66 results about "Avionics" patented technology

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 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 utility model discloses a vibration test module protection box, including box body, apron, limit stop, high hardness rubber pad, wedge locking strip, not to come out screw and wave circular washer. Box body and apron inboard are pasted with high hardness rubber pad, are used for buffering and isolating module and outside hard contact, avoid scratch and surface damage, limit stop sets up in box body lateral wall, is connected through not to come out screw and wave circular washer, possesses automatic release structure, and it is convenient for module dismounting, wedge locking strip installs in box body outside, is used for firmly locking protection box in vibration test fixture. The module protection box simple structure, the protection effect is remarkable, and the adaptability is strong, is applicable to the vibration test of various kinds of avionics module, can effectively promote module appearance quality grade and test pass rate, has good engineering application value.

This utility model relates to the field of calibrating airborne avionics products for aircraft, specifically disclosing a fixture for measuring the installation error of an aircraft accelerometer. The fixture includes a docking seat, one side of which is connected to the top side of an extension rod via a lead-out plate. A measuring body is connected to the bottom side of the extension rod, and the measuring body and the docking seat are located on the same side. This solves the problem of difficulty in measuring accelerometer installation errors, enables indirect measurement of the three-dimensional installation angle, and ensures measurement accuracy.

The utility model relates to controller machine case technical field, and disclose an aviation controller machine case, including the machine case shell, the upper end intercommunication of machine case shell has the heat abstractor, the inside of heat abstractor is equipped with the heat abstracting mechanism for to part heat abstractor, the inside of machine case shell is equipped with the fixing mechanism for to part assembly, the heat abstracting mechanism includes semiconductor refrigeration piece, the semiconductor refrigeration piece is fixed in the upper end of heat abstractor inner wall, the lower surface of semiconductor refrigeration piece is connected with the cold -conducting sheet, the inside of heat abstractor horizontal direction is equipped with two fixed plates, and the inside of two fixed plates all is equipped with circulating fan, the utility model discloses through the air in the machine case shell inhale to the heat abstractor, and circulating fan blows the air in the heat abstractor into the machine case shell, and when air passes through the cold -conducting sheet, can carry out the cooling, and then carries out the heat abstractor to the device inside.

This invention belongs to the field of avionics component testing technology, and discloses a universal DIP-packaged digital integrated circuit chip testing device and method, solving the technical problem of poor versatility of DIP-packaged integrated circuits of different models and functions. It effectively solves the problems of poor versatility, inconvenient pin connections, and low testing efficiency in existing DIP-packaged digital integrated circuit chip testing, achieving rapid, accurate, and convenient testing of different DIP-packaged digital integrated circuit chips.

This invention belongs to the field of artificial intelligence and intelligent control system technology, and discloses an aircraft avionics management method and system based on a centralized power supply and signal hub. The method includes: performing power supply channel status analysis and energy consumption analysis on the overall aircraft power supply and distribution data to obtain overall aircraft power supply and distribution analysis results; performing protocol analysis and topology connectivity judgment on the overall aircraft signal data to obtain overall aircraft signal link analysis results; using flight control status data as status anchors and mission phase data as semantic context to construct an overall aircraft energy information status fusion map; extracting a multi-dimensional coupling feature set of the overall aircraft avionics; and combining pre-set avionics control rules to achieve centralized management of aircraft avionics energy flow and data flow. This invention lays a solid foundation for achieving predictive maintenance, energy efficiency optimization, and adaptive mission configuration.

This invention provides an electromagnetic lock module for an aircraft cockpit door with power-off reset and anti-blocking functions, belonging to the field of aircraft avionics system technology. It includes a base, housing, door locking mechanism, stepper motor assembly, control circuit board, and status detection module. The door locking mechanism includes an anti-blocking hook assembly and a locking pin assembly. The stepper motor assembly is energized only momentarily during action, driving the locking pin to move and achieve locking and unlocking, solving the problems of overheating, high energy consumption, and short lifespan caused by continuous power supply in traditional electromagnetic locks. The module integrates multiple detections, including locking pin position and door position, for real-time status monitoring. A specially designed anti-blocking transmission mechanism allows for separation and automatic reset when the locking pin is jammed, preventing damage. The module has an automatic release function upon power failure, ensuring reliability for emergency evacuation. This invention features a robust structure, high fault tolerance, and meets aviation standard requirements.

