CN112215982A - Helicopter data acquisition method, system, device and storage medium - Google Patents
Helicopter data acquisition method, system, device and storage medium Download PDFInfo
- Publication number
- CN112215982A CN112215982A CN202011037797.4A CN202011037797A CN112215982A CN 112215982 A CN112215982 A CN 112215982A CN 202011037797 A CN202011037797 A CN 202011037797A CN 112215982 A CN112215982 A CN 112215982A
- Authority
- CN
- China
- Prior art keywords
- monitoring
- acquisition
- helicopter
- data
- data acquisition
- 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.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 48
- 238000012544 monitoring process Methods 0.000 claims abstract description 128
- 238000005070 sampling Methods 0.000 claims description 20
- 238000012545 processing Methods 0.000 claims description 14
- 238000012360 testing method Methods 0.000 claims 1
- 238000003745 diagnosis Methods 0.000 abstract description 6
- 230000036541 health Effects 0.000 abstract description 6
- 230000001960 triggered effect Effects 0.000 abstract description 4
- 238000001514 detection method Methods 0.000 abstract description 2
- 230000005540 biological transmission Effects 0.000 description 13
- 230000006870 function Effects 0.000 description 11
- 230000001360 synchronised effect Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 4
- 230000008901 benefit Effects 0.000 description 3
- 238000004364 calculation method Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000006641 stabilisation Effects 0.000 description 3
- 238000011105 stabilization Methods 0.000 description 3
- 238000012935 Averaging Methods 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 2
- 230000006399 behavior Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000007405 data analysis Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000007123 defense Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000013307 optical fiber Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0808—Diagnosing performance data
-
- G—PHYSICS
- G07—CHECKING-DEVICES
- G07C—TIME OR ATTENDANCE REGISTERS; REGISTERING OR INDICATING THE WORKING OF MACHINES; GENERATING RANDOM NUMBERS; VOTING OR LOTTERY APPARATUS; ARRANGEMENTS, SYSTEMS OR APPARATUS FOR CHECKING NOT PROVIDED FOR ELSEWHERE
- G07C5/00—Registering or indicating the working of vehicles
- G07C5/08—Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle or waiting time
- G07C5/0841—Registering performance data
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The invention discloses a helicopter data acquisition method, a system and a device. The method comprises the following steps: determining a packet acquisition trigger event according to a monitoring component; grouping the monitoring channels according to the monitoring components to obtain an acquisition group; when a packet acquisition trigger event occurs, acquiring monitoring data by using the acquisition packets. According to the method, the trigger events and the collection groups are collected in groups, when one or some of the group collection trigger events occur, the corresponding collection groups are triggered to collect the monitoring data on the corresponding monitoring components, the monitoring data are the monitoring data of the helicopter in a stable working state, the method has important significance for health monitoring and fault diagnosis of the helicopter, meanwhile, the collected monitoring data can effectively reduce storage capacity and calculated amount, and operation efficiency is improved. The invention can be widely applied to the technical field of helicopter health detection and fault diagnosis.
Description
Technical Field
The invention relates to the technical field of helicopter health detection and fault diagnosis, in particular to a helicopter data acquisition method, a system, a device and a storage medium.
Background
The noun explains:
RTB: the rotor cone is dynamically balanced.
Helicopters play an increasingly important role in the field of national defense and civil aviation, but with the great investment and use of helicopters, faults of helicopters, especially faults of three major moving parts (transmission system, engine and rotor system) occur sometimes, and catastrophic accidents are often caused, causing serious casualties and economic losses. Therefore, the method has very important significance in carrying out state monitoring and fault diagnosis of three major moving parts of the helicopter.
The existing helicopter has long monitoring data acquisition time and large data acquisition amount, and thus has higher requirements on the storage and processing performance of an acquisition device. The one-time flight time of the helicopter can reach more than 2 hours, all monitoring channels uninterruptedly acquire monitoring data in the whole flight process, and after the flight is finished, a large amount of acquired monitoring data needs to be downloaded, decoded and analyzed, so that a Condition Indicator (CI) curve capable of reflecting the health Condition of the helicopter is obtained, and a reference function is provided for Condition monitoring and fault diagnosis of the helicopter.
