77 results about "Aerodynamics" patented technology

The invention relates to an aerodynamic profile body with an outer flow surface for flow through a fluid, wherein the aerodynamic profile body comprises:a first surface layer and a second surface layer, which form at least part of the outer flow surface and are designed to be flexible in an end section of the aerodynamic profile body,a connection arrangement that flexibly connects the first surface layer to the second surface layer of the profile body in the end section, andan actuator device with at least one actuator provided in an interior of the aerodynamic profile body which interacts with at least one of the surface layers in the flexible end section in such a way that the cross-section of the aerodynamic profile body in the flexible end section can be changed by the at least one actuator,characterized in thatthe outer flow surface of at least one of the surface layers in the flexible end section has, at least in sections, a surface profile that extends parallel to the direction of flow.

This invention discloses a method and system for close following control of a spherical airship robot under strong airflow disturbances. The method includes: establishing a three-dimensional kinematic model for close following; establishing an aerodynamic influence model mimicking bird flock close following; establishing the spatial dynamic equations of the spherical airship; establishing collision detection-assisted control based on tactile sensors; and constructing model predictive control equations for close following. This invention addresses the technical shortcomings of traditional control methods by drawing on bird flock formation strategies, constructing a dynamic model integrating aerodynamic characteristics, employing tactile sensor collision detection-assisted control, and using precise model predictive control algorithms. It overcomes the technical deficiencies of traditional control methods in effectively establishing aerodynamic interactions between airships and addressing collision problems caused by missing positioning data during close flight. This achieves stable close following control of the airship, providing technical support for multi-airship collaborative tasks in complex, confined spaces.

The invention relates to a manufacturing method (1) for obtaining any type of shape and size of aerodynamic or hydrodynamic structure incorporating an electronic device within its core. The multi-step design allows the electronic device to be placed and fixed to a first internal intermediate part manufactured beforehand, then the fabrication of the aerodynamic or hydrodynamic structure to be completed by filling an internal cavity of the first internal intermediate part with a filler material, before partially or completely overmolding the filled internal intermediate part. The aerodynamic or hydrodynamic structure thus obtained has an optimal external geometry because it is not affected by the presence of the electronic device within its core. Figure to be published with the abbreviation: Fig. 1

A method and apparatus for in-situ calibration of longitudinal load on a standard wind tunnel force measurement model, belonging to the field of aerodynamic wind tunnel testing technology, addresses the lack of in-situ loading correction methods in wind tunnel testing. The method ensures accurate loading of the standard wind tunnel force measurement model on-site through weight loading and high-precision angle sensor monitoring. By loading the model in-situ, the center distance, fixed installation angle, and elastic installation angle are obtained, thus ensuring accurate conversion of the balance force to the model's axis system and enabling real-world verification of the balance's accuracy under the same axis system. Based on the loading verification results, single-component in-situ calibration is performed on the non-compliant components. The principal coefficients obtained from the in-situ calibration are used to replace the principal coefficients of the non-compliant components, and constantization is applied to establish a new calibration formula model. The balance formula is recalculated using offline calibration data, and iterative corrections are performed until the balance measurement error meets the requirements.

To improve aerodynamic characteristics. [Solution] The wind-powered propulsion device of the embodiment is a wind-powered propulsion device installed on a moving body that generates a propulsive force by receiving wind, and comprises a rotating body that is rotatable around a rotation axis and has a frame that is formed in an annular shape around a rotation axis, and a plurality of blades that are fixed to the frame and are provided such that imaginary straight lines connecting their respective ends in a direction perpendicular to the rotation axis are parallel, and the plurality of blades include a central blade whose imaginary straight line connecting its respective ends passes through the center of the frame.

The application relates to a kind of distributed ultrasonic wind field detection methods based on multi-unmanned aerial vehicle cooperation, belong to low-altitude meteorological detection field, method includes: multi-source high-precision space-time datum acquisition;Each unmanned aerial vehicle node is launched by its ultrasonic transducer array and executes the composite modulation emission and echo demodulation of detection signal to obtain accurate sound wave round trip propagation time;Link length is weighted and fused calibration, and the spatial direction vector under non-orthogonal topology is reconstructed;Kinematics projection elimination and rotor flow field distortion compensation are carried out to extract pure aerodynamic wind field information;By constructing non-orthogonal observation matrix, the horizontal wind field component of the to-be-measured meteorological airspace is solved;Original solving vector is subjected to time domain filtering processing, and stable wind direction and wind speed information is output.The application eliminates the influence of carrier motion and mechanical vibration on acoustic measurement and adapts flexible detection topology, so that high-precision, multi-point correlation real-time stable monitoring of low-altitude area wind field is realized.

