CN117009908A - Flight abnormal state identification and prediction system and method - Google Patents
Flight abnormal state identification and prediction system and method Download PDFInfo
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- CN117009908A CN117009908A CN202311237715.4A CN202311237715A CN117009908A CN 117009908 A CN117009908 A CN 117009908A CN 202311237715 A CN202311237715 A CN 202311237715A CN 117009908 A CN117009908 A CN 117009908A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000001514 detection method Methods 0.000 claims description 85
- 238000007790 scraping Methods 0.000 claims description 22
- 238000007664 blowing Methods 0.000 claims description 9
- 230000005856 abnormality Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 6
- 238000004590 computer program Methods 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 abstract description 3
- 238000012545 processing Methods 0.000 abstract description 2
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- 238000013480 data collection Methods 0.000 description 1
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- 230000007257 malfunction Effects 0.000 description 1
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F18/00—Pattern recognition
- G06F18/20—Analysing
- G06F18/24—Classification techniques
- G06F18/243—Classification techniques relating to the number of classes
- G06F18/2433—Single-class perspective, e.g. one-against-all classification; Novelty detection; Outlier detection
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F18/00—Pattern recognition
- G06F18/20—Analysing
- G06F18/22—Matching criteria, e.g. proximity measures
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F18/00—Pattern recognition
- G06F18/20—Analysing
- G06F18/25—Fusion techniques
- G06F18/254—Fusion techniques of classification results, e.g. of results related to same input data
- G06F18/256—Fusion techniques of classification results, e.g. of results related to same input data of results relating to different input data, e.g. multimodal recognition
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- 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
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
Abstract
The invention relates to a flight abnormal state identification and prediction system and a method, which belong to the technical field of electric digital data processing, and are used for designing a set of aircraft flight state abnormal identification and prediction scheme aiming at the influence of blocking force when in heavy rain or strong wind weather, wherein the actual flight height is not matched with the target flight height, the actual flight angle is not matched with the target flight angle and the like.
Description
Technical Field
The invention belongs to the technical field of electric digital data processing, and particularly relates to a flight abnormal state identification and prediction system and method.
Background
At present, the aircraft is very common to collect relevant data from a position with a severe environment, and when the aircraft performs a data collection task, the aircraft can hover in the air and continuously collect relevant data at fixed points for a long time.
When the environment of the aircraft is extremely severe, the flight state of the aircraft may be abnormal; such as: the aircraft adjusts the flying height and the flying angle of the aircraft according to the control instruction; however, if it is affected by a strong force in a heavy rain or a strong wind, the actual flying height does not match with the target flying height, the actual flying angle does not match with the target flying angle, etc., resulting in an abnormal flying state of the aircraft.
Therefore, a system, a method and a storage medium for identifying and predicting abnormal flight states are needed to solve the above problems.
Disclosure of Invention
The invention aims to provide a flight abnormal state identification and prediction system, a method and a storage medium, which are used for solving the technical problems in the prior art, and an aircraft adjusts the flight height and the flight angle of the aircraft according to a control instruction; however, if it is affected by a strong force in a heavy rain or a strong wind, the actual flying height does not match with the target flying height, the actual flying angle does not match with the target flying angle, etc., resulting in an abnormal flying state of the aircraft.
In order to achieve the above purpose, the technical scheme of the invention is as follows:
the flight abnormal state identification and prediction system comprises a rainfall intensity detection device, a wind-blowing intensity detection device, a height instruction acquisition device, an angle instruction acquisition device, an actual height detection device, an actual angle detection device and a main control device, wherein the main control device is respectively connected with the rainfall intensity detection device, the wind-blowing intensity detection device, the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device;
the rainfall intensity detection device is used for detecting whether rainfall intensity of the environment where the aircraft is located is abnormal or not;
the wind-scraping intensity detection device is used for detecting whether the wind-scraping intensity of the environment where the aircraft is located is abnormal or not;
the altitude command acquisition device is used for detecting the flight altitude corresponding to the control command executed by the current aircraft and recording the flight altitude as a target flight altitude;
the angle instruction acquisition device is used for detecting a flight angle corresponding to a control instruction executed by the current aircraft and recording the flight angle as a target flight angle;
the actual height detection device is used for detecting the actual flying height of the current aircraft;
the actual angle detection device is used for detecting the actual flight angle of the current aircraft;
the main control device is used for controlling the running states of the rainfall intensity detection device, the wind-scraping intensity detection device, the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device.