Disclosure of Invention
The invention aims to solve at least one technical problem existing in the prior art to a certain extent, and aims to: a helicopter data acquisition method, system, device and storage medium are provided.
The technical scheme adopted by the invention on one hand is as follows:
in a first aspect, the invention provides a helicopter data acquisition method, which comprises the following steps:
determining a packet acquisition trigger event according to a monitoring component;
grouping the monitoring channels according to the monitoring components to obtain an acquisition group;
when a packet acquisition trigger event occurs, acquiring monitoring data by using the acquisition packets.
Further, the helicopter data acquisition method further comprises the following steps:
and processing the monitoring data.
Further, the helicopter data acquisition method further comprises the following steps:
determining a priority of the packet acquisition trigger event.
Further, the helicopter data acquisition method further comprises the following steps:
determining a sampling frequency of the monitoring channel.
Further, the helicopter data acquisition method further comprises the following steps:
a sampling time of the acquisition packet is determined.
In a second aspect, the present invention provides a helicopter data acquisition system, including:
an event determination module for determining a packet acquisition trigger event according to the monitoring component;
the grouping determination module is used for grouping the monitoring channels according to the monitoring components to obtain an acquisition grouping;
and the data acquisition module is used for acquiring monitoring data by utilizing the acquisition grouping when a grouping acquisition triggering event occurs.
Further, a helicopter data acquisition system further comprises:
and the data processing module is used for processing the monitoring data.
Further, a helicopter data acquisition system further comprises:
and the priority determining module is used for determining the priority of the packet acquisition triggering event.
In a third aspect, the present invention provides a helicopter data acquisition apparatus, comprising:
at least one processor;
at least one memory for storing at least one program;
when executed by the at least one processor, the at least one program causes the at least one processor to implement the helicopter data acquisition method.
In a fourth aspect, the present invention provides a storage medium having stored therein a processor-executable program, which when executed by a processor, is configured to implement a helicopter data acquisition method as described.
Advantages and benefits of the present invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention:
according to the method, the trigger events and the collection groups are collected in groups, when one or some of the group collection trigger events occur, the corresponding collection groups are triggered to collect the monitoring data on the corresponding monitoring components, the monitoring data are the monitoring data of the helicopter in a stable working state, the method has important significance for health monitoring and fault diagnosis of the helicopter, meanwhile, the collected monitoring data can effectively reduce storage capacity and calculated amount, and operation efficiency is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following description is made on the drawings of the embodiments of the present invention or the related technical solutions in the prior art, and it should be understood that the drawings in the following description are only for convenience and clarity of describing some embodiments in the technical solutions of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a flow chart of the steps of a helicopter data acquisition method of the present invention;
FIG. 2 is a schematic structural view of a helicopter data acquisition system of the present invention;
fig. 3 is a schematic structural diagram of a helicopter data acquisition device according to the present invention.
Detailed Description
Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to the same or similar elements or elements having the same or similar function throughout. The embodiments described below with reference to the accompanying drawings are illustrative only for the purpose of explaining the present invention, and are not to be construed as limiting the present invention. The step numbers in the following embodiments are provided only for convenience of illustration, the order between the steps is not limited at all, and the execution order of each step in the embodiments can be adapted according to the understanding of those skilled in the art.
A helicopter data acquisition method, a system, an apparatus, and a storage medium according to embodiments of the present invention will be described in detail below with reference to the accompanying drawings, and first, a helicopter data acquisition method according to embodiments of the present invention will be described with reference to the accompanying drawings.
