569 results about "Avionics" patented technology

The invention discloses an airborne radar ground moving target stable tracking method, and belongs to the technical field of avionics, and the method comprises the following steps: S1, obtaining and fusing multi-modal measurement data; s2, clutter suppression and pretreatment; s3, target state estimation; s4, data association and track repair; s5, group target collaborative tracking; and S6, outputting a tracking result. According to the airborne radar ground moving target stable tracking method, multi-mode fusion and track adhesion are used for supplementing a single measurement short plate and repairing a broken track; by means of clutter map and optimization filtering strong clutter suppression, the state precision is improved; the multi-target tracking is optimized by using the graph model and the group target modeling, the complexity is reduced, the prior is fused, and the tracking stability of the complex scene is enhanced.

The invention discloses an avionics system evaluation index system construction method based on a large language model agent. The avionics system evaluation index system construction method comprises the steps that a knowledge extraction module performs knowledge extraction on a design document of an avionics system by using the large language model agent and preliminarily constructs a knowledge graph; the reflection verification module automatically checks and corrects entities and relationships in the knowledge graph based on a large language model agent in combination with a learning normal form, and finally outputs an optimized knowledge graph; and the index generation module automatically generates an evaluation index for each entity node in the optimized knowledge graph based on a large language model agent to form an avionics system evaluation index system. According to the method, extraction, induction and system construction of avionics system evaluation indexes are automatically completed, and the method has the advantages that manual decomposition is not needed, the process is traceable, the coverage is wide, and the efficiency is high.

The present invention relates to the technical field of avionics equipment, and disclosed is a cross-domain maintenance decision-making method for coordinated optimization of maintenance service outlets, activities, and resources. The method comprises the steps of: on the basis of a fault phenomenon, acquiring a set of a variety of maintenance activities; determining whether resources required for a faulty product are missing at a current service outlet, and if the resources are missing, separately computing a resource scheduling time and cost required for each maintenance activity for which resources are missing; computing a fault repair time, repair costs, and repair probability of a certain maintenance activity; and determining a goal of a maintenance decision, and outputting an optimal maintenance scheme. The present invention can assist technicians in making maintenance decisions during maintenance of electronic products, reduce the waste of time and resources caused by the inconsistencies and uncertainties of maintenance activities, guide maintenance activities of remote operation and maintenance, reduce maintenance time, and reduce operation and maintenance costs.

The invention belongs to the field of automatic testing, and particularly relates to an automatic testing system and method for aviation fly-by-wire flight control equipment, and the system comprises a system self-inspection unit, a system resource unit, a system interface adaption unit, and a system testing control unit. And the system self-checking unit controls the automatic test system to execute a self-checking function through operation software. The test efficiency and the test coverage rate can be remarkably improved, the problem of function test omission can be effectively solved, the fault of the tested airborne avionics equipment is analyzed by adding the YMECA fault analysis module and combining the definition event and the structure function of the fault tree, qualitative analysis is carried out on the fault, a professional basis is provided for fault diagnosis, the maintenance difficulty is reduced, and the test efficiency is improved. The aircraft maintenance guarantee efficiency is improved, and joint test of a plurality of airborne avionics devices and parallel test of a plurality of airborne avionics devices of the same model in a fly-by-wire flight control system of a certain type of fighter can be realized.

The invention relates to an aircraft data transmission method and system based on a security network. The method comprises: receiving data from an airborne device via an avionics network, where the data is unidirectionally received via the avionics network over an interactive network bus, and where the unidirectional receiving is effected by the information system configuring an interactive network port as a receiving port; an acknowledgement message or a negative acknowledgement message of the data is transmitted to the onboard device via a peer-to-peer bus.

