A method for diagnosing compliance data of airborne equipment identification test

Abstract

The present invention relates to a method for diagnosing compliance data of an airborne equipment identification test. The method comprises: obtaining an output signal of a tested device according to an airborne equipment identification test; matching the output signal with an entryized signal definition, and setting a corresponding time threshold and amplitude threshold; collecting a real-time measurement value of the output signal in the airborne equipment identification test; taking an absolute value after subtracting the real-time measurement value from the corresponding expected value; comparing the absolute value with the amplitude threshold, and obtaining a delay count value; when the delay count value reaches the corresponding time threshold, determining it as a fault signal. The present invention can not only well balance the system safety and robustness requirements, accurately identify factors that affect or hinder the aircraft from continuing to fly or land safely, but also effectively avoid system false alarms by adopting a time threshold and amplitude threshold monitoring method during the identification test process.

Description

Technical Field

[0001] The embodiment of the present invention relates to the technical field of aviation engineering flight control data testing, and in particular to a method for diagnosing airborne equipment identification test compliance data. Background Art

[0002] Civil aircraft must pass strict airworthiness certification in accordance with airworthiness regulations before they can be put into operation. Currently, most domestic aircraft are subject to airworthiness review in accordance with CAAR Part 25 airworthiness standards. Aircraft manufacturers generally present "equipment qualification certification" for airborne equipment to demonstrate the equipment's compliance with clauses 1301 and 1309. Each supplier conducts equipment qualification certification through a large number of tests to demonstrate the compliance of airborne equipment with airworthiness clauses. The most critical part is to determine the typical environment that airborne equipment may encounter during its operation on board, such as its working characteristics when struck by external lightning or high radiation fields.

[0003] However, it is very difficult to accurately define the working characteristics of airborne equipment and obtain the approval of the authority during the identification test. The authority requires that when the equipment under test is placed in typical environmental conditions, the equipment must be able to operate reliably and stably, the tolerance of the equipment to external interference must be quantitatively described and judged, the faults in the test can be accurately identified and located, and the robustness of the equipment must also be considered, with a certain degree of fault tolerance.

[0004] Regarding the above technical solution, the inventors found that there are at least the following technical problems:

[0005] During the identification test process, the system safety and robustness requirements cannot be taken into account at the same time, and the factors that affect or hinder the aircraft's continued safe flight or landing cannot be accurately identified, and there will also be problems with system false alarms.

[0006] Therefore, it is necessary to improve one or more problems existing in the above-mentioned related technical solutions.

[0007] It should be noted that this section is intended to provide background or context for the technical solutions of the present invention stated in the claims. The description herein is not admitted to be prior art by inclusion in this section. Summary of the invention

[0008] The object of the present invention is to provide an airborne equipment identification test compliance data diagnosis method, thereby at least to a certain extent solving one or more of the above-mentioned problems caused by the limitations and defects of the relevant technology.

[0009] The present invention provides an airborne equipment identification test compliance data diagnosis method, comprising:

[0010] Obtaining output signals of the equipment under test according to the airborne equipment identification test;

[0011] Matching the output signal with the entryized signal definition, and setting the corresponding time threshold and amplitude threshold;

[0012] Collecting real-time measurement values ​​of the output signals in the airborne equipment identification test;

[0013] Subtract the real-time measured value from the corresponding expected value and take the absolute value;

[0014] Compare the absolute value with the amplitude threshold and obtain a delay count value;

[0015] When the delay count value reaches the corresponding time threshold, it is determined to be a fault signal.

[0016] Optionally, in the step of obtaining the output signal of the device under test according to the airborne device identification test:

[0017] The output signals include: discrete signals, VDT signals, BNR signals and control surface signals.

[0018] Optionally, the step of comparing the absolute value with the amplitude threshold and obtaining the delay count value includes:

[0019] When the absolute value is compared with the amplitude threshold, the delay count value is obtained by using increase and decrease proportional counting.

