CN114184879B - Abnormal frequency point monitoring method for helicopter vibration data - Google Patents
Abnormal frequency point monitoring method for helicopter vibration data Download PDFInfo
- Publication number
- CN114184879B CN114184879B CN202111316250.2A CN202111316250A CN114184879B CN 114184879 B CN114184879 B CN 114184879B CN 202111316250 A CN202111316250 A CN 202111316250A CN 114184879 B CN114184879 B CN 114184879B
- Authority
- CN
- China
- Prior art keywords
- vibration
- data
- helicopter
- aircraft
- frequency
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 230000002159 abnormal effect Effects 0.000 title claims abstract description 41
- 238000012544 monitoring process Methods 0.000 title claims abstract description 37
- 238000000034 method Methods 0.000 title claims abstract description 25
- 238000012216 screening Methods 0.000 claims abstract description 6
- 230000009466 transformation Effects 0.000 claims abstract description 5
- 238000006243 chemical reaction Methods 0.000 claims description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000004458 analytical method Methods 0.000 description 2
- 238000013461 design Methods 0.000 description 2
- 239000013589 supplement Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000009469 supplementation Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01R—MEASURING ELECTRIC VARIABLES; MEASURING MAGNETIC VARIABLES
- G01R31/00—Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere
- G01R31/08—Locating faults in cables, transmission lines, or networks
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention provides an abnormal frequency point monitoring method of helicopter vibration data, which comprises the following steps: s1, resolving helicopter vibration original data and comprehensive monitoring data to obtain a vibration original value, a vibration frequency value and an aircraft necessary parameter value; s2: analyzing the data file of the engineering value of the essential parameter of the aircraft to obtain an aircraft state envelope, and establishing a vibration frequency point index; s3: establishing a time sequence by using the aircraft state envelope and the vibration frequency value engineering data file, and introducing the preliminary screening of abnormal line vibration frequency points; s4: and establishing a time sequence by using the aircraft state envelope and the vibration original engineering data file, then carrying out frequency domain transformation, and then carrying out rechecking. According to the method, vibration frequency values are divided by utilizing a helicopter flight state envelope, abnormal vibration frequency points of the helicopter are screened by adopting a big data method, frequency characteristics which possibly influence the flight safety of the helicopter are found on the premise of relatively low professional background, and the natural frequency points of the vibration characteristics of the helicopter are supplemented.
Description
Technical Field
The invention belongs to the technical field of avionics, and particularly relates to an abnormal frequency point monitoring method for helicopter vibration data.
Background
Because the helicopter system adopts a rotor wing layout, factors influencing the flight safety of the aircraft comprise mechanical components such as a main rotor wing system, an engine system, a tail rotor system and the like of the aircraft besides the health state of relevant equipment of the aircraft avionics system. The existing flying process of the helicopter mostly depends on the rapid interpretation result of the flying data of each avionics system of the helicopter acquired by the flight parameters, and the interpretation result can only reflect part of fault information reported by the avionics system and the engine to the outside and cannot judge the health state of the mechanical system of the aircraft, particularly each vibration part.
Therefore, the design of monitoring the health state of the helicopter vibration component becomes particularly urgent, and the helicopter vibration monitoring system (HUMS) or the monitoring of the helicopter vibration component by additionally installing a vibration sensor can realize the safety monitoring of a key mechanical system of the helicopter, so that the safety flying capacity of the helicopter is greatly improved, and the abnormal frequency point monitoring system based on vibration data can be used as the supplement of the safety of the helicopter vibration component interpreted by ground staff.
Disclosure of Invention
In order to solve the technical problems, the invention designs an abnormal frequency point monitoring method for helicopter vibration data, which effectively identifies unknown vibration frequency points of a helicopter, supplements and perfects a helicopter vibration frequency point sword monitoring library and improves the flight safety of the helicopter.