Referring to fig. 1, a helicopter data acquisition method in an embodiment of the present invention mainly includes the following steps:
s1, determining grouping acquisition trigger events according to the monitoring component;
specifically, the group acquisition trigger event refers to a relatively stable operating state of the helicopter, and when the helicopter reaches the relatively stable operating state, the acquisition of monitoring data of each monitoring component of the helicopter is started.
The monitoring objects in this application are the three major moving parts of the helicopter, namely the rotor system, the transmission system and the engine, wherein the helicopter relies on the rotor system as the aircraft of the lift and steering mechanism, which rotor system corresponds to the wings, ailerons, elevators and propellers of a fixed wing aircraft. The transmission system is used as a power transmission component and is used for transmitting power provided by the engine to a rotor system and other components so as to drive the helicopter to fly. Therefore, the rotor system, the transmission system and the engine are three major moving parts of the helicopter, and the performance of the three major parts directly influences the performance and the reliability of the helicopter.
Each monitoring object comprises a plurality of monitoring components, for example, the monitoring components of the rotor system comprise a main rotor, a tail rotor and the like, the monitoring components of the transmission system comprise gears, shafts, bearings and the like, and the monitoring components of the engine are the engine per se.
According to the type of the monitoring component and the event trigger condition, firstly, the group acquisition trigger events are classified into a plurality of categories, in the embodiment, the categories of the group acquisition trigger events mainly include 5 categories of manual RTB (group acquisition trigger event category manually operated by a pilot), engine starting, rotor RTB (event category for performing group acquisition triggered by condition judgment through flight parameters), transmission system and engine stability, and secondly, each category of the group acquisition trigger events comprises a plurality of specific group acquisition trigger events, for example, the categories of the manual RTB group acquisition trigger events include a plurality of group acquisition trigger events such as pilot operation-ground, pilot operation-hovering, pilot operation-small speed level flight, pilot operation-large speed level flight and the like. The rotor RTB grouping acquisition trigger event category comprises a plurality of grouping acquisition trigger events such as ground small pitch, hovering, small-speed level flight, large-speed level flight and the like. The class of driveline group acquisition trigger events includes cruise and other group acquisition trigger events. Engine start includes engine start, etc. group acquisition trigger events. The engine stabilization includes a group acquisition trigger event such as engine start stabilization, where the group acquisition trigger event refers to the state of the engine reaching a steady state after a period of engine start.
S2, grouping the monitoring channels according to the monitoring components to obtain an acquisition group;
the sensor collects monitoring data on each monitoring part of a monitoring object, and transmits the collected monitoring data to the collector, namely a monitoring channel is formed. Each monitoring unit may have multiple types of sensors, and there may be multiple sensors of a certain type, for example, multiple vibration sensors, azimuth sensors, and rotor track sensors mounted on the main rotor for detecting the vibration, azimuth, and rotor track conditions on the main rotor, respectively, so that the monitoring channels of the main rotor include a main rotor vibration monitoring channel, a main rotor azimuth monitoring channel, a main rotor track monitoring channel, and the like.
Because the types and the rotating speeds of the monitoring components are different, the lengths of the monitoring channels and the collected monitoring data are determined to be different, so that the monitoring channels are grouped, and the required data length can be ensured to be collected according to the actual conditions of the monitoring components.
The monitoring channels are grouped, so that when a group acquisition triggering event occurs, data information of one or some monitoring components can be acquired in a targeted mode.
The grouping principle of the acquisition grouping comprises the following two points:
firstly, the monitoring channels for monitoring the monitoring components of the same type are classified into a group, and if the monitoring channels for monitoring the rotor wing are classified into a group, the monitoring channels for monitoring the engine are classified into a group according to table 1.
And secondly, grouping the monitoring channels of the monitoring components with the same or similar rotating speeds into a group. Referring to table 1, for example, the monitoring channels of the tail transmission shaft with the same rotating speed are grouped into one group; grouping the monitoring channels with similar rotating speeds of the transmission system and middle and tail reduction into a group; monitoring channels of accessory casings with similar rotating speeds in a transmission system are grouped, and the like.
