Design and application method of helicopter avionics system in-situ detection equipment

Abstract

The application provides a design method of a helicopter avionics system in-situ detection device, comprising the following steps: constructing an avionics system testability model, determining in-situ test items based on a D-matrix analysis diagnosis model, and then determining the minimum resources required by the in-situ detection device; outputting test information in the avionics system testability model as a test description document in an ATML standard, and compiling the test description document into a signal-oriented test code; and performing secondary packaging on the minimum resources; meanwhile, the application also provides an application method of the helicopter avionics system in-situ detection device; the application adopts the ATML standard and IVI technology, realizes automatic generation of a test program and instrument driver development and configuration of a detection device, and solves the problems of unclear test requirements, long time consumption of test code, driver development and debugging, poor interchangeability of instrument drivers of the detection device, and complicated on-board detection operation of the avionics system.

Description

Technical Field

[0001] This application belongs to the field of electronic system testing technology, and in particular relates to the design and application method of an in-situ testing device for helicopter avionics systems. Background Technology

[0002] In-situ testing equipment for helicopter avionics systems is a crucial support device under the two-tiered maintenance system for helicopters, providing users with a convenient and effective means of maintenance support during field operations. When maintenance personnel conduct inspections or maintenance work on helicopters, they can perform rapid testing and fault location using in-situ testing equipment without disassembling onboard equipment.

[0003] Currently, the development of in-situ testing equipment for helicopter avionics systems uses the Test Requirements Documents (TRDs) provided by various airborne equipment manufacturers as design inputs to carry out the architecture design, instrument selection, test program (TP) and driver packaging, and debugging of the testing equipment.

[0004] The main problems under this model are as follows: 1) The quality of the test requirements documents provided by the manufacturer is difficult to control, which is reflected in the non-standard description of test signals, incomplete fault modes, and unclear test logic. This requires the developers of the on-site testing equipment to spend a lot of time sorting out the test signals, test logic, and fault modes in order to determine the instrument resources of the testing equipment; 2) The test requirements between the various subsystems of avionics are unclear, and the test items are bloated, resulting in a waste of instrument resources of the testing equipment; 3) The signal interconnection of the avionics system is complex, and there are many test items. The development and debugging of test programs are time-consuming, laborious, and the quality is difficult to guarantee; 4) The interchangeability of the instrument driver after secondary packaging is poor. The driver needs to be repackaged when the instrument of the testing equipment is replaced later; 5) The on-board testing operation of the avionics system is complicated and the accessibility of the test points is poor. Summary of the Invention

[0005] Purpose of the invention: This invention clarifies the in-situ testing requirements of avionics systems. By adopting the ATML standard and IVI technology, it enables the automatic generation of test procedures and the development and configuration of instrument drivers for testing equipment. This solves problems such as unclear test requirements, time-consuming test code and driver development and debugging, poor interchangeability of instrument drivers for testing equipment, complicated on-board testing operations for avionics systems, and poor accessibility of test points.

[0006] In a first aspect, this application provides a design method for in-situ testing equipment for helicopter avionics systems, the method comprising the following steps:

[0007] Step 1: Construct a testability model for the avionics system, determine in-situ test items based on the D-matrix analysis and diagnostic model, and then determine the minimum resources required for in-situ testing equipment:

[0008] Step 2: Output the test information in the avionics system testability model as an ATML standard test description document, and compile the test description document into signal-oriented test code;

[0009] Step 3: Perform secondary encapsulation on the minimized resources, write a capability description file for the minimized resources based on the signal library, and configure it.

[0010] Preferably, step 1 includes:

[0011] Based on the FMECA, interface control documents, and external signal cross-linking diagrams of each LRU in the avionics system, test point analysis was performed on the test model of each LRU.

[0012] Import the test models of each LRU into the TADS test modeling software, and add the signal cross-linking relationship between each LRU according to the avionics system signal cross-linking diagram to complete the design of the avionics system test model.

