4118results about "Aircraft components testing" patented technology

Disclosed in the present invention is a neural network-based defect detection method for gluing quality on aircraft skin. The method includes: data acquisition: taking photos of aircraft skin by using a camera to acquire image data; preprocessing the acquired image data; annotating the data by using annotation software to acquire a data set for network training; establishing a defect detection network model based on feature erasure and boundary refinement, where the defect detection network model includes a feature extraction network, a semantic-guided feature erasure module, a multi-scale feature fusion network, and a defect prediction network based on boundary refinement, which are sequentially connected, the data set is used for training the network model, and trained model parameters are saved; and detecting a directly collected skin gluing image by using the trained network model and outputting detection results.

Aspects of the present disclosure generally relate to systems and methods for flight control of aircrafts driven by electric propulsion systems and in other types of vehicles. In some embodiments, a computer-implemented method for controlling an aircraft is disclosed, comprising: receiving, from a source processor, a first copy of a signal corresponding to an input device; sending a second copy of the signal to all other processors; receiving a number of second copies of the signal from all other processors, the number of second copies being equal to the number of all other processors excluding the source processor; determining a consensus signal based on the first copy and the second copies of the signal; and determining a command signal for an effector of the aircraft based on the consensus signal, and wherein no two processors are configured to receive signals from a same input device.

The embodiment of the invention provides a multi-configuration relay-oriented aircraft electrical box parameter measurement system and method, and belongs to the field of aircraft electrical box test and diagnosis. According to the hardware level, flexible access of a multi-configuration relay electrical box is achieved based on a universal adapter interface, core parameter measurement is completed in combination with an integrated measurement and control circuit, and synchronous acquisition and processing are conducted on multiple paths of signals through a signal acquisition and processing unit; according to the software level, the pull-in / release time, the rebound time and the voltage parameters are accurately calculated through a parameter calculation module on the basis of waveform feature point recognition and dynamic excitation-response theories, and the functions of fault diagnosis, safety protection and data storage are integrated. According to the method, the crossing from on-off judgment to parameterized precise evaluation is realized, the detection efficiency, the measurement precision and the equipment reliability evaluation capability are remarkably improved, and an integrated solution is provided for external field maintenance and state prediction of the aircraft relay.

A disclosed leaky coaxial resonant sensor system and methods. In use, the system includes at least one split-ring resonator (SRR) embedded within a material of the component. The at least one SRR is formed from a composite material. Additionally, the at least one SRR is configured to resonate at a first frequency in response to an interrogation signal from a leaky coaxial cable antenna. In some aspects, each SRR may resonate at a first frequency in response to an electromagnetic ping when the composite material is in a first state, and may resonate at a second frequency in response to the electromagnetic ping when the composite material is in a second state. A resonant frequency of the composite material may be based on physical characteristics of the composite material.

Methods and scan systems for analyzing an object. The methods include obtaining a local operation dataset that includes a plurality of operation data points obtained from an object and a corresponding location, within the operation coordinate system, for each operation data point of the plurality of operation data points. The methods also include mapping the plurality of operation data points from the operation coordinate system to a global coordinate system for the object. The mapping includes mapping to generate a global operation dataset that includes the plurality of operation data points and a corresponding global location, within the global coordinate system, for each operation data point. The scan systems include a robot that performs a plurality of operations on an object within an operation coordinate system and a computing device that maps the plurality of operation data points from the operation coordinate system to a global coordinate system.

A system for detecting a state of a mechanism includes processing circuitry. The mechanism includes multiple components, at least some of which are capable of moving relative to each other. At least one state is specified for the mechanism, based on the alignment of the mechanism components. The processing circuitry identifies, within image data of the mechanism, reference points on at least two of the components. Based on respective locations of the reference points, it determines whether the components of mechanism are in one of the specified alignments (i.e. states), and outputs an indicator.