The application discloses a kind of unstructured grid flow field prediction method and system based on ordered state space model, comprising: the geometric physical feature extraction of input unstructured grid;Massive node features are aggregated and reduced to a small number of macroscopic physical perception slices by learnable physical slicing mechanism;Innovatively introduce the spatial weighting center ordering mechanism based on flow field principal axis, convert unordered slices into ordered sequence strictly conforming to fluid evolution direction;Global feature interaction and evolution are carried out on ordered sequence using bidirectional selective state space model with linear complexity;Finally, the evolved features are restored to the original grid and the prediction result is output.The application reduces the computing cost significantly while achieving high-precision prediction by explicitly modeling the directionality and causality of fluid evolution, and is suitable for rapid flow field analysis and optimization design in the field of vehicle aerodynamics.

A method for validating aerodynamic measurements implemented by an architecture including N separate measurement paths each including Pm probes, including: acquisition of an elementary measurement from each probe; for each measurement path, determination of a resultant measurement from the probes belonging to this path, and comparison of the resultant measurements. When the resultant measurements are consistent, validation of the measurements. When a resultant measurement related to path k is inconsistent: selection of a measurement path i, determination of Pi+Pk consistence values, determination of an inconsistent value among all the consistence values, and invalidation of any elementary measurement from the probe corresponding to the inconsistent value.

This utility model relates to the field of missile aerodynamics and structural technology, and in particular to a missile wing deployment device. It includes a wing housing, with adapter shafts rotatably connected to both sides of the wing housing. Each adapter shaft has a wing deployment rocker arm, and each wing deployment rocker arm has a folding wing on the side closest to the wing housing. A servo motor is located under the adapter shaft. It is mainly used for the rapid deployment of missile wings, folding them when the missile is in a negative phase of flight and deploying them when it is in an active phase, fully utilizing the advantages of the wings. In the deployed state, the missile's aerodynamic shape changes significantly, and its flight trajectory deviates considerably, making it harder for air defense systems to predict and intercept during penetration.

This invention relates to the field of aerodynamic component technology, and in particular to a wing spoiler device for a ground effect vehicle (GEV). The wing spoiler device for a GEV includes: a base, a movable flap, the front end of which is hinged to the front of the base, and the rear end of which is fixed to the rear of the base via an adjusting fastener passing through a pre-set first adjusting and fixing hole. The spoiler device is mounted above the front wing of the GEV via the base, so that when the incoming airflow passes over the upper wing surface, it obstructs the downwash airflow converging at the trailing edge of the wing, generating vortices inside the spoiler device to reduce the lift of the upper wing surface and increase the ground effect ratio of the lower wing surface, thereby suppressing the aerodynamic center of gravity shift of the GEV. The advantages of this invention are its simple structure, low manufacturing cost, and the elimination of the need for active control components such as servos or other transmission electronic devices. It also features a robust structure, better adaptability to harsh water environments, reduced safety hazards, and extended service life of the aircraft.

This utility model discloses an active flapping-wing aircraft, comprising a fuselage, a flapping-wing drive mechanism, wings, a folding-wing drive mechanism, and a tail fin. The flapping-wing drive mechanism is installed at the front of the fuselage. The wings are symmetrically installed on both sides of the fuselage, and the flapping-wing movement is achieved by using servos and rocker arms in the flapping-wing drive mechanism. The folding-wing drive mechanism is installed on the fuselage, and the folding and unfolding of the wings is achieved by using servos and crank-rocker mechanisms in the folding-wing drive mechanism. The tail fin is installed at the rear of the fuselage and is used to adjust the vertical flight of the wings. The active flapping-wing aircraft provided by this utility model can change the aerodynamic characteristics of the wings by actively unfolding and folding them during flight, achieving efficient flight. Furthermore, by adjusting the tail fin, the flight attitude of the flapping-wing aircraft is made more stable during takeoff, landing, and gliding, thus overcoming the shortcomings of existing flapping-wing aircraft, such as limited foldable wings, uncontrollable folding, small retractable area, and unstable flight.