Further, the main control device controls the running states of the rainfall intensity detection device and the wind-scraping intensity detection device to be normally open, and controls the running states of the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device to be normally closed;
when the rainfall intensity detection device detects that the rainfall intensity of the environment where the aircraft is located is abnormal or the wind scraping intensity detection device detects that the wind scraping intensity of the environment where the aircraft is located is abnormal, the main control device controls the altitude command acquisition device, the angle command acquisition device, the actual altitude detection device and the actual angle detection device to be started;
and if the target flying height is not matched with the actual flying height or the target flying angle is not matched with the actual flying angle, the main control device judges that the aircraft is in a flying abnormal state caused by severe weather.
Further, the rainfall intensity detection device comprises a rainfall sensor, a first processor and a first memory, wherein the first processor is respectively connected with the rainfall sensor, the first memory and the main control device;
the rainfall sensor is used for detecting real-time rainfall data of the environment where the aircraft is located;
the first memory is used for storing preset rainfall data of the environment where the aircraft is located;
the first processor is used for comparing and analyzing the real-time rainfall data with the preset rainfall data, and if the real-time rainfall data and the preset rainfall data are matched, the first processor feeds back rainfall intensity abnormality of the environment where the aircraft is located to the main control device.
Further, the rainfall intensity detection device further comprises a pressure-bearing sensor, and the pressure-bearing sensor is connected with the first processor;
the pressure-bearing sensor is used for detecting real-time pressure-bearing data of the top of the aircraft;
the first storage is further used for storing preset pressure-bearing data of the top of the aircraft, wherein the preset pressure-bearing data are pressure-bearing data of the top of the aircraft when rainfall intensity of the environment where the aircraft is located is the preset rainfall data;
the first processor controls the pressure-bearing sensor to be normally closed;
when the real-time rainfall data is matched with the preset rainfall data, the first processor controls the pressure-bearing sensor to be started;
if the real-time pressure-bearing data is not matched with the preset pressure-bearing data, the first processor feeds back rainfall intensity judgment abnormality to the main control device.
Further, the wind-scraping intensity detection device comprises a wind sensor, a second processor and a second memory, wherein the second processor is respectively connected with the wind sensor, the second memory and the main control device;
the wind sensor is used for detecting real-time wind power data of the environment where the aircraft is located;
the second memory is used for storing preset wind power data of the environment where the aircraft is located;
the second processor is used for comparing and analyzing the real-time wind power data with the preset wind power data, and if the real-time wind power data and the preset wind power data are matched, the second processor feeds back the abnormal wind scraping intensity of the environment where the aircraft is located to the main control device.
Further, the system also comprises a wireless communication device and a remote intelligent terminal, wherein the main control device is connected with the remote intelligent terminal through the wireless communication device in a network manner.
A method for identifying and predicting the abnormal flight state adopts the system for identifying and predicting the abnormal flight state.
A storage medium having stored thereon a computer program which, when executed, performs a method of identifying and predicting a flight anomaly condition as described above.
Compared with the prior art, the invention has the following beneficial effects:
one of the beneficial effects of this scheme lies in, when weather is heavy rain or strong wind, the influence of the blocking force, its actual flight altitude and target flight altitude mismatch, actual flight angle and target flight angle mismatch etc. "design a set of aircraft flight condition unusual discernment and prediction scheme, through rainfall intensity detection device, wind-force intensity detection device, altitude command acquisition device, angle command acquisition device, actual altitude detection device, the orderly cooperation action between the actual angle detection device, can avoid most devices to be in invalid action state for a long time, reduce the system energy consumption, simultaneously reduce the malfunction rate of system, ensure the reliability of the whole discernment of system and prediction result.
Drawings
Fig. 1 is a schematic system configuration diagram of the embodiment.
Fig. 2 is a schematic diagram of the system operation principle of the embodiment.
Detailed Description
For the purpose of making the technical solution and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and examples. It should be understood that the particular embodiments described herein are illustrative only and are not intended to limit the invention, i.e., the embodiments described are merely some, but not all, of the embodiments of the invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by a person skilled in the art without making any inventive effort, are intended to be within the scope of the present invention. It is noted that relational terms such as "first" and "second", and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions.
Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article or apparatus that comprises the element.
As shown in fig. 1, a flight abnormal state identifying and predicting system is provided, which comprises a rainfall intensity detecting device, a wind-blowing intensity detecting device, a height command acquiring device, an angle command acquiring device, an actual height detecting device, an actual angle detecting device and a main control device, wherein the main control device is respectively connected with the rainfall intensity detecting device, the wind-blowing intensity detecting device, the height command acquiring device, the angle command acquiring device, the actual height detecting device and the actual angle detecting device;
the rainfall intensity detection device is used for detecting whether rainfall intensity of the environment where the aircraft is located is abnormal or not;
the wind-scraping intensity detection device is used for detecting whether the wind-scraping intensity of the environment where the aircraft is located is abnormal or not;
the altitude command acquisition device is used for detecting the flight altitude corresponding to the control command executed by the current aircraft and recording the flight altitude as a target flight altitude;
the angle instruction acquisition device is used for detecting a flight angle corresponding to a control instruction executed by the current aircraft and recording the flight angle as a target flight angle;
the actual height detection device is used for detecting the actual flying height of the current aircraft;
the actual angle detection device is used for detecting the actual flight angle of the current aircraft;
the main control device is used for controlling the running states of the rainfall intensity detection device, the wind-scraping intensity detection device, the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device.
