A comprehensive test system suitable for an airborne PHM system

Abstract

The application provides a comprehensive test system suitable for an airborne PHM system, and belongs to the technical field of test of the airborne PHM system.The comprehensive test system comprises a comprehensive test main control device, a fault injector, a region general-purpose signal exciter, a ground display control tester, an airborne display control tester and a data monitor.The comprehensive test system can realize synchronous or asynchronous program-controlled operation of a test device, meets the test demand of system comprehensive fault injection, designs an interactive environment meeting airborne and ground operation, meets the test verification based on actual operation and management and maintenance of an aircraft, provides comprehensive verification capability for the test of the airborne PHM system, realizes comprehensive test verification of the airborne PHM system of a complex aircraft, can meet the test and troubleshooting demand of the PHM system in the development stage and even the test and service stage, solves the problem that the development of the PHM system lacks a special test environment, and improves the development efficiency and quality of the PHM system.

Description

Technical Field

[0001] This invention belongs to the field of airborne PHM system testing technology, and specifically relates to a comprehensive testing system suitable for airborne PHM systems. Background Technology

[0002] Ground testing and verification is a crucial aspect of developing airborne PHM (Prognostics and Health Management) systems. The content of ground testing and verification varies depending on the stage of PHM system development. For example, the detailed design phase primarily involves functional testing of the PHM system; the prototype testing phase focuses on fault injection and cross-linking tests; and the flight test and service phase primarily involves troubleshooting and upgrades. Different stages typically require the construction of corresponding test systems to support the PHM system's testing and verification efforts. However, currently, almost all aircraft PHM systems lack complete and dedicated test systems. PHM system testing and verification are conducted using the test environments of other systems, often resulting in insufficient verification and uncontrollable development cycles. Summary of the Invention

[0003] The purpose of this invention is to provide a comprehensive testing system suitable for airborne PHM systems to solve or mitigate at least one of the problems in the prior art.

[0004] The technical solution of the present invention is: a comprehensive test system suitable for airborne PHM system, comprising: a comprehensive test main control device, a fault injector, a regional universal signal exciter, a ground display control tester, an airborne display control tester, and a data monitor;

[0005] The integrated test main control device is connected to the fault injector, the regional universal signal exciter, the ground display control tester, the airborne display control tester, and the data monitor, respectively. It is used to carry out integrated control and scheduling of the test equipment based on the test process, and to perform test operations according to the test process.

[0006] The fault injector has regional and system adaptation capabilities, and is used to perform fault injection operations based on the electrical layer, protocol layer, and application layer for regional systems and airborne PHM systems, respectively.

[0007] The area-wide universal signal exciter is used to provide a signal excitation that is universal across multiple aircraft models based on the fault injection operation of the fault injector, thereby enabling access support for specific airborne areas or airborne equipment 300.

[0008] The ground display control test apparatus is used to provide an airborne PHM system information interaction and display control environment consistent with the ground PHM environment, so as to realize the test simulation of the ground-side display control and information interaction environment;

[0009] The airborne display control tester is used to provide an airborne PHM system information interaction and display control environment consistent with the onboard PHM environment, so as to realize the test simulation of the airborne display control and information interaction environment;

[0010] The data monitor is used to monitor test process data in real time, including test process data between the fault injector and the airborne PHM system, test process data between the fault injector and the area universal signal exciter, test process data between the airborne PHM system and the airborne display control tester, and real-time process data between the airborne PHM system and the ground display control tester.

[0011] In a preferred embodiment of the present invention, the fault injector is a general-purpose fault injection device based on a first bus. The type or quantity of fault signals injected by the fault injector can be configured and adjusted as needed, and the signal type configured by the general-purpose signal exciter in the coverage area is also included.

[0012] In a preferred embodiment of the present invention, the regional universal signal exciter provides universal modular signal excitation based on a second bus. The signals include airborne bus signals, analog signals, and digital signals. Different configurations of signal excitation are achieved by loading different second bus boards, thereby realizing the construction of universal signal excitation for multiple aircraft models.

[0013] In a preferred embodiment of the present invention, the regional universal signal exciter is configured as an avionics region PHM exciter, an electromechanical region PHM exciter, a power region PHM exciter, and a flight control and flight management region PHM exciter according to the division of PHM member systems. The excitation signal provided by the corresponding regional exciter is consistent with the signal provided by each PHM member system to the PHM system.

[0014] In a preferred embodiment of the present invention, the data monitor monitors the test process data in real time through bus monitoring or signal monitoring.