[0020] Optionally, when comparing the absolute value with the amplitude threshold, the step of obtaining the delay count value by using increase and decrease proportional counting includes:

[0021] When the absolute value exceeds the amplitude threshold, performing up-proportional counting;

[0022] When the absolute value is less than the amplitude threshold, a down-proportional count is triggered;

[0023] When the increase / decrease ratio count reaches the corresponding time threshold, it is determined to be a fault signal.

[0024] Optionally, when comparing the absolute value with the amplitude threshold, the step of obtaining the delay count value by using increase and decrease proportional counting includes:

[0025] The increase and decrease ratio count corresponding to the output signal is calculated according to the duration of the fluctuation after being stimulated by the external signal in the airborne equipment identification test.

[0026] Optionally, when comparing the absolute value with the amplitude threshold, the step of obtaining the delay count value by using increase and decrease proportional counting includes:

[0027] The increase and decrease ratio counts corresponding to the output signals are calculated according to different acquisition cycles of the output signals.

[0028] Optionally, the step of matching the output signal with the entry-based signal definition and setting the corresponding time threshold and amplitude threshold comprises:

[0029] The corresponding amplitude threshold is set according to the influence of the output signal on the device under test after being disturbed.

[0030] Optionally, the step of setting the corresponding amplitude threshold according to the influence of different output signals on the device under test after being disturbed includes:

[0031] Different output signals have corresponding amplitude thresholds set according to their respective percentages.

[0032] Optionally, in the step of matching the output signal with the entry-based signal definition and setting the corresponding time threshold and amplitude threshold:

[0033] The itemized signal definition includes: data packet name, signal name, signal carrier, signal type, operating mode, signal identification number, sub-identification number, signal word starting position, signal word ending position, bit starting position, bit ending position and resolution.

[0034] The technical solution provided by the present invention may include the following beneficial effects:

[0035] In the present invention, by adopting the time threshold and amplitude threshold monitoring method during the identification test process, it is possible to well take into account the system safety and robustness requirements, accurately identify the factors that affect or hinder the aircraft from continuing to fly or land safely, and effectively avoid system false alarms. BRIEF DESCRIPTION OF THE DRAWINGS

[0036] The accompanying drawings herein are incorporated into and constitute a part of the specification, illustrate embodiments consistent with the present invention, and together with the specification are used to explain the principles of the present invention. Obviously, the accompanying drawings described below are only some embodiments of the present invention, and for those of ordinary skill in the art, other accompanying drawings can be obtained based on these accompanying drawings without creative work.

[0037] Figure 1 A schematic flow chart showing a method for diagnosing airborne equipment identification test compliance data in an exemplary embodiment of the present invention;

[0038] Figure 2 A schematic diagram showing the decision logic of an airborne equipment identification test compliance data diagnosis method in an exemplary embodiment of the present invention is shown. DETAILED DESCRIPTION

[0039] Example embodiments will now be described more fully with reference to the accompanying drawings. However, example embodiments can be implemented in many forms and should not be construed as limited to the examples set forth herein; rather, these embodiments are provided so that the present invention will be more comprehensive and complete and fully convey the concepts of the example embodiments to those skilled in the art. The described features, structures, or characteristics may be combined in any suitable manner in one or more embodiments.

[0040] In addition, the accompanying drawings are only schematic illustrations of embodiments of the present invention and are not necessarily drawn to scale. The same reference numerals in the drawings represent the same or similar parts, and their repeated descriptions will be omitted. Some of the block diagrams shown in the accompanying drawings are functional entities and do not necessarily correspond to physically or logically independent entities.

[0041] The present invention provides an airborne equipment identification test compliance data diagnosis method, referring to Figure 1 As shown in , the following steps are included:

[0042] Step S100: obtaining the output signal of the device under test according to the airborne device identification test.

[0043] Step S200: matching the output signal with the entryized signal definition, and setting the corresponding time threshold and amplitude threshold.