The subject matter described herein includes methods, systems, and computer program products for AI tagging of airline fault codes. According to one method, a transformer-based natural language processing (NLP) artificial intelligence (AI) model trained on a dataset is provided. The training dataset includes a plurality of text strings tagged with at least one associated air transport association (ATA) code. The trained AI model then receives an untagged text string as input and automatically tags the text string with an ATA code.

The invention discloses an output voltage detection method and system based on an aviation power supply, and relates to the technical field of aviation power supply voltage detection. A differential voltage sensor is connected to the output end of an aviation power supply, a high-frequency suppression capacitor is connected in parallel, the sampling rate of 20-50 times of the working frequency is set according to the type of the power supply, and the signals are collected and converted into analog voltage signals; the analog signal is subjected to two-stage filtering, is amplified to 0-5V through an instrument amplifier, and is converted into a digital voltage sequence through a 16-bit ADC (Analog to Digital Converter); calculating AC power supply effective value, peak value and other parameters, DC power supply average value, ripple coefficient and other parameters; comparing the characteristic parameters with a preset threshold value, determining that the characteristic parameters exceed the threshold value and recording related information; and a detection result is transmitted to a monitoring terminal through an RS485, data is locally stored, and a switching value is output to an alarm device when the data is abnormal. The method adapts to aviation power supply load fluctuation and environment temperature change, detection precision is high, data transmission and storage are safe, abnormity is accurately identified and early warning is carried out in advance, and aviation power supply operation and maintenance reliability and efficiency are improved.

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 provides an unmanned aerial vehicle testing method, device and equipment, belongs to the technical field of unmanned aerial vehicles, and solves the problems that a traditional unmanned aerial vehicle is low in testing efficiency, long in time consumption and high in testing cost, and the accuracy is difficult to guarantee. The method comprises the steps of generating a test instruction and sending the test instruction to the unmanned aerial vehicle; acquiring flight state data of the unmanned aerial vehicle; processing the flight state data to obtain performance data, the performance data including at least one of endurance time, a climbing rate, a maximum voyage, a maximum flight height and a maximum flight speed; and inputting the flight state data and the performance data into a flight state test model for processing to obtain test data. According to the scheme, the testing efficiency and accuracy of the unmanned aerial vehicle are improved, and the testing cost is reduced.

The invention discloses an aircraft landing gear shimmy test bed and a test method, the aircraft landing gear shimmy test bed comprises a main body rack, a hanging basket system, a large flywheel, a flywheel driving system, an excitation device and a follow-up displacement measurement system.The aircraft landing gear shimmy test bed can simulate the shimmy of an aircraft after undercarriages of different design configurations are subjected to interference excitation force or interference torque in the process of takeoff, taxiing, landing and the like of the aircraft; the control effect of the shimmy damping system on the stability of the undercarriage has short excitation time so as to simulate real working conditions, the shimmy stability performance of the undercarriage can be accurately detected, excitation is continuously carried out under the condition that the test state is continuously changed, and the working efficiency is greatly improved. The follow-up displacement measuring system designed by the invention can enable the exciting force and the center of the axle to be always kept on the same horizontal plane, can apply torque control and torque excitation control, is suitable for undercarriage shimmy tests with different axle heights, different tire diameters and different excitation modes, and has certain universality.

The utility model discloses an undercarriage drop test stand, which comprises a vertical track support, a vertical pulley assembly is arranged on the vertical track support, the vertical pulley assembly moves up and down along the vertical track support, and a cantilever pulley track assembly is fixedly connected to the vertical pulley assembly. The cantilever pulley track assembly moves up and down along the vertical track support along with the vertical pulley assembly, a horizontal pulley assembly is connected to the cantilever pulley track assembly in a sliding mode, an undercarriage mounting base is arranged on the lower side of the horizontal pulley assembly, and the undercarriage mounting base directly faces an inclined plane base plate arranged on the ground. According to the invention, impact generated by vertical falling of the undercarriage can be simulated, horizontal displacement generated by falling contact with a slope can also be simulated, various simulation test environments are provided, and the damage degree of the undercarriage and the stability of a connection area of the undercarriage and an aircraft main body are judged according to recorded test data.