The invention aims to provide an abnormal frequency point monitoring method for helicopter vibration data, which comprises the following steps:
s1, resolving helicopter vibration original data and comprehensive monitoring data to obtain three types of engineering value data files including a vibration original value, a vibration frequency value and an airplane necessary parameter value;
s2: analyzing the data file of the engineering value of the essential parameter of the aircraft to obtain an aircraft state envelope, and establishing a vibration frequency point index by using the vibration amplitude file;
s3: establishing a time sequence by using the aircraft state envelope and the vibration frequency value engineering data file, and carrying out preliminary screening on the vibration abnormal frequency points according to the vibration frequency point index;
s4: and establishing a time sequence by using the aircraft state envelope and the vibration original engineering data file, then carrying out frequency domain transformation, and carrying out the rechecking of the vibration abnormal frequency point according to the vibration frequency point index.
The abnormal frequency point monitoring method of the helicopter vibration data provided by the invention also has the characteristics that the S1 comprises the following steps:
s1.1: reading vibration original data and comprehensive monitoring data of a helicopter;
s1.2: acquiring parameter resolving configuration;
s1.3: and (3) according to the parameter resolving configuration in the step S1.2, resolving the vibration original data and the comprehensive monitoring data in the step S1.1.
The method for monitoring the abnormal frequency point of the helicopter vibration data provided by the invention is also characterized in that the essential parameters of the aircraft comprise the parameters of the flight height, the flight speed, the rotor wing rotating speed and the attitude angle of the aircraft.
The method for monitoring the abnormal frequency point of the helicopter vibration data provided by the invention is also characterized in that the vibration amplitude file contains flight state, vibration frequency and vibration amplitude threshold information and is obtained through abnormal frequency point iteration in the history flight process of the aircraft.
The abnormal frequency point monitoring method for the helicopter vibration data provided by the invention also has the characteristic that the frequency conversion is carried out by using FFT conversion in S4.
Compared with the prior art, the invention has the beneficial effects that:
according to the method for monitoring the abnormal frequency points of the helicopter vibration data, provided by the invention, under the condition of a helicopter vibration monitoring system or recording of the helicopter vibration data, the vibration frequency values are divided by utilizing the flight state envelope of the helicopter, so that the abnormal frequency points of the helicopter vibration are screened by adopting a big data method, the frequency characteristics which possibly influence the flight safety of the helicopter can be found on the premise of relatively low professional background, the supplementation of the inherent frequency points of the helicopter vibration characteristics is completed, and the labor cost and the learning cost are reduced.
Drawings
In order to more clearly illustrate the technical solutions of the present invention, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and that other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1: the invention provides a flow chart of an abnormal frequency point monitoring method of helicopter vibration data;
FIG. 2 is a flow chart of data splitting and storing management in the monitoring method provided by the invention;
fig. 3 is a flowchart for screening abnormal vibration frequency points in the monitoring method provided by the invention.
Detailed Description
In order to make the technical means, the creation characteristics, the achievement of the purposes and the effects of the present invention easy to understand, the following embodiments specifically describe the monitoring method provided by the present invention with reference to the accompanying drawings.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
1-2, the embodiment of the invention provides an abnormal frequency point monitoring method of helicopter vibration data, which comprises the following steps:
s1, resolving helicopter vibration original data and comprehensive monitoring data to obtain three types of engineering value data files including a vibration original value, a vibration frequency value and an airplane necessary parameter value; the aircraft necessary parameters refer to parameters which can be used for dividing the flight state of the aircraft, namely the aircraft necessary parameters;
s2: analyzing the data file of the engineering value of the essential parameter of the aircraft to obtain an aircraft state envelope, and establishing a vibration frequency point index by using the vibration amplitude file;
s3: establishing a time sequence by using the aircraft state envelope and the vibration frequency value engineering data file, and carrying out preliminary screening on the vibration abnormal frequency points according to the vibration frequency point index;
s4: and establishing a time sequence by using the aircraft state envelope and the vibration original engineering data file, then carrying out frequency domain transformation, and carrying out the rechecking of the vibration abnormal frequency point according to the vibration frequency point index.
