32 results about "General aviation" patented technology

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 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 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.

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 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 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.

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.

A general aviation portable electric towbar that uses a frame to couple to the aircraft on one end, has a handle on the other end for the operator to press a drive roller against the wheel to be driven. The chuck of a drill directly mounts to a drive roller shaft without any other method of motion transfer. Since the drill is mounted on the opposite end as the handle, the drill is controlled by a remote trigger mechanism. Since this configuration can use a drill that is commonly available that directly drives a drive roller without any other method of motion transfer, this device has few parts which reduces weight, costs and complexity, making for a simple, reliable, lightweight and affordable portable electric towbar for general aviation use.

The invention discloses an aircraft comprehensive performance quantitative evaluation method based on a new energy civil aircraft. The method comprises the following steps: constructing a new energy civil aircraft comprehensive evaluation multistage index system; establishing a comprehensive evaluation model; quantifying index parameters; and calculating a comprehensive evaluation result. According to the method, the comprehensive performance of the new energy civil aircraft is comprehensively evaluated from different dimensions, the incomparability caused by differences of dimensions, orders of magnitude and scale types among various indexes is eliminated, and the performance evaluation of the new energy civil aircraft is more comprehensive and real; complex application conditions of new energy power are compared and evaluated in a standardized mode, and a more comprehensive analysis and prediction method is provided for development of new energy civil aircrafts.

The utility model provides a waterproof terminal of a photoelectric glass handrail, which comprises a wire outlet terminal component assembly part, the wire outlet terminal component assembly part comprises a base, a side cover and an upper cover, the side cover is arranged on the end face of the base, the upper cover is arranged on the top of the base, the base, the side cover and the upper cover are fixed to form an inner cavity, and the inner cavity is arranged in the inner cavity. An inner cavity is formed in the base, the upper cover and the base are fixedly connected with a single-head aviation plug wire, a circuit module is installed in the inner cavity, the upper cover is provided with a plurality of glue injection holes, and the glue injection holes are used for injecting glue into the inner cavity and exhausting air. A soft and hard circuit board and a general aviation plug wire are combined, the base, the side cover and the upper cover are fixed through the glue injection holes to form an inner cavity for glue injection, the glue filling process is performed twice in sequence to ensure that glue in the terminal is filled compactly, and the purposes of sealing, water resistance and moisture resistance are achieved.

This invention belongs to the field of aircraft teaching technology, specifically a simulation method and system for a general aviation aircraft control system, comprising the following steps: S1, setting control parameters and flight state parameters, and calculating the transmission ratio of the control mechanism and the transmission ratio of the transmission mechanism; S2, operating the control mechanism, the movement of the control mechanism is transmitted to the control surface through the transmission mechanism, and calculating the deflection angle of the control surface based on the movement distance of the control point, the transmission ratio of the control mechanism, and the transmission ratio of the transmission mechanism; S3, updating the lift coefficient based on the deflection angle, and calculating the theoretical aerodynamic force that the control surface should bear based on the lift coefficient and flight state parameters; S4, applying aerodynamic simulated loads to the control surface through the control surface loading unit, and feeding back the aerodynamic simulated loads to the control mechanism through the transmission mechanism. This invention can provide aerodynamic feedback of the control surface, improving the realism of the simulation.

The present application belongs to the field of aviation flight training, modern aviation logistics, general aviation production service, aviation training equipment management and intelligent inventory optimization, and discloses a kind of management and inventory optimization method and system of flight simulation equipment, solve the technical problems existing in the management of current flight simulation equipment management, such as scattered management, inaccurate life prediction, unreasonable inventory scheduling and maintenance plan lag.The present application collects multi-source operation data of flight simulation equipment and constructs a life prediction model that integrates physical degradation law and data-driven learning, and realizes accurate calculation of equipment residual life by combining with the health coefficient after repair;Based on the residual life failure probability, an inventory decision model is constructed with the goal of minimizing total cost, and particle swarm algorithm is used to output inventory strategies such as dynamic reorder point and order quantity;Relying on the prediction error, a hierarchical adaptive correction mechanism is established.The present application realizes the closed-loop intelligentization of equipment management, improves the prediction and scheduling level, reduces the risk of missing parts, and guarantees flight training.

The application relates to the field of aircraft maintenance data processing, and particularly discloses a general aviation aircraft maintenance cycle determination method based on a Bayes-Bootstrap method. The method comprises the following steps: measuring characteristic parameters of horizontal measurement elements of each aircraft; constructing a sample data set, and performing normal distribution testing and effective sample point set construction; creating a set containing n data points; determining a probability density function on which virtual augmentation is based; calculating and storing the data points into the augmented sample point set; introducing a parameter, calculating the augmented sample points; repeating step S6 for 6 times to obtain a data point set for the Bayes-Bootstrap method after expansion; calculating a confidence interval of the sample mean under a confidence level; calculating an early warning failure rate; comprehensively considering the service life of the aircraft and the early warning failure rate, querying an aircraft failure curve table to determine the next maintenance time of the aircraft, effectively reducing hidden troubles caused by untimely aircraft maintenance and reducing the manpower and material resources consumed by large-scale maintenance.

The utility model discloses a general airplane emergency battery box which comprises a battery box body and single batteries, a plurality of battery mounting positions for accommodating the single batteries are arranged in the battery box body, and a first row of conducting strips and a second row of conducting strips which are respectively contacted with two ends of the single batteries are arranged on the battery box body. And the battery mounting position is positioned between the first row of conducting strips and the second row of conducting strips. The general airplane emergency battery box is simple in structure, low in production cost and convenient to maintain and replace.

