60 results about "General aviation" patented technology

The invention provides a multi-scale cross-space learning general aviation aircraft landing runway detection method, and relates to the technical field of computer vision. The method comprises the following steps: firstly, collecting a runway image data set when a general aviation aircraft lands, preprocessing the data set, and dividing the data set into a training set and a test set; then, an AES-YOLOv8 network model for detecting a multi-scale runway target is constructed; the model is based on a YOLOv8s network of multi-scale cross-space learning, and a Backbone network comprises a plurality of improved lightweight channel attention convolution modules LA-AKConv; an EMA attention mechanism is introduced after a spatial pyramid pooling module SPPF of the Backbone network; the Neck network comprises a plurality of C2fSCConv modules fused by C2f and a space and channel reconstruction convolution module SCConv; and the AES-YOLOv8 network model is trained based on the preprocessed data set to obtain a multi-scale cross-space learning airport runway detection model, and the runway state of the general aviation aircraft during landing is detected in real time through the multi-scale cross-space learning airport runway detection model.

The invention discloses a multi-source sensing airport scene moving target cooperative monitoring and conflict early warning system, and relates to the technical field of airport scene traffic management, a millimeter wave radar, a laser radar and the like form a heterogeneous network, and the whole area of an airport is synchronously covered through a TSN network; cascading filtering denoising is adopted, GPS time service and Kalman filtering are combined to realize space-time calibration, and a data complementation mechanism is established; based on a multi-modal model classification target, the tracking continuity is kept through an improved algorithm; fusing multiple factors and predicting a path by using an ST-GNN model to adapt to different scenes; constructing a four-dimensional judgment space to evaluate risks in a grading manner, and performing grading response and multi-channel information pushing according to the risks; and the system performance is continuously optimized through federated learning and digital twinborn verification. According to the invention, the method achieves the precise monitoring of the whole area of the airport scene, improves the target recognition and tracking stability, has the self-optimization capability, balances the operation safety and efficiency, and supports the high-quality development of aviation logistics and general aviation services.

The invention provides an aviation permanent magnet synchronous motor control architecture based on master-slave redundancy and model prediction, belongs to the field of aviation electric propulsion control systems, and aims to solve the problems of extreme environment parameter drift, single-fault shutdown, multi-target control conflict, fault diagnosis lag and the like of an existing system. The control architecture comprises a master-slave dual-redundancy control unit, a wide-temperature-range adaptive model prediction control unit, an electromagnetic interference adaptive suppression unit and a multi-dimensional fault tolerance unit. According to the invention, a DSP + FPGA heterogeneous redundant architecture is matched with two-out-of-three voting logic, so that fault non-perception switching is realized; an extended Kalman filter observer is embedded to update motor parameters on line, and take-off / cruise / landing three modes are preset; interference at the frequency band of 100kHz-10MHz is controlled and suppressed through adaptive notch filtering and a sliding mode variable structure; a long short-term memory network is fused to realize accurate diagnosis of early faults, and the system is adaptive to aviation scenes such as electric general aviation aircrafts and unmanned aerial vehicles.

The invention discloses a general aviation demand-oriented trunk and branch multi-layer transportation network optimization method, relates to the technical field of aviation hub site selection, and aims to solve the problems of accurate prediction of general aviation short-distance transportation demands and connection of general aviation and trunk and branch aviation networks. The method comprises the following steps: firstly, establishing an airline passenger transport demand influence factor index system, and extracting a similar airline reference sample set; secondly, considering characteristics of different types of airports and airlines, and designing a gravity model based on similarity to carry out airline demand prediction; then, by taking minimization of transportation cost and hub construction cost, minimization of longest transportation time and maximization of general aviation short-distance transportation demand coverage rate as targets, constructing a single-allocation allowed direct connection shaft spoke type network hub site selection model; and finally, designing an NSGA-III algorithm to solve the multi-objective optimization model. According to the method, economic benefits, transportation efficiency and demand coverage can be comprehensively considered, a hub layout scheme is obtained, and reference is provided for decision makers of governments, airports and airlines.