[0044] Step S300: collecting the real-time measurement value of the output signal in the airborne equipment identification test.

[0045] Step S400: subtract the real-time measurement value from the corresponding expected value and take the absolute value.

[0046] Step S500: Compare the absolute value with the amplitude threshold and obtain a delay count value.

[0047] Step S600: When the delay count value reaches the corresponding time threshold, it is determined to be a fault signal.

[0048] It is important to understand that during the equipment identification test, the equipment under test will be interconnected with the data acquisition system. The data acquisition system collects the output signals of the equipment under test in real time during the test. These output signals represent the various states of the equipment under test. The acquisition system makes real-time judgments on the output signals of the equipment according to the identification test data diagnostic method to determine the disturbance of the equipment under test during the test. The identification test data diagnostic method includes itemized signal definitions and data fault diagnosis with dual thresholds of time and amplitude. At the same time, the diagnostic method is defined as a standard file template to support the automated diagnosis of the test process, which can be used as a general reference for subsequent topics.

[0049] It is also necessary to understand that the data fault diagnosis method is mainly used for fault identification. By defining the content, signal faults can be reported in a timely manner. At the same time, the robustness of the system is also taken into account, allowing small disturbances of the signal within a certain range and time. The signal mainly includes: allowable deviation range, expected value (fixed value), amplitude threshold, increase count, decrease count, time threshold, maximum increase and decrease count, etc.

[0050] It is also necessary to understand that the device under test will fluctuate after being stimulated by external factors. When considering the tolerance of the device under test to external interference, it is necessary to comprehensively consider transient effects and system robustness, and accurately define the product's anti-interference ability. The first condition is that the fluctuation of the signal must meet the flight safety requirements and will not cause harm to the aircraft. Secondly, the interference cannot affect the flight quality and cannot have an adverse effect on the pilot's operation. Time and amplitude dual threshold monitoring are set in the judgment document. Only when the amplitude and time of the monitored object exceed the threshold, the fault is reported. According to the characteristics of the monitored object and the fault scenario, the monitoring threshold is reasonably set in the judgment criteria to achieve accurate capture and reasonable judgment of the time when the fault occurs. The amplitude threshold is used to identify the degree of fluctuation of the device after being disturbed, allowing the device to fluctuate within a certain range. If the threshold is exceeded, the device fault will be reported. The time threshold represents the length of the fluctuation time after the device is disturbed. A reasonable time threshold is designed to prevent frequent false alarms while meeting the timely reporting requirements.

[0051] It is also necessary to understand that comprehensive assessment and analysis of the characteristics of the equipment under test in the test environment will transform the traditional qualitative product diagnosis method into quantitative judgment, which can accurately identify faults during the test process and precisely locate the cause of the problem of the product under test, thus achieving efficient and accurate test process analysis and providing an effective method to demonstrate compliance to the authorities.

[0052] It is also necessary to understand that a good data diagnosis strategy is defined in this diagnostic method. Through dual threshold monitoring of time threshold and amplitude threshold, based on the impact on aircraft safety and flight quality, it takes into account the good robustness of the system and the ability to accurately identify and locate faults, and sets reasonable fault time threshold and amplitude threshold for the entry signal definition.

[0053] It is also important to understand that this diagnostic strategy has good versatility and can cover almost all types of data on civil aircraft, including hard wires and various data buses, such as 429, Avionics Full Duplex Switched Ethernet (AFDX), Service Integration Bus (SIB) and other data buses. The diagnostic strategy is embodied in the form of a criterion file, forming a standard identification test criterion file, which has great promotion significance.

[0054] It is also necessary to understand that civil aircraft need to carry out CCAR25-oriented conformity tests, among which the identification test to demonstrate equipment qualification is the key test for airworthiness certification to obtain approval from the authority. In the process of demonstrating equipment qualification, quantitatively determining the equipment status and providing sufficient and complete evidence materials are the key to obtaining approval from the authority. This application uses the designed quantitative itemized test data diagnostic method to demonstrate the qualification of airborne equipment. It is a method that has been approved by the authority and is of great significance for demonstrating equipment qualification for civil aircraft certification. Based on the design judgment method, a standard judgment document template was formed, which defines the key elements of signal characteristics and the judgment elements of data fault diagnosis, laying the foundation for supporting the automated diagnosis capability of the test process.