The application provides an anti-single event upset processing method for avionics, which comprises the following steps: step one, defining and initializing a configurable hierarchical check data structure; step two, entering a loop task and obtaining to-be-written data; step three, writing the to-be-written data and a correction detection mode into the data structure; and step four, when the data needs to be read, reading to-be-read data from the data structure in groups. Compared with a traditional triple modular redundancy scheme, the application reduces storage occupation by more than 60%, solves the problem of high cost of directly using Hamming code for real-time correction and detection of memory data in an aviation device, and reduces resource consumption of encoding and decoding while having correction and detection capability, thereby meeting high requirements of the aviation device on real-time performance and resource efficiency.

This utility model relates to a modular avionics box, including an equipment box and an equipment mounting plate. The equipment box consists of an insulated housing and side covers. An opening on the front of the insulated housing allows the side covers to be fastened. One end of the equipment mounting plate is fixedly connected to the side wall of the side cover. Ventilation / sealing openings are provided on the side wall of the insulated housing. Avionics equipment is replaceably arranged on the equipment mounting plate. Openings in the side covers allow the avionics equipment wiring harnesses to pass through. This utility model, by designing an independent equipment box and modularly mounting the avionics equipment on the equipment mounting plate, creates an insulated, waterproof, moisture-proof, and anti-aging environment for the avionics equipment. The insulated housing and side covers are connected by spring-loaded latches for opening and closing, allowing for quick maintenance of all avionics equipment after opening the housing.

This invention belongs to the field of satellite navigation and avionics technology, and proposes a deep learning-based adaptive integrity enhancement method and system for ionospheric scintillation-multipath coupling. The method includes: S1, signal data acquisition and preprocessing; S2, disturbance feature extraction and state identification; S3, generation of a comprehensive disturbance intensity index; S4, calculation of the adaptive Sigma expansion coefficient; S5, integrity calculation; and S6, integrity enhancement and adaptive optimization. This invention improves the integrity accuracy and reliability of navigation systems in complex signal environments, ensuring that the airborne equipment of the Global Navigation Satellite System (GLS) meets airworthiness standards during the CAT II / III precision approach phase.

The application relates to a longitudinal double-rotor unmanned aerial vehicle avionics system, which comprises a starting motor, an engine, a generator, an ACDC airborne power supply, a starting battery, a first battery, a second battery, a knob switch, a gear shifting switch, an ECU, a wind cooling fan, a water cooling fan, a control collection box, a flight control, a radio, a gyroscope, a rudder, a temperature sensor, an oil level sensor, a receiver, a lamp panel and an air speed meter; the generator serves as a main power supply of the unmanned aerial vehicle; the first battery and the second battery jointly constitute a standby power supply of the unmanned aerial vehicle; the wind cooling fan control signal, the water cooling fan control signal, the air speed meter signal and other control signals which have little influence on flight and are prone to interference are concentrated in the control collection box and are separately controlled with the flight control; the application determines the minimum avionics system which satisfies normal flight of the longitudinal double-rotor unmanned aerial vehicle, clearly defines the key components of the unmanned aerial vehicle flight, and improves the flight safety of the unmanned aerial vehicle through improvement of the power supply system operation scheme and the separate control method.

