Helicopter avionics system in-situ detection equipment design and application method

Abstract

The invention provides a helicopter avionics system in-situ detection equipment design method which comprises the following steps: constructing an avionics system testability model, and determining in-situ test items based on a D matrix analysis and diagnosis model, testing information in the avionics system testability model is output as a testing description document of the ATML standard, and the testing description document is compiled into a signal-oriented testing code; carrying out secondary packaging on the minimum resources; meanwhile, the invention further provides an application method of the helicopter avionics system in-situ detection equipment. The ATML standard and the IVI technology are adopted, automatic generation of the test program and instrument drive development and configuration of the detection equipment are achieved, and the problems that the test requirement is not clear, test codes are needed, drive development and debugging are time-consuming, instrument drive interchangeability of the detection equipment is poor, and onboard detection operation of the avionics system is complex are solved.

Description

Technical Field

[0001] The present application belongs to the technical field of electronic system testing, and in particular, relates to a design and application method of in-situ detection equipment for helicopter avionics systems. Background Art

[0002] The helicopter avionics system in-situ detection equipment is an important support equipment under the two-level maintenance system of helicopters, providing users with a convenient and effective means of maintenance support during field maintenance. When maintenance personnel conduct inspections or maintenance work on helicopters, they can use the in-situ detection equipment to quickly detect and locate faults without disassembling the onboard equipment.

[0003] At present, the research and development of in-situ detection equipment for helicopter avionics systems uses the test requirement documents (TRD) provided by various airborne equipment manufacturers as design input to carry out the architecture design, instrument selection, test program (TP) and driver program packaging, and debugging of the detection equipment.

[0004] The main problems in this mode are as follows: 1) The quality of the test requirement documents provided by the manufacturer is difficult to control, which is manifested in the non-standard description of test signals, incomplete failure modes, unclear test logic, etc., resulting in the need for on-site detection equipment developers to spend a lot of time sorting out test signals, test logic, and failure modes to determine the instrument resources of the detection equipment; 2) The test requirements between avionics subsystems are unclear, and the test items are bloated, resulting in a waste of detection equipment and instrument resources; 3) The avionics system signal cross-linking is complex, there are many test items, and the development and debugging of test programs is time-consuming and labor-intensive, and the quality is difficult to ensure; 4) The instrument driver has poor interchangeability after secondary packaging, and the instrument replacement of the subsequent detection equipment requires repackaging of the driver; 5) The on-board detection operation of the avionics system is complicated, and the accessibility of the measurement points is poor. Summary of the invention

[0005] Purpose of the invention: The present invention can clarify the in-situ test requirements of the avionics system, adopt the ATML standard and IVI technology, realize the automatic generation of test programs and the development and configuration of instrument drivers for detection equipment, and solve the problems of unclear test requirements, time-consuming development and debugging of test codes and drivers, poor interchangeability of instrument drivers for detection equipment, complicated on-board detection operations of avionics systems, and poor accessibility of measurement points.

[0006] In a first aspect, the present application provides a method for designing an in-situ detection device for a helicopter avionics system, the method comprising the following steps:

[0007] Step 1: Build an avionics system testability model, determine the in-situ test items based on the D matrix analysis and diagnosis model, and then determine the minimum resources required for the in-situ detection equipment:

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

[0009] Step 3: re-encapsulate the minimized resources, compile a capability description file of the minimized resources based on the signal library, and configure it.

[0010] Preferably, the step 1 comprises:

[0011] According to the FMECA, interface control files, and external signal cross-linking diagram files of each LRU of the avionics system, conduct measurement point analysis on each LRU testability model;

[0012] Import each LRU testability model through TADS testability modeling software, and add the signal cross-linking relationship between each LRU according to the avionics system signal cross-linking diagram to complete the avionics system testability model design;

[0013] Based on the D-matrix analysis model, the undetected fault set and fuzzy group set at LRU level are used as the input of in-situ test 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 testability model, configure in-situ test items and the test signal types, number of channels, and test criteria they contain in the test points, and achieve full coverage of the failure modes in the undetected fault set and fuzzy group set;

[0016] Based on the in-situ test items in the model, the minimized in-situ test requirements can be determined, and the architectural design, instrument models and quantity of the in-situ detection equipment can be further clarified.

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

[0018] Preferably, the undetected fault set and the fuzzy group set are classified and managed to establish a signal library, including:

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

[0020] Preferably, step 2 comprises:

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

[0022] Output the in-situ test items and loading signal information in the model into an XML test description document that complies with the ATML standard through the testability 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 pins is performed.