[0055] By adopting the above-mentioned airborne equipment identification test compliance data diagnosis method and using time threshold and amplitude threshold monitoring methods during the identification test, it is possible to not only take into account the system safety and robustness requirements, accurately identify factors that affect or hinder the aircraft's continued safe flight or landing, but also effectively avoid system false alarms.

[0056] Next, we will refer to Figure 1 to Figure 2 Each step of the above-mentioned airborne equipment identification test compliance data diagnosis method in this example embodiment is described in more detail.

[0057] In some embodiments, reference Figure 2 As shown in FIG. , in step S100:

[0058] The output signals include: discrete signals, voltage fluctuation (VDT, voltage detect) signals, binary number (BNR, Binary Number Representation) signals and control surface signals.

[0059] It is important to understand that discrete signals are core variables used to characterize the status of equipment; VDT signals are used to characterize the health status of sensors; the carrier of BNR signals is the digital bus; and control surface signals include parameters such as control instructions and motion strokes received by the aircraft's actuators, and are key characteristic parameters of the aircraft body.

[0060] In some embodiments, reference Figure 2 As shown in , step S500 includes:

[0061] Step S510: When comparing the absolute value with the amplitude threshold, an increase-decrease proportional counting is used to obtain a delay count value.

[0062] It should be understood that the time threshold uses an increase or decrease proportional count, rather than an absolute time constant, to determine the disturbance of the signal under the excitation field. The use of an increase or decrease proportional count method can effectively avoid missed reports and false alarms.

[0063] In some embodiments, reference Figure 2 As shown in , step S510 includes:

[0064] Step S511: when the absolute value exceeds the amplitude threshold, performing up-proportional counting;

[0065] Step S512: When the absolute value is less than the amplitude threshold, triggering a proportional count reduction;

[0066] Step S513: When the increase / decrease ratio count reaches the corresponding time threshold, it is determined to be a fault signal.

[0067] It should be understood that the specific application scenario of the time threshold and amplitude threshold is that during the test, the acquisition system compares the collected signal with the expected value defined in the criterion file, compares the difference between the two with the amplitude threshold, and triggers the increase or decrease proportional counting. When it exceeds the amplitude threshold, the increase proportional counting is executed. When it is less than the amplitude threshold, the decrease proportional counting is triggered. When the increase or decrease proportional counting reaches the time threshold, the system declares the signal as a fault signal.

[0068] In some embodiments, reference Figure 2 As shown in , step S510 includes:

[0069] The increase and decrease ratio count corresponding to the output signal is calculated according to the duration of the fluctuation after being stimulated by the external signal in the airborne equipment identification test.

[0070] It should be understood that a time threshold is set during the test to diagnose the duration of fluctuations after the device is stimulated by an external signal, and the increase and decrease proportional counts are calculated during the duration, and the delayed count value is compared with the time threshold to determine the fault signal.

[0071] In some embodiments, reference Figure 2 As shown in , step S510 includes:

[0072] The increase and decrease ratio counts corresponding to the output signals are calculated according to different acquisition cycles of the output signals.

[0073] It should be understood that the threshold setting is based on the acquisition cycle of various signals. The importance of discrete quantity signals does not allow a single beat to be lost or jittered. The bus is the carrier of various data signals on the aircraft, and it does not allow a single beat to be lost or jittered. VDT signals and BNR signals are allowed to fluctuate within a certain range according to the physical meaning represented by the signals, but the signal fluctuation must not cause aircraft oscillation and must not affect the safety and control quality of the aircraft.