In some embodiments, the S1 includes:
s1.1: reading vibration original data and comprehensive monitoring data of a helicopter;
s1.2: acquiring parameter resolving configuration;
s1.3: and (3) according to the parameter resolving configuration in the step S1.2, resolving the vibration original data and the comprehensive monitoring data in the step S1.1.
In some embodiments, the aircraft-necessary parameters include aircraft altitude, speed of flight, rotor speed, and attitude angle parameters.
In some embodiments, the vibration amplitude file includes flight status, vibration frequency, and vibration amplitude threshold information, and is obtained through abnormal frequency point iteration during historical flight of the aircraft.
In some embodiments, the S4 intermediate frequency transform is performed using an FFT transform.
In some embodiments, as shown in fig. 3, the helicopter data characteristics and the flight state expert knowledge base are utilized, the flight state is identified by utilizing the aircraft necessary parameter values, the vibration frequency amplitude files are split and stored according to the flight state by utilizing the time sequence mapping relation, and the vibration original data engineering value files are managed by adopting single parameters and a time index sequence table is established according to the flight state.
In some embodiments, as shown in fig. 3, the vibration anomaly frequency point monitoring and screening flow is as follows: reading vibration frequency amplitude data in batches according to time sequences of which the flight phases are divided, obtaining the amplitude of each frequency point of each channel in each flight phase, analyzing the amplitude of each frequency point by using a big data analysis method of clustering analysis, dividing the data into two types of normal and abnormal, finding out abnormal data points, marking time information of the abnormal frequency points after the abnormal frequency points are identified, carrying out FFT analysis on engineering values of vibration original data of corresponding channels at corresponding moments, reporting the abnormal frequency points after verifying that the vibration frequency amplitude of the point recorded by the comprehensive monitoring system is effective, and reversely pushing out a new abnormal identification criterion from an abnormal identification result and adding the new abnormal identification criterion to an abnormal interpretation library.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention. The foregoing is merely a preferred embodiment of the present invention, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present invention, and these modifications and variations should also be regarded as the scope of the invention.
Claims (2)
1. The abnormal frequency point monitoring method for the helicopter vibration data is characterized by comprising the following steps of:
s1, resolving helicopter vibration original data and comprehensive monitoring data to obtain three types of engineering value data files including a vibration original value, a vibration frequency value and an airplane necessary parameter value; the S1 comprises the following steps:
s1.1: reading vibration original data and comprehensive monitoring data of a helicopter;
s1.2: acquiring parameter resolving configuration;
s1.3: according to the parameter resolving configuration in the step S1.2, resolving vibration original data and comprehensive monitoring data in the step S1.1;
s2: analyzing the data file of the engineering value of the essential parameter value of the aircraft to obtain an aircraft state envelope, and establishing a vibration frequency point index by using the vibration amplitude file; the aircraft essential parameter values comprise parameters of the flight height, the flight speed, the rotor wing rotating speed and the attitude angle of the aircraft; the vibration amplitude file comprises flight state, vibration frequency and vibration amplitude threshold information, and is obtained through abnormal frequency point iteration in the aircraft historical flight process;
s3: establishing a time sequence by using the aircraft state envelope and the vibration frequency value engineering value data file, primarily screening the vibration abnormal frequency points according to the vibration frequency point index, and marking the time information of the abnormal frequency points after the abnormal frequency points are identified;
s4: and (3) establishing a time sequence by using the aircraft state envelope and the vibration original engineering value data file, then carrying out frequency domain transformation, carrying out frequency domain transformation on the vibration original engineering value data file of the corresponding channel corresponding to the time of the abnormal frequency point screened in the step (S3), and carrying out the rechecking of the vibration abnormal frequency point according to the vibration frequency point index.