The invention discloses a general aviation short-distance transportation demand spatial heterogeneity analysis method based on multi-scale geographically weighted regression (MGWR), relates to the technical field of aviation transportation demand prediction and influence factor analysis, and aims to accurately predict general aviation short-distance transportation demands. And the spatial heterogeneity characteristics of the key factors influencing the general aviation requirements are accurately revealed. The method comprises the following steps: firstly, constructing a generalized cost function containing different types of costs in combination with an inter-city traffic trip mode; secondly, introducing an improved condition Logit model, constructing a competition model among different intercity transportation modes, and predicting potential demands of general aviation short-distance transportation; thirdly, screening factor indexes influencing general aviation short-distance transportation; and finally, constructing an MGWR model, and revealing changes and differences of influence degrees of different factors in space. According to the method, the spatial heterogeneity of the regional general aviation short-distance transportation demand influence factors can be effectively evaluated, and technical support is provided for general aviation airport layout planning and operation management.

The invention discloses a wing body fusion layout vertical aircraft with T-shaped tilting power distribution. The vertical take-off and landing fixed-wing aircraft is mainly applied to a power system and aerodynamic layout design of the vertical take-off and landing fixed-wing aircraft, T-shaped power distribution is formed through cooperation of the wingtip tilting rotors and the tail ducted fans, and the composite power layout form of vertical take-off and landing, hovering, transition and horizontal cruise multi-working-condition stable flight is achieved. The technology can be widely applied to the fields of unmanned aerial vehicles, general aviation aircrafts, special task platforms and the like, and is suitable for efficient flight tasks in surveying and mapping inspection, logistics transportation, emergency rescue and complex terrain environments.

The invention discloses a general aero-engine sample gas measuring device and method and a simulation system, and the device comprises a bypass dilution module which is communicated with a sampling rake and can carry out the dilution or non-dilution of a first proportion on a sample gas sampled by the sampling rake; the gaseous five-component analyzer is communicated with the sampling rake and is used for detecting gaseous components of the sample gas output by the sampling rake; the first dilution module is communicated with the bypass dilution module and is used for diluting the discharged sample gas output by the bypass dilution module according to a second proportion to obtain a to-be-detected sample; and the multi-component analysis module is used for performing non-volatile particulate matter mass concentration detection, particle number concentration detection, brown carbon mass concentration detection, particle size distribution detection, volatile organic compound concentration detection and CO2 concentration detection on the to-be-detected sample output by the first dilution module. The method can be suitable for sample gas detection of various types of aero-engines.

The application discloses a kind of lightweight explainable aviation equipment abnormal state perception method and system, belong to aircraft health management and deep learning technical field.The application constructs 1+1 branch's LiteInception light weight feature extraction network, designs and aligns two-stage cascaded diagnosis process with aviation maintenance process: first stage adopts LiteInception and hybrid architecture of Transformer to execute fault detection binary classification, and priority is guaranteed recall rate;Second stage adopts pure LiteInception architecture to execute fault identification multi-classification to abnormal sample, and priority is guaranteed accuracy and explainability.The application significantly compresses model size, adapts edge device real-time inference needs, can output the diagnosis evidence chain that can be traced to specific sensor, specific time period, considers diagnosis efficiency, precision and compliance, and provides complete solution for general aircraft fault diagnosis.

This invention provides a control architecture for aerospace permanent magnet synchronous motors based on master-slave redundancy and model prediction, belonging to the field of aerospace electric propulsion control systems. It aims to solve problems in existing systems such as extreme environment parameter drift, single-fault shutdown, multi-objective control conflicts, and fault diagnosis lag. The control architecture includes a master-slave dual-redundant control unit, a wide-temperature-range adaptive model prediction control unit, an electromagnetic interference adaptive suppression unit, and a multi-dimensional fault-tolerant unit. This invention employs a DSP+FPGA heterogeneous redundancy architecture combined with a 3-out-of-2 voting logic to achieve seamless fault switching; it embeds an extended Kalman filter observer to update motor parameters online, preset takeoff / cruise / landing three modes; it suppresses interference in the 100kHz~10MHz frequency band through adaptive notch filtering and sliding mode variable structure control; and it integrates a long short-term memory network to achieve accurate early fault diagnosis, adapting to aerospace scenarios such as electric general aviation aircraft and drones.