[0074] In some embodiments, reference Figure 2 As shown in , step S200 includes:

[0075] Step S210: setting the corresponding amplitude threshold according to the influence of the output signal on the device under test after being disturbed.

[0076] It is important to understand that the amplitude threshold design method is: for different signals, different thresholds are set according to the degree of correlation between the signals and the degree of impact on the device or the system in which the device is located after being disturbed.

[0077] In some embodiments, reference Figure 2 As shown in , step S210 includes:

[0078] Step S211: different output signals are configured to have corresponding amplitude thresholds according to their respective percentages.

[0079] It should be understood that discrete signals are core variables used to characterize the state of equipment. During the test, there should be no signal changes when subjected to external excitation interference, and they must remain completely consistent. VDT signals use sum values ​​to characterize the health status of the sensor. Considering the allowable range of sensor tolerance and the acquisition accuracy of the sensor signal by the acquisition equipment, a fluctuation of ±n% is allowed in the initial state without excitation. The carrier of the BNR signal is a digital bus, and the bus signal has a strong anti-interference ability. Therefore, this type of signal is allowed to fluctuate by ±n%*full working stroke in the test field. The rudder signal includes parameters such as the control instructions and motion stroke received by the aircraft's actuators. It is a key characteristic parameter of the aircraft body and the threshold needs to be tightened. The allowable interference range is ±m%*full working stroke.

[0080] In some embodiments, reference Figure 2 As shown in, in step S200:

[0081] The itemized signal definition includes: data packet name, signal name, signal carrier, signal type, operating mode, signal identification number, sub-identification number, signal word starting position, signal word ending position, bit starting position, bit ending position and resolution.

[0082] It should be understood that signal definition is mainly used for precise data positioning. The definition content can accurately identify which signals of the equipment have been interfered with during the test. The signal definition mainly includes: data packet name, signal name, signal carrier, signal type, working mode, signal identification number, sub-identification number, signal word starting position, signal word ending position, bit starting position, bit ending position, resolution, etc.

[0083] The functional results of the present invention are specifically exemplified in conjunction with the above embodiments.

[0084] Table 1 Signal definition and data diagnosis of the example

[0085]

[0086] The left steering wheel command signal is a signal in the sensor data status data packet. The signal is transmitted in the system in the 429 bus mode. The data packet can be accurately located in the data link through the identification number 372, and the signal can be accurately located through the bit start position 10 and the bit end position 28. During the test, the left steering wheel command signal is collected and resolved in real time. The received 429 data is identified and resolved according to the signal type BNR quantity. The original code data is resolved according to the resolution of 0.0001234. The resolved value is compared with the expected value 4.00. When the difference between the two is greater than 0.08 (amplitude threshold), the comparison deviation time begins to accumulate. Each time a comparison deviation occurs, the time constant is accumulated plus 10. When the next beat resolution value is no more than 0.08 compared with the expected value, the time constant is accumulated minus 2, and the accumulation continues. When the time constant is greater than 100 (time threshold), the signal will report a fault. When the cumulative count value is greater than the maximum value of the cumulative count 110, the maximum value is output.

[0087] The working mode switch signal is a signal in the system working status data packet. The signal is transmitted in the system in the bus mode of SIB. The data packet can be accurately located in the data link through the identification number 1801 and the sub-identification number 1701. The signal can be accurately located through the signal word starting position 1 and the signal word ending position 2, the bit starting position 8 and the bit ending position 9. During the test, the working mode switch signal is collected and solved in real time, and the received SIB original code data is identified and solved according to the signal type boolean quantity. The solved value is compared with the expected value 1. When the two are inconsistent (the amplitude threshold is 0), the comparison deviation time begins to accumulate. Each time the comparison deviation occurs, the time constant accumulates and increases by 1. When the next beat solution value is consistent with the expected value, the time constant accumulates and decreases by 1. The accumulation continues. When the time constant is greater than 2 (time threshold), the signal will report a fault. When the cumulative count value is greater than the maximum value of the cumulative count 3, the maximum value is output.