Referring to table 1, each collection packet includes a packet name and a packet number.
TABLE 1
And S3, when a grouping collection triggering event occurs, collecting monitoring data by utilizing the collection grouping.
Specifically, since the helicopter has a long flight time, all monitoring channels continuously acquire monitoring data in the whole flight process, and after the flight is finished, a large amount of acquired monitoring data needs to be downloaded, decoded and analyzed, so that a CI curve capable of reflecting the health condition of the helicopter is obtained.
Based on the above reasons, the present application defines the grouping acquisition trigger event and the acquisition grouping, see table 1, and when one or some grouping acquisition trigger events occur, the corresponding acquisition grouping is triggered to acquire the monitoring data on the corresponding monitoring component, so that only the monitoring data in the stable operating state of the helicopter is acquired, the monitoring data in the unstable operating state is not acquired, the storage amount and the calculation amount of the monitoring data are reduced, and the operating efficiency is improved.
As a further optional implementation, a helicopter data acquisition method further includes the steps of:
and S4, processing the monitoring data.
Specifically, the time domain averaging algorithm can extract a specific frequency component from the complex component signal, thereby effectively improving the signal-to-noise ratio. Therefore, the monitoring data acquired by the acquired packets are preprocessed on the machine by adopting a time domain synchronous averaging algorithm, so that the stored data volume can be further reduced, and meanwhile, the calculation speed of the CI curve of the ground station and the data analysis efficiency are improved.
As a further optional implementation, a helicopter data acquisition method further includes the steps of:
and S5, determining the priority of the packet acquisition triggering event.
Specifically, each grouping acquisition trigger event triggers a corresponding acquisition grouping to acquire monitoring data, and when a plurality of grouping acquisition trigger events occur, data processing congestion is caused due to large data volume of the monitoring data acquired at the same time, and efficiency of data acquisition and data processing is reduced.
In a particular embodiment, the packet acquisition trigger event categories are prioritized by setting a first level priority, and the packet acquisition trigger events under each packet acquisition trigger event category are prioritized by setting a second level priority. For example, one level of priority may set manual TRB highest, the priority for engine start-up second, rotor RTB, drive train, engine stabilization may set continuous loop acquisition. When several group acquisition trigger events under a certain group acquisition trigger event category occur simultaneously, the priority level of the acquisition group trigger event corresponding to the acquisition group with the front group acquisition number can be set to be higher, and after the acquisition of the monitoring data of the acquisition group with the front group acquisition number is finished, the acquisition group with the back group acquisition number is executed to acquire the monitoring data.
In a certain group acquisition trigger event category, when the acquisition of the monitoring data of the acquisition group is being performed, if the working state of the helicopter changes (that is, the group acquisition trigger event changes), the behavior of acquiring the monitoring data of the acquisition group with the current priority will exit or be interrupted, then:
if the collection behavior of the current collection packet is interrupted by the type of the packet collection trigger event with high priority, the monitoring data collected by the current collection packet is discarded (because the cache needs to be emptied for storing the high-priority collection data);
if the current grouping collection is quitting (the working state of the helicopter does not meet the current grouping collection conditions, including not meeting the collection conditions of all the collection groups, meeting the collection conditions of the collection groups with low priority, or meeting the collection conditions of other collection groups with the same priority), the processing and the storage of the collected data of the current grouping are preferably finished;
when the original exit or interrupted packet acquisition trigger event is re-entered, acquisition of monitoring data should be performed sequentially starting from the last outstanding acquisition packet.
As a further optional implementation, a helicopter data acquisition method further includes the steps of:
and S6, determining the sampling frequency of the monitoring channel.