The invention particularly relates to an exciter virtualization-based airborne application software simulation running environment construction method, which comprises the following steps of: carrying out digital packaging on an operating system interface to realize virtualization running of an embedded real-time operating system; digitally packaging communication interfaces such as a 1553B bus, an ARINC429 bus, discrete magnitude and the like so as to reproduce real avionics communication characteristics in a virtual environment; and simulating a peripheral software and signal interaction process so as to realize virtual generation and response of the multi-source excitation signal. By constructing the simulation running environment, the dynamic test of the airborne embedded software can be carried out under the condition of no real hardware, so that the test sample space is expanded, the test coverage rate and sufficiency are improved, the design and execution efficiency of a dynamic test case is improved, repeated manual operation is reduced, the test cost of the airborne embedded software is reduced, and the test efficiency of the airborne embedded software is improved. The economic benefit is improved.

The present invention relates to the field of avionics equipment. Provided is an avionics fault knowledge fusion method oriented to distributed collaboration. The method comprises the following steps: S1, acquiring multi-source fault knowledge data of avionics equipment, and performing analysis processing and screening on the acquired multi-source fault knowledge data of the avionics equipment; S2, for the problem of knowledge conflicts across different timelines, comprehensively calculating machining fault knowledge on the basis of attribute similarity, in order to complete fault knowledge fusion; S3, for the problem of fault knowledge conflicts from different sources, completing fault knowledge fusion by means of fault element annotation and identification; and S4, constructing a fault knowledge graph, and storing fused fault knowledge. The present invention can mitigate knowledge conflicts during both the initial construction of a fault knowledge model and the expansion of existing fault knowledge models, thereby improving the accuracy, reliability and integrity of knowledge model construction for avionics information equipment, and thus providing better support for fault localization and maintenance of the avionics equipment.

Systems, methods, and non-transitory computer readable media for identifying a cockpit alert context during an aircraft mission are provided. The system includes a controller configured to: store message content in a clearance look-up table for one or more clearance messages received from air traffic control (ATC) during the aircraft mission that contain cockpit data about which an avionic system in an aircraft may later sense and generate a cockpit system alert for display on a cockpit display device; monitor a plurality of avionic systems in the aircraft for a cockpit system alert; retrieve an ATC clearance message from the clearance look-up table that corresponds to a detected cockpit system alert when a cockpit system alert is detected; and signal an aircraft display device to display the ATC clearance message in a visually distinguishable manner that indicates that the displayed ATC clearance message relates to a detected cockpit system alert.

The invention belongs to the technical field of avionics system design, and particularly relates to an integrated task computer and a backup upgrading method thereof. The comprehensive task computer comprises a core processor and a FLASH memory, the FLASH memory is provided with a starting mirror image file and an application mirror image file from low to high according to addresses, the starting mirror image file is internally provided with a first boot loader, a first PL end bit stream and a system configuration program from low to high according to the addresses, and the application mirror image file is internally provided with a second boot loader, a second PL end bit stream and a system configuration program from low to high according to the addresses. The system configuration program is internally provided with a bootstrap program of the application mirror image file and an identification module for identifying whether the application software is upgraded or not; and the application mirror image file is provided with a second boot loader, a second PL end bit stream and an application software program from low address to high address. According to the invention, the online upgrading function of the equipment master control software and the underlying firmware thereof is realized, and the stability and convenience of the system are enhanced.

The invention belongs to the technical field of radar test and simulation, and particularly discloses a multimode mixed injection type semi-physical radar target simulation evaluation system and method, which comprises a radar / electronic warfare beam synchronization unit, an injection type radar target simulation evaluation system and a simulation control unit. The system obtains radar real-time beam scanning information through a beam synchronization unit, carries out real-time fusion on the radar real-time beam scanning information and avionics control data from an avionics system test bench, drives an injection type system to generate a simulation radio frequency target containing a sum signal, an azimuth difference signal and a pitch difference signal, and provides the simulation radio frequency target to a radar to be tested in an injection mode. And the simulation control unit is responsible for man-machine interaction, controlling a test process and performing automatic comprehensive evaluation on a simulation result. According to the method, automatic evaluation of dynamic closed-loop simulation, multi-mode seamless switching and high-order tactical indexes can be realized, and the method is suitable for high-fidelity performance verification of a modern radar system.