This application discloses a method, system, device, medium, and product for predicting far-field noise of helicopters based on deep learning, relating to the field of aerodynamics. The method includes: acquiring environmental parameters from multiple observation points of a target helicopter; and determining the far-field noise sound pressure level distribution of the target helicopter using a far-field noise prediction model based on the environmental parameters. The far-field noise prediction model is obtained by training a deep neural network using a sample database, which includes multiple sets of environmental parameters and corresponding far-field noise sound pressure levels. In this application, by inputting environmental parameters into the far-field noise prediction model, the model does not rely on large-scale computing power. It transforms the complex physical solution process into efficient network inference, quickly outputting the noise sound pressure level distribution, significantly reducing computational resource consumption in complex environments and long propagation distance scenarios, thereby achieving efficient and accurate prediction of far-field noise.

The present application relates to the control adjustment technical field, especially a kind of high-altitude region potato's storage method and system, method constructs aerodynamics model by collecting environmental parameter and inverts respiration heat production rate, according to moisture dispersion potential energy and cooling condition, in oscillation ventilation and closed bud inhibition mode between alternative decision-making;Utilize sinusoidal pulsating airflow to destroy laminar boundary layer, utilize carbon dioxide accumulation to inhibit metabolism;Effectively solve the problem that physical cooling and moisture retention are difficult to consider under high-altitude low-pressure environment, realize the dynamic coupling of flow state reconstruction and metabolism inhibition;Not only greatly improve the heat exchange efficiency under low wind speed and reduce dry consumption through unsteady flow, but also can use biological spontaneous controlled atmosphere to block the accumulation of respiratory heat from the source under extreme dry conditions, significantly prolong the shelf life and commodity value of potato.

This invention relates to the field of flight safety monitoring technology, specifically to a method and system for real-time detection and assessment of aircraft icing. The method includes: acquiring icing images to obtain raw image data, and performing enhancement processing to obtain enhanced image data; using a semantic segmentation model to detect icing regions in the enhanced image data, obtaining multi-view icing mask two-dimensional image data; using a deep learning three-dimensional reconstruction model to extract features and fuse multi-view information from the multi-view icing mask two-dimensional image data, obtaining an icing surface triangular mesh model; fusing the icing surface triangular mesh model with an existing wing three-dimensional model through three-dimensional mesh Boolean addition operations to generate a fused model containing the ice layer morphology; and inputting the fused model into an aerodynamic evaluation model to perform aerodynamic assessment of the icy wing, obtaining the evaluation result. This invention enables an end-to-end closed loop from icing detection to aerodynamic performance evaluation, outputting evaluation results in real time to support flight safety decision-making.

A method for drift detection and control for a vehicle may include determining an intentional drift probability of the vehicle based at least in part on one or more occupant inputs. The method further may include determining an initial aero bias upper bound using a first control system. The method further may include determining an initial aero bias command using a second control system. The method further may include determining a final aero bias upper bound based at least in part on the intentional drift probability, the initial aero bias upper bound, and the initial aero bias command. The method further may include controlling one or more aerodynamic actuators of the vehicle based at least in part on the final aero bias upper bound and the initial aero bias command.

The invention relates to a blade (16) comprising a blade body (18) made of a fiber-reinforced organic matrix composite and a leading edge shield (20) having better resistance to point impact than the composite of the blade body, the leading edge shield (20) being assembled on the blade body (18) and comprising a pressure side fin (32) and a suction side fin (30) connected by a thicker central portion (34), the blade (16) comprising an aerodynamic profile height and a chord length; the suction side fin (30) having a first length (36) projected on the chord, a second length projected on the chord and a third length projected on the chord; the first length being between 10% and 18% of the chord length, the first length (36) being disposed between 70% and 80% of the aerodynamic profile height; the second length being between 18% and 26% of the chord length, the second length being disposed between 85% and 95% of the aerodynamic profile height; the third length being between the first length and the second length, the third length being disposed at 100% of the aerodynamic profile height. A turbine engine comprising the blade.