Further, as shown in fig. 2, the main control device controls the running states of the rainfall intensity detection device and the wind-blowing intensity detection device to be normally open, and controls the running states of the altitude command acquisition device, the angle command acquisition device, the actual altitude detection device and the actual angle detection device to be normally closed;
when the rainfall intensity detection device detects that the rainfall intensity of the environment where the aircraft is located is abnormal or the wind scraping intensity detection device detects that the wind scraping intensity of the environment where the aircraft is located is abnormal, the main control device controls the altitude command acquisition device, the angle command acquisition device, the actual altitude detection device and the actual angle detection device to be started;
and if the target flying height is not matched with the actual flying height or the target flying angle is not matched with the actual flying angle, the main control device judges that the aircraft is in a flying abnormal state caused by severe weather.
In the scheme, a set of aircraft flight state anomaly identification and prediction scheme is designed aiming at the influence of blocking force when in heavy rain or strong wind weather, namely, the actual flight height is not matched with the target flight height, the actual flight angle is not matched with the target flight angle and the like, and the orderly matching actions among a rainfall intensity detection device, a wind-blowing intensity detection device, a height instruction acquisition device, an angle instruction acquisition device, an actual height detection device and an actual angle detection device can be avoided, so that most devices are in an invalid action state for a long time, the system energy consumption is reduced, the false action rate of the system is reduced, and the reliability of the overall identification and prediction result of the system is guaranteed.
Further, the rainfall intensity detection device comprises a rainfall sensor, a first processor and a first memory, wherein the first processor is respectively connected with the rainfall sensor, the first memory and the main control device;
the rainfall sensor is used for detecting real-time rainfall data of the environment where the aircraft is located;
the first memory is used for storing preset rainfall data of the environment where the aircraft is located;
the first processor is used for comparing and analyzing the real-time rainfall data with the preset rainfall data, and if the real-time rainfall data and the preset rainfall data are matched, the first processor feeds back rainfall intensity abnormality of the environment where the aircraft is located to the main control device.
Further, the rainfall intensity detection device further comprises a pressure-bearing sensor, and the pressure-bearing sensor is connected with the first processor;
the pressure-bearing sensor is used for detecting real-time pressure-bearing data of the top of the aircraft;
the first storage is further used for storing preset pressure-bearing data of the top of the aircraft, wherein the preset pressure-bearing data are pressure-bearing data of the top of the aircraft when rainfall intensity of the environment where the aircraft is located is the preset rainfall data;
the first processor controls the pressure-bearing sensor to be normally closed;
when the real-time rainfall data is matched with the preset rainfall data, the first processor controls the pressure-bearing sensor to be started;
if the real-time pressure-bearing data is not matched with the preset pressure-bearing data, the first processor feeds back rainfall intensity judgment abnormality to the main control device.
In the above scheme, considering that the rainfall intensity detection device adopts a single rainfall sensor as a judgment standard, the detection accuracy is possibly insufficient, therefore, the pressure-bearing sensor and the rainfall sensor are designed to cooperate, the reliability of the detection result of the rainfall intensity detection device can be greatly improved by double judgment, and the misoperation rate of the system is further reduced.
Further, the wind-scraping intensity detection device comprises a wind sensor, a second processor and a second memory, wherein the second processor is respectively connected with the wind sensor, the second memory and the main control device;
the wind sensor is used for detecting real-time wind power data of the environment where the aircraft is located;
the second memory is used for storing preset wind power data of the environment where the aircraft is located;
the second processor is used for comparing and analyzing the real-time wind power data with the preset wind power data, and if the real-time wind power data and the preset wind power data are matched, the second processor feeds back the abnormal wind scraping intensity of the environment where the aircraft is located to the main control device.
Further, the remote data transmission system also comprises a wireless communication device and a remote intelligent terminal, wherein the main control device is connected with the remote intelligent terminal through the wireless communication device in a network manner, so that remote data transmission is realized.
A method for identifying and predicting the abnormal flight state adopts the system for identifying and predicting the abnormal flight state.
A storage medium having stored thereon a computer program which, when executed, performs a method of identifying and predicting a flight anomaly condition as described above.