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

[0025] Preferably, the step 3 comprises:

[0026] Based on the IVI-COM standard, with the signal as the interface, the instrument underlying driver is repackaged into a dynamic library file using VC software;

[0027] According to the signal library file in the avionics system testability model, establish the instrument signal capability model and write the driver capability description file;

[0028] Deploy the dynamic library file and driver capability description file to the test equipment and configure them through the automatic test software.

[0029] In a second aspect, the present application also provides an application method of an in-situ detection device for a helicopter avionics system, the method comprising:

[0030] Based on the minimum in-situ test requirements, determine the measurement points, analyze the mapping relationship between the measurement points and the diagnostic requirements, and determine the onboard avionics equipment and location to which the measurement points belong;

[0031] 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 operations;

[0032] Analyze the electrical interface form of the avionics measurement point and determine the operational requirements involved in the interface connection architecture;

[0033] Determine the resource operation requirements of the in-situ detection equipment in combination with the resource allocation results of the in-situ detection equipment;

[0034] Encode and configure on-machine inspection operation procedures in the in-situ inspection equipment.

[0035] Beneficial technical effects of this application:

[0036] The present invention clarifies the need to minimize detection equipment resources by constructing a system-level testability model and analyzing and determining the in-situ test requirements, realizes the automatic generation of signal-oriented test codes from the testability model, improves the portability of the test code and the interchangeability of the instrument through the IVI technology, optimizes the poor accessibility of the on-board detection operation of the avionics system based on the design of the measurement point, and improves the field support capability of the in-situ detection equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1It is a schematic diagram of the in-situ detection equipment design method provided in an embodiment of the present application. DETAILED DESCRIPTION

[0038] See also Figure 1 The present invention designs a method for designing in-situ detection equipment for helicopter avionics systems. Based on this method, the in-situ test requirements of the avionics system can be clarified. The ATML standard and IVI technology are used to realize the automatic generation of test programs and the development and configuration of instrument drivers for detection equipment, solving the problems of unclear test requirements, time-consuming development and debugging of test codes and drivers, poor interchangeability of instrument drivers for detection equipment, complicated on-board detection operations for avionics systems, and poor accessibility of measurement points.

[0039] The present invention performs test point analysis on the testability model of each LRU in the avionics system, increases the signal cross-linking relationship, and forms a system-level testability model; performs testability analysis on the system-level model based on the D matrix to determine the in-situ test points and test items, clarifies the minimized in-situ test requirements and the types of signals, number of channels, precision, etc. involved, and performs classification management after integration to further determine the architecture design and instrument model of the in-situ detection equipment; at the same time, the model test information is generated into an XML test description document and a fault diagnosis strategy that conforms to the ATML standard; the XML document is compiled into a test code through the SAX technology, and the automatic generation of signal TP is realized; the in-situ detection equipment instrument driver is secondary packaged based on the IVI-COM standard, and the driver configuration is performed, so as to solve the problem that the driver needs to be repackaged when the detection equipment instrument is replaced in the later stage, and the interchangeability of the detection equipment instrument is improved; based on the measurement points determined by the minimum in-situ test requirements, the on-board detection operation process is designed to solve the problem of poor accessibility of the measurement points.

[0040] In an embodiment of the present application, a method for designing an in-situ detection device for a helicopter avionics system based on a testability model is provided, comprising the following steps:

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

[0042] Step 1.1: According to the FMECA, interface control files, external signal cross-linking diagrams and other files of each LRU of the avionics system, conduct measurement point analysis on each LRU testability model, including failure mode type, port information, signal direction, etc.;

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

[0044] Step 1.3: Analyze the undetected fault set and fuzzy group set at the LRU level in the D matrix model as the input of the in-situ test requirements;

[0045] Step 1.4: Classify and manage the types, number of channels, and attribute parameters of the signals included in the undetected fault set and fuzzy group set, and establish a signal library;

[0046] Step 1.5: Add in-situ test points to the testability model, configure in-situ test items and the test signal types, number of channels, test criteria, etc. contained in the test points, to achieve full coverage of the failure 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, and further clarify the architectural design, instrument model and quantity of the in-situ detection equipment.

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

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

[0050] Step 2.2: Output the in-situ test items and loading signal information in the model into an XML test description document that complies with the ATML standard through the testability modeling software;

[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 pins.

[0052] Step 3: Re-encapsulate the instrument driver determined in step 1; write the capability description file of the instrument driver based on the signal library and configure it.

