to solve the problem of limited effect during simulation control of the control load system in the prior art. The method comprises the following steps: acquiring manipulation input data; carrying out filtering processing on the joystick force / torque data, and carrying out dynamic simulation on the control load system through a pre-constructed digital twin system based on the filtered joystick force / torque data and the control position data so as to determine a virtual force / torque track of the control load system for responding to the control input data; acquiring current flight parameters of the flight simulator, and resolving according to a preset aerodynamic model to obtain a reference force / torque trajectory; and taking the reference force / torque track as a control target, performing optimization solution on the virtual force / torque track, and determining an actuator driving instruction. According to the method, the effect is better when the control of the control load system is executed.

The invention discloses a physical feature perception large language model construction method for flow field understanding and generation, and belongs to the technical field of intelligent aerodynamics, multi-modal deep learning and computer vision crossing. High-level aerodynamic semantics and bottom-level physical feature learning of a flow field are decoupled through a double-codebook sharing mapping mechanism, and alignment of the high-level aerodynamic semantics and the bottom-level physical feature learning is kept at the same time. The discrete unified representation obtained through the token device is combined with a large language model, high-precision physical reconstruction and deep aerodynamic semantic understanding of the flow field image can be achieved at the same time under a single model framework, and the core problems that in the prior art, perception and generation tasks are split, and the fidelity of physical characteristics is low are effectively solved.

The invention relates to the technical field of aircraft design, in particular to an aircraft cost-efficiency optimization system construction method based on collaborative optimization. The method comprises the steps of carding design variables and constraints of engine, pneumatic and structural subjects, constructing a collaborative optimization framework and defining a hierarchical relationship between a system-level optimizer and a subject-level optimizer; constructing a BP neural network agent model for each subject, configuring a unified network structure and training to a precision requirement; integrating an agent model on an Isight platform, and constructing an automatic workflow to realize parameter transfer and iterative optimization; and on the basis of a QT development user interface, parameter setting, workflow calling and result visualization are supported. According to the method, traditional simulation is replaced by proxy model accelerated evaluation, and multidisciplinary coupling conflicts are solved; manual coordination cost is eliminated through automatic workflow; the integrated system improves the optimization efficiency and the research and development automation level, and effectively reduces the research and development cost of the aircraft.

The invention discloses a fan blade icing monitoring method based on mechanism analysis, and the method comprises the steps: 1, constructing a dynamic mechanism model of "pneumatic-thermal-quality" three-phase strong coupling, local micrometeorological conditions and water drop impact characteristics of each airfoil section and feedback effects of icing growth on aerodynamic configuration and subsequent icing in the blade rotation process are calculated in real time; 2, performing icing prediction based on the constructed dynamic mechanism model, wherein the icing prediction comprises local microenvironment calculation, dynamic icing growth calculation and pneumatic feedback calculation; step 3, judging an icing state; step 4, outputting an icing state and early warning information; the problems that a data-based driving method needs to depend on a large amount of high-quality annotation data, when the data size is insufficient or data distribution changes, the generalization ability and prediction precision of a prediction model can be greatly reduced, the internal mechanism of icing cannot be explained, and the reliability requirement in engineering application is difficult to meet are solved.

The invention relates to the technical field of high-speed railway tunnel aerodynamics, in particular to a railway tunnel micro-pressure wave pneumatic analysis and evaluation management system which comprises the following steps: S1, speed verification: acquiring the current train speed; s2, track type judgment: obtaining the track type of the tunnel; s3, tunnel length judgment: obtaining the tunnel length; s4, micro-pressure wave evaluation: calculating a micro-pressure wave peak value, comparing the micro-pressure wave peak value with a control standard, and judging whether the micro-pressure wave peak value meets the standard or not; s5, mitigation measures: when the micro-pressure crest value exceeds the standard, adopting the mitigation measures, and updating the input parameters to perform modeling simulation and evaluation again; and S6, outputting a result: generating a report. According to the method, the automation level and the intelligent degree of tunnel pneumatic safety design are effectively improved, and the risk of environment and safety problems caused by micro-pressure waves is reduced.