[0015] The integrated test system of this invention can realize synchronous or asynchronous programmed operation of the test equipment, meet the construction requirements of the peripheral signals of the airborne PHM system, support universal configuration to meet the test and access operation of different aircraft types, regions, and equipment components, support fault injection with full signal coverage, meet the test requirements of comprehensive system fault injection, and is designed to meet the interactive environment of airborne and ground operation, meet the test verification of aircraft based on actual operation and management and maintenance processes, provide comprehensive verification capabilities for the test of airborne PHM systems, realize the integrated test verification of complex aircraft airborne PHM systems, meet the test and troubleshooting requirements of PHM systems in the development stage and even the flight test and service stage, solve the problem of lack of dedicated test environment in PHM system development, and improve the development efficiency and quality of PHM systems. Attached Figure Description

[0016] To more clearly illustrate the technical solution provided by the present invention, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention.

[0017] Figure 1 This is a schematic diagram of a comprehensive test system applicable to airborne PHM systems. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0019] To address the problems raised in the background art, this invention provides a comprehensive test system suitable for airborne PHM systems. This system can meet the testing and troubleshooting needs of PHM systems during the development and even flight test and service phases, solve the problem of lacking a dedicated test environment during the development of PHM systems, improve the development efficiency and quality of PHM systems, and promote continuous product maturation.

[0020] like Figure 1 As shown, the integrated test system 100 for airborne PHM systems provided by the present invention includes: an integrated test main control device 101, a fault injector 102, a regional universal signal exciter 103, a ground display control tester 104, an airborne display control tester 105, and a data monitor 106. The integrated test environment is composed of these devices, and by constructing an environment that conforms to the real airborne hardware and software interaction information and equipment environment, the system requirements for the integrated test environment of the airborne PHM system 200 are met. Furthermore, the system provides test methods and operations according to the integrated test process, thereby realizing the integrated test verification of the airborne PHM system 200.

[0021] The integrated test main control device 101 is connected to the fault injector 102, the area-wide universal signal exciter 103, the ground display control tester 104, the airborne display control tester 105, and the data monitor 106, respectively. It can perform synchronous or asynchronous programmable control operations on the fault injector 102, the area-wide universal signal exciter 103, the ground display control tester 104, the airborne display control tester 105, and the data monitor 106. The integrated test main control device 101 performs integrated control and scheduling of the tested equipment based on the test process, and provides test operations such as PHM test planning, PHM test design, PHM test execution, and PHM test analysis according to the test process.

[0022] The fault injector 102 is a general-purpose fault injection device based on the LXI bus. The type or number of fault signals injected by the fault injector 102 can be flexibly configured and adjusted as needed, and it covers the signal types configured by the area general-purpose signal exciter 103. The fault injector 102 has area adaptation and system adaptation, and is used to carry out fault injection operations based on the electrical layer, protocol layer, and application layer for the area system and the airborne PHM system 200, respectively. The fault injection signal types that the fault injector 102 can provide cover all signal types of the airborne PHM system 200 and its member systems, and it can support fault injection configuration switching.

[0023] The area-wide universal signal exciter 103 provides universal modular signal excitation based on the PXI bus, supporting mainstream airborne signals such as general airborne buses, analog signals, and digital signals. It also supports customized configurations for different aircraft models, allowing for differentiated signal excitation configurations by loading different PXI boards. This enables the construction of a universal signal excitation system for multiple aircraft models, while also supporting adaptation to specific areas or devices, achieving access support for specific airborne areas or airborne devices 300. In this invention, the area-wide universal signal exciter 103 is configured as an avionics area PHM exciter, an electromechanical area PHM exciter, a power area PHM exciter, and a flight control and flight management area PHM exciter according to the PHM member system division. Furthermore, the excitation signals provided by the corresponding area exciter are consistent with the signals provided to the PHM system by each member system.

[0024] The ground display control test apparatus 104 is used to provide an airborne PHM system information interaction and display control environment consistent with the ground PHM environment, and to realize the test simulation of the ground-side display control and information interaction environment.

[0025] The airborne display control tester 105 provides an airborne PHM system information interaction and display control environment consistent with the onboard PHM environment. It enables PHM system display control operations through manual touch control, simulating the airborne display control and information interaction environment. In this invention, the adapter interface between the airborne display control tester 105 and the PHM system is consistent with the actual interface. Furthermore, the human-machine interface of the airborne display control tester 105 is consistent with the actual display and operation interface of the PHM system.