Method and electronic device for managing the execution of software application(s) services on an avionics platform, computer program and associated avionics system. This method for managing the execution of software services on an avionics platform comprising resources for the execution of said services is implemented by an electronic device and comprises: - acquisition (110) of contextual data for a group of software services to be executed; the contextual data comprising, for each software service: a maximum quantity of resources used by said service; an operating constraint of said service equal to fault resistance or non-fault resistance; and if the operating constraint of said service is equal to fault resistance, a number of faults to which said service must be resistant;- calculation (120), based on acquired contextual data, of a context for the software service group; - launch (130) of the execution of the software service(s) of the group according to a set of service distribution rules and based on the calculated context. Figure for the abbreviation: Figure 4;

The application relates to the field of avionics, and discloses a lifting speed filtering method and system based on a second-order Butterworth filter, which comprises the following steps: collecting an atmospheric pressure signal of an airplane in real time, calculating an air pressure height according to the atmospheric pressure signal, calculating a lifting speed signal according to the air pressure height, performing amplitude-frequency characteristic analysis on the lifting speed signal to determine a cutoff frequency of the second-order Butterworth filter, dynamically adjusting the cutoff frequency of the second-order Butterworth filter according to the flight state of the airplane, inputting the lifting speed signal into the second-order Butterworth filter with the adjusted cutoff frequency, and obtaining a filtered lifting speed signal. The application realizes scientific design of filter parameters by performing amplitude-frequency characteristic analysis on the lifting speed signal and obtaining a digital filter structure through denormalization processing and bilinear transformation, determines the cutoff frequency based on the physical characteristics of the signal, and avoids the disadvantages of selecting parameters by experience in the traditional method.

The application discloses an avionics system fault diagnosis method and device based on fault propagation, comprising the following steps: constructing an architecture model of an avionics system, constructing a fault propagation model, traversing the fault propagation model, obtaining fault information of an airborne maintenance system, obtaining operation information and operation phenomena generated in a line maintenance process, inputting the operation information generated in the line maintenance process into the fault propagation model, obtaining a fault propagation model after line maintenance, traversing the fault propagation model after line maintenance, obtaining cockpit effects of the fault propagation model, obtaining cockpit effects of the fault propagation model after line maintenance, and finally locating a fault source according to the above information. The application considers the problem of fault cross-component and cross-system propagation caused by the complexity of the avionics system, and improves the accuracy and rapidity of fault source positioning caused by fault propagation.

The present application belongs to the technical field of aircraft design, and particularly relates to an avionics Ethernet-based bus architecture for an avionics system of a trainer aircraft. The bus architecture comprises a core processor and devices / subsystems, wherein the devices / subsystems comprise a video processor, a display end, a data loading recorder and an electromechanical management computing system; the video processor, the display end, the data loading recorder and the electromechanical management computing system are all connected to the core processor; the core processor comprises a first core processor and a second core processor, the first core processor and the second core processor are hot standbys for each other, and the first core processor and the second core processor are both interconnected to the devices / subsystems by means of a bus; and when an error occurs in either core processor, the core processor in a normal state can continue operating, without affecting normal task processes of the devices / subsystems, and without propagating the error throughout the entire combat flight software, thereby ensuring the normal operation of the avionics system.

The utility model provides a kind of atmospheric data calibration adapter, it is related to the technical field of avionics test equipment, the utility model includes an electrical male plug and an electrical female plug, the electrical male plug with the electrical female plug is electrically connected by wire, the electrical male plug is 78 needle D-sub type electrical plug, the electrical male plug is electrically connected with the data end of GDC74 series atmospheric data computer, the electrical female plug is electrically connected with the data end of calibration computer, for carrying out the data communication transmission between GDC74 series atmospheric data computer and calibration computer, compared with prior art, by setting electrical male plug and electrical female plug, physical connection is established between GDC74 series atmospheric data computer and calibration computer end, it is convenient to calibrate GDC74 series atmospheric data computer work.

This invention provides an on-chip integrated intelligent actuation control device for aircraft based on a software-defined and hardware-accelerated collaborative paradigm using silicon photonic interconnects, belonging to the field of avionics and flight control technology. The device uses software-defined methods for functional configuration and reconfiguration, while hardware acceleration ensures link determinism and performance. Its core features include: achieving highly interference-resistant signal sensing and isolated transmission through a software-configurable silicon photonic interconnect intelligent interface; integrating a reconfigurable sensor computation and a hard real-time control law engine through a heterogeneous computing acceleration center, providing deterministic and high-performance sensor computation and control law execution; achieving efficient and safe energy conversion through a software-defined intelligent power drive module; and performing global collaborative configuration and online optimization of the above modules through an edge intelligent management unit. This invention resolves the contradiction between task adaptability, extreme real-time performance, and operational reliability in actuation control, and is applicable to distributed intelligent actuation systems for multi-electric / all-electric and hypersonic aircraft.