This invention discloses a method and apparatus for simulating the motion of a projectile landslide. The method includes: acquiring rock mass parameters of the projectile rock mass; calculating the initial state parameters of the projectile rock mass during the landslide; analyzing the flight process of the projectile rock mass in the air using an aerodynamic analysis model based on the rock mass parameters and the initial state parameters to determine the state parameters of the projectile rock mass before impact with the ground; and analyzing the motion process of the projectile rock mass after impact and after impact using a discrete element method (DEM) model based on the state parameters before impact with the ground to obtain the final shape of the projectile rock mass. This embodiment, by simultaneously utilizing both an aerodynamic analysis model and a DEM model, can more realistically simulate the motion process of a projectile landslide.

The invention discloses an engine blade design method based on a high-quality curved surface. The engine blade design method comprises the following steps: S1, constructing a two-dimensional section of a turbine engine blade according to key parameters and a mathematical geometrical relationship; s2, constructing a three-dimensional model of the turbine engine blade by combining the two-dimensional cross section with a blade front edge vertex equation and a blade rear edge vertex equation; s3, performing high-quality optimization on the two-dimensional section of the turbine engine blade by referring to a high-quality curved surface standard; s4, performing high-quality optimization on the three-dimensional model of the turbine engine in combination with a high-quality curved surface standard; and S5, detecting the high-quality turbine engine blade model. According to the method, a turbine engine blade high-quality model which has good aerodynamic performance and meets a high-quality curved surface process is designed through parametric modeling, and the feasibility and effectiveness of the design and optimization method in the paper are verified through a fluid mechanics simulation experiment.

The invention discloses a data driving and mechanism analysis combined unmanned aerial vehicle power consumption prediction method and device, a medium and equipment, and the method comprises the steps: decomposing the total power consumption of an unmanned aerial vehicle into a parasitic power component, an induction power component and a leaf surface power component, calculating the theoretical value of each component, and obtaining a mechanism feature vector; extracting hidden feature variables of flight state parameters of the unmanned aerial vehicle by using a feature extraction network, performing hierarchical fusion on the hidden feature variables and mechanism feature vectors through feature splicing in a middle feature layer to obtain an unmanned aerial vehicle power consumption prediction model, and performing joint optimization on prediction errors and regularization constraints by using a composite loss function to obtain the unmanned aerial vehicle power consumption prediction model. Training the unmanned aerial vehicle power consumption prediction model to obtain an optimized unmanned aerial vehicle power consumption prediction model; and inputting the flight state parameters of the unmanned aerial vehicle into the optimized unmanned aerial vehicle power consumption prediction model, and outputting an unmanned aerial vehicle power consumption prediction result, and realizing high-precision and high-stability power consumption prediction by fusing the mechanism characteristics of aerodynamics and the deep neural network.

The invention relates to the technical field of vehicles, in particular to a hole repairing method, device, equipment and medium for CFD pretreatment, and the method comprises the steps: analyzing an initial vehicle body three-dimensional model, and under the condition that at least one hole exists in the initial vehicle body three-dimensional model, according to the hole boundary information of each hole, carrying out hole repairing on the initial vehicle body three-dimensional model; and calculating a normal partial derivative vector of the boundary edge of each hole, generating a corresponding Coons curved surface, and filling and repairing each hole based on each Coons curved surface to obtain a repaired vehicle body three-dimensional model. Therefore, the problems that in an existing geometric cleaning method for the automobile body model, the efficiency is low due to the fact that an existing geometric cleaning method depends on manual work or a general algorithm, and the repairing precision of the hole type topology problem is insufficient are solved, and automatic batch detection and high-quality curved surface repairing of the upper automobile body hole topology defects in automobile aerodynamics CFD pretreatment are achieved; the pretreatment period is obviously shortened; and the simulation model precision is improved.

To provide a rotary wing aircraft having improved safety with a simple structure.SOLUTION: This rotary wing aircraft 1 has a body surrounded by a cage side 3A, and includes an aerodynamic parts side 3A composed of a plate-shaped body inclined to the outside of the cage side 3A, and arranged so as to surround an upper surface, in the edge of the upper surface for constituting the cage side 4A.SELECTED DRAWING: Figure 1

The application discloses a kind of civil aircraft aerodynamic theme data management methods, belong to aerodynamics test data management technical field, the core of management method is using aerodynamic wind tunnel test train table to realize the management of test data for the basic model of civil aircraft and its research category;Managed data includes four levels of research category, research object, project and result, each level contains relevant data resources;The application includes civil aircraft aerodynamic theme data warehousing method based on train table, civil aircraft aerodynamic theme data organization management, civil aircraft aerodynamic theme data retrieval and display, civil aircraft aerodynamic theme data maintenance and civil aircraft aerodynamic theme data call.The application replaces the mode of original data organization with test condition and test state, and operation is more simple, intuitive and convenient and fast.