[0026] The data monitor 106 monitors the test process data in real time via bus monitoring or signal monitoring, including real-time process data between the fault injector 102 and the airborne PHM system 200, between the fault injector 102 and the area universal signal exciter 103, between the airborne PHM system 200 and the airborne display control tester 105, and between the airborne PHM system 200 and the ground display control tester 104. The data monitor 106 has real-time data storage capability and can directly store the raw data of the real-time process data by link and by time period. In this invention, the type and number of external cross-link interfaces of the data monitor 106 are consistent with the cross-link interfaces of the PHM system and member systems.

[0027] This invention addresses the needs of airborne PHM systems in the design and development process, including health management function design, fault diagnosis model design, data analysis method design, state monitoring and prediction design, as well as the experimental verification and iterative optimization of corresponding functions. It constructs a comprehensive test environment consisting of a comprehensive test main control device 101, a regional universal signal exciter 103, a fault injector 102, a data monitor 106, an airborne display control tester 105, and a ground display control tester 104. This comprehensive test environment can provide signal interfaces and signal input / output interactions consistent with the airborne PHM system, constructing the same hardware and software conditions as after airborne installation, and maximally replicating the system's actual working conditions. This integrated test system can realize synchronous or asynchronous programmed operation of the test equipment, meet the construction requirements of the peripheral signals of the airborne PHM system, support universal configuration to meet the testing and access operations of different aircraft types, regions, and equipment components, support fault injection with full signal coverage, meet the test requirements of comprehensive system fault injection, and is designed to meet the interactive environment of airborne and ground operations. It meets the test verification of aircraft based on actual operation and management and maintenance processes, provides comprehensive verification capabilities for the testing of airborne PHM systems, realizes the comprehensive test verification of complex aircraft airborne PHM systems, and can meet the testing and troubleshooting needs of PHM systems in the development stage and even the flight test and service stage. It solves the problem of lack of dedicated test environment in PHM system development and improves the development efficiency and quality of PHM systems.

[0028] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A comprehensive test system suitable for airborne PHM systems, characterized in that, include: The integrated test main control device (101), fault injector (102), regional universal signal exciter (103), ground display control tester (104), airborne display control tester (105) and data monitor (106). The integrated test main control device (101) is connected to the fault injector (102), the regional universal signal exciter (103), the ground display control tester (104), the airborne display control tester (105), and the data monitor (106) respectively. It is used to carry out integrated control and scheduling of the test equipment based on the test process, and to perform test operations according to the test process. The fault injector (102) has regional adaptation and system adaptation, and is used to carry out fault injection operations based on the electrical layer, protocol layer and application layer for regional systems and airborne PHM systems (200) respectively. The area-wide universal signal exciter (103) is used to provide a multi-model universal signal excitation according to the fault injection operation of the fault injector (102), so as to realize access support for specific airborne areas or airborne equipment 300. The ground display control test apparatus (104) is used to provide an airborne PHM system information interaction and display control environment consistent with the ground PHM environment, and to realize the test simulation of the ground-side display control and information interaction environment; The airborne display control tester (105) is used to provide an airborne PHM system information interaction and display control environment consistent with the airborne PHM environment, and to realize the test simulation of the airborne display control and information interaction environment. The data monitor (106) is used to monitor the test process data in real time, including the test process data between the fault injector (102) and the airborne PHM system (200), the test process data between the fault injector (102) and the area universal signal exciter (103), the test process data between the airborne PHM system (200) and the airborne display control tester (105), and the real-time process data between the airborne PHM system (200) and the ground display control tester (104).

2. The integrated test system for airborne PHM systems as described in claim 1, characterized in that, The fault injector (102) is a general-purpose fault injection device based on the first bus. The type or number of fault signals injected by the fault injector (102) can be configured and adjusted as needed, and the signal type configured by the general-purpose signal exciter (103) of the coverage area can be used.

3. The integrated test system for airborne PHM systems as described in claim 2, characterized in that, The regional universal signal exciter (103) provides universal modular signal excitation based on the second bus. The signals include airborne bus signals, analog signals, and digital signals. Different configurations of signal excitation are achieved by loading different second bus boards, thus realizing the construction of universal signal excitation for multiple models.

4. The integrated test system for airborne PHM systems as described in claim 3, characterized in that, The regional universal signal exciter (103) is configured as an avionics region PHM exciter, an electromechanical region PHM exciter, a power region PHM exciter, and a flight control and flight management region PHM exciter according to the division of PHM member systems. The excitation signal provided by the corresponding regional exciter is consistent with the signal provided by each PHM member system to the PHM system.

5. The integrated test system for airborne PHM systems as described in claim 4, characterized in that, The data monitor (106) monitors the test process data in real time through bus monitoring or signal monitoring.

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