1. The name of the design product: aviation power interface control box. 2. The use of the design product: for local control of intermediate frequency, DC power output, display power supply state. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view.

This invention discloses an airborne network path planning method based on multi-objective constraints and deep reinforcement learning. The method includes: creating a task set Q containing several tasks q in an airborne network model; constructing a path optimization fusion model that integrates a multi-objective collaborative optimization model and a deep reinforcement learning algorithm network; the deep reinforcement learning algorithm network constructs a task path set based on the start and end nodes of the tasks in the task set Q and selects a subset of task paths that satisfy path risk constraints and task isolation constraints; obtaining the optimal task path combination from the task path subset through a path link balancing module; and using the optimal task path combination as the path planning result for the task set Q. This invention, considering reliable data flow transmission and network load, combines the service attributes of the tasks and plans paths that achieve risk balancing across network links and meet isolation requirements, thereby improving the overall network transmission security of the aircraft avionics system.

This invention discloses a method for stimulating solder joint desoldering failure in avionics products under complex operating conditions. The test chamber begins a temperature rise program from a low temperature (T) while the product is powered on. At a high temperature (T), the test chamber temperature is maintained for 10-15 minutes, vibration is applied, and functional performance testing is performed to determine if a failure has occurred. The product is then powered off, and the test chamber is cooled to the low temperature (T). This process is repeated. This invention simulates the complex environment of a product in the field through a comprehensive test profile of temperature, vibration, and electrical stress, stimulating solder joint desoldering failure in the product's chips. It verifies the mechanism of solder joint desoldering failure analysis and provides a basis for product design improvements, thereby enhancing the long-term reliability of the product in the field.

The invention relates to a safety module used in civil and military aircraft, in which the control of power layers is carried out via a safety analysis algorithm on an internal programmable digital logic circuit, where the temperature, current, and voltage values of the hardware are monitored with a contactless and integrated sensor in order to detect situations of overheating, excessive power consumption, overvoltage, spark, and gas – smoke emission.

This invention discloses a method and system for data expansion and reliability analysis of avionics equipment, comprising: collecting reliability growth test data of avionics equipment to obtain a full sample dataset and a candidate subsample set; evaluating the information content of the candidate subsample set by maximizing Rényi entropy; constructing a dual-objective collaborative optimization model of entropy constraint and distribution distance by minimizing the distribution difference between the candidate subsample set and the full sample set by minimizing the Wasserstein distance metric; determining the globally optimal subsample set and sample reuse degree by using a greedy search to traverse the sample reuse degree; establishing an avionics equipment reliability analysis model based on a two-parameter Weibull distribution; adaptively selecting a hyperparameter estimation method according to prior information conditions and model complexity and constructing a posterior distribution based on Bayes' theorem; and using a step-by-step sampling method for avionics equipment reliability analysis and life prediction. This invention achieves both information content and distribution representativeness in data expansion and reliability analysis.

This invention belongs to the field of system architecture and standards technology, and discloses a method and system for constructing an avionics standard system based on a system architecture model. It constructs a multi-dimensional model of avionics system capability requirements, mission activities, and functional requirements, comprehensively evaluates the applicability and deficiencies of existing avionics system standards according to the principle of standard requirement capture, and proposes suggestions for standard adoption and new revision requirements, thus constructing a scientific and complete avionics standard system framework and achieving unified management of standard resources. This invention solves the problems of one-sidedness, redundancy, and ex-post nature of traditional bottom-up generation of avionics system standard requirements, improves the efficiency of standardization work, perfects the standard system architecture, and fully leverages the coordination and compatibility among standards.

