A method for helicopter fault diagnosis and elimination

Abstract

The present application relates to the field of aircraft maintenance technology, and particularly relates to a method for helicopter fault diagnosis and elimination. The method comprises the following steps: accurate description of fault phenomena: objectively and clearly determine the fault location, parameter abnormal value, occurrence stage, reproduce the fault and record the conditions, compare with the normal state, verify with relevant personnel, and form an unambiguous fault description; multi-dimensional information collection: collect system working principle, maintenance records, flight parameters, HUMS system vibration and sensor data, and count the same type of helicopter fault history to form a fault information set; standardized process reduces the dependence on the experience of maintenance personnel, and can be executed by new and old personnel; multi-dimensional information collection and hierarchical verification greatly improve the fault diagnosis accuracy and shorten the diagnosis cycle; block splitting and single variable control avoid secondary damage and reduce maintenance cost; knowledge base deposition realizes reuse of fault experience, supports fault prediction, and improves overall maintenance level.

Description

Technical Field

[0001] This invention relates to the field of aircraft maintenance technology, specifically to a method for diagnosing and troubleshooting helicopter malfunctions. Background Technology

[0002] Helicopters, as complex and precision aircraft, are widely used in both military and civil aviation. Their systems are numerous and their components complex, making them prone to failure under load, environmental corrosion, vibration, and other factors. Currently, helicopter fault diagnosis and troubleshooting heavily rely on the experience and theoretical knowledge of maintenance personnel, resulting in low standardization, long troubleshooting cycles, and inconsistent accuracy. Complex system faults are prone to misdiagnosis and missed diagnosis, affecting not only helicopter uptime and service life but also posing safety hazards and failing to meet the demands for efficient maintenance and support.

[0003] Therefore, a standardized, streamlined, and replicable method for helicopter fault diagnosis and troubleshooting is needed to reduce reliance on personnel experience and improve troubleshooting efficiency and accuracy. Summary of the Invention

[0004] This invention provides a method for helicopter fault diagnosis and troubleshooting, which solves the problems of existing helicopter troubleshooting relying on experience, non-standardized procedures, low efficiency, and poor accuracy, and realizes standardized and procedural operation for fault diagnosis and troubleshooting.

[0005] Technical solution

[0006] A method for diagnosing and troubleshooting helicopter malfunctions includes the following steps:

[0007] 1. Accurate description of fault phenomenon: Objectively and clearly identify the fault location, abnormal parameter values, and stage of occurrence; reproduce the fault and record the conditions; compare with the normal state; verify with relevant personnel; and form an unambiguous fault description.

[0008] 2. Multi-dimensional information collection: Collect system working principle, maintenance records, flight parameters, HUMS system vibration and sensor data, and statistically analyze the history of similar faults of the same type of helicopter to form a fault information set;

[0009] 3. Listing and prioritizing fault hypotheses: Based on the fault phenomena and collected information, list all potential causes and prioritize them according to both the probability of fault occurrence and the difficulty of verification.

[0010] 4. Graded testing and verification: Following the principles of starting with the easy and then moving to the difficult, using a single variable, and prioritizing economic benefits, we employ methods such as controlled variable method, comparison method, segmentation method, component replacement method, and block-based decomposition verification to quickly locate the root cause;

[0011] 5. Repair plan determination and verification: Develop and implement repair plans based on the root cause. For simple systems, directly reproduce and verify the fault. For complex systems, indirectly verify the function and continuously monitor to ensure that the fault is completely eliminated.

[0012] 6. Fault summarization and knowledge base accumulation: Completely record the entire troubleshooting process, analyze fault patterns, formulate maintenance suggestions, and store them in the maintenance database to support subsequent fault prediction and rapid troubleshooting.

[0013] As a further aspect of the present invention, the fault hypothesis sorting method includes: sorting by historical fault probability from high to low; and sorting by the ease of verification operation from easy to difficult.

[0014] As a further aspect of the present invention: the experimental verification prioritizes test items with no risk of secondary damage, and complex systems are traced in segments using a binary search method to narrow down the scope of the fault.

[0015] As a further aspect of the present invention, the diagnostic technology also includes: identifying abnormal parameters based on flight parameter records; acquiring data from vibration sensors based on the HUMS system; and implementing monitoring using simulation software in conjunction with the data and a dual-priority test scheme.

[0016] The beneficial effects of this invention are:

[0017] Standardized processes reduce reliance on the experience of maintenance personnel, allowing both new and experienced staff to follow them effectively.

[0018] Multi-dimensional information collection and hierarchical verification significantly improve the accuracy of troubleshooting and shorten the diagnostic cycle;

[0019] Block-based partitioning and single-variable control avoid secondary damage and reduce maintenance costs;

[0020] Knowledge base accumulation enables the reuse of fault experience, supports fault prediction, and improves the overall maintenance level.

[0021] Obviously, based on the above description of the present invention, and according to common technical knowledge and conventional methods in the field, various other modifications, substitutions or alterations can be made without departing from the basic technical concept of the present invention.

[0022] The following detailed embodiments further illustrate the above-described content of the present invention. However, this should not be construed as limiting the scope of the present invention to the following examples. All technologies implemented based on the above-described content of the present invention fall within the scope of the present invention. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the process structure of the present invention. Detailed Implementation

[0024] The present invention is illustrated below with specific embodiments, but these are not intended to limit the scope of the invention. Figure 1 As shown, a method for helicopter fault diagnosis and troubleshooting is presented.