A Lidar-based SkyVoice Alert LHA 500 for a general aviation aircraft provides audible announcements of height above a landing surface (e.g., a runway) when the aircraft that is descending on approach or taking off, reaches a specific height above the ground. It gives repeated Gear warnings until the Gear is down and locked. It audibly announces preset GPS / MSL heights. It also announces various user selectable reminders like CheckList, LC GUMPS, Flaps, Check Oxygen, Check Altimeter, Check Fuel, Switch Tank, Top of Descent. The SkyVoice Alert LHA 500 is contained in a housing that mounts onto a removable access plate in a wing cavity, with the Lidar arranged to provide a vertical downward beam though a window formed in the access plate. A connector cable provides connection and disconnection between the SkyVoice Alert LHA 500 and the plane's audio panel.

The application relates to an artificial intelligence-based general aviation monitoring and early warning method and system, and belongs to the technical field of general aviation monitoring. The method comprises the following steps: collecting point cloud data through an airborne laser radar, aligning the point cloud data sequences through a hardware time stamp, obtaining point cloud cluster sequences through point cloud preprocessing, and obtaining target point cloud cluster sequences through a matching algorithm; a preset time window is used to cut the target point cloud cluster sequences to obtain test point cloud cluster sequences, state vectors of each point cloud cluster are calculated, sequences are constructed, dynamic probabilities are calculated through a classification model, a preset comparison threshold is compared, and the point cloud clusters are divided into two categories of dynamic and static; the centroid coordinates of the static point cloud clusters and the centroid coordinate sequences of the dynamic point cloud clusters are obtained, predicted point coordinates are calculated through a prediction model, starting and ending point coordinates of an aircraft are combined, and an obstacle avoidance path is calculated through an avoidance algorithm. The general aviation monitoring and early warning are realized.

The invention discloses a process method for a universal low-altitude engine key core part casing, and relates to the field of machining of casings for low-altitude engines, and the process method specifically comprises the following operation steps that S1, a machine brake is disassembled; s2, processing an upper inner ring; s3, processing an upper outer ring; s4, processing a lower leaf disc; s5, machining a phi10 boss; s6, a first square boss is machined; s7, a second square boss is machined; and S8, gate combination machining is carried out. The process method for the universal low-altitude engine key core part cartridge receiver can be directly applied to trial-manufacturing and machining of new products of the universal low-altitude engine key core part cartridge receiver, it is ensured that the cartridge receiver can reach the conformity of a design drawing in the trial-manufacturing stage through the digital machining and combined assembly technology, and the machining efficiency of the cartridge receiver is improved. Therefore, consistency and interchangeability of products are improved, and the method is suitable for research, development and production of low-altitude general aero-engines.

This invention discloses a deep learning-based fatigue life assessment system for general aviation facilities, comprising the following modules: a data acquisition and preprocessing module for acquiring multi-dimensional monitoring data of various components of the general aviation facility and performing preprocessing; a data dimensionality reduction module for applying the Isomap algorithm for dimensionality reduction; a facility status quantification module for performing quantification processing and generating a facility status quantification feature set; a crack propagation path map generation module for generating a crack propagation path map based on the Gromov-Wasserstein distance; a fatigue life assessment module for performing fatigue life assessment based on crack propagation characteristics and the structural characteristics of the facility; a risk assessment module for performing risk assessment on the fatigue life assessment result set; and a result visualization module for presenting the fatigue life assessment result set through a graphical interface. This invention combines multi-dimensional data with deep learning to accurately assess the fatigue life and crack propagation of general aviation facilities.