The invention discloses a carrier rocket avionics system based on a TSN (Time Sensitive Network) and a carrier rocket avionics data transmission method, and belongs to the technical field of carrier rocket control. A network is physically or logically divided into a periodic time-sensitive data stream, a high-speed time-sensitive data stream and a best effort data stream, the three data streams are subjected to isolation management, and transparent interconnection between a 1553B bus network and a TSN switching network is realized on a protocol layer through an intelligent protocol conversion gateway. Meanwhile, in a network management layer, through an instruction response type configuration protocol, common Ethernet equipment is seamlessly incorporated into the global scheduling and control category of the TSN network. According to the invention, by constructing the avionics network system with three-layer partition and dual-network fusion, multi-network seamless fusion on the rocket can be realized, the real-time performance of the network is improved, and the key requirements of rocket recovery are met.

The invention discloses a circuit breaker switch intelligent detection method and system based on deep learning, a medium and equipment. The method comprises the following steps: acquiring a circuit breaker image and forming a training set; based on the YOLOV8 model, replacing a convolution module of the YOLOV8 with a depth separable asymmetric convolution module to obtain a YOLOV8m model; and training by using the training set to obtain a circuit breaker switch identification model. Inputting the training set into a circuit breaker switch identification model and outputting rectangular frame coordinate information of a switch, intercepting a switch image from an original circuit breaker image according to the output rectangular frame coordinate, and classifying according to a switch state to form a data set; replacing an SE module in the MoblieNetV3 network with a module fusing space attention and channel attention, and obtaining the MoblieNetV3 network fusing an attention mechanism; and training by adopting the data set to obtain a switch state recognition model. And converting the circuit breaker switch identification model and the switch state identification model into ONNX formats, and deploying the ONNX formats on equipment. According to the invention, efficient and accurate circuit breaker state detection on a mobile terminal or embedded equipment is realized, and the intelligent level and the detection efficiency of avionics experiments are improved.

The invention relates to the cross technical field of avionics and edge computing, in particular to a comprehensive cockpit intelligent edge computing method and system, which comprises the following steps: receiving a computing instruction from ground equipment or an airborne module, scheduling corresponding edge computing application store software from a control module based on the computing instruction, and sending the edge computing application store software to the control module; the method comprises the steps of obtaining an edge calculation application demand, collecting target data from a sensor module and / or an airborne module according to the edge calculation application demand, preprocessing the target data to obtain target processing data, distributing the target processing data to an AI calculation module for AI reasoning calculation, and obtaining structured result data; structured result data is analyzed through the control module, an operation scheme is generated and displayed through the display control device, and the technical problems that due to framework rigidity, an existing cabin computing system cannot flexibly schedule computing resources, the real-time processing requirement under complex tasks is difficult to meet, and the overall processing efficiency is low are solved.

Provided in the present invention is a multi-level equipment cross-platform fault knowledge recommendation and adaptive transfer method, comprising: constructing an association relationship between product structure tree nodes and a fault knowledge base; calculating the similarity between first-level nodes of a start-domain product structure tree and a target-domain product structure tree, so as to obtain a similar first-level node pair set; calculating the similarity between child node sets of a similar parent node pair, and outputting a similar second-level node pair set; repeating the previous steps on a next-level node until a terminal node is reached, and outputting a final similar node pair set; calculating the fault case knowledge similarity between every two nodes in the similar node pair set, and excluding, from the similar node pair set, node pairs having relatively low similarities; and selecting a fault knowledge type that needs to be transferred, acquiring and copying, from node pairs having relatively high similarities, fault knowledge data of a start domain, modifying into a target domain a node to which related data is bound, and writing the related data into a database. The present invention can solve the problem of rapid transfer of fault knowledge between different items in avionics equipment.

The utility model discloses an avionics control system for a small sounding rocket, and the system comprises a power voltage stabilizing circuit and an STM32 microprocessor. The STM32 microprocessor is respectively connected with the MOS tube switching circuit, the emission level reading module, the buzzer driving circuit, the steering engine driving circuit, the height sensor BMP280 driving circuit, the six-axis acceleration sensor MPU6050 driving circuit and the storage module W25Q64 driving circuit; the system can quickly, simply and conveniently complete flight data acquisition and attitude control of the rocket, is simple in structure and convenient to operate, has high integration level, high flexibility and stable attitude control and data acquisition and storage capabilities, is suitable for diversified experiment requirements, greatly simplifies the rocket control process, reduces the dependence on the experiment environment, and improves the experiment efficiency. The method is suitable for various engineering education and scientific research scenes, and the application value of the small sounding rocket in teaching and scientific research is improved.