Specifically, among the prior art, the sampling frequency of the monitoring data of gathering the helicopter is lower, only several kilohertz, and all vibration channel's sampling frequency is the same, like this, only can monitor the rotor system of helicopter, the lower parts of rotational speed such as engine and transmission system's transmission shaft, the inside high-speed moving gear of transmission system, parts such as bearing, the monitoring data can not be gathered, consequently, this application sets up vibration channel's sampling frequency according to monitoring part's characteristic, thereby gather suitable monitoring data, do benefit to subsequent data analysis and processing.
In view of the above, the present application is directed to a specific monitoring component for which a specific and suitable sampling frequency is set. In a specific embodiment, according to the requirements of gear vibration monitoring and state index calculation, each tooth acquires data of 8 points at minimum, namely the minimum sampling frequency of a vibration channel of a monitoring gear is eight times of the gear meshing frequency; monitoring the vibration channel of the shaft according to a sampling theorem when the shaft monitoring frequency reaches 2-order rotation frequency, wherein the minimum sampling frequency rate is 2.56 times of the monitoring frequency; extracting bearing fault characteristic frequency by adopting a high-frequency demodulation algorithm in bearing vibration monitoring, wherein the minimum sampling frequency of vibration channel data of the monitored bearing is 102400 Hz; the rotor wing system monitors 2 times of rotor wing passing frequency, according to the sampling theorem, the sampling frequency meets the monitoring frequency of 2 times of rotor wing frequency, and the requirement that the precision of the dynamic balance phase is not more than 3 degrees when dynamic balance processing is carried out is compatible, namely the minimum sampling frequency is the maximum value of the two; the vibration channel for monitoring the engine meets the requirement of monitoring the rotating speed of a gas turbine, the rotating speed of a power turbine and an effective value of the engine, and the minimum sampling frequency is the maximum value of the three.
As a further optional implementation, a helicopter data acquisition method further includes the steps of:
and S7, determining the sampling time of the acquisition packet.
Specifically, different monitoring components determine the time for collecting the grouped monitoring data of the monitoring components, allocate proper collecting time for one collecting group, collect the monitoring data with proper data quantity, and solve the problems of excessive consumption of computing resources caused by overlarge data quantity and difficulty in reflecting the real condition of the helicopter due to small data quantity. In a specific embodiment, the acquisition time of the acquisition packet is:
the collecting time of the collecting groups of the rotor wing body, the gear and the shaft is the product of the time of one rotation of the rotating component and the number of rotations, the time of one rotation of the rotating component is the time of one rotation of the rotating component which rotates slowest in the collecting groups, the number of rotations is the number of time domain synchronous average turns, the time domain synchronous average needs to divide the vibration signal according to each rotation of the rotating component, then all the turns are added and averaged, and the total number of the collecting turns needing to be collected is the total number of turns obtained after the vibration signal is divided by a time domain synchronous average method, namely the number of the time domain synchronous average turns; according to the length required by analysis, determining the sampling time of the collection group of the bearing to be 2 s; the sampling time of the collection group of the engine starting is the time required by the whole starting process of the engine under the engine starting condition; the acquisition time of the engine-stable acquisition packet was 2s, according to the length required for the analysis.
Next, a helicopter data acquisition system proposed according to an embodiment of the present invention is described with reference to the drawings.
Fig. 2 is a schematic structural diagram of a helicopter data acquisition system according to an embodiment of the present invention.
The system specifically comprises:
an event determining module 201, configured to determine a group acquisition trigger event according to the monitoring component;
the grouping determination module 202 is used for grouping the monitoring channels according to the monitoring components to obtain an acquisition grouping;
and the data acquisition module 203 is used for acquiring the monitoring data by utilizing the acquisition packets when the packet acquisition trigger event occurs.
As a further optional implementation, the system further comprises:
and the data processing module 204 is configured to process the monitoring data.
As a further optional implementation, the system further comprises:
a priority determination module 205, configured to determine a priority of the packet acquisition trigger event.
It can be seen that the contents in the foregoing method embodiments are all applicable to this system embodiment, the functions specifically implemented by this system embodiment are the same as those in the foregoing method embodiment, and the advantageous effects achieved by this system embodiment are also the same as those achieved by the foregoing method embodiment.
