911 results about "Avionics" patented technology

A multi-model fused avionic product health assessment method includes the following steps: collecting relevant data of an avionic product; performing data pre-processing on the relevant data to obtain first data and second data; training a plurality of base models on the basis of the first data; performing quantitative measurement and fusion on the plurality of base models to obtain an integrated model; and inputting into the integrated model the second data which serves as a test sample to obtain a health assessment result of the avionic product. A plurality of base models are integrated by using an AdaBoost algorithm, and a reference can be provided for a method based on data driving in terms of application in the health assessment, prediction and management of an avionic product.

The invention provides avionic equipment based on high-precision inertial navigation and a signal processing method, relates to the technical field of aviation navigation control, and aims to evaluate the selection of a driving sensor by using environmental complexity, optimize the acquisition quality of inertial data such as angular velocity and acceleration, pixel coordinates and specific optical data in real time, reduce redundancy and improve the precision of navigation. Spectral decomposition and adaptive filtering are utilized, signals are dynamically cleaned according to environment noise of different frequency bands, key features are reserved, high-dimensional feature vectors are generated through spatial-temporal feature reconstruction, the expression ability of low-quality data is enhanced, fusion weights are dynamically adjusted based on the signal-to-noise ratio and consistency indexes, predictive error correction is combined, and long-term drift is eliminated. Hardware support ensures that processing delay is less than 10ms, anti-interference shielding maintains data stability, dependence of traditional navigation on external signals is broken through, long-time high-precision navigation is realized, the method is particularly suitable for aviation secret tasks and civil aviation flight in severe weather, and task success rate and safety are improved.

The invention provides an integrated avionics system schedulability analysis method based on reinforcement learning, and the method comprises the steps: designing a Markov decision process according to an integrated avionics system schedulability problem, and constructing a virtual environment; combining a value-based reinforcement learning algorithm with a multi-head attention mechanism, interacting with a virtual environment through an intelligent agent, and learning to obtain an optimal state-action value function; when the intelligent agent interacts with the environment, obtaining the value of each feasible action in the current state by using the optimal state-action value function; selecting the feasible action with the highest value, and executing the feasible action; acquiring a next state and rewards, and accumulating the rewards; or combining a strategy-based reinforcement learning algorithm with a multi-head attention mechanism, and learning to obtain an optimal strategy function; and obtaining a plurality of pre-selected actions by using the optimal strategy function, and executing a candidate action sequence with the highest score.

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 a conflict resolution method for an open avionics architecture. The method comprises the following steps: constructing an avionics field standardized ontology model, an entity type, a semantic relationship and a constraint rule; the entity types comprise a standard type, a resource type, an interface type and a security type; the semantic relationship comprises inclusion, inheritance, compatibility, dependence, conflict, constraint and version evolution; the constraint rule comprises version consistency, function interoperability and performance index constraint; building a multi-standard library based on the knowledge graph; and through a conflict detection and resolution mechanism, standard conflicts possibly occurring in the open avionics architecture design process are identified and eliminated. According to the method, unified modeling, multi-standard library construction and semantic level conflict detection and resolution of the multi-source heterogeneous avionics standard are realized.

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 invention provides a switching type flexible production line task scheduling method and system based on a multi-pointer network, and relates to the field of production line task scheduling, and the method comprises the steps: building a switching type flexible production line-oriented task scheduling mathematical model; converting the task scheduling mathematical model for the switched flexible production line into a Markov decision process model; establishing a multi-pointer network based on a multi-head attention mechanism based on a Markov decision process model; through an MO-PPO training module, parameters of a multi-pointer network based on a multi-head attention mechanism are optimized; through the optimized multi-pointer network based on the multi-head attention mechanism, switching type flexible production line task scheduling is carried out, and the method has the advantage of improving the efficiency and accuracy of switching type flexible production line task scheduling in the manufacturing and testing process of avionics equipment products.

The invention relates to the technical field of data processing, and provides a data processing method for testing avionics equipment, which comprises the following steps of: testing a communication optical cable of an aircraft communication system through an optical time domain reflectometer; analyzing the deviation between the loss value of the reflection intensity of the optical signal at each moment and the reflection loss threshold value to obtain the fault probability of the optical cable in the monitoring time period; analyzing the difference between the moment when the optical signal reaches the bending position of the optical cable and the moment corresponding to the peak point, and obtaining the reflection unpredictability of the optical signal in the monitoring time period; combining the light source power difference to obtain an optical cable performance error in the monitoring time period; obtaining the extra loss degree of the optical cable in the monitoring time period by combining the change condition of the temperature data; determining a test result correction coefficient of the monitoring time period; and correcting the reflected signal oscillogram, and testing the communication optical cable. The invention aims to solve the problem that the actual performance judgment of the optical cable is influenced by the fine change interference of various factors in the optical signal propagation process of the communication optical cable.