The application belongs to the technical field of general aviation ground test, and particularly relates to a fuselage oil tank ventilation system performance verification system and method. The system comprises: a fuselage test oil tank for storing test fuel and providing a mounting mechanical interface of the fuselage oil tank ventilation system; a flight environment pressure simulation box for simulating the external environment pressure of an airplane under high-altitude conditions; a fuselage cargo compartment environment pressure simulation box for simulating the internal environment pressure of the fuselage cargo compartment of the airplane; a test control computer for providing a certain human-computer interaction interface, manually inputting a pre-setting of a test parameter change process; a pressure controller connected with the test control computer, for receiving a pressure control instruction issued by the test control computer, directly sending a control instruction to each electric regulating valve, and making the electric regulating valve adjust in real time according to the instruction opening degree; and a pressure sensor connected with the pressure controller, for measuring the internal pressure of the fuselage test oil tank, the internal pressure of the flight environment pressure simulation box and the internal pressure of the fuselage cargo compartment environment pressure simulation box.

This utility model discloses an intelligent distribution device for general aviation maintenance worksheet cards, including a mounting frame, a conveying mechanism disposed on the upper end of the mounting frame, a mounting platform, and a control box disposed at one end of the mounting frame. The mounting frame is composed of a first support frame, a second support frame, and a third support frame. The conveying mechanism includes multiple parallel conveyor belts, and the two ends of the conveyor belts are respectively connected to the upper ends of the first support frame and the second support frame. A storage slot is correspondingly provided at the end of the conveyor belt away from the control box. The mounting platform is connected to the upper ends of the first support frame and the third support frame through a sliding mechanism. A placement slot is provided on the upper surface of the mounting platform. The beneficial effects of this utility model are: the worksheet is identified by an identification device, and the control box automatically classifies and organizes the worksheets according to the identification results, which greatly improves work efficiency while ensuring accuracy.

The invention provides an oil tank and an airplane, and relates to the technical field of general aviation. The oil tank comprises a shell, first mortises and second mortises are formed in the two ends of the shell respectively, the first mortises are evenly formed in the edge of one end of the shell, and the second mortises are evenly formed in the edge of the other end of the shell; the first head plate is provided with a first tenon matched with the first mortise; the first head plate is provided with a first tenon matched with the first mortise, the second head plate is provided with a second tenon matched with the second mortise, and the first tenon and the second tenon can be bent, so that the shell, the first head plate and the second head plate are fixed under the condition that the first tenon is embedded into the first mortise and the second tenon is embedded into the second mortise, and a sealed cavity is defined by the first head plate, the second head plate and the shell. The fuel tank provided by the invention is particularly suitable for fuel storage of an airplane, can meet the strict technical requirements of the airplane on the air tightness, the oil tightness and the pressure resistance of the fuel tank, and meanwhile, realizes low-cost and high-efficiency production and manufacturing.

The utility model discloses an auxiliary tool for assembling aircraft wings, and relates to the technical field of general aviation auxiliary equipment. Comprising a supporting base, a hydraulic jack is rotationally arranged on the upper surface of the supporting base, a vertically-arranged lifting rod is arranged on the top face of the hydraulic jack, and a wing connecting structure is arranged at the top of the lifting rod. On one hand, through the design of the supporting base, the hydraulic jack, the lifting rod and the wing connecting structure, the assembling efficiency of the aircraft wings and the aircraft body is improved, the auxiliary tool cannot move after being wholly conveyed to a designated position, and the overall positioning effect is good; on the other hand, the hydraulic jack is rotationally arranged on the upper surface of the supporting base, so that the assembling flexibility of the aircraft wings and the aircraft body is improved.

The invention discloses an all-working-condition risk quantification method applied to a new energy civil aircraft power system, which comprehensively considers the influence of discrete factors and continuous factors, quantifies the performance risk of the power system under all working conditions into a probability density distribution function, and comprises the following steps: defining a discrete variable and continuous variable distribution set; establishing a power system performance change degree probability density function PDFcon under the influence of continuous variables; establishing a power system performance probability density function PDFsys under the common influence of the continuous variable and the discrete variable; and step 4, quantifying the system risk, namely quantifying the system risk under the common influence of the discrete variable and the continuous variable into a probability density distribution function for evaluating the risk of the system at the moment. According to the method, quantitative analysis of all-working-condition risks can be realized, and reliable support is provided for airworthiness verification, safety evaluation and engineering application of a new energy power system.