The application provides a 1-meter wind tunnel support interference test follow-up false tail support simulation test method, and belongs to the technical field of wind tunnel test of aviation aerodynamics. The purpose is to solve the problems of easy deviation and interference of the post-root false tail support simulation under large wind load, difficult simulation of large sideslip, and the problem of non-real simulation of the relative position of the false tail support to the model caused by the limitation of the position compensation mechanism of the domestic 1-meter high-speed wind tunnel, which affects the test results. The application comprises the following steps: S1. determining the relative length of the false tail support simulation; S2. selecting a false tail support small balance according to the relative length determined in S1, designing a false tail support small balance adapter and a false tail support rod, reducing the weight of the model, and manufacturing the model; and S3. performing the wind tunnel test according to the two-step method of the test mapping. The application adopts the front-root false tail support force measuring small balance connection, realizes the real-time synchronous movement of the false tail support and the model, avoids the relative position deviation, structural interference and difficult simulation of large sideslip, and reduces the measurement error of the support interference.

The invention relates to a method for manufacturing an aerodynamic panel (32) for an aircraft propulsion assembly (10), comprising the steps of: a) applying at least one reinforcing plate (38, 42, 44) to a first surface (34a) of a wall (34); the method includes the steps of a) forming a wall (34, 36), b) rigidly attaching a reinforcing plate (38, 42, 44) to the wall (34, 36) by friction stir welding, c) forming through holes (50) through the wall (34) and the reinforcing plate (38, 42, 44), the holes (50) being formed through a bead (40), and d) fitting screws (52, 54, 56) into the holes (50), the screws (52, 54, 56) including countersunk heads (58) having a thickness (H) greater than the thickness (E1) of the wall (34) and less than the thickness (E3) of the bead (40).

The invention discloses a turbulence model construction method for aerodynamic simulation of a hybrid three-compartment vehicle, and relates to the field of model simulation, and the method comprises the steps: S1, employing a flow field inversion method, and obtaining the dense space distribution of a turbulence model correction term; s2, screening local flow field characteristics related to the correction distribution characteristics; s3, training by adopting a symbol regression method to obtain an analytical expression of a turbulence model correction term; s4, through mathematical derivation, an analytical expression of a correction term is migrated into the standard model, so that the correction term is added in front of a damage term of a transport equation of the dissipation rate of the standard model; s5, selecting an initial value of a to-be-calibrated coefficient in the correction item according to the smoothness degree of the chassis of the hybrid three-compartment vehicle; and S6, calibrating the to-be-calibrated coefficient in the expression in the step S4 on the basis of real vehicle experimental data of the hybrid three-compartment vehicle to obtain the turbulence model for aerodynamic simulation of the hybrid three-compartment vehicle.

The invention relates to a turbine engine (20) comprising a casing intended to improve aerodynamics and air flow management. The casing comprises an annular wall (1) comprising guiding micro-corrugations formed by alternating troughs (60) and crests (40). The micro-corrugations help to reduce turbulence, thereby stabilizing the air flow and improving the overall efficiency of the turbine engine (20).

The present application relates to the technical field of aerodynamic test device, and provides a stage free separation structure and a two-body free separation wind tunnel test device, the stage free separation structure comprises a target aircraft model, the target aircraft model comprises a front stage model and a rear stage model, the rear end surface of the front stage model and the front end surface of the rear stage model are abutted, and the two are fixed by a first electromagnet and a first electromagnetic armature, a power supply and a controller are arranged in the target aircraft model, the power supply is electrically connected with the electromagnet, and the controller is electrically connected with the power supply; a force generating component is arranged between the rear end surface of the front stage model and the front end surface of the rear stage model, so as to generate thrust to overcome the magnetic force generated by the residual magnetism of the first electromagnet. The present application can not only make the front stage model and the rear stage model freely separated, but also make the front stage model and the rear stage model separated at a certain relative speed.