[0013] The LRU-level set of undetected faults and the fuzzy group set in the D matrix analysis model are used as inputs for in-situ testing requirements.

[0014] Classify and manage undetected fault sets and fuzzy group sets, and establish a signal library;

[0015] Add in-situ test points to the test model, and configure in-situ test items and their included test signal types, number of channels, and test criteria in the test points to achieve full coverage of fault modes in the undetected fault set and the fuzzy group set.

[0016] Based on the in-situ test items in the model, the minimum in-situ test requirements are determined, which further clarifies the architecture design, instrument model, and quantity of in-situ testing equipment.

[0017] Preferably, the measurement point analysis includes fault mode type, port information, and signal flow.

[0018] Preferably, the step of classifying and managing the undetected fault set and fuzzy group set to establish a signal library includes:

[0019] The types, number of channels, and attribute parameters of signals contained in the undetected fault set and the fuzzy group set are integrated and classified for management, and a signal library is established.

[0020] Preferably, step 2 includes:

[0021] Inject the required loading signals and parameters into the established test model and add them to the signal library; map the injection points to the corresponding ports in the model;

[0022] The in-situ test items and loaded signal information in the model are output as XML test description documents conforming to the ATML standard through test modeling software.

[0023] Based on SAX technology, the XML test description document is compiled into signal-oriented test code, and the connection configuration between the model port and the LRU physical pin is performed.

[0024] Preferably, the loading signals and parameters include analog excitation and bus excitation.

[0025] Preferably, step 3 includes:

[0026] Based on the IVI-COM standard, using signals as the interface, the instrument's low-level driver is repackaged into a dynamic library file using VC software;

[0027] Based on the signal library files in the avionics system test model, establish an instrument signal capability model and write a drive capability description file;

[0028] The dynamic library files and driver capability description files are deployed to the testing device and configured through automated testing software.

[0029] Secondly, this application also provides a method for applying in-situ testing equipment for helicopter avionics systems, the method comprising:

[0030] Based on the minimum in-situ testing requirements, the measurement points are determined, the mapping relationship between the measurement points and diagnostic requirements is analyzed, and the onboard avionics equipment and location to which the measurement points belong are determined.

[0031] Analyze the electrical characteristics of the avionics equipment measurement points to determine the detection or monitoring methods to be used, as well as the requirements for onboard operation;

[0032] Analyze the electrical interface forms of avionics measurement points to determine the operational requirements involved in the interface connection architecture;

[0033] Based on the resource allocation results of the in-situ testing equipment, determine the resource operation requirements of the in-situ testing equipment;

[0034] The coding configuration process for on-site testing is carried out in the in-situ testing equipment.

[0035] The beneficial technical effects of this application are as follows:

[0036] This invention constructs a system-level testability model and analyzes and determines in-situ testing requirements, clarifies the minimum requirements for testing equipment resources, realizes the automatic generation of signal-oriented test codes from the testability model, improves the portability of test codes and the interchangeability of instruments through IVI technology, optimizes poor accessibility for on-board testing operations of avionics systems based on the design of test points, and enhances the field support capability of in-situ testing equipment. Attached Figure Description

[0037] Figure 1This is a schematic diagram of the design method for the in-situ detection equipment provided in the embodiments of this application. Detailed Implementation

[0038] Please see Figure 1 This invention presents a design method for in-situ testing equipment for helicopter avionics systems. Based on this method, the in-situ testing requirements of the avionics system can be clearly defined. Employing the ATML standard and IVI technology, the method enables the automatic generation of test programs and the development and configuration of instrument drivers for the testing equipment. This solves problems such as unclear test requirements, time-consuming test code and driver development and debugging, poor interchangeability of instrument drivers for testing equipment, complex on-board testing operations for avionics systems, and poor accessibility of test points.