The application discloses a kind of civil aviation aviation material inventory guarantee management and control method, system and electronic equipment, it is related to aviation material inventory management field, its method includes: in future time period T, based on routine maintenance work calendar time, service time and service cycle are calculated respectively, and the demand of aviation material is calculated, and the demand quantity of aviation material i is obtained by comprehensive calculation;In time period T, aviation material corresponding to machine part is divided into MEL list and MEL list not belonging to two types and is calculated for non-routine work demand;Supplement calculation associated with the demand of aviation material, and the demand of aviation material for non-routine work is obtained by comprehensive calculation;On the basis of superimposed fleet size, the demand quantity of aviation material is calculated.The application realizes the accurate control of each type general aviation material inventory quantity, scientific configuration and dynamic adjustment, and then optimizes general aviation enterprise aviation material inventory structure and safety inventory level, improves aviation material inventory guarantee timeliness, saves operating cost.

The present application relates to general aviation equipment mobile edge computing data security technical field, specifically relates to the security mobile edge computing secret throughput efficiency optimization method of multi-unmanned plane cooperation, the method includes: building multi-unmanned plane cooperation security mobile edge computing system;Channel and rate model, task and delay model are constructed, and a secret throughput efficiency model is constructed;Based on the secret throughput efficiency model, a joint optimization problem with the maximum secret throughput efficiency as the target is constructed;The joint optimization problem is solved.The present application strengthens the data transmission security of physical layer by multi-unmanned plane cooperation, realizes the balance of data security and computing efficiency with composite index, and the solving framework is efficient and feasible, significantly improves the effective bit number of safe task completion per unit time of unmanned plane, and is suitable for low-altitude economy and other security sensitive edge computing scenarios.

This invention discloses a method for generating a general aviation terrain warning envelope map and a warning notification method. The method for generating the general aviation terrain warning envelope map combines the flight path, initial trajectory position, and flight position information of the general aviation aircraft to draw a general aviation terrain warning envelope map, which helps to accurately warn general aviation aircraft about safe flight and avoid accidents such as general aviation aircraft crashing into the ground. By combining the flight path, flight characteristics, and flight position of the general aviation aircraft to generate the warning envelope map, real-time warnings are provided about the current flight position of the general aviation aircraft to achieve accurate warnings and prevent false alarms.

1. The name of the design product: Ducted fan. 2. The use of the design product: For air cars, general aviation aircraft, fixed-wing drones, vertical take-off and landing drones, airships and air-propelled boats, etc. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: Design 1 perspective view. 5. Design 1 is designated as the basic design.

This invention relates to the field of target detection technology and discloses a method for detecting the compliance of reflective vests worn by general aviation training flight trainees. The method involves collecting and constructing a dedicated dataset for general aviation training scenarios, containing fine-grained labels for compliant and non-compliant wear. The YOLOv11 model is improved by introducing a higher-resolution P2 feature layer to construct a three-scale detection head. A multi-expansion rate residual module is used in the neck network to aggregate multi-scale features. A context aggregation module is integrated before the detection head to incorporate global contextual information. Based on the trained model, adaptive target-scale dynamic spatial association rules are used to match personnel with reflective vest targets in different states and determine the final compliance status. This invention significantly improves the detection accuracy and robustness of small targets at long distances and achieves accurate determination of fine-grained states such as whether wear is compliant, providing an efficient and intelligent automated monitoring solution for general aviation training safety management.

This invention discloses a dual-fuel blending system based on flight altitude and attitude. A remote control command sending unit sends a set target blending ratio (SAF) command to the main control unit. An adaptive command generation unit based on altitude and attitude collects flight altitude data and aircraft pitch angle and attitude data in real time and sends the aircraft data to the main control unit. The main control unit includes a receiving end, an RP-3 aviation kerosene supply unit, and an SAF fuel supply unit. The receiving end receives either the set target blending ratio command or a target blending ratio command generated based on aircraft altitude and attitude data. It drives the RP-3 aviation kerosene supply unit and the SAF fuel supply unit according to the target blending ratio command, achieving phased dynamic blending of SAF and RP-3 aviation kerosene. This invention can achieve a continuously adjustable SAF blending ratio of 0-50%, with a control error ≤ ±2% and a response time ≤ 20ms. It is suitable for dynamic fuel blending scenarios in civil aviation aircraft, general aviation aircraft, and other aircraft, balancing emission reduction benefits and fuel economy.