The invention belongs to the technical field of avionics, and particularly discloses an airborne synthetic visual dynamic threat intelligent identification system based on multi-source fusion, which comprises a multi-source data acquisition module, an integrated GNSS unit, an IMU unit, a camera, a laser radar and a millimeter wave radar, and is used for acquiring images, point cloud and meteorological data of a flight environment through a space-time calibration mechanism; the dynamic threat analysis module is used for performing fusion processing on the multi-source data, identifying a dynamic threat target based on a target detection model and outputting a threat level; and the visual scene display module is used for dynamically adjusting the display content and the alarm mode of the synthetic visual scene according to the threat level in combination with the eye movement tracking data and the flight stage information. The problems that a traditional synthetic visual system is lagged in dynamic threat perception, insufficient in multi-source data fusion and low in man-machine interaction efficiency are solved, and the situation awareness and safety guarantee capability of an aircraft in a complex airspace environment is remarkably improved.

A method for providing a streaming display with surrounding aircraft information on an aircraft. The method includes receiving a streaming image from a camera on the aircraft, receiving navigation information representative of the location and orientation of the aircraft, and receiving surrounding aircraft information associated with each of one or more surrounding aircraft. Based upon the navigation information and the surrounding aircraft information, a location of each surrounding aircraft with respect to the streaming image is determined. A surrounding aircraft identifier for each surrounding aircraft, and a surrounding aircraft-annotated streaming image based upon the streaming image are generated. The surrounding aircraft-annotated image includes each surrounding aircraft identifier, and each surrounding aircraft identifier is at a location in the surrounding aircraft-annotated streaming image corresponding to the location of the associated surrounding aircraft. The surrounding aircraft-annotated streaming image is displayed in the aircraft.

The invention discloses an airborne flight safety enhancement system and method based on multi-modal interaction, and relates to the field of crossing of avionics systems and artificial intelligence, and the method comprises the steps that an environment sensing module generates structured environment information; the airborne equipment monitoring module performs real-time health state analysis; the large language model module comprises a computing platform sub-module, a language model sub-module, a knowledge base sub-module, a voice recognition sub-module and a voice synthesis sub-module; and the output module is used for displaying the decision support information generated by the large language model module on a cockpit display device. The method has the advantages that through deep cooperation of multi-mode perception fusion, distillation large language model intelligent decision, natural voice interaction and airborne health monitoring, on the premise of ensuring airworthiness safety, the flight safety is remarkably improved, the pilot load is reduced, and the decision efficiency is optimized.

This invention discloses a comprehensive identification test device and method based on software-defined radio technology, belonging to the field of avionics equipment testing. The device includes: a core processing and control unit, employing a multi-channel high-speed AD / DA and MPSoC FPGA architecture, supporting concurrent operation of various conventional aircraft identification functions through multiple internally integrated models; a radio frequency transceiver module, connected to the core processing and control unit, used for digital frequency conversion and analog-to-digital conversion of signals; a high-power radio frequency front-end component, internally equipped with multi-stage attenuation circuits and isolation devices, used for physical isolation and filtering attenuation of transmitted and received signals, ensuring its power covers the dynamic range of airborne received signals; and a remote control interface for receiving remote control commands to achieve automated test linkage. This invention allows direct connection to test the receiving performance of airborne equipment without the need for external high-power accessories, achieving a high degree of integration and automation of the test equipment, significantly improving detection and troubleshooting efficiency.

The gateway, which connects a low-trust domain (12) and a high-trust domain (13) of an avionics computing infrastructure, provides a plurality of security functions, each function being performed by a data processing node. The gateway comprises, connected in series along a filtering chain of a data flow received from the low-trust domain: a firewall data processing node (4); a protocol break data processing node (5); a master data processing node (1) and an inverse protocol break data processing node (6), the gateway further including a security data processing node (2) connected to each of the data processing nodes of the filtering chain, the different data processing nodes being physically segregated.