A vehicle autonomously inspects an object within an environment. The vehicle includes an inspection sensor, a localization sensor, and a computing system. The localization sensor can detect three-dimensional surfaces within the environment. The inspection sensor can characterize the object. The computing system includes a memory configured to store a three-dimensional model of the object and predetermined inspection instructions. The computing system further includes a processor configured to register the model of the object within the environment based on information gathered by the localization sensor on an initial journey of the vehicle. The processor can also adjust the predetermined inspection instructions based on the information gathered by the localization sensor on an initial journey of the vehicle.

Disclosed in the present application are an aircraft final assembly and integration testing platform and testing method. On the basis of a rational platform architecture, structured process data preparation, model-based operation guideline document preparation, and dispatch assistance decision-making are realized by means of an application layer, such that uniform data sources in the field of final assembly can be achieved. Data uploading and issuing between an industrial control network and an internal network, and data interaction control between layers are implemented by means of the mutually collaborative operation of the application layer, a storage layer, an edge layer and an execution layer, thereby improving the information acquisition efficiency and the operating efficiency. The edge layer and the execution layer collaboratively operate, so as to realize the interactive collaboration between the assembly guidance work for operators and automatic testing, thereby improving the efficiency of data information acquisition, operation instruction and fault handling during a final assembly and testing process of an aircraft.

The invention discloses an aircraft front wheel electrical zero calibration method, device and equipment and a medium, relates to the technical field of aircraft front wheel control, is applied to ground comprehensive maintenance equipment, and comprises the steps that a target angle instruction is used for controlling a scale line of a rotating sleeve in a nose landing gear to be aligned with a scale line of a front supporting column outer cylinder; a front wheel shimmy damping instruction is sent to a front wheel operation control box of the aircraft, so that the front wheel operation control box controls front wheels to keep stable; the current angle information of the front wheel angle sensor is determined as current electrical zero position reference information; the front wheel and the rotating sleeve are controlled to rotate through a front wheel rotating instruction, and if the deflection angle of the scale mark of the rotating sleeve is matched with the front wheel rotating instruction, it is judged that front wheel electrical zero calibration of the aircraft is completed. And the accuracy and simplicity of the electrical zero calibration of the airplane front wheel are improved.

The invention provides an inclined variable-angle aircraft interstage separation ground test device. The inclined variable-angle aircraft interstage separation ground test device comprises an aircraft separation device, an angle adjusting device, a temperature control and acquisition device, a vibration control and impact acquisition device, an ignition control device and a device base. The angle adjusting device comprises a device side plate, an arc groove, an angle ruler, a separation mechanism mounting plate, a supporting hinge, a supporting rod, an adjusting sliding rail, an adjusting base, a locking device, a device base gradienter, a rotating bearing and an auxiliary fixing block. The temperature control device comprises a quartz lamp array heating cage, an outer wall temperature control thermocouple and an inner wall temperature acquisition thermocouple, and can simulate a pneumatic heating environment at a separation moment, so that the thermal deformation matching capability of the separation mechanism in a high-temperature environment and the operation reliability of the separation mechanism are obtained. The vibration control and impact acquisition device is composed of a vibration table, a vibration control sensor and an impact sensor.

The invention discloses an unmanned aerial vehicle wind resistance performance evaluation method, device and equipment and a storage medium, and the method comprises the steps: obtaining flight parameters of an unmanned aerial vehicle under different wind speed conditions, and carrying out the quantification processing of the flight parameters, and obtaining flight stability performance scores under different wind speed conditions; according to the flight stability performance scores under the different wind speed conditions and the actual wind speed, wind resistance scores of the unmanned aerial vehicle under the different wind speed conditions are calculated; and based on the wind resistance score and the weight coefficients corresponding to different wind speeds, determining a comprehensive wind resistance score of the unmanned aerial vehicle. According to the quantitative evaluation method, the comprehensive wind resistance performance of the unmanned aerial vehicle at low, medium and high wind speeds can be comprehensively evaluated, the limitation of evaluation under a single wind speed condition is avoided, objective quantitative evaluation of the wind resistance performance is realized, and the wind resistance performance of the unmanned aerial vehicle can be accurately reflected.