Referring to fig. 3, an embodiment of the present invention provides a helicopter data acquisition apparatus, including:
at least one processor 301;
at least one memory 302 for storing at least one program;
a helicopter data acquisition method that when executed by at least one processor 301 causes the at least one processor 301 to implement.
Similarly, the contents of the method embodiments are all applicable to the apparatus embodiments, the functions specifically implemented by the apparatus embodiments are the same as the method embodiments, and the beneficial effects achieved by the apparatus embodiments are also the same as the beneficial effects achieved by the method embodiments.
In alternative embodiments, the functions/acts noted in the block diagrams may occur out of the order noted in the operational illustrations. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality/acts involved. Furthermore, the embodiments presented and described in the flow charts of the present invention are provided by way of example in order to provide a more thorough understanding of the technology. The disclosed methods are not limited to the operations and logic flows presented herein. Alternative embodiments are contemplated in which the order of various operations is changed and in which sub-operations described as part of larger operations are performed independently.
Furthermore, although the present invention is described in the context of functional modules, it should be understood that, unless otherwise stated to the contrary, one or more of the described functions and/or features may be integrated in a single physical device and/or software module, or one or more functions and/or features may be implemented in a separate physical device or software module. It will also be appreciated that a detailed discussion of the actual implementation of each module is not necessary for an understanding of the present invention. Rather, the actual implementation of the various functional modules in the apparatus disclosed herein will be understood within the ordinary skill of an engineer, given the nature, function, and internal relationship of the modules. Accordingly, those skilled in the art can, using ordinary skill, practice the invention as set forth in the claims without undue experimentation. It is also to be understood that the specific concepts disclosed are merely illustrative of and not intended to limit the scope of the invention, which is defined by the appended claims and their full scope of equivalents.
The functions, if implemented in the form of software functional units and sold or used as a stand-alone product, may be stored in a computer readable storage medium. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a Random Access Memory (RAM), a magnetic disk or an optical disk, and other various media capable of storing program codes.
The logic and/or steps represented in the flowcharts or otherwise described herein, e.g., an ordered listing of executable instructions that can be considered to implement logical functions, can be embodied in any computer-readable medium for use by or in connection with an instruction execution system, apparatus, or device, such as a computer-based system, processor-containing system, or other system that can fetch the instructions from the instruction execution system, apparatus, or device and execute the instructions. For the purposes of this description, a "computer-readable medium" can be any means that can contain, store, communicate, propagate, or transport the program for use by or in connection with the instruction execution system, apparatus, or device.
More specific examples (a non-exhaustive list) of the computer-readable medium would include the following: an electrical connection (electronic device) having one or more wires, a portable computer diskette (magnetic device), a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber device, and a portable compact disc read-only memory (CDROM). Additionally, the computer-readable medium could even be paper or another suitable medium upon which the program is printed, as the program can be electronically captured, via for instance optical scanning of the paper or other medium, then compiled, interpreted or otherwise processed in a suitable manner if necessary, and then stored in a computer memory.
It should be understood that portions of the present invention may be implemented in hardware, software, firmware, or a combination thereof. In the above embodiments, the various steps or methods may be implemented in software or firmware stored in memory and executed by a suitable instruction execution system. For example, if implemented in hardware, as in another embodiment, any one or combination of the following techniques, which are known in the art, may be used: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, an application specific integrated circuit having an appropriate combinational logic gate circuit, a Programmable Gate Array (PGA), a Field Programmable Gate Array (FPGA), or the like.
In the foregoing description of the specification, reference to the description of "one embodiment/example," "another embodiment/example," or "certain embodiments/examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
While embodiments of the present invention have been shown and described, it will be understood by those of ordinary skill in the art that: various changes, modifications, substitutions and alterations can be made to the embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the claims and their equivalents.