The invention discloses a method suitable for cooperative operation of civil aviation and general aviation, which is applied to civil aviation air traffic control and general aviation flight service, and comprises the following steps: collecting multi-source data, carrying out data cleaning, standardized processing and real-time analysis, and sending the processed data to the civil aviation or the general aviation; based on the processed data, the real-time flight demand and the airspace use condition, the airspace of civil aviation and general aviation is dynamically allocated; based on the punctuality rate requirement of the civil aviation flight, the timeliness of the general aviation task and the airspace limitation, carrying out collaborative optimization on the flight plans of the civil aviation and the general aviation; and constructing a collaborative coping scheme according to the emergencies. According to the method, the flight safety of civil aviation and general aviation can be guaranteed, the comprehensive utilization rate of airspace resources is improved, and the efficiency of a whole aviation operation system is enhanced.

The present application relates to the field of general aviation technology, and in particular to a method for optimizing the site selection of low-altitude flight service stations and related products. The method predefines target continuous decision variables based on factors such as the characteristics of the low-altitude flight service stations, evaluation priorities, and data availability; utilizes multi-objective decision analysis to comprehensively and accurately evaluate the performance of each low-altitude flight service station to be selected in the target site selection area in different performance dimensions, and determines the low-altitude flight service stations whose comprehensive performance meets the requirements; and then forms a unified evaluation standard by combining multiple indicators of different dimensions and dimensions, so as to facilitate more intuitive and scientific selection decisions for flight service stations, provide a strong basis for comprehensive evaluation and ultimately accurately and effectively determining the optimal flight service station, and be conducive to the rapid development of the low-altitude industry.

1. The name of the design product: aircraft (RX4M). 2. The use of the design product: general aviation aircraft. 3. The design points of the design product: the combination of shape, pattern and color. 4. The picture or photo that best indicates the design points: perspective view. 5. The design for which protection is sought includes color. 6. Other circumstances that need to be explained: the positions of the aircraft windows in the perspective view A and B are designed with transparent material.

A fixing device for a disassembled general aircraft comprises a transportation frame, a fuselage fixing assembly, a wing fixing assembly arranged on a frame bottom plate, an engine fixing assembly arranged on the frame bottom plate and a horizontal stabilizer fixing assembly arranged on the frame bottom plate. The transportation frame is provided with a frame bottom plate. The machine body fixing assembly comprises a machine body fixing base part arranged on the frame bottom plate. The central wing fixing assembly comprises a first supporting piece arranged at one end of the fuselage fixing base piece at a first preset angle, and a second supporting piece arranged at the top of the first supporting piece. The central wing fixing piece is arranged at one end of the fuselage fixing base piece and forms a second preset angle with the fuselage fixing base piece; the fuselage tail boom fixing assembly is arranged at the other end of the fuselage fixing base piece and forms a third preset angle; and the fuselage tail boom fixing piece is arranged at the top of the second supporting piece and forms a fourth preset angle with the central wing fixing piece. And parallel fixation of the disassembly parts of the general aircraft is realized. And the occupied space of the fuselage of the general aircraft in the horizontal direction is reduced.

1. Name of the product in this design: Airplane (Flying Feather Flying Fish). 2. Intended use of this design: general aviation aircraft. 3. The key design elements of this product are the combination of shape, pattern, and color. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The design for which protection is sought includes color. 6. Other situations requiring explanation: The airplane windows at points A and B in the 3D diagram are designed with transparent material.

1. Name of the product in this design: Airplane (Lightning Double Image). 2. Intended use of this design: general aviation aircraft. 3. The key design elements of this product are the combination of shape, pattern, and color. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The design for which protection is sought includes color. 6. Other situations requiring explanation: The airplane windows at points A and B in the 3D diagram are designed with transparent material.