The invention discloses an aircraft shell surface quality detection method. According to the method, a passenger cabin pressure difference curve and a shell outer surface temperature curve are calculated to obtain a pressure difference change node and a temperature difference change node respectively, and then partitioning is carried out to obtain phase thermoelastic coupling partitions; when a temperature difference change node reaches a phase change threshold value, performing beta-phase to alpha-phase transformation on the polyvinylidene fluoride microcapsule premixed in the finish paint, and forming a polarized memory cavity at a defect cementing position; when a voltage difference change node reaches a peak value, triggering a polarized memory hole to release charges, exciting a high-order thin film elastic wave, and performing integer ratio phase locking on the high-order thin film elastic wave and a natural vibration wave of a machine body to obtain a defect harmonic signal; carrying out acoustic-mechanical coupling calculation according to the amplitude of the defect harmonic signal to obtain a virtual work increment, and recording the virtual work increment to a damage matrix; and performing multi-leg accumulation calculation on the virtual work increment, and outputting a defect early warning signal when an accumulation value exceeds a material fatigue critical value. According to the invention, the hidden fatigue defect of the surface of the aircraft shell under the dynamic load can be detected.

A system for identifying a failure of the primary load path in an actuator. The actuator includes a screw shaft and a nut assembly moveable along the screw shaft. The nut assembly comprises a primary nut for transmitting load through the actuator along a primary load path, and a secondary nut for transmitting load through the actuator along a secondary load path. The nut assembly is configured such that, in normal operation, the secondary nut is not engaged with the screw shaft and load is transmitted through the actuator along the primary load path, and such that, upon failure of the primary load path, the secondary nut is configured to engage the screw shaft and transmit load through the actuator along the secondary load path. The system includes a strain gauge configured to be mounted to the actuator and to measure vibrations of the actuator.

The embodiment of the invention provides an airplane windshield glass service reliability test method and system and a medium, and the method comprises the steps: carrying out the coupling simulation of a test environment based on a plurality of environmental factors, and building a plurality of environmental factor cooperative control test modes; performing an impact test on the aircraft windshield based on the collaborative test mode to generate damage monitoring data; analyzing the damage monitoring data based on the damage mechanical model, and generating damage acceleration state data; inputting the damage monitoring data and the damage acceleration state data into a life prediction model, and outputting residual life prediction data; analyzing the damage acceleration state data and the residual life prediction data based on the reliability standard information to obtain a reliability test result, and transmitting the reliability test result to the terminal in real time; the mode testing environment is carried out through multiple environmental factors, so that impact testing of different environments is carried out on the aircraft windshield glass, the testing diversity is improved, damage monitoring is carried out on the glass, and the reliability testing precision of the glass is improved.

There is no established immunity test method for unmanned aerial vehicles. Because unmanned aerial vehicles fly and move, it is difficult to conduct immunity tests under actual operating conditions. [Solution] The immunity test device and test method disclosed herein utilize a test environment used for general electronic devices, etc., to enable testing of unmanned aerial vehicles in conditions close to their actual operation. A simulated signal is used to perform immunity testing in a simulated flight state equivalent to an actual operating state, with the unmanned aerial vehicle remaining at a fixed position in a certain space. A GTEM cell can be used as a shielding structure to house the unmanned aerial vehicle. An evaluation configuration is also proposed for analyzing parts of the unmanned aerial vehicle that are vulnerable to electromagnetic interference and identifying parts that cause malfunctions.