The invention belongs to the field of electric vertical take-off and landing aircrafts, and discloses a novel vertical take-off and landing remote high-speed manned electric tilt-rotor aircraft structure which comprises an aircraft body, wings, a V-shaped empennage, six supporting arms, six tilt-rotor units, an energy system, an avionics system and an undercarriage. The six tilting rotor wing units are symmetrically installed on the wings and the V-shaped empennage through the six supporting arms. The aircraft is mainly characterized in that the design of six tilting rotor units is adopted, so that the aircraft has the advantages of vertical take-off and landing, high-speed forward flight, no structural'dead weight 'and useless power consumption; the design that the supporting arms extend out of the wings and the empennage to exceed the radius length of the rotors is adopted, and the downward projection of a rotor disc is not overlapped with the wings and the empennage in the vertical flight state, so that downward washing flow of the rotors cannot generate downward loads on the wings and the empennage, and power consumption for overcoming the downward loads is avoided; the design of the wings with high aspect ratio and winglets is adopted, so that the forward flying lift-drag ratio and the cruising efficiency are improved, and the aircraft has high-speed forward flying and remote flying capabilities; and the six tilting rotor units adopt the same tilting mechanism, so that the complexity of design and manufacturing is reduced.

The invention belongs to the technical field of aircraft avionics airworthiness, and particularly discloses a reaction type wind shear alarm reliability evaluation method based on flight parameter data, which comprises the following steps: extracting flight wind shear operation data; calibrating a wind shear alarm event; calculating a wind shear alarm reliability evaluation index; building and training based on a VAE-LSTM model; and performing reactive wind shear alarm reliability evaluation by using the trained VAE-LSTM model. According to the method, the reliability of a wind shear alarm event is evaluated and calibrated by analyzing sample data, then the wind shear recognition reliability is converted into an abnormal detection problem of a time sequence index based on a VAE-ISTM model, and the energy change rate cumulative sum is selected as a judgment index; the invention provides an approach stage reactive wind shear alarm reliability evaluation method based on energy change rate accumulation, and provides technical support for avionics equipment manufacturers to optimize reactive wind shear alarm system design and bureau to better carry out airworthiness certification on related equipment.

The invention provides an open type avionics system for a multipurpose unmanned aerial vehicle, and relates to an unmanned aerial vehicle electronic system, the system comprises a comprehensive processing module, a navigation module, a servo module, a power supply and distribution module and a load module, and the modules realize data interaction through an interconnection bus; a protocol conversion module with standardized interfaces is further arranged between the load module and the comprehensive processing module, and the protocol conversion module is used for converting various non-standardized load interfaces into unified and standardized interfaces so as to support effective communication and data exchange between the load module and the comprehensive processing module. Based on the design ideas of comprehensive modularization, bus interconnection and interface standardization, all functional modules of an existing unmanned aerial vehicle electronic system are designed in a centralized and integrated mode, and the multipurpose unmanned aerial vehicle electronic system with high integration and interface standardization is formed.

The invention discloses an aircraft avionics system fault diagnosis method and system, relates to the technical field of avionics system fault detection, and is used for solving the technical problems that in the prior art, the extraction accuracy of avionics system fault features is low, and complex fault modes cannot be effectively recognized. The invention discloses an aircraft avionics system fault diagnosis method. The aircraft avionics system fault diagnosis method comprises the following steps: improving a Transform model to obtain a multi-scale frequency attention Transform model; the multi-scale frequency attention Transform model is integrated with a multi-scale frequency attention mechanism in a Transform encoder framework of the multi-scale frequency attention Transform model; in the training stage, aircraft avionics system fault information vectors are obtained to form a training sample set; the method comprises the following steps of: training a multi-scale frequency attention Transform model to obtain a trained multi-scale frequency attention Transform model; in the application stage, aircraft avionics system information is input into the trained multi-scale frequency attention Transform model, and fault information of an aircraft avionics system is output.

The invention discloses a flight parameter loading method based on software internal data acquisition, belongs to the technical field of airborne avionics, and aims at the problems of limited data acquisition flexibility, low resource utilization efficiency and difficulty in problem positioning. A detailed parameter recording instruction is set on a TIDE software interface, the TIDE software encapsulates the instruction into a request packet and sends the request packet to the FDR software, the FDR software verifies and analyzes the request packet and stores the request packet in a temporary storage area, the FDR software reencapsulates request information into a request packet conforming to an IVOS software receiving format and forwards the request packet to the IVOS software, and the IVOS software receives the request packet and sends the request packet to the TIDE software. Carrying out integrity verification on the data packet; through cooperative work of the IVOS software module, the FDR software module and the TIDE software module, key data related to research and development tests can be accurately collected, research and development personnel do not need to blindly find useful information in mass data, and the data processing and analysis efficiency is greatly improved.