[0039] This invention analyzes the test points of each LRU in the avionics system to increase signal cross-linking relationships and construct a system-level test model. Based on the D-matrix, it performs test analysis on the system-level model to determine in-situ test points and test items, clarifying the minimum in-situ test requirements and their associated signal types, channel numbers, and accuracy. These are then integrated and categorized for further determination of the architecture design and instrument models of the in-situ testing equipment. Simultaneously, it generates XML test description documents and fault diagnosis strategies conforming to the ATML standard from the model test information. Using SAX technology, the XML documents are compiled into test code, enabling automatic generation of signal-oriented test points (TPs). Based on the IVI-COM standard, the in-situ testing equipment instrument drivers are repackaged and configured, solving the problem of needing to repackage drivers when replacing testing equipment and improving the interchangeability of testing equipment. Based on the test points determined by the minimum in-situ test requirements, an onboard testing operation process is designed to address the problem of poor test point accessibility.

[0040] In this application embodiment, a design method for an in-situ testing device for a helicopter avionics system based on a test model is provided, comprising the following steps:

[0041] Step 1: Construct a testability model for the avionics system, determine in-situ test items based on D-matrix analysis, and then determine the minimum resources required for in-situ testing equipment:

[0042] Step 1.1: Based on the FMECA, interface control documents, external signal crosstalk diagrams, and other documents of each LRU in the avionics system, perform test point analysis on each LRU test model, including fault mode types, port information, signal flow, etc.

[0043] Step 1.2: Import the test models of each LRU into the TADS test modeling software, and add the signal cross-linking relationship between each LRU according to the avionics system signal cross-linking diagram to complete the design of the avionics system test model;

[0044] Step 1.3: Based on the LRU level undetected fault set and fuzzy group set in the D matrix analysis model, use them as input for in-situ testing requirements;

[0045] Step 1.4: After integrating the types, number of channels, and attribute parameters of signals contained in the undetected fault set and the fuzzy group set, classify and manage them to establish a signal library;

[0046] Step 1.5: Add in-situ test points to the test model, and configure in-situ test items and their included test signal types, number of channels, test criteria, etc. in the test points to achieve full coverage of fault modes in the undetected fault set and fuzzy group set;

[0047] Step 1.6: Based on the in-situ test items in the model, determine the minimum in-situ test requirements, which can further clarify the architecture design, instrument model and quantity of the in-situ testing equipment.

[0048] Step 2: Output the test information from the avionics system testability model established in Step 1 as an ATML standard test description document; compile the test description document into signal-oriented test code.

[0049] Step 2.1: Inject the load signals and parameters required for testing, such as analog excitation and bus excitation, into the test model established in Step 1, and add them to the signal library; map the injection points to the corresponding ports in the model;

[0050] Step 2.2: Use test modeling software to output the in-situ test items and loaded signal information in the model as an XML test description document conforming to the ATML standard;

[0051] Step 2.3: Based on SAX technology, compile the XML test description document into signal-oriented test code, and configure the connection between the model port and the LRU physical pin.

[0052] Step 3: Perform secondary encapsulation of the instrument driver determined in Step 1; write and configure the capability description file of the instrument driver based on the signal library.

[0053] Step 3.1: Based on the IVI-COM standard, using signals as the interface, use VC software to repackage the instrument's low-level driver into a dynamic library file;

[0054] Step 3.2: Based on the signal library files in the avionics system test model, establish the instrument signal capability model and write the drive capability description file;

[0055] Step 3.3: Deploy the dynamic library files and driver capability description files to the testing device and configure them through the automated testing software.

[0056] Step 4: Based on the minimum in-situ testing requirements and the determined test points, design the on-machine testing operation procedure.

[0057] Step 4.1: Based on the minimum in-situ testing requirements, determine the measurement points, analyze the mapping relationship between the measurement points and diagnostic requirements, and determine the onboard avionics equipment and location to which the measurement points belong;

[0058] Step 4.2: Analyze the electrical characteristics of the avionics equipment measurement points to determine the detection or monitoring method to be used, as well as the requirements for onboard operation;

[0059] Step 4.3: Analyze the electrical interface type of the avionics measurement points and determine the operational requirements involved in the interface connection architecture;

[0060] Step 4.4: Based on the resource allocation results of the in-situ testing equipment, determine the resource operation requirements of the in-situ testing equipment;

[0061] Step 4.5: Encode and configure the on-machine testing operation process in the in-situ testing equipment.