The application belongs to the technical field of avionics, and particularly relates to a JTAG interface-based ATSU board data reading and writing system and method, which comprises an upper computer and an embedded control device, the embedded control device comprises an STM32 module, an FPGA module, a JTAG module and a first relay module, the upper computer and the FPGA module are in communication connection with the STM32 module respectively, the JTAG module is connected with the FPGA module and the first relay module respectively, the FPGA module is in communication connection with the first relay module, and the first relay module is used for controlling the on-off between the JTAG module and the ATSU board. The application can reduce manual operation actions on the ATSU board and reduce the probability of manual operation failure.

The application discloses an airborne data information transmission method, device and system, electronic equipment and a readable storage medium. The method comprises the following steps: when an airborne avionics access signal is monitored, transmission data information of a to-be-accessed device is acquired; a best data transmission mode currently supported by the airborne device is determined according to a link quality detection result; a transmission mode negotiation result is determined according to the transmission data information and the best data transmission mode, and the transmission mode negotiation result is fed back to the to-be-accessed device; and the transmission data of the to-be-accessed device is transmitted by using a data transmission mode corresponding to the transmission mode negotiation result. The application can efficiently support various avionics access devices.

The application belongs to the technical field of avionics system integration test, and discloses a kind of aircraft avionics multi-system hybrid simulation and collaborative efficiency evaluation verification system and method.The system includes avionics simulation and collaborative verification master unit, space-time consistency synchronization and integration hub, optical fiber reflection memory network, integrated large-scale program-controlled switch matrix and multi-specialty hybrid simulation cluster.The system injects high-stable clock source into the physical layer of optical fiber reflection memory network through space-time consistency synchronization and integration hub, establishes microsecond-level precision global unified hardware time base;Using integrated large-scale program-controlled switch matrix realizes the software-defined rapid reconfiguration of various verification modes such as "all-digital-hardware-in-the-loop";The master unit is built-in real-time performance evaluation engine, and the quantitative indexes such as collaborative action synchronization error and task chain completion rate are calculated online based on global timestamp.The application effectively solves the problems such as loose cross-system timing, complicated physical link reconstruction and lagging evaluation in the prior art, and significantly improves the verification efficiency and evaluation confidence of complex avionics system.

An avionics electronic computer with a virtual machine management hypervisor, and an aircraft comprising such a computer. This avionics electronic computer on board an aircraft comprises a group of computing electronic card(s) (25) having computing resources and storage resources (40); a set of microservices executed independently of each other, with at least a part of the resources; a set of software application(s) to call one or more of the microservices; and a set of orchestrator(s) (55, 56) to implement the set of microservices by allocating at least a part of the resources.The orchestrator set includes several orchestrators (55, 56), and the computing card group comprises at least two virtual machines (50) and a virtual machine management hypervisor (45), common to the computing card group and configured to distribute at least some of the resources among the virtual machines (50), each hosting one of the orchestrators and making its resources available to that orchestrator. See Figure 2 for abbreviations.

The application relates to the field of image processing and embedded visualization, and discloses an embedded high-performance map rendering method, which solves the problems in the background art and comprises the following steps: S1, data preprocessing and coordinate conversion, wherein SQLite is used to carry out hierarchical thinning compression on geographical data, and the geographical data is converted into an ENU or NED coordinate system; S2, lightweight map presentation, wherein a CPU rendering pipeline is constructed by using a QPainter of Qt, and a hierarchical drawing strategy is adopted to dynamically adjust display priority; S3, optimized rendering and real-time updating, wherein an LOD algorithm is adopted in combination with difference detection to redraw only the changed area; S4, graphic drawing and performance optimization, wherein a caching and area clipping mechanism is adopted in combination with spatial index optimization to improve retrieval efficiency; and S5, intelligent display and path planning, wherein a task planning module is integrated to realize real-time visualization of a flight path. The application realizes efficient and smooth map rendering on an embedded platform, and significantly improves the navigation accuracy and task execution efficiency of a low-altitude flight avionics system.