The invention belongs to the field of avionics system design, and particularly relates to a large amphibious aircraft radio compass deviation calibration method, which comprises the following steps of: completing installation, calibration and power-on inspection according to the size of an aircraft and part of airborne equipment, and calibrating a site environment state, coordinates of a ground omnidirectional beacon station and the like. The invention provides a compass deviation calibration method for the radio compass of the aircraft, so that the radio compass compass deviation calibration of the aircraft can be more efficiently completed in a general assembly base, the cost is reduced, and the production efficiency is improved.

The invention relates to an avionics application configuration method based on message driving and a dynamic loading mechanism, which comprises the following steps of: generating a hierarchical binary configuration file containing port configuration information and mapping configuration information based on an avionics system interface control file in a construction stage, and analyzing and loading the binary configuration file to a global structure body in an operation stage, according to the method and the system, the mapping configuration information is automatically matched according to the message type of the to-be-processed message, and after parameter configuration is carried out on the corresponding equipment port according to the port configuration information, data reading and writing are carried out by utilizing the information in the equipment resident index, so that message driving and dynamic loading of application configuration are realized. According to the method, manual configuration errors can be avoided, multi-protocol adaptation is supported, only binary configuration files need to be updated when protocols are modified, the operation can be carried out offline, port mapping and related settings are automatically matched by the system according to message types, and therefore the configuration management efficiency and reliability of the avionics system are improved, and the integrity of configuration data is guaranteed.

The application discloses an ADS-B signal receiving device for aviation and relates to the field of avionics equipment. The device comprises a columnar antenna body and a mounting seat. The mounting seat is provided with a telescopic unit. The telescopic unit can be sleeved on the antenna body and forms a heating cavity. The movable end of the telescopic unit is provided with a movable assembly. The movable assembly comprises an adjusting piece and a first air bag which is sleeved on the antenna body. When the adjusting piece is in contact with the antenna body, the adjusting piece can inflate the first air bag and expand the first air bag along the radial direction of the antenna body. When the adjusting piece moves to the outside of the end of the antenna body, the inside of the telescopic unit is communicated with the heating cavity. The telescopic unit can be covered on the antenna body. The hot air which is introduced into the telescopic unit can remove the ice layer on the antenna body. In the process of retracting the telescopic unit, the first air bag in the expanded state can wipe the water drops remaining on the antenna body, thereby improving the removal strength of the ice layer on the antenna body.

An avionics system can provide data to first receiving components associated with a proprietary first protocol and second receiving components associated with a non-proprietary second protocol. A configuration tool generates a first configuration file including instructions for a data access component to provide a first data output to the first receiving components and a second data output to the second receiving components. The configuration tool can generate a second configuration file including instructions to translate the second data output. The data access component can receive a definition database defining the first protocol to translate data according to the non-proprietary second protocol. The data access component can provide requested data to the first and second receiving components according to the non-proprietary second protocol. The second receiving components are configured to translate data received based on the second configuration file.

The application relates to the technical field of avionics chassis, and particularly discloses a device and a method for quickly locking and disassembling a cover plate of an avionics chassis, which are used for assembling and disassembling the chassis and the cover plate; the device is characterized in that a plurality of groups of elastic screwing pieces are arranged on the cover plate, and a plurality of groups of pin shaft pieces are arranged on the chassis and correspond to the screwing pieces one by one; the side of the chassis close to the cover plate is provided with a plurality of groups of insertion holes corresponding to the pin shaft pieces, the pin shaft pieces are located in the insertion holes, the screwing pieces are provided with spiral grooves, the screwing pieces are inserted into the insertion holes, and the spiral grooves are in clamping cooperation with the pin shaft pieces. Through cooperation of the screwing pieces and the pin shaft pieces, the chassis and the cover plate can be quickly locked or disassembled without using tools, the structure is simple, and the device is practical.

