CN-122018480-A - Method for verifying compliance of integrated modularized avionics platform for CCAR-25 airplane

CN122018480ACN 122018480 ACN122018480 ACN 122018480ACN-122018480-A

Abstract

The invention provides a compliance verification method of a comprehensive modularized avionics platform for a CCAR-25 aircraft, which comprises the steps of accessing a modularized hardware platform architecture into a system integration verification platform for hardware crosslinking and software deployment, executing tests step by step according to a configuration integration test-path test-platform service test-robustness test four-level compliance verification system and recording test results, judging whether the test results are all passed, giving a problem report according to a quality problem processing method if the test results are not passed, carrying out targeted optimization according to a root cause analysis result, executing S2 again, and forming a verification document containing test data and a problem return-to-zero report if all passed verification closed loops. The compatibility and maintainability of the system are improved through the modularized design, the requirements of the aviation clause are met through a full-dimension verification system, and the system is suitable for the design and aviation verification process of the CCAR-25 transportation type aircraft comprehensive modularized avionics platform.

Inventors

LUAN JIANZE
DING HAN
WANG JIALIANG
ZHANG HE
HOU XIAOMEI
Gao Zengcheng
XU YUSONG
FU LIANG
LIU YISHAN

Assignees

中国航空无线电电子研究所

Dates

Publication Date: 20260512
Application Date: 20251227

Claims (8)

1. The method for verifying the compliance of the integrated modularized avionics platform facing the CCAR-25 aircraft is characterized by comprising the following steps of: s1, accessing a modularized hardware platform architecture into a system integration verification platform to perform hardware cross-linking and software deployment; The modularized hardware platform framework comprises a first core processing unit, a second core processing unit, a first remote data interface unit, a second remote data interface unit, a third remote data interface unit, a fourth remote data interface unit, a first external switch and a second external switch; S2, performing testing step by step according to a four-level compliance verification system of configuration integration testing, path testing, platform service testing and robustness testing, and recording a testing result; The system comprises a partition scheduling compliance test, a data conversion logic correctness test, an ARINC664 network connectivity test, a path test, a platform service test, a robustness test and a system stability and environment adaptability test, wherein the partition scheduling compliance test is used for verifying partition scheduling compliance, the data conversion logic correctness and ARINC664 network connectivity; s3, judging whether the test results are all passed or not, if the test results are not passed, giving a problem report according to a quality problem processing method, performing targeted optimization according to root cause analysis results, and executing S2 again, and if the test results are all passed, verifying a closed loop to form a verification document containing test data and a problem return-to-zero report.
2. The method for verifying compliance of a CCAR-25 aircraft-oriented integrated modular avionics platform of claim 1, wherein the core processing unit integrates a first general purpose processing module, a second general purpose processing module, a third general purpose processing module, and a fourth general purpose processing module, the first general purpose processing module, the second general purpose processing module, the third general purpose processing module, and the fourth general purpose processing module are provided with programmable logic, an ARINC664 network end system, and initial boot software, support division computation of ARINC653 specifications, and allocate independent operating resources for resident applications.
3. The method for verifying compliance of a CCAR-25 aircraft-oriented comprehensive modular avionics platform of claim 2, wherein the first general purpose processing module is populated with primary avionics applications, the second general purpose processing module is populated with secondary avionics applications, the third general purpose processing module is populated with tertiary avionics applications, and the fourth general purpose processing module is populated with quaternary avionics applications.
4. The method for verifying the compliance of a comprehensive modularized avionics platform for a CCAR-25 aircraft according to claim 3, wherein the first-level avionics application software, the second-level avionics application software, the third-level avionics application software and the fourth-level avionics application software are divided according to development security levels of different avionics applications, so that hardware-level isolation of the avionics application software with different development security levels among different general processing modules is realized, and partition-level isolation of avionics applications with the same development security level on the same general processing module is realized.
5. The method for verifying compliance of a CCAR-25 aircraft-oriented integrated modular avionics platform of claim 1, wherein the modular software architecture adapted to the modular hardware platform architecture comprises a configuration software layer and an operational software layer.
6. The method for verifying compliance of a CCAR-25 aircraft-oriented integrated modular avionics platform of claim 5, wherein the configuration software layer comprises core processing unit configuration software, remote data interface unit configuration software, and external switch configuration software for defining hardware interface mapping rules, data conversion logic, and ARINC664 network communication parameters; The operation software layer comprises core processing unit operation software, remote data interface unit operation software and external switch operation software, and is used for realizing a data calculation function, a data conversion function and a data transmission function.
7. The method for verifying compliance of a CCAR-25 aircraft-oriented integrated modular avionics platform of claim 1, wherein the remote data interface unit is configured to carry programmable logic and ARINC664 network side systems to provide bi-directional conversion capabilities for ARINC429, ARINC664, ARINC717, discrete and analog data.
8. The method for verifying compliance of a CCAR-25 aircraft-oriented integrated modular avionics platform of claim 1, wherein accessing a modular hardware platform architecture to a system integrated verification platform for hardware cross-linking and software deployment comprises: accessing a first core processing unit, a second core processing unit, a first remote data interface unit, a second remote data interface unit, a third remote data interface unit, a fourth remote data interface unit, a first external switch and a second external switch to a system integration verification platform; loading core processing unit configuration software and core processing unit operation software to the first core processing unit and the second core processing unit through ARINC615A protocol; loading remote data interface unit configuration software and remote data interface unit operation software to the first remote data interface unit, the second remote data interface unit, the third remote data interface unit and the fourth remote data interface unit through ARINC615A protocol; And loading external switch configuration software and external switch operation software to the first external switch and the second external switch through an ARINC615A protocol.