While the preferred embodiments of the present invention have been illustrated and described, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (10)
1. A helicopter data acquisition method is characterized by comprising the following steps:
determining a packet acquisition trigger event according to a monitoring component;
grouping the monitoring channels according to the monitoring components to obtain an acquisition group;
when a packet acquisition trigger event occurs, acquiring monitoring data by using the acquisition packets.
2. A helicopter data acquisition method according to claim 1 further comprising the steps of:
and processing the monitoring data.
3. A helicopter data acquisition method according to claim 1 further comprising the steps of:
determining a priority of the packet acquisition trigger event.
4. A helicopter data acquisition method according to claim 1 further comprising the steps of:
determining a sampling frequency of the monitoring channel.
5. A helicopter data acquisition method according to claim 1 further comprising the steps of:
a sampling time of the acquisition packet is determined.
6. A helicopter data acquisition system comprising:
an event determination module for determining a packet acquisition trigger event according to the monitoring component;
the grouping determination module is used for grouping the monitoring channels according to the monitoring components to obtain an acquisition grouping;
and the data acquisition module is used for acquiring monitoring data by utilizing the acquisition grouping when a grouping acquisition triggering event occurs.
7. A helicopter data acquisition system according to claim 6 further comprising:
and the data processing module is used for processing the monitoring data.
8. A helicopter data acquisition system according to claim 6 further comprising:
and the priority determining module is used for determining the priority of the packet acquisition triggering event.
9. A helicopter data acquisition system apparatus, comprising:
at least one processor;
at least one memory for storing at least one program;
when executed by the at least one processor, cause the at least one processor to implement a helicopter data acquisition testing method as defined in any one of claims 1-5.
10. A storage medium having stored therein a program executable by a processor, characterized in that: the processor executable program when executed by a processor is for implementing a helicopter data acquisition method as claimed in any one of claims 1 to 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011037797.4A CN112215982A (en) | 2020-09-28 | 2020-09-28 | Helicopter data acquisition method, system, device and storage medium |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011037797.4A CN112215982A (en) | 2020-09-28 | 2020-09-28 | Helicopter data acquisition method, system, device and storage medium |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112215982A true CN112215982A (en) | 2021-01-12 |
Family
ID=74052079
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011037797.4A Pending CN112215982A (en) | 2020-09-28 | 2020-09-28 | Helicopter data acquisition method, system, device and storage medium |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112215982A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963533A (en) * | 2012-12-14 | 2013-03-13 | 中国航空工业集团公司上海航空测控技术研究所 | Helicopter health and usage monitoring system (HUMS) and method thereof |
| CN105741381A (en) * | 2016-01-28 | 2016-07-06 | 中国人民解放军空军装备研究院航空装备研究所 | Method for confirming flight-parameter recording parameter set of airplane |
| CN109743344A (en) * | 2018-10-12 | 2019-05-10 | 比亚迪股份有限公司 | The event storage method and its equipment of comprehensive monitoring system based on rail traffic |
| EP3518062A2 (en) * | 2016-03-08 | 2019-07-31 | Harris Corporation | Wireless engine monitoring system of an aircraft |
| CN110233776A (en) * | 2019-05-31 | 2019-09-13 | 湃方科技(北京)有限责任公司 | A kind of rotary-type mechanical equipment state monitoring method and equipment |
| CN110582802A (en) * | 2017-03-24 | 2019-12-17 | 深圳市大疆创新科技有限公司 | Vehicle behavior monitoring system and method |