[0062] This invention constructs a system-level testability model and analyzes and determines in-situ testing requirements, clarifies the minimum requirements for testing equipment resources, realizes the automatic generation of signal-oriented test codes from the testability model, improves the portability of test codes and the interchangeability of instruments through IVI technology, optimizes poor accessibility for on-board testing operations of avionics systems based on the design of test points, and enhances the field support capability of in-situ testing equipment.

Claims

1. A design method for in-situ testing equipment for helicopter avionics systems, characterized in that, The design method includes the following steps: Step 1: Construct a testability model for the avionics system, determine in-situ test items based on the D-matrix analysis and diagnostic model, and then determine the minimum resources required for in-situ testing equipment; Step 1 includes: Based on the FMECA, interface control documents, and external signal cross-linking diagrams of each LRU in the avionics system, test point analysis was performed on the test model of each LRU. Import the test models of each LRU into the TADS test modeling software, and add the signal cross-linking relationship between each LRU according to the avionics system signal cross-linking diagram to complete the design of the avionics system test model. The LRU-level set of undetected faults and the fuzzy group set in the D matrix analysis model are used as inputs for in-situ testing requirements. Classify and manage undetected fault sets and fuzzy group sets, and establish a signal library; Add in-situ test points to the test model, and configure in-situ test items and their included test signal types, number of channels, and test criteria in the test points to achieve full coverage of fault modes in the undetected fault set and the fuzzy group set. Based on the in-situ test items in the model, the minimum in-situ test requirements are determined, which can further clarify the architecture design, instrument model and quantity of in-situ testing equipment; Step 2: Output the test information in the avionics system testability model as an ATML standard test description document, and compile the test description document into signal-oriented test code; Step 3: Perform secondary encapsulation on the minimized resources, write a driving capability description file for the minimized resources based on the signal library, and configure it based on the automatic testing software.

2. The design method according to claim 1, characterized in that, The measurement point analysis includes fault mode types, port information, and signal flow.

3. The design method according to claim 2, characterized in that, The classification and management of undetected fault sets and fuzzy group sets, and the establishment of a signal library, include: The types, number of channels, and attribute parameters of signals contained in the undetected fault set and the fuzzy group set are integrated and classified for management to establish a signal library.

4. The design method according to claim 3, characterized in that, Step 2 includes: Inject the required loading signals and parameters into the established test model and add them to the signal library; map the injection points to the corresponding ports in the model; The in-situ test items and loaded signal information in the model are output as XML test description documents conforming to the ATML standard through test modeling software. Based on SAX technology, the XML test description document is compiled into signal-oriented test code, and the connection configuration between the model port and the LRU physical pin is performed.

5. The design method according to claim 4, characterized in that, The loading signals and parameters include analog excitation and bus excitation.

6. A method for applying in-situ testing equipment for helicopter avionics systems, characterized in that, The application method is applied to the design method of in-situ testing equipment for helicopter avionics systems as described in any one of claims 1-5, and the application method includes: Based on the minimum in-situ testing requirements, the measurement points are determined, the mapping relationship between the measurement points and diagnostic requirements is analyzed, and the onboard avionics equipment and location to which the measurement points belong are determined. Analyze the electrical characteristics of the avionics equipment measurement points to determine the detection or monitoring methods to be used, as well as the requirements for onboard operation; Analyze the electrical interface forms of avionics measurement points to determine the operational requirements involved in the interface connection architecture; Based on the resource allocation results of the in-situ testing equipment, determine the resource operation requirements of the in-situ testing equipment; and encode and configure the on-machine testing operation process in the in-situ testing equipment.

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