Disclosed are methods, systems, and one or more computer-readable mediums for receiving, at an edge device from an external server, a rules database comprising a set of rules; receiving, by the edge device, first data from at least one device; processing, by the edge device, the received first data by comparing the received data to each rule among the set of rules; identifying a first triggering event in response to detecting a match between the received data and a rule of the rules database; and outputting an alert corresponding to the first triggering event.

The invention relates to the technical field of avionics and flight control, in particular to a multi-source fusion avionics control system and method, a multi-source acquisition and compression module synchronously acquires inertial measurement, star sensor and radar data under a unified time reference, and generates observation data through random projection compression; the fusion twinning module obtains a fusion state and a hypergraph based on compressed observation data, generates pneumatic, electromagnetic and structural twinning environments in real time on a shared three-dimensional grid through physical constraint diffusion, and outputs a registration result by adopting entropy regularization optimal transmission; the decision execution module maps discrete control variables quantified by a flight control computer into an Isinus model, obtains control sequence seeds through quantum annealing, generates a decision instruction through pulse sinus strategy network optimization, issues the decision instruction to a control execution unit to generate control execution data, and updates a hypergraph in combination with execution feedback for next cycle use. According to the method, the attitude estimation precision and the control robustness under the conditions of high maneuverability and strong interference are improved.

The invention provides a nickel-zinc ferrite material as well as a preparation method and application thereof. The nickel-zinc ferrite material comprises main components and auxiliary components, the main components comprise 65.8 to 67.8 wt% of Fe2O3, 6.8 to 7.5 wt% of NiO, 16.5 to 17 wt% of ZnO and 6.2 to 8.5 wt% of CuO, and the auxiliary components comprise Bi2O3, MgO and nano SiO2, and the main components comprise the following components in percentage by mass: 65.8 to 67.8 wt% of Fe2O3, 6.8 to 7.5 wt% of NiO, 16.5 to 17 wt% of ZnO and 6.2 to 8.5 wt% of CuO. The nickel-zinc ferrite material has the excellent performance of high frequency, low power consumption and high Tc, the problem of high loss of the nickel-zinc ferrite material under the high-frequency condition is solved, the output stability applicability of the inductor at the high frequency is improved, and the nickel-zinc ferrite material can be applied to the fields of avionics, automotive electronics and communication electronics.

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 relates to the technical field of unbalanced data processing, in particular to an oversampling method, system and device for avionics equipment test data and a medium, and the method comprises the steps: dividing original avionics equipment test data into minority class samples and majority class samples; respectively clustering the two types of samples by using a density peak value clustering algorithm, redistributing a new label according to a cluster to which each sample belongs, removing noise samples, and combining into a new unbalanced training set; constructing a sample generation model, and training the sample generation model with the new unbalanced training set until the sample generation model is converged to an equilibrium state; and determining the number of new and minority class samples required to be generated, and inputting the minority class samples in the new unbalanced training set into the trained sample generation model to obtain the required number of new and minority class samples. The method can highly fit and approach the real distribution of minority samples, enhance the comprehensiveness, diversity and fidelity of the generated samples, and effectively improve the performance of the sample generation model.

The invention relates to the technical field of natural resource saving, in particular to a construction project land-saving optimization method and system oriented to resource saving and efficient utilization, and provides a three-level index case library construction and dynamic weight matching technology. The method comprises the following steps: firstly, performing multi-level classification on historical cases based on industry types, regional conditions and construction scales, and extracting standardized land use data (L), unit capacity (E) and land saving effects (S) to construct a case library; secondly, dynamically allocating weight coefficients of industries, regions and scales through an analytic hierarchy process (AHP), calculating case similarity in combination with a weighted Euclidean distance, and accurately screening matched cases; according to the method, the land use nuclear reduction rate reaches 26.48% in projects such as a Minjiang old wood hole avionics hub project, and the intensive utilization level of land resources is remarkably improved.

Provided in the present invention are a knowledge model-driven avionics fault reasoning method, a medium, and a device. The method comprises: building an entity extraction model, constructing an entity extraction data set, and using the entity extraction data set to train the entity extraction model; building a semantic similarity calculation model, constructing a semantic similarity calculation data set, and using the semantic similarity calculation data set to train the semantic similarity calculation model; inputting a fault description text into the entity extraction model and extracting entity information; processing the extracted entity information to generate a new fault description text; and using the semantic similarity calculation model to perform similarity calculation on the fault description text and a plurality of standard fault modes in a corresponding faulty module so as to obtain a fault reasoning result. The present invention improves the maintenance success rate and efficiency of maintenance personnel, reduces the factory return rate of modules, improves the response efficiency of battlefield equipment, and has great significance and value.

