19 results about "Integrated modular avionics" patented technology

The invention relates to an LLM-based comprehensive modular avionics system resource allocation method and system, and the method comprises the steps: removing a universal semantic module through model pruning, taking an IMA configuration description material as a training corpus, forming a lightweight IMA exclusive large language model which is finely adjusted by the training corpus, collecting a user natural language, analyzing a configuration interaction instruction of the user, and carrying out the resource allocation of the user. And then the configuration interpretation model / configuration generation model is called to execute interpretation and change tasks, so that natural language interaction of resource configuration of the integrated modular avionics system is realized on the basis of ensuring functional integrity, and the change cost of resource configuration is obviously reduced. Compared with the prior art, the method has the advantages that the lightweight LLM is trained and deployed in combination with avionics field knowledge, efficient deployment of the model is realized, and the accuracy of semantic understanding of the model in professional scenes in the avionics field is enhanced.

The application discloses a system for controlling an auxiliary power unit of an aircraft to perform an automatic start operation in the air, characterized by comprising: an auxiliary power unit (APU) for providing an air source and a power source for the aircraft; an integrated modular avionic system (IMA) for receiving an emergency state signal and an operating state signal associated with the aircraft, and generating an APU auto-start signal according to a preset decision logic based at least in part on the emergency state signal and the operating state signal; and the APU controller is in communication connection with the IMA and is used for controlling the APU to execute an automatic starting operation after receiving the APU automatic starting signal. A method for controlling an auxiliary power plant (APU) of an aircraft to perform an autostart operation in the air, as well as numerous other aspects, is also disclosed.

The invention discloses a model-based civil aircraft integrated modular avionics resident system design method. The method comprises the steps of S1, resident system demand modeling and demand confirmation based on a customized MBSE method; s2, performing resident application software function logic modeling based on a Simulink model; s3, performing qualitative security analysis on the resident system based on the function scene and the fault combination; the input of the step S1 comes from a technical protocol of a resident system issued by a host, and through modeling iteration, the demand of the resident system is captured and issued to the step S2; s2, feeding back a system design problem identified in the modeling process; the step S1 synchronously sends the demand of the resident system to the step S3, and at the same time, the step S3 feeds back the identified security demand and constraint to the step S1 to support system demand iteration. According to the invention, an efficient, replicable and landing design thought is provided for the integrated modular avionics residence system, the system design efficiency is improved, and the verification cost is reduced.

A cockpit display system for an aircraft including an off-board graphics rendering gateway system providing additional cockpit display and other functionality. The cockpit display system includes a cockpit display subsystem having a display, a subsystem processor and integrated modular avionics (IMA) with user applications and cockpit display software. The cockpit display system also includes an off-board processor for processing aircraft functionality applications that are not available on the cockpit display subsystem, where the off-board processor provides graphical data over fiber optics to the cockpit display subsystem to be displayed by the cockpit display subsystem. The off-board processor includes a graphics gateway sub-processor that is in communication with the cockpit display subsystem, where the graphics gateway sub-processor exchanges data and information with the cockpit display subsystem over Ethernet cables to provide synchronization with the graphical data provided by the off-board processor to the cockpit display subsystem.

The invention relates to a computing system (1) with a plurality of avionics computers (5) for an aircraft (3), wherein the computing system (1) assigns volatile partitions to the avionics computers (5), which partitions are started in response to a respective trigger signal and terminated by their respective generation of a current return value, wherein the computing system (1) has a respective memory for a volatile partition assigned to the respective memory, which can be written to and / or read from the respective volatile partition and serves to keep at least one return value of the return variable and / or a value of a defined partition state variable of the volatile partition assigned to the memory stored at least for a predetermined time.

This invention discloses a model-based design method for a modular avionics-based resident system for civil aircraft, comprising: S1, resident system requirement modeling and requirement verification based on a customized MBSE method; S2, resident application software functional logic modeling based on a Simulink model; and S3, resident system qualitative safety analysis based on functional scenarios and fault combinations. The input to step S1 comes from the resident system's technical protocol issued by the host. Through iterative modeling, the resident system's requirements are captured and sent to step S2. Step S2 provides feedback on system design issues identified during the modeling process. Step S1 simultaneously sends the resident system's requirements to step S3, while step S3 feeds back the identified safety requirements and constraints to step S1 to support system requirement iteration. This invention provides an efficient, replicable, and implementable design approach for modular avionics-based resident systems, improving system design efficiency and reducing verification costs.

The present invention belongs to the field of integrated avionics technology, specifically to a method for managing the status of platform components within an integrated modular avionics system. This invention proposes a design concept in which a universal processing module serves as a central management component. This universal processing module, acting as the central management component, is responsible for receiving external inputs, calculating system-level status, and distributing this system-level status to switches and remote data interface units within the integrated modular avionics system. This universal processing module calculates the system-level status and distributes this unique system-level status to other components, resolving the issue of asynchronous and disorganized initialization of various platform components.

The invention provides a CCAR-25 aircraft-oriented comprehensive modular avionics platform conformity verification method, which comprises the following steps of: accessing a modular hardware platform architecture into a system integration verification platform, and carrying out hardware cross-linking and software deployment; testing is executed step by step according to a configuration integration testing-path testing-platform service testing-robustness testing four-level conformity verification system, and testing results are recorded; s2, judging whether all the test results pass or not, if the test results do not pass, issuing a problem report according to a quality problem processing method, performing targeted optimization according to a root cause analysis result, and executing S2 again; if all the test data and the problem return-to-zero report pass, verifying the closed loop to form a verification document containing the test data and the problem return-to-zero report. The compatibility and maintainability of the system are improved through modular design, the requirement of airworthiness clauses is ensured to be met through a full-dimension verification system, and the method is suitable for the design and airworthiness verification process of a CCAR-25 transportation type aircraft comprehensive modular avionics platform.

The present invention provides a method for safety management of basic equipment of an integrated modular avionics system, which relates to the field of integrated avionics technology, including: Instance 1 and Instance 2 for basic equipment health management are powered on separately and start arbitration, and the master instance and the slave instance are determined by the start arbitration, wherein the instance 1 and the instance 2 determine each other's current status by obtaining the heartbeat message published by the other party; the master instance and the slave instance perform post-start arbitration in real time to determine whether to switch the master-slave status; the slave instance reports its current status to the master instance by publishing heartbeat information, and the master instance reports the functional status of all basic equipment in the entire cabinet to the health management platform. The present invention ensures that a robust and guaranteed basic equipment health management service is provided for the platform-level health management function by switching between master and slave instances in abnormal scenarios.

The invention relates to a computing system (1) for executing software applications in aircraft (3), said computing system (1) being designed to use volatile partitions for an at least temporal resource allocation of one or more computing processes to physical resources available in the computing system (1). Each of the volatile partitions is started by a trigger signal and is ended in response to the generation, by means of the partition, of a current return value for a return variable which is the same for each execution of a plurality of sequential executions such that each of the volatile partitions is restarted at a plurality of points in time over a continuous runtime of the computing system (1) and is ended again after the calculated return value of the partition has been output.

A cockpit display system for an aircraft including an off-board graphics rendering gateway system providing additional cockpit display and other functionality. The cockpit display system includes a cockpit display subsystem having a display, a subsystem processor and integrated modular avionics (IMA) with user applications and cockpit display software. The cockpit display system also includes an off-board processor for processing aircraft functionality applications that are not available on the cockpit display subsystem, where the off-board processor provides graphical data over fiber optics to the cockpit display subsystem to be displayed by the cockpit display subsystem. The off-board processor includes a graphics gateway sub-processor that is in communication with the cockpit display subsystem, where the graphics gateway sub-processor exchanges data and information with the cockpit display subsystem over Ethernet cables to provide synchronization with the graphical data provided by the off-board processor to the cockpit display subsystem.

A cockpit display system for an aircraft including an off-board graphics rendering gateway system providing additional cockpit display and other functionality. The cockpit display system includes a cockpit display subsystem having a display, a subsystem processor and integrated modular avionics (IMA) with user applications and cockpit display software. The cockpit display system also includes an off-board processor for processing aircraft functionality applications that are not available on the cockpit display subsystem, where the off-board processor provides graphical data over fiber optics to the cockpit display subsystem to be displayed by the cockpit display subsystem. The off-board processor includes a graphics gateway sub-processor that is in communication with the cockpit display subsystem, where the graphics gateway sub-processor exchanges data and information with the cockpit display subsystem over Ethernet cables to provide synchronization with the graphical data provided by the off-board processor to the cockpit display subsystem.

The invention relates to a computing system (1) for executing software applications in an aircraft (3), wherein the computing system (1) is designed to use volatile partitions for at least temporal resource allocation of one or more computing processes to physical resources available in the computing system (1), wherein a respective one of the volatile partitions is started by a trigger signal and is terminated upon its generation of a current return value of a return variable that is the same for each execution of a plurality of sequential executions, so that over a contiguous runtime of the computing system (1), a respective one of the volatile partitions is restarted at a plurality of times and is terminated again after its calculated return value has been output.

The invention relates to a computing system (1) having a plurality of avionics computers (5) for aircraft (3). The computing system (1) assigns volatile partitions to the avionics computers (5), each partition being started in response to a respective trigger signal and being ended by the generation, by means of the respective partition, of a current return value, and the computing system (1) has a respective storage unit for a volatile partition associated with the respective storage unit, which can be written and / or read by the respective volatile partition and which is used to keep at least one return value for the return variable and / or a value for a defined partition state variable of the volatile partition associated with the storage unit stored at least for a specified duration.

A real-time computer network application in the aeronautic industry for in-flight reconfiguring of the integrated modular avionics modules onboard aircraft, via spatial and temporal partitioning of modules conforming a data processing system including a computer-implemented method for in-flight Integrated Modular Avionics reconfiguration, a data processing system for the mentioned reconfiguration, a computer program product and a computer-readable medium, both to perform such reconfiguration.

The application discloses a kind of determination method, device, computer equipment and storage medium of equipment failure rate, related to aviation technology field, for determining the failure rate of each equipment in integrated modular avionics system.The main technical scheme of the application is: according to the importance value, complexity value, maintenance value, test value of each device type in integrated modular avionics system, the distribution failure rate of each device type is determined;The device type with the distribution failure rate less than the corresponding estimated failure rate is determined as the target device type;According to the importance value, cost value, time value, quality value of the target device type, the distribution failure rate and the corresponding estimated failure rate, the failure rate of the target device type is redetermined.

The present invention belongs to the general technical field of airborne integrated modular avionics, and particularly relates to a method for automatically detecting a robust IMA master-slave distributed configuration item. The method includes: Step 1: After the IMA is powered on on the ground or the ground hardware reset signal is valid, or after the data loading is completed, the master node of the configuration management function confirms the consistency between the currently installed aircraft model and the system configuration file; Step 2: When the currently installed aircraft model is consistent with the system configuration file, the master node of the configuration management function distributes the aircraft model information to the slave nodes of the IMA configuration management function, and the slave nodes of the IMA configuration management function perform automatic detection of the IMA configuration items; Step 3: After the slave nodes complete the automatic detection of the IMA configuration items, they report the detection results to the master node. This not only ensures the correctness of the IMA configuration items but also enhances the robustness of the IMA configuration management.

The application discloses a comprehensive modular avionics system, a data transmission method, an aircraft and a readable storage medium. The comprehensive modular avionics system in the application can simultaneously process operation instructions input by a crew through a heterogeneous processing module, a first avionics core resource module and a second avionics core resource module, obtain respective corresponding processing results, and compare the respective corresponding processing results. Since the hardware bases of the first avionics core resource module and the second avionics core resource module are different, the probability of simultaneous processing errors is low. Therefore, if the comparison result is that the processing result of the first avionics core resource module matches the processing result of the second avionics core resource module, it is indicated that the processing of the operation instruction is not wrong. The situation of error response due to the fact that the processing of each avionics core resource module is wrong due to the common mode problem when the same hardware structure is used for calculation in the traditional method is avoided.