The application discloses a kind of aircraft wind tunnel test half model attitude angle leveling device and application, belong to experimental aerodynamics measurement field, purpose is to solve in the half model attitude angle adjustment process on the upper wall plate of wind tunnel test section, prior art usually uses laser or gyroscope to measure, measurement process is tedious, calibration period is long, checking and adjusting time-consuming and labor-consuming problem.This leveling device includes positioning base plate, distance measuring device, for installing on the upper wall plate of test section of wind tunnel half model, the positioning base plate includes first connecting plate, second connecting plate, the first connecting plate is used to be connected with the upper wall plate of test section, the second connecting plate is arranged along vertical direction, the first connecting plate is vertically connected with second connecting plate.This application can be applicable to aircraft wind tunnel test in the half model attitude angle measurement and fast leveling installed on the upper wall plate of wind tunnel test section, simple operation, fast, high efficiency, with very high industrial application value.

This invention discloses a method and system for adaptive allocation of preheating power for a target drone turbojet engine based on dynamic compensation of environmental parameters. It relates to the field of aero-engine control and thermodynamic process optimization technology, and includes: collecting flight environmental parameters and calculating the mass flow rate of air at the combustion chamber inlet; constructing a multi-condition compensation matrix to determine aerodynamic reference quantities; dividing the combustion chamber into regions based on the reference quantities; establishing a thermodynamic unsteady model and generating a combustion instability sensitivity matrix; calculating the dynamic instability index and performing thermoacoustic risk classification; constructing a preheating energy transfer matrix based on the risk level; introducing an inertia factor to achieve adaptive allocation of preheating power in each region; converting the allocation strategy into injector pulse modulation control commands; and performing dynamic iterative optimization by combining a spatiotemporal evolution model of thermoacoustic parameters and wall temperature. This invention can achieve refined allocation of preheating power, effectively suppress thermoacoustic instability, and improve engine preheating uniformity and operational reliability.

This invention provides a method and system for measuring atmospheric data using integrated optical sensing, comprising: real-time acquisition of surface pressure distribution and surface recovery temperature using a FADS subsystem, and inversion of Mach number, static pressure, and attack angle parameters; periodic laser emission using a MOADS subsystem, and analysis of atmospheric parameters such as air velocity, attack angle, and density through backscattering spectroscopy; independent Kalman filters running on the FADS and MOADS subsystems, performing local optimal estimations using aerodynamic equations and observation equations; employing a federated Kalman filtering algorithm, dynamically adjusting the weights based on the residual covariance matrix of the two subsystems, and jointly solving the pressure, temperature data, and optical signals based on the adjusted weights, outputting Mach number, attack angle, total / static pressure, total / static temperature, and atmospheric density. The technical solution of this invention addresses the technical problems of high cost and limited environmental adaptability associated with using FADS or MOADS systems alone in existing technologies.

The application discloses an interpretable intelligent analysis method for three-dimensional aircraft aerodynamic parameter prediction, and belongs to the technical field of aerodynamics, deep learning and computer vision, which first converts a three-dimensional model into a two-dimensional image sequence through standardized orthogonal projection, constructs a deep neural network containing five parallel branches to extract geometric features, combines with flow field working condition coding, carries out training by introducing a fine-grained physical constraint step, generates an aerodynamic sensitivity heat map by using an attention mechanism, and verifies the interpretation result by using occlusion sensitivity analysis; the scheme reduces the dimension of a complex three-dimensional problem through standardized orthogonal projection, combines with the global modeling capability of ViT, maintains the second-level prediction speed, and realizes higher prediction accuracy than traditional point cloud networks.

The application discloses a high-speed rare thin flow field prediction method and system based on a mask self-encoder, and belongs to the technical field of cross hyper-sonic aerodynamics and artificial intelligence. The application mainly comprises the following steps: constructing a cross-flow multi-scale flow field database; constructing and pre-training a multi-scale mask self-encoder model, forcing the model to learn to reconstruct the full-field flow field from sparse information through a random mask strategy; introducing a physical information constraint to fine-tune the model, wherein the physical information constraint comprises a Chapman-Enskog distribution function constraint, a moment equation conservation residual and a wall Maxwell slip boundary condition; introducing a Knudsen number self-adaptive reasoning mechanism to automatically adjust the feature weight through a gate network; and using the trained model to predict the flow field. The application realizes cross-flow unified rapid prediction covering a wide Knudsen number range, guarantees the prediction accuracy, significantly improves the calculation efficiency, and has good physical consistency and generalization ability.