The present invention relates to the field of fault self-diagnosis technology, and in particular to a method and system for self-diagnosis of faults in an avionics system. The method comprises the following steps: dynamically sampling fault modules of an avionics system, and performing temporal data association between monitoring modules to generate temporal association data between modules; modeling module time-varying causal relationships based on temporal association data between modules to generate causal network data between modules; performing fault confidence calculation using the causal network data between modules to obtain fault location confidence data; performing intelligent fault diagnosis processing on the avionics system using the fault location confidence data to generate system fault self-diagnosis report data. The present invention realizes rapid positioning and intelligent diagnosis of fault modules by tracing the fault propagation path, and significantly improves the diagnostic accuracy and fault handling efficiency for the intelligent control system integration of the avionics system, thereby ensuring the efficient and safe operation of the avionics system.

A method for separating avionics charts into a plurality of display panels is disclosed. The method may include receiving chart data for a virtual avionics chart. The method may include determining whether the received chart data exceeds a predetermined threshold. The method may include generating a plurality of display panels if the received chart data exceeds the predetermined threshold. The method may include determining one or more buffer lengths for the generated plurality of display panels. The method may include generating a plurality of output files based on the generated plurality of display panels and the determined one or more buffer lengths.

A method and system for detecting foreign object debris (FOD) from an UAV is disclosed herein. The UAV comprises avionics, an airframe, a location sensor, an attitude sensor, an intelligent payload comprising an edge processor capable of executing a machine learning model, at least one gimballed camera sensor, a data connection to the UAV avionics, and a data connection to a ground based data center.

The invention provides a comprehensive display device based on an FPGA (Field Programmable Gate Array) and double-ARM processor architecture, and relates to the field of avionics, which is characterized in that flight attitude data of a target aircraft are firstly collected and transmitted to a first ARM processor through an MIPI (Mobile Industry Processor Interface), the data are preprocessed by the first ARM processor and then stored in an input buffer area of a double-port shared memory, and the input buffer area is used for storing the data into a second ARM processor; then the FPGA chip reads the preprocessed data from the input buffer area to generate a flight attitude indication image, the flight attitude indication image is written into the output buffer area, the second ARM processor reads the attitude indication image from the output buffer area, the attitude indication image and the navigation image are subjected to image synthesis based on semantic feature interaction to obtain a synthesized flight display image, the synthesized flight display image is stored in a display frame buffer area, and finally, the flight display image is displayed. And reading the synthesized image from the display frame buffer region, and transmitting the synthesized image to a multifunctional display screen of a cockpit for display through an LVDS interface. Therefore, more efficient, accurate and reliable flight information display can be realized.

The invention discloses an EVTOL aircraft and a flight control electronic system thereof, and relates to the technical field of aircrafts. The flight control electronic system comprises a plurality of cockpit interface modules and a flight control computer; the inputs of the plurality of cockpit interfaces are respectively in communication connection with the airborne driving control system; the outputs of the plurality of cockpit interfaces are respectively in communication connection with at least one flight control computer; the input of each flight control computer is in communication connection with the airborne avionics system and / or the air-ground data link system, and the output of each flight control computer is connected with the actuator; the flight control computer receives instructions from the cockpit interface module and / or the airborne avionics system and / or the air-ground data chain system, outputs control signals through the flight control computer, and controls the actuator to act according to the control signals. The system can be adapted to aircrafts with various safety targets, and is adapted to human driving and unmanned driving configurations, the repeated design of one aircraft and one system is abandoned, the development cost is reduced, and the development period is shortened.

The invention belongs to the technical field of airborne equipment, and provides a general frequency conversion VPX module, which comprises a local oscillator source, a transmitting frequency conversion channel and a receiving frequency conversion channel, and is characterized in that the local oscillator source is used for generating a fixed dot frequency local oscillator LO3, a frequency hopping source local oscillator signal LO2 and a frequency hopping source local oscillator signal LO1; the transmitting frequency conversion channel is used for combining transmitting intermediate-frequency inputs with different bandwidths and signals generated by the local oscillator source, and performing up-conversion to generate radio-frequency signals for output; and the receiving frequency conversion channel is used for combining the radio frequency signal with the signal generated by the local oscillator source, performing down-conversion to generate an intermediate frequency signal, and outputting the intermediate frequency signal according to a corresponding bandwidth. Based on the general frequency conversion VPX module provided by the invention, adaptive function adjustment can be carried out according to different requirements of the avionics system, so that the frequency conversion module resources can realize the effects of resource standardization, universalization, reconfigurability and low comprehensive cost in the next generation of airborne avionics system.

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.