2. The method for monitoring abnormal frequency points of helicopter vibration data according to claim 1, wherein said S4 frequency conversion is performed using FFT conversion.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316250.2A CN114184879B (en) | 2021-11-08 | 2021-11-08 | Abnormal frequency point monitoring method for helicopter vibration data |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111316250.2A CN114184879B (en) | 2021-11-08 | 2021-11-08 | Abnormal frequency point monitoring method for helicopter vibration data |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114184879A CN114184879A (en) | 2022-03-15 |
| CN114184879B true CN114184879B (en) | 2024-01-23 |
Family
ID=80601983
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111316250.2A Active CN114184879B (en) | 2021-11-08 | 2021-11-08 | Abnormal frequency point monitoring method for helicopter vibration data |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114184879B (en) |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9311080D0 (en) * | 1992-06-03 | 1993-07-14 | Westland Helicopters | Method & apparatus for in-flight shake testing |
| JP2007326541A (en) * | 2006-06-09 | 2007-12-20 | Kawasaki Heavy Ind Ltd | Vibration reducing method, vibration reduction assisting device, and program |
| CA2798644A1 (en) * | 2011-12-16 | 2013-06-16 | Instytut Lotnictwa W Warszawie | A method for in-flight assessment of freedom from flutter of an airplane |
| CN204082695U (en) * | 2014-08-07 | 2015-01-07 | 杭州中环化工设备有限公司 | Blower fan automatic flushing device |
| CN106769089A (en) * | 2016-12-19 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane during flying performance evaluation and the flight quality integrated method for real-time monitoring of assessment |
| KR20170081355A (en) * | 2016-01-04 | 2017-07-12 | 한국항공우주산업 주식회사 | Drive system for helicopter vibration diagnosis method |
| RU2667830C1 (en) * | 2017-12-15 | 2018-09-24 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Method of diagnostics of the technical condition of the aviation drive aggregate |
| CN109973325A (en) * | 2017-12-20 | 2019-07-05 | 北京金风科创风电设备有限公司 | Method and apparatus for identifying abnormal vibration |
| FR3079977A1 (en) * | 2018-04-09 | 2019-10-11 | Safran | METHOD AND DEVICE FOR MONITORING A ROTATING MACHINE |
| CN110929342A (en) * | 2019-12-04 | 2020-03-27 | 中国直升机设计研究所 | Helicopter vibration response data processing method |
| FR3095906A1 (en) * | 2019-05-09 | 2020-11-13 | Lefebure | DEVICE AND PROCEDURE FOR MONITORING ELECTRICITY DISTRIBUTION TO AN AIRCRAFT |
| CN112556930A (en) * | 2020-12-25 | 2021-03-26 | 中国人民解放军32382部队 | Helicopter moving part vibration signal data quality calculation method |
| CN112991579A (en) * | 2021-01-14 | 2021-06-18 | 北京航空航天大学 | Helicopter mobile part abnormity detection method based on generation countermeasure network |
-
2021
- 2021-11-08 CN CN202111316250.2A patent/CN114184879B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB9311080D0 (en) * | 1992-06-03 | 1993-07-14 | Westland Helicopters | Method & apparatus for in-flight shake testing |
| JP2007326541A (en) * | 2006-06-09 | 2007-12-20 | Kawasaki Heavy Ind Ltd | Vibration reducing method, vibration reduction assisting device, and program |
| CA2798644A1 (en) * | 2011-12-16 | 2013-06-16 | Instytut Lotnictwa W Warszawie | A method for in-flight assessment of freedom from flutter of an airplane |
| CN204082695U (en) * | 2014-08-07 | 2015-01-07 | 杭州中环化工设备有限公司 | Blower fan automatic flushing device |
| KR20170081355A (en) * | 2016-01-04 | 2017-07-12 | 한국항공우주산업 주식회사 | Drive system for helicopter vibration diagnosis method |
| CN106769089A (en) * | 2016-12-19 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | Unmanned plane during flying performance evaluation and the flight quality integrated method for real-time monitoring of assessment |
| RU2667830C1 (en) * | 2017-12-15 | 2018-09-24 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Method of diagnostics of the technical condition of the aviation drive aggregate |