1. Name of the designed product: airplane (lightning arrow). 2. Use of the designed product: general aviation airplane. 3. Design points of the designed product: combination of shape, pattern and color. 4. Picture or photo best indicating the design points: perspective view. 5. The designed product contains color. 6. Other circumstances needing explanation: the airplane window positions at points A and B in the perspective view are designed of transparent material.

The invention relates to the field of general aviation aircraft flight parameter identification, in particular to a flight parameter multi-task identification method and system based on a progressive extension one-time network. According to the scheme, the method comprises the steps that a cabin video containing an electronic integrated display is collected through a cabin camera device, a standardized electronic display image sequence is obtained after preprocessing, and on this basis, a progressive expansion one-time super network supporting variable four dimensions of network depth, width, convolution kernel size and input resolution is constructed; a shared backbone network is trained in combination with knowledge distillation, a flight parameter display area detection head, a flight parameter numerical value identification head and a time sequence consistency modeling head are arranged on the backbone network, target sub-networks meeting different airborne platform computing power constraints are automatically selected and deployed to an airborne reasoning module, and joint optimization is performed by using a multi-task loss function. And unified identification of flight parameters such as air speed, attitude, course, height and vertical speed is realized. The method is suitable for identifying the flight parameters of the general aviation aircraft.

The present application relates to the field of general aviation flight parameter identification, and particularly relates to a flight parameter multi-task identification method and system based on a progressive expansion one-off network. The scheme comprises collecting cockpit video containing an electronic integrated display through a cockpit camera device, obtaining a standardized electronic display image sequence after preprocessing, constructing a progressive expansion one-off super network with four dimensions of variable support network depth, width, convolution kernel size and input resolution, combining knowledge distillation to train a shared backbone network, setting a flight parameter display area detection head, a flight parameter value identification head and a timing consistency modeling head on the backbone network, automatically selecting a target sub-network meeting different airborne platform computing power constraints to deploy in an airborne inference module, using a multi-task loss function for joint optimization, and realizing unified identification of flight parameters such as airspeed, attitude, heading, altitude and vertical speed. The present application is suitable for general aviation flight parameter identification.

The application discloses a kind of civil aircraft co-pilot take-off and landing critical stage control ability evaluation method and system, it is related to passenger plane driving capacity evaluation field, its method includes: obtaining the QAR sequence data of fly-by-wire passenger plane flight, identify several key sub-stages in take-off and landing process from QAR sequence data;Build the co-pilot operation evaluation model based on co-pilot operation evaluation factor system, and the co-pilot operation evaluation model is calculated according to key sub-stage based on co-pilot operation evaluation factor system to obtain the ability evaluation value of each key sub-stage;The total value of flight ability evaluation of all key sub-stages of fly-by-wire passenger plane flight is calculated by weighted summation, and the co-pilot operation ability grade is judged and output.The application can calculate the ability evaluation value of each key sub-stage and the total value of flight ability evaluation of fly-by-wire passenger plane flight according to key sub-stage based on co-pilot operation evaluation factor system, form objective, unified, traceable co-pilot ability evaluation result.

The utility model discloses a general-purpose airplane composite material luggage compartment which comprises a compartment body and a fixed edge, the compartment body and the fixed edge are integrally formed, the fixed edge is fixedly connected with an airplane body, the fixed edge is located at the front end of the compartment body, the outer diameter of the fixed edge is larger than that of the compartment body, and a plurality of embedded fixing rings are arranged on the fixed edge. A plurality of embedded fixing rings are distributed along the circumferential direction of the fixing edge, and the fixing edge is fixedly installed on the fuselage through connecting pieces matched in the fixing rings. The luggage compartment is convenient to mount, and the air conditioner is convenient to mount. The multi-layer structure of the luggage compartment can improve the rigidity and tensile strength of the luggage compartment.

The invention belongs to the field of aviation flight training, modern aviation logistics, general aviation production service, aviation training equipment management and intelligent inventory optimization, and discloses a management and inventory optimization method and system for flight simulation equipment. The technical problems of scattered management, inaccurate life prediction, unreasonable inventory scheduling and delayed maintenance plan in existing flight simulation equipment management are solved. According to the method, multi-source operation data of flight simulation equipment is collected, a life prediction model fusing a physical degradation law and data-driven learning is constructed, and the residual life of the equipment is accurately measured and calculated in combination with a post-repair health coefficient; on the basis of the residual life failure probability, constructing an inventory decision-making model taking total cost minimization as a target, and outputting inventory strategies such as dynamic reorder opportunity and order batch by adopting a particle swarm algorithm; and establishing a layered self-adaptive correction mechanism based on the prediction error. According to the invention, closed-loop intelligentization of equipment management is realized, the prediction and scheduling level is improved, the risk of missing parts is reduced, and flight training is guaranteed.

This invention provides a general aviation low-altitude flight information service system, comprising: a ground-based surveillance data acquisition and processing module, a TIS-B server, an ADS-B ground station, a BeiDou command aircraft, a flight service cloud server, and a general aviation low-altitude flight information service terminal; and an airborne ADS-B transceiver module, a TIS-B receiver module, a BeiDou short message communication module, an airborne display and control terminal, and a black box. This invention utilizes BeiDou short message service, 1090ES link, 5G air-to-ground communication link, and low-orbit satellite link to exchange traffic situation information, meteorological information, aeronautical information, and aircraft quality parameters according to standardized or customized protocols, enabling efficient collaborative general aviation low-altitude flight information services between airborne pilots and ground monitoring personnel.