[0053] Step 3.1: Based on the IVI-COM standard, using the signal as the interface, use VC software to re-encapsulate the instrument's underlying driver into a dynamic library file;

[0054] Step 3.2: According to the signal library file in the avionics system testability model, establish the instrument signal capability model and write the driver capability description file;

[0055] Step 3.3: Deploy the dynamic library file and driver capability description file to the test device and configure them through the automatic test software.

[0056] Step 4: Design the on-machine inspection operation process based on the minimum in-situ test requirements and the determined test points

[0057] Step 4.1: Based on the measurement points determined by the minimum in-situ test requirements, analyze the mapping relationship between the measurement points and the 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 form of the avionics measurement point and determine the operational requirements involved in the interface connection architecture;

[0060] Step 4.4: Determine the resource operation requirements of the in-situ detection equipment in combination with the resource allocation results of the in-situ detection equipment;

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

[0062] The present invention clarifies the need to minimize detection equipment resources by constructing a system-level testability model and analyzing and determining the in-situ test requirements, realizes the automatic generation of signal-oriented test codes from the testability model, improves the portability of the test code and the interchangeability of the instrument through the IVI technology, optimizes the poor accessibility of the on-board detection operation of the avionics system based on the design of the measurement point, and improves the field support capability of the in-situ detection equipment.

Claims

1. A method for designing an in-situ detection device for a helicopter avionics system, characterized in that: The method comprises the following steps: Step 1: Build an avionics system testability model, determine the in-situ test items based on the D matrix analysis and diagnosis model, and then determine the minimum resources required for the in-situ detection equipment: Step 2: Output the test information in the avionics system testability model as a test description document in the ATML standard, and compile the test description document into a signal-oriented test code; Step 3: re-encapsulate the minimized resources, compile a capability description file of the minimized resources based on the signal library, and configure it.

2. The method according to claim 1, characterized in that The step 1 comprises: According to the FMECA, interface control files, and external signal cross-linking diagram files of each LRU of the avionics system, conduct measurement point analysis on each LRU testability model; Import each LRU testability model through TADS testability modeling software, and add the signal cross-linking relationship between each LRU according to the avionics system signal cross-linking diagram to complete the avionics system testability model design; Based on the D-matrix analysis model, the undetected fault set and fuzzy group set at LRU level are used as the input of in-situ test requirements; Classify and manage undetected fault sets and fuzzy group sets, and establish a signal library; Add in-situ test points to the testability model, configure in-situ test items and the test signal types, number of channels, and test criteria they contain in the test points, and achieve full coverage of the failure modes in the undetected fault set and fuzzy group set; Based on the in-situ test items in the model, the minimized in-situ test requirements can be determined, and the architectural design, instrument models and quantity of the in-situ detection equipment can be further clarified.

3. The method according to claim 2, characterized in that The measurement point analysis includes the type of fault mode, port information, and signal direction.

4. The method according to claim 3, characterized in that The undetected fault set and fuzzy group set are classified and managed to establish a signal library, including: The types of signals, number of channels, and attribute parameters contained in the undetected fault set and fuzzy group set are integrated and classified and managed to establish a signal library.

5. The method according to claim 4, characterized in that The step 2 comprises: Inject the load signals and parameters required for the test into the established test model and add them to the signal library; match the injection points with the corresponding ports in the model; Output the in-situ test items and loading signal information in the model into an XML test description document that complies with the ATML standard through the testability 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 pins is performed.

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

7. The method according to claim 6, characterized in that The step 3 comprises: Based on the IVI-COM standard, with the signal as the interface, the instrument underlying driver is repackaged into a dynamic library file using VC software; According to the signal library file in the avionics system testability model, establish the instrument signal capability model and write the driver capability description file; Deploy the dynamic library file and driver capability description file to the test equipment and configure them through the automatic test software.

8. An application method of an in-situ detection device for a helicopter avionics system, characterized in that: The method comprises: Based on the minimum in-situ test requirements, determine the measurement points, analyze the mapping relationship between the measurement points and the diagnostic requirements, and determine the onboard avionics equipment and location to which the measurement points belong; 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 operations; Analyze the electrical interface form of the avionics measurement point and determine the operational requirements involved in the interface connection architecture; Determine the resource operation requirements of the in-situ detection equipment in combination with the resource allocation results of the in-situ detection equipment; and encode and configure the on-machine detection operation process in the in-situ detection equipment.

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