[0088] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example" or "some examples" etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification.

[0089] Those skilled in the art will readily appreciate other embodiments of the present invention after considering the specification and practicing the invention disclosed herein. The present invention is intended to cover any variations, uses or adaptations of the present invention that follow the general principles of the present invention and include common knowledge or customary techniques in the art that are not disclosed by the present invention. The specification and examples are to be considered exemplary only, and the true scope and spirit of the present invention are indicated by the appended claims.

Claims

1. A method for diagnosing airborne equipment identification test compliance data, characterized in that: include: Obtaining output signals of the equipment under test according to the airborne equipment identification test; Matching the output signal with the entryized signal definition, and setting the corresponding time threshold and amplitude threshold; Collecting real-time measurement values ​​of the output signals in the airborne equipment identification test; Subtract the real-time measured value from the corresponding expected value and take the absolute value; Compare the absolute value with the amplitude threshold and obtain a delay count value; When the delay count value reaches the corresponding time threshold, it is determined to be a fault signal; The content of the signal fault declaration is defined, including: allowable deviation range, expected value, amplitude threshold, increase count, decrease count, time threshold, and maximum increase and decrease count; when comparing the absolute value with the amplitude threshold, using increase and decrease proportional counting to obtain the delay count value; when the absolute value exceeds the amplitude threshold, performing increase proportional counting; when the absolute value is less than the amplitude threshold, triggering decrease proportional counting; when the increase and decrease proportional counting reaches the corresponding time threshold, it is determined to be a fault signal; Among them, the left steering wheel command signal is collected and solved in real time, and the solved value is compared with the expected value of 4.

00. When the difference between the two is greater than the amplitude threshold of 0.08, the comparison deviation time begins to accumulate. Each time a comparison deviation occurs, the time constant is accumulated and increased by 10. When the next solved value does not exceed the amplitude threshold of 0.08 compared with the expected value, the time constant is accumulated and reduced by 2. The accumulation continues. When the time constant is greater than the time threshold of 100, the signal reports a fault.

2. The airborne equipment identification test compliance data diagnosis method according to claim 1, characterized in that: In the step of obtaining the output signal of the device under test according to the airborne equipment identification test: The output signals include: discrete signals, VDT signals, BNR signals and control surface signals.

3. The airborne equipment identification test compliance data diagnosis method according to claim 1, characterized in that: When comparing the absolute value with the amplitude threshold, the step of obtaining the delay count value by using increase and decrease proportional counting comprises: The increase and decrease ratio count corresponding to the output signal is calculated according to the duration of the fluctuation after being stimulated by the external signal in the airborne equipment identification test.

4. The airborne equipment identification test compliance data diagnosis method according to claim 1, characterized in that: When comparing the absolute value with the amplitude threshold, the step of obtaining the delay count value by using increase and decrease proportional counting comprises: The increase and decrease ratio counts corresponding to the output signals are calculated according to different acquisition cycles of the output signals.

5. The airborne equipment identification test compliance data diagnosis method according to claim 2, characterized in that: The step of matching the output signal with the entry-based signal definition and setting the corresponding time threshold and amplitude threshold comprises: The corresponding amplitude threshold is set according to the influence of the output signal on the device under test after being disturbed.

6. The airborne equipment identification test compliance data diagnosis method according to claim 5, characterized in that: The step of setting the corresponding amplitude threshold according to the influence of different output signals on the device under test after being disturbed comprises: Different output signals set corresponding amplitude thresholds according to their respective percentages.

7. The airborne equipment identification test compliance data diagnosis method according to any one of claims 1 to 6, characterized in that: In the step of matching the output signal with the entryized signal definition and setting the corresponding time threshold and amplitude threshold: The itemized signal definition includes: data packet name, signal name, signal carrier, signal type, operating mode, signal identification number, sub-identification number, signal word starting position, signal word ending position, bit starting position, bit ending position and resolution.

Images