The invention discloses an unmanned aerial vehicle load engine state identification method based on deep learning, and the method comprises the following steps: S1, collecting the multi-mode operation data of an unmanned aerial vehicle load engine, and completing the standardization preprocessing; s2, inputting the spatial data into a spatial pyramid pooling network, and extracting a multi-scale spatial feature matrix; s3, inputting the spatial features into a masking auto-encoder, performing feature masking, encoding and reconstruction, and generating reconstruction features and error information; s4, fusing the original features, the reconstructed features and the non-spatial data, inputting a discrimination network, and outputting a health label and a risk score; and S5, according to an identification result, a flight control system or a maintenance platform is linked to realize alarm and scheduling. According to the method, intelligent identification and abnormal risk early warning of the state of the load engine of the unmanned aerial vehicle are realized by fusing multi-scale spatial feature extraction and a covering self-encoding reconstruction mechanism.

A system and method for gust load reduction testing of an elastic full-aircraft model in a large low-speed wind tunnel, which belong to the technical field of wind tunnel test apparatuses. The system in the present invention comprises a gust generator and a supporting device that are mounted in a wind tunnel. The supporting device comprises a model sliding guide rail, mounting bases and a trolley, wherein the mounting bases are fixedly mounted at two ends of the model sliding guide rail, the trolley is mounted on the model sliding guide rail, an aircraft model is mounted on the trolley, two parallel sliding rails are mounted on each mounting base, a slider is mounted on each of the two sliding rails, the two sliders are connected by means of a slider connecting base, a lifting ring assembly plate is mounted on the slider connecting base, a plurality of first lifting rings are welded on the bottom face of the lifting ring assembly plate, second lifting rings are welded on the mounting base, springs are hooked between the first lifting rings and the second lifting rings, and a smooth shaft sleeve and a smooth shaft are mounted in the mounting base, one end of the smooth shaft being fixedly mounted in the slider connecting base by means of a bolt, and a limiting block being fixedly mounted at the other end of the smooth shaft. The present invention has a compact structure, involves simple installation and is low cost.

The invention discloses a deicing system real-time state evaluation and fault prediction method and system, and the method comprises the steps: simulating the fault state of a deicing system through a ground state monitoring test of the deicing system, and obtaining sensor data in different fault states; constructing a data set by using sensor data in different fault states to train a state evaluation model and a fault prediction model; the method comprises the following steps: installing a sensor on an aircraft deployed with a deicing system to collect working data of the deicing system; and inputting data acquired by the sensor into the trained state evaluation model and the fault prediction model, evaluating the real-time state of the deicing system, and predicting possible faults. According to the invention, the current working state of the anti-icing and deicing system can be evaluated according to the current state monitoring data, and possible faults of the system can be predicted.

A two-point excitation air cannon impact test system, comprising two air cannons (38, 39), a supporting structure, a resonator plate (37), spacer blocks (36) and a test tool (35). The air cannons (38, 39) each comprise an air path integrated system and a synchronous controller; the resonator plate (37) is fixedly connected to the supporting structure; the test tool (35) is fixed on the resonator plate (37) by means of the spacer blocks (36); the two air cannons (38, 39) are respectively located directly below the test tool (35); the two air cannons (38, 39) are respectively pressurized by means of the air path integrated systems; the pressurizing process of the air path integrated systems can ensure that the two air cannons (38, 39) release completely the same pressure; and the synchronous controllers control the air cannons (38, 39) to synchronously drive projectiles in the air cannons to impact the resonator plate (37), so as to form the two-point excitation air cannon impact test system.

Disclosed in the present invention is a neural network-based defect detection method for gluing quality on aircraft skin. The method includes: data acquisition: taking photos of aircraft skin by using a camera to acquire image data; preprocessing the acquired image data; annotating the data by using annotation software to acquire a data set for network training; establishing a defect detection network model based on feature erasure and boundary refinement, where the defect detection network model includes a feature extraction network, a semantic-guided feature erasure module, a multi-scale feature fusion network, and a defect prediction network based on boundary refinement, which are sequentially connected, the data set is used for training the network model, and trained model parameters are saved; and detecting a directly collected skin gluing image by using the trained network model and outputting detection results.