Disclosed are a wing for an aircraft, a leading edge high lift assembly and an aircraft, the wing comprising a main wing and a leading edge high lift assembly, the leading edge high lift assembly comprising a slat and a connecting assembly movably connecting the slat to the main wing, and a connecting assembly for connecting the slat to the main wing such that the slat is movable between a retracted position, a first extended position, and a second extended position, where the connecting assembly comprises an elongate slat track, a first end and / or a middle portion of which is mounted to the slat, the slat track being mounted to the main wing by means of a roller support. The aim of providing a wing with a beneficial ratio of aerodynamic performance to noise resulting from the extension of the slat is achieved, in which the slat track and the roller support are configured such that, in a retracted position and a first extended position, the slat rests against the main wing and, in a second extended position, the slat rests against the main wing. A gap is formed between the trailing edge of the slat and the leading edge of the main wing.

The invention belongs to the field of aerodynamics, and particularly relates to a quick treatment method for a trailing edge step of an airfoil profile. The method comprises the following steps: standardizing airfoil profile data, calculating a thickness distribution curve and a camber distribution curve of the airfoil profile through airfoil profile coordinates, constructing a new continuous disturbance function which is a continuous derivable function, and the disturbance quantity of the function at the rear edge is just the required step thickness. And the smooth and continuous disturbance function is superposed on the thickness distribution, so that local rapid adjustment of the thickness of the step on the rear edge of the airfoil is realized, finally, the coordinates of the airfoil are inversely calculated through the camber distribution and the thickness distribution, and the airfoil profile meeting the requirement is obtained. Due to the fact that the camber distribution and the maximum thickness of the airfoil profile modified through the method are not changed, the requirement for continuity of the appearance is met, and it can be guaranteed that the overall aerodynamic characteristics of the airfoil profile before and after adjustment are basically consistent.

A cryogenic insulated pipe having a conformally-bonded aerogel paper layer on an outer surface of the pipe. The conformally-bonded aerogel paper layer is conformally-bonded to the pipe outer surface in a pre-applied resin layer. An insulative blanket is applied over the aerogel paper, and a breathable protective layer is applied over the insulative blanket. Also disclosed is a cryogenic fuel tank for retrofitting a conventional fossil fuel-powered aircraft, or for a purposely built aircraft to run on hydrogen has an aerodynamically shaped outer surface including an ogive shaped nose cone, and a tapered tail cone, wherein the tapered tail cone includes actively adjustable elements for adjusting aerodynamic characteristics of the cryogenic fuel tank. The cryogenic fuel tank is configured to be attached below wings of the aircraft, through support pylons, which include sensors configured to measure forces applied by the cryogenic fuel tank to the airframe. The cryogenic fuel tank includes a nozzle and valve configured to vent gas from the cryogenic fuel tank by expansion through the nozzle in the event that the cryogenic fuel tank is j ettisoned from the aircraft.

This invention belongs to the field of aerospace aerodynamics technology, and particularly relates to a wide-temperature-range integrated thermally protected cryogenic PSP excitation light source device. It includes: a light source host, an optical transmission module, and a light output module; wherein, the light source host is deployed in a room temperature environment to generate PSP and / or TSP excitation light; the optical transmission module, internally composed of optical fibers, includes a room-temperature protection system deployed in the room temperature environment and a wide-temperature-range protection system deployed inside the wind tunnel chamber; the light output module consists of an optical fiber lens, which performs secondary light distribution and can adjust the light output angle and spot size, and has a pre-reserved vent in the lens for anti-fogging design. This invention significantly saves the space cost of the excitation light source during cryogenic wind tunnel experiments, making it more suitable for the experimental environment of small research cryogenic wind tunnels, easily adjustable in angle, and ensuring stable light output; the anti-fogging design of the optical fiber lens by pre-reserved vents in the lens avoids fogging and affects the light transmission effect.

The invention discloses a water pumping compressed air energy storage efficiency optimization method, and aims to solve the problem that in the prior art, it is difficult to accurately predict and efficiently suppress aerodynamic instability of a compressor. The method comprises the steps that an original pressure signal and a velocity field slice of a compressor inlet flow field are obtained, and a dominant unstable mode set representing the flow field instability characteristic is generated through vortex-pressure coupling analysis; based on the dominant unstable mode set, a radial basis function neural network embedded with eddy current physical characteristics is adopted, a nonlinear relation between the flow deflector angle and eddy current induced impedance is constructed, and a three-dimensional control mapping table is generated; and according to the pressure pulsation dominant frequency monitored in real time, querying and solving are carried out in the three-dimensional control mapping table, and an optimal flow deflector angle instruction used for suppressing surge is generated. According to the method, the surge precursor can be accurately predicted and actively inhibited, the stable working range of the compressor is widened, and the overall operation efficiency and safety of the energy storage system are improved.