The invention relates to a unified management platform and method for a multi-protocol data interface of an unmanned aerial vehicle, and the platform comprises a hardware layer, a drive layer, middleware and an application layer, the hardware layer is used for providing a hardware interface for protocol conversion and logic operation, and achieving the function of the platform; the driving layer is used for configuring the hardware layer and generating an IP core of each communication protocol interface; the middle layer is used for carrying out data transmission and protocol conversion on the hardware layer and the driving layer; and the application layer is used for recording the working state and the fault of the platform. The multi-protocol management platform can adapt to conversion of communication protocols of various existing unmanned aerial vehicle airborne equipment, the universality and expansibility of an avionics communication network can be improved, and the integration complexity is reduced.

The invention discloses an airborne three-dimensional graphic engine display optimization method based on particle filter optimization, and relates to the technical field of airborne avionics graphics. According to the method, optimization strategies such as a particle filtering optimization technology, a three-dimensional pixelating technology, dynamic scene management, resource optimization management, hardware acceleration, an asynchronous shader technology and optimization renderer design are introduced, so that the rendering efficiency, the display quality and the resource utilization rate of the graphics engine are remarkably improved, and the rendering efficiency of the graphics engine can be greatly improved in a resource limited environment. And high-precision and low-delay three-dimensional graphic rendering is realized, the requirement of the aircraft on real-time display is met, and the method has important application value and popularization prospect.

The invention discloses an airborne integrated task processor I / O interface module fault diagnosis method and system, and relates to the technical field of avionics equipment fault diagnosis. The method comprises the following steps of: acquiring partial analog quantity and digital quantity information from an I / O (Input / Output) interface module of an airborne integrated task processor, and acquiring corresponding temperature and vibration information through a temperature sensor and a vibration sensor; after preprocessing and labeling, constructing a combined model based on an attention network and a depth separable convolution strategy; and training the combined model, and performing real-time fault diagnosis on the I / O interface module. Hardware protection is triggered for a permanent fault, and replacement of a fault module is prompted; for intermittent faults, fault types and occurrence time are recorded, a degradation trend report is generated, and follow-up key monitoring is facilitated; according to the invention, additional acquisition equipment is reduced, the fault diagnosis accuracy of the I / O interface module of the IMP is improved, accurate fault positioning and targeted processing are realized, and the reliability and maintainability are improved.

The invention discloses a function detection device and method for a separation pin, an electric detonator and a thermal battery, and relates to the technical field of avionics, the function detection device comprises a control panel, and a power supply module, a low-resistance test module and a voltage and current test module which are installed on the control panel, and an externally used 220V power supply is sent to the power supply module through a fuse F1 and a power switch S1; after voltage stabilization and filtering of the power supply module, the voltage is converted into a required 27V linear direct-current power supply and instrument working voltage 24V, the instrument working voltage 5V, the 27V linear direct-current power supply is sent to a control panel through a fuse F2 and a 27V voltage switch S2, and the 27V linear direct-current power supply is connected in parallel with a 27V voltmeter PV0; instrument working voltage 24V is respectively sent to a control panel and a state indicating lamp through fuses F3 and F4, and instrument working voltage 5V is sent to a voltage and current test module and an instrument of the control panel. The device is easy to operate, accurate in measurement, capable of meeting detection requirements, safe and stable in operation and convenient to carry.

The application discloses a kind of flight record data air-ground transmission components, the air-ground transmission component includes basic application module, acquisition and processing module, link security negotiation module and transmission control module, air-ground transmission component is independent hardware or exists in the form of software in IMA. The aircraft record data air transmission component increases flight record data air-ground transmission function, avoids the problem that flight record data is difficult to obtain due to flight data recorder loss, salvage difficulty, serious damage in air disaster accident, effectively reduces the overhead generated by searching and recovering flight data recorder, air-ground transmission component fully reuses the flight record system composition architecture and air-ground communication capability of existing aircraft, without too much change to avionics system, facilitate to the aircraft produced to carry out modification work, air-ground transmission component supports multiple transmission encryption methods, to ensure the safety and confidentiality of flight record data in transmission process.