| CN109973325A (en) * | 2017-12-20 | 2019-07-05 | 北京金风科创风电设备有限公司 | Method and apparatus for identifying abnormal vibration |
| FR3079977A1 (en) * | 2018-04-09 | 2019-10-11 | Safran | METHOD AND DEVICE FOR MONITORING A ROTATING MACHINE |
| FR3095906A1 (en) * | 2019-05-09 | 2020-11-13 | Lefebure | DEVICE AND PROCEDURE FOR MONITORING ELECTRICITY DISTRIBUTION TO AN AIRCRAFT |
| CN110929342A (en) * | 2019-12-04 | 2020-03-27 | 中国直升机设计研究所 | Helicopter vibration response data processing method |
| CN112556930A (en) * | 2020-12-25 | 2021-03-26 | 中国人民解放军32382部队 | Helicopter moving part vibration signal data quality calculation method |
| CN112991579A (en) * | 2021-01-14 | 2021-06-18 | 北京航空航天大学 | Helicopter mobile part abnormity detection method based on generation countermeasure network |
Non-Patent Citations (2)
| Title |
|---|
| Finite element analysis and test study of dynamic behavior of single-tower and double-face cable-stayed bridge;Ju Yan-zhong 等;《2010 International Conference on Mechanic Automation and Control Engineering。;全文 * |
| 某型直升机振动信号采集系统设计;申江江 等;《仪表技术》;全文 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114184879A (en) | 2022-03-15 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20220196720A1 (en) | Single-ended fault positioning method and system for high-voltage direct-current transmission line of hybrid network | |
| CN103090898A (en) | Flight data recording equipment ground integrated test system | |
| CN109886116A (en) | Specific emitter identification method and device based on ADS-B | |
| CN113884961B (en) | SOC calibration method, modeling device, computer equipment and medium | |
| EP4155974A1 (en) | Knowledge graph construction method and apparatus, check method and storage medium | |
| US11423713B2 (en) | Systems and methods to determine maintenance-focused aircraft data recording frame configurations | |
| CN106646169A (en) | Electrical device partial discharge detection data collection cloud strategy | |
| CN104569694A (en) | Electric signal feature extraction and recognition system oriented to aircraft flying process | |
| CN106780831A (en) | It is a kind of can online programming general winged ginseng collector | |
| CN114184879B (en) | Abnormal frequency point monitoring method for helicopter vibration data | |
| CN109165625A (en) | A kind of test report intelligent generation method based on image recognition | |
| CN115291006A (en) | Method for identifying environmental protection working condition abnormity of polluted enterprise based on electricity utilization data | |
| CN106771910B (en) | Method and device for detecting defects of combined electrical appliance | |
| CN115221210A (en) | Method for analyzing maneuvering capacity based on aviation equipment flight parameter data | |
| CN111275101A (en) | Fault identification method and device for aircraft hydraulic system and readable storage medium | |
| CN110920931B (en) | Static load and dynamic load separation method for flight test of rotating part | |
| CN112865295A (en) | Power transmission line operation monitoring system for smart power grid | |
| CN115437663A (en) | Upgrade strategy updating method and device, electronic equipment, storage medium and vehicle | |
| CN103746781A (en) | Method and apparatus for processing response information in reception sensitivity test | |
| US11134496B2 (en) | Auto-detection of AxC mapping within a CPRI link | |
| CN106776236A (en) | The method and apparatus of the execution of monitoring program | |
| Chin et al. | Knowledge Discovery Within ADS-B Data from Routine Helicopter Tour Operations | |
| CN112612663A (en) | Method for reversely solving 1553B bus ICD | |
| CN117472674B (en) | Software radio measurement method based on resource pool | |
| CN110816877B (en) | Pneumatic servo elastic airborne real-time analysis system of airplane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |