8 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.

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 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.

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 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 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.