The invention relates to the field of aircraft simulation test, particularly discloses a simulation test device for an aircraft rudder transmission mechanism, and solves the problems that an existing winged unmanned aircraft cannot conveniently perform simulation test on a rudder deflection angle and maximum stress and cannot conveniently perform accurate test on flight control performance. The device comprises a base, a mounting table, an adjusting assembly, a second telescopic part, a disc, a driving motor, a frame body, a front sliding rod, a mounting frame, a clamping frame, a sliding frame and a clamping plate, the driving assembly is arranged on the clamping frame, a limiting assembly is arranged in the frame body and used for limiting the mounting frame on the surface of the front sliding rod, and a supporting assembly is further arranged on the base and used for supporting the mounting frame on the surface of the front sliding rod. The supporting assembly is used for horizontally supporting the clamping frame. The device can perform simulation test on the angle adjustment precision of an elevator or a rudder of the winged unmanned aerial vehicle and the maximum stress of a transmission mechanism of the winged unmanned aerial vehicle, so that the flight control performance of the distance can be known conveniently, and the accurate control of the aerial vehicle is realized.

The invention belongs to the field of unmanned aerial vehicle safety, and particularly relates to an unmanned aerial vehicle high-speed collision body safety evaluation test device, which comprises a collision protection cabin, a speed measurement device, a sabot separation mechanism, a special-shaped gun barrel, a rapid bomb loading device and a gas storage tank, the special-shaped gun barrel is cylindrical and horizontally arranged, the impact protection cabins are arranged on the outer side of the output end of the special-shaped gun barrel at intervals, and the speed measuring device is arranged between the impact protection cabins and the output end of the special-shaped gun barrel. The high-speed impact test of the unmanned aerial vehicle is realized by adopting the special-shaped gun barrel and the integrated sabot separation mechanism and adopting the 400mm large-diameter gas gun impact test device to accelerate the unmanned aerial vehicle to a specified speed, so that the reliability of a test result is ensured, and the test cost and the test difficulty are also remarkably reduced. Meanwhile, the method has wide applicability, can be used for the unmanned aerial vehicle, and is also suitable for impact damage evaluation of an object of 2 kg or above at the speed of 150 m / s.

The invention relates to an abnormal unmanned aerial vehicle detection method fusing internal anomaly detection and external environment adaptation, which adopts a three-layer collaborative architecture design and comprises an external environment perception module, an internal anomaly detection module and a virtual-real fusion digital twinning module. And the external environment sensing module is responsible for external environment interference identification, regularly acquiring data of each unmanned aerial vehicle in the unmanned aerial vehicle group, and realizing stability discrimination. Environmental stability judgment and task switching are regarded as conditions of entering a buffer state, and are used for internal anomaly detection of the unmanned aerial vehicle group. In an internal anomaly detection module, real-time operation data of multiple unmanned aerial vehicles are analyzed based on a data flow driving mechanism, and abnormal individuals are identified. And the virtual-real fusion digital twinning updating module is responsible for constructing a high-fidelity digital twinning virtual space and dynamically updating internal and external constraint information to a digital twinning platform to support the next decision. The collaborative fusion of the three modules breaks through the limitation of a single constraint view angle, and realizes the collaborative constraint of internal state monitoring and external environment perception.

A system for inspecting surfaces of an aircraft prior to takeoff. The system includes a device movable relative to the surfaces of the aircraft. At least one camera on the device is provided for determining conditions of the surfaces of the aircraft. The at least one camera is configured to provide images indicative of the presence or absence of contaminates and / or fluid failure on the critical surfaces of the aircraft. A control module is provided for receiving the images from the at least one camera. The control module is programmed to determine, based on the images from the at least one camera, a status of the surfaces of the aircraft and to communicate that status to an external location.