Description

Method for verifying compliance of integrated modularized avionics platform for CCAR-25 airplane Technical Field The invention belongs to the technical field of comprehensive avionics, and particularly relates to a method for verifying compliance of a comprehensive modularized avionics platform for a CCAR-25 aircraft. Background With the continuous rise of requirements of civil air transportation on aircraft safety, economy and maintainability, avionics systems have evolved from discrete architectures with one-to-one correspondence between traditional functions and hardware, gradually toward integrated, modular Integrated and Modular (IMA) platform architectures. The IMA platform realizes resource sharing by integrating multiple avionics functions through a standardized hardware module, becomes the main development direction of the current aircraft avionics system, but a key technical barrier still exists when the strict navigability requirements of the CCAR-25 part are adapted. The hardware architecture level, the core processing unit integrates only 1-2 general processing modules and does not follow ARINC653 partition specifications to realize resource isolation, or the module function division does not match the real-time level of different avionics applications, so that key applications are easy to be interfered, the software architecture level, the configuration function and the operation function are in deep coupling, the configuration software layer and the operation software layer are not explicitly divided, so that the hardware module replacement or parameter adjustment needs to be carried out on the whole software system, the maintenance period is obviously prolonged, the maintenance cost is greatly increased, a custom loading protocol is adopted, the ARINC615A avionics loading standard is not compatible, the compatibility with an airborne maintenance system and ground assurance equipment is poor, the compliance verification level is lack of a complete compliance verification system, the coverage range is incomplete, when the test fails, an unexplained complete closed-loop mechanism is caused, similar problems repeatedly appear, the defects directly cause the fact that the existing IMA platform cannot pass through CCAR-25 airworthiness inspection, the CCAR-25 type plane developed autonomously has high dependence on an imported IMA platform, meanwhile, the system has a long period, and has extreme flying safety hidden trouble in the environment. Therefore, there is a need for an IMA platform compliance verification method that accurately matches the requirements of CCAR-25 for airworthiness, and can solve the above technical problems, so as to support the autonomous development and airworthiness approval of such an aircraft avionics system. Disclosure of Invention The invention provides a method for verifying the compliance of a comprehensive modularized avionics platform for a CCAR-25 aircraft, which ensures that an IMA platform meets the requirements of the CCAR-25 on system redundancy, reliability, environmental suitability and verification traceability and supports autonomous research and development and navigability approval of a transportation civil aircraft avionics system. The invention provides a method for verifying the compliance of a comprehensive modularized avionics platform facing a CCAR-25 plane, which comprises the following steps: s1, accessing a modularized hardware platform architecture into a system integration verification platform to perform hardware cross-linking and software deployment; The modularized hardware platform framework comprises a first core processing unit, a second core processing unit, a first remote data interface unit, a second remote data interface unit, a third remote data interface unit, a fourth remote data interface unit, a first external switch and a second external switch; S2, performing testing step by step according to a four-level compliance verification system of configuration integration testing, path testing, platform service testing and robustness testing, and recording a testing result; The system comprises a partition scheduling compliance test, a data conversion logic correctness test, an ARINC664 network connectivity test, a path test, a platform service test, a robustness test and a system stability and environment adaptability test, wherein the partition scheduling compliance test is used for verifying partition scheduling compliance, the data conversion logic correctness and ARINC664 network connectivity; s3, judging whether the test results are all passed or not, if the test results are not passed, giving a problem report according to a quality problem processing method, performing targeted optimization according to root cause analysis results, and executing S2 again, and if the test results are all passed, verifying a closed loop to form a verification document containing test data and a problem return-to-zero report. Optionally, the c