Device (1) for cleaning at least one vehicle part (5), wherein at least one active aerodynamic element (3) is provided, and the active aerodynamic element (3) is designed to redirect the airflow such that the at least one vehicle part (5) can be cleaned, characterized in that a rain sensor is provided for controlling the aerodynamic element, by which rain can be detected, wherein the rainwater can be used for cleaning by being redirected by the active aerodynamic element (3), wherein it can be deduced from the vehicle speed whether cleaning is possible, and wherein it can be determined with the help of the sensors in the vehicle whether this rain was caused by spray and is therefore unsuitable for cleaning, or whether this rain was caused by natural rain and is therefore suitable for cleaning.

Aeronautical measuring instrument and associated manufacturing method. The present invention relates to an aeronautical measuring instrument (10) comprising a body (22) and a heating element (40), the body (22) defining a region of interest (25) intended to be exposed to aerodynamic flows. The instrument (10) is characterized in that the heating element (40) is encapsulated in the body (22) and configured to heat the region of interest (25). Figure for the abstract: Figure 1

The application discloses a method and structure for controlling shock wave boundary layer interference by active and passive mixing, and belongs to the technical field of aerodynamics and flow control. The application is directed to an inlet channel with shock wave turbulent boundary layer interaction (SWTBLI), a top circular arc surface of a rotating structural member with a circular cross section is extended into the inlet channel and occupies the main space of an initial separation zone, thereby forming a passive wall bulge; the initial separation zone is an area defined by a zero-speed envelope surface along the main flow direction of the original inlet channel under working conditions; meanwhile, the rotating structural member is driven to rotate around the central axis, and the tangential driving force generated by the top circular arc surface due to rotation is used to actively perform momentum compensation on near-wall fluid. The application can significantly improve the aerodynamic performance of SWTBLI, inhibit large-scale separation and weaken the intensity of turbulent kinetic energy for complex flow conditions such as supersonic inlets.

This invention discloses a high-speed sparse flow field prediction method and system based on a masked autoencoder, belonging to the interdisciplinary field of hypersonic aerodynamics and artificial intelligence. The invention mainly includes: constructing a cross-basin multi-scale flow field database; constructing and pre-training a multi-scale masked autoencoder model, forcing the model to learn to reconstruct the entire flow field from sparse information through a random masking strategy; introducing physical information constraints to fine-tune the model, including Chapman-Enskog distribution function constraints, moment equation conservation residuals, and wall Maxwell slip boundary conditions; introducing a Knudsen number adaptive inference mechanism, automatically adjusting feature weights through a gating network; and using the trained model for flow field prediction. This invention achieves unified and rapid cross-basin prediction covering a wide range of Knudsen numbers, significantly improving computational efficiency while ensuring prediction accuracy, and possessing good physical consistency and generalization ability.

This paper presents a method and system for correcting and predicting supersonic internal flow fields by integrating topology consistency evaluation and physical constraint latent space mapping, belonging to the interdisciplinary fields of fluid aerodynamics design and artificial intelligence. The method first employs a topology consistency evaluation based on a self-organizing mapping grid to realize the nonlinear coupling evolution of parameter sets and spatial errors under supersonic conditions in a hexagonal topological space. Gaussian smoothing and dot product operations are used to quantify the topology consistency between parameters and spatial errors, automatically selecting core parameters. Next, a physical constraint latent space mapping architecture is constructed, introducing a composite physical loss function to reduce the dimensionality of high-dimensional flow field features and establish a mapping model from core parameters to the latent space. Decoder weights are frozen to ensure the continuity of physical laws and derivatives. Finally, an error-driven correction mechanism is used to statistically analyze residuals and generate an error feedback matrix to complete the implicit core parameters, achieving closed-loop reconstruction and corrective prediction of the surrogate model. This method can significantly improve the physical fidelity of supersonic internal flow field reconstruction and effectively solve the problem of large prediction deviations in the flow field behind the gate.