[0025] Example: Diagnosis and troubleshooting of overheating fault in the No. 2 engine of a certain type of helicopter

[0026] 1. Description of the fault phenomenon: After the helicopter is started on the ground and hovered for inspection, when the total distance to the ground is increased, the temperature of engine 2 T45 rises rapidly, reaching 875℃ at an altitude of 5m, entering the red zone. The Ng speed is higher than that of other engines in the same aircraft. The parameters are normal when the engine is shut down. The fault can be reproduced by repeated hovering.

[0027] 2. Information collection: Obtain information such as engine working principle, daily atmospheric temperature of 36.7℃, no recent engine maintenance, engine cumulative working time of 1746:43, no inspection or adjustment of vent valve closing point, and previous cases of overheating due to delayed vent valve closing point of the same model.

[0028] 3. Listing and ranking of fault hypotheses: List 11 causes, including the influence of other aircraft, engine performance degradation, delayed bleed valve closing point, bleed valve failure, sensor failure, electronic controller failure, mechanical fuel regulation failure, compressor blade damage, combustion chamber damage, free turbine failure, and gas turbine blade damage, and rank them by probability and operability.

[0029] 4. Experimental verification:

[0030] An endoscopic examination of the compressor and free turbine blades revealed no damage or dust accumulation, ruling out the corresponding cause.

[0031] After cleaning the engine, the bleed valve closing point was measured. The valve continued to bleed air without a closing signal, and adjustments did not improve the situation.

[0032] Disassembly and inspection of the vent valve revealed that the piston was stuck. After cleaning and repair, it was readjusted and the closing point met the manual requirements.

[0033] The power guarantee check confirmed that the engine performance had not declined.

[0034] Solution confirmation and verification: The bleed valve was repaired to eliminate the jamming, the closing point was adjusted to the standard value, the ground test was normal, and the test flight verified that the high-power status parameters met the requirements, and the fault was eliminated;

[0035] Summary: Record the troubleshooting process and root cause. It is recommended to check and adjust the vent valve closing point in a timely manner when the season changes, and to regularly maintain and clean the electronic vent valve, and incorporate it into the daily maintenance procedures.

[0036] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0037] The above description is merely a preferred embodiment of the present invention and does not limit the patent scope of the present invention. Any equivalent structural transformations made using the contents of the present invention's specification and drawings under the inventive concept of the present invention, or direct / indirect applications in other related technical fields, are included within the patent protection scope of the present invention.

[0038] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A method for diagnosing and troubleshooting helicopter faults, characterized in that, Includes the following steps: S1: Fault Phenomenon Description: Objectively and clearly identify the fault location, abnormal parameters, and stage of occurrence; reproduce the fault and record the conditions; compare with the normal state and verify the information to form an unambiguous fault description. S2: Information Collection: Collect system working principle, maintenance records, flight parameters, HUMS system vibration and sensor data, and statistically analyze the history of similar faults of the same type of helicopter to form a fault information set; S3: Listing and prioritizing fault hypotheses: Based on the fault phenomena and collected information, list all potential causes and prioritize them according to the probability of fault occurrence and the difficulty of verification. S4: Experimental verification: Following the principles of starting with the easy and then moving to the difficult, using a single variable, and prioritizing economic benefits, we will use the controlled variable method, the comparison method, the segmentation method, the component replacement method, and the block-based decomposition verification to locate the root cause; S5: Solution Determination and Verification: Develop and implement maintenance solutions based on the root cause, directly reproduce and verify simple systems, and indirectly verify and continuously monitor complex systems. S6: Summary and Conclusion: Completely record the entire troubleshooting process, analyze the fault patterns, formulate maintenance suggestions, and store them in the database.

2. The method according to claim 1, characterized in that, The sorting described in S3 includes: sorting by historical failure probability from high to low; and sorting by the ease of verification operation from easy to difficult.

3. The method according to claim 1, characterized in that, S4: Prioritize test items with no risk of secondary damage; for complex systems, use a binary search method for segmented tracing to quickly narrow down the fault range.

4. The method according to claim 1, characterized in that, It also includes the following diagnostic technologies: identifying abnormal parameters based on flight parameter records; acquiring vibration sensor data based on the HUMS system; and implementing monitoring using simulation software in conjunction with data and a dual-priority test scheme.

5. The method according to claim 1, characterized in that, S4: For fault causes with similar probabilities, perform simple tests first and then complex tests according to the difficulty of verification.

6. The method according to claim 1, characterized in that, S5: After troubleshooting a complex system fault, it is necessary to trace back the unverified causes and test them one by one to ensure that the fault is completely eliminated.

7. The method according to claim 1, characterized in that, S2: Information collection includes: environmental conditions in which the fault occurred, recent maintenance work, cumulative engine operating time, and historical parameter records.

8. The method according to claim 1, characterized in that, S4: Verification was performed using endoscopic inspection, measurement of the vent valve closing point, power assurance check, and control mode switching comparison.

9. The method according to claim 1, characterized in that, It is applicable to the diagnosis and troubleshooting of overheating faults in helicopter power system engines.

10. A helicopter field maintenance system, characterized in that, Perform the fault diagnosis and troubleshooting method as described in any one of claims 1-9.

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