| CN110654399A (en) * | 2018-06-29 | 2020-01-07 | 比亚迪股份有限公司 | System monitoring method and device |
| CN110992516A (en) * | 2018-10-03 | 2020-04-10 | 美光科技公司 | Automatic collection of autonomous vehicle recorded data |
| CN111361758A (en) * | 2018-12-07 | 2020-07-03 | 波音公司 | Method and system for determining whether to perform aircraft maintenance |
-
2020
- 2020-09-28 CN CN202011037797.4A patent/CN112215982A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102963533A (en) * | 2012-12-14 | 2013-03-13 | 中国航空工业集团公司上海航空测控技术研究所 | Helicopter health and usage monitoring system (HUMS) and method thereof |
| CN105741381A (en) * | 2016-01-28 | 2016-07-06 | 中国人民解放军空军装备研究院航空装备研究所 | Method for confirming flight-parameter recording parameter set of airplane |
| EP3518062A2 (en) * | 2016-03-08 | 2019-07-31 | Harris Corporation | Wireless engine monitoring system of an aircraft |
| CN110582802A (en) * | 2017-03-24 | 2019-12-17 | 深圳市大疆创新科技有限公司 | Vehicle behavior monitoring system and method |
| CN110654399A (en) * | 2018-06-29 | 2020-01-07 | 比亚迪股份有限公司 | System monitoring method and device |
| CN110992516A (en) * | 2018-10-03 | 2020-04-10 | 美光科技公司 | Automatic collection of autonomous vehicle recorded data |
| CN109743344A (en) * | 2018-10-12 | 2019-05-10 | 比亚迪股份有限公司 | The event storage method and its equipment of comprehensive monitoring system based on rail traffic |
| CN111361758A (en) * | 2018-12-07 | 2020-07-03 | 波音公司 | Method and system for determining whether to perform aircraft maintenance |
| CN110233776A (en) * | 2019-05-31 | 2019-09-13 | 湃方科技(北京)有限责任公司 | A kind of rotary-type mechanical equipment state monitoring method and equipment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109083747B (en) | Hybrid electric propulsion system, method of evaluating engine, and evaluation control system | |
| EP3171142A1 (en) | Systems and methods for monitoring gearbox health by vibration | |
| CN105865793B (en) | A kind of method for improving more rotor vibration monitoring of aero-engine precision | |
| CN106769033A (en) | Variable speed rolling bearing fault recognition methods based on order envelope time-frequency energy spectrum | |
| CN109682597A (en) | A kind of gear-box vibration signal processing and analysis method | |
| CN103595327A (en) | Experiment estimation method of motor rotational inertia in electrical drive system | |
| CN110262559A (en) | A kind of unmanned plane method for security protection, device and unmanned plane | |
| CN111060277A (en) | Helicopter tail rotor simulation test device and vortex ring verification method | |
| CN112215982A (en) | Helicopter data acquisition method, system, device and storage medium | |
| US10444254B2 (en) | Virtual tachometers based on time series filtering | |
| CN110388302A (en) | The data exception detection method and equipment of wind-driven generator | |
| CN108087121A (en) | A kind of aero-engine eccentric contract | |
| CN108494292A (en) | Motor control method and device | |
| US20180045791A1 (en) | Power supply condition monitor | |
| CN206192657U (en) | Bearing failure diagnostic equipment | |
| US20160076931A1 (en) | Assembly and method of component monitoring | |
| CN102410436A (en) | Bearing self-lubricating method and device for feedback control based on rotary encoder | |
| CN110470265B (en) | Synchronous acquisition method for blade tip clearance and blade tip timing data based on FPGA and DSP | |
| CN117842372A (en) | Helicopter vibration data acquisition and processing method, system, equipment and medium | |
| CN102798519A (en) | System and method for monitoring health of airfoils | |
| CN105929198B (en) | High stability based on principle of inertia predicts rotating speed measurement method in real time | |
| CN112298584B (en) | Helicopter main speed reducer rotating speed vibration data synchronization and fusion method | |
| CN108520093A (en) | A kind of Trouble Diagnostic Method of Machinery Equipment and device in knowledge based library | |
| EP1300668A1 (en) | Method for the separation of epicyclic planet gear vibration signatures | |
| EP3868659A1 (en) | Power margin monitoring device for rotorcraft, associated rotorcraft and corresponding method |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210112 |