The above is a preferred embodiment of the present invention, and all changes made according to the technical solution of the present invention belong to the protection scope of the present invention when the generated functional effects do not exceed the scope of the technical solution of the present invention.
Claims (8)
1. The flight abnormal state identification and prediction system is characterized by comprising a rainfall intensity detection device, a wind-blowing intensity detection device, a height instruction acquisition device, an angle instruction acquisition device, an actual height detection device, an actual angle detection device and a main control device, wherein the main control device is respectively connected with the rainfall intensity detection device, the wind-blowing intensity detection device, the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device;
the rainfall intensity detection device is used for detecting whether rainfall intensity of the environment where the aircraft is located is abnormal or not;
the wind-scraping intensity detection device is used for detecting whether the wind-scraping intensity of the environment where the aircraft is located is abnormal or not;
the altitude command acquisition device is used for detecting the flight altitude corresponding to the control command executed by the current aircraft and recording the flight altitude as a target flight altitude;
the angle instruction acquisition device is used for detecting a flight angle corresponding to a control instruction executed by the current aircraft and recording the flight angle as a target flight angle;
the actual height detection device is used for detecting the actual flying height of the current aircraft;
the actual angle detection device is used for detecting the actual flight angle of the current aircraft;
the main control device is used for controlling the running states of the rainfall intensity detection device, the wind-scraping intensity detection device, the height instruction acquisition device, the angle instruction acquisition device, the actual height detection device and the actual angle detection device.
2. The system for identifying and predicting abnormal flight conditions according to claim 1, wherein the main control device controls the running states of the rainfall intensity detection device and the wind-blowing intensity detection device to be normally open, and controls the running states of the altitude command acquisition device, the angle command acquisition device, the actual altitude detection device and the actual angle detection device to be normally closed;
when the rainfall intensity detection device detects that the rainfall intensity of the environment where the aircraft is located is abnormal or the wind scraping intensity detection device detects that the wind scraping intensity of the environment where the aircraft is located is abnormal, the main control device controls the altitude command acquisition device, the angle command acquisition device, the actual altitude detection device and the actual angle detection device to be started;
and if the target flying height is not matched with the actual flying height or the target flying angle is not matched with the actual flying angle, the main control device judges that the aircraft is in a flying abnormal state caused by severe weather.
3. The system for identifying and predicting abnormal flight conditions according to claim 2, wherein the rainfall intensity detection device comprises a rainfall sensor, a first processor and a first memory, and the first processor is respectively connected with the rainfall sensor, the first memory and a main control device;
the rainfall sensor is used for detecting real-time rainfall data of the environment where the aircraft is located;
the first memory is used for storing preset rainfall data of the environment where the aircraft is located;
the first processor is used for comparing and analyzing the real-time rainfall data with the preset rainfall data, and if the real-time rainfall data and the preset rainfall data are matched, the first processor feeds back rainfall intensity abnormality of the environment where the aircraft is located to the main control device.
4. A flight anomaly identification and prediction system according to claim 3 wherein the rainfall intensity detection device further comprises a pressure sensor, the pressure sensor being coupled to the first processor;
the pressure-bearing sensor is used for detecting real-time pressure-bearing data of the top of the aircraft;
the first storage is further used for storing preset pressure-bearing data of the top of the aircraft, wherein the preset pressure-bearing data are pressure-bearing data of the top of the aircraft when rainfall intensity of the environment where the aircraft is located is the preset rainfall data;
the first processor controls the pressure-bearing sensor to be normally closed;
when the real-time rainfall data is matched with the preset rainfall data, the first processor controls the pressure-bearing sensor to be started;
if the real-time pressure-bearing data is not matched with the preset pressure-bearing data, the first processor feeds back rainfall intensity judgment abnormality to the main control device.
5. The system for identifying and predicting abnormal flight conditions according to claim 4, wherein the wind-scraping intensity detection device comprises a wind sensor, a second processor and a second memory, and the second processor is respectively connected with the wind sensor, the second memory and the main control device;
the wind sensor is used for detecting real-time wind power data of the environment where the aircraft is located;
the second memory is used for storing preset wind power data of the environment where the aircraft is located;
the second processor is used for comparing and analyzing the real-time wind power data with the preset wind power data, and if the real-time wind power data and the preset wind power data are matched, the second processor feeds back the abnormal wind scraping intensity of the environment where the aircraft is located to the main control device.
6. The system for identifying and predicting abnormal flight conditions according to claim 5, further comprising a wireless communication device and a remote intelligent terminal, wherein the master control device is in network connection with the remote intelligent terminal through the wireless communication device.
7. A method for identifying and predicting abnormal states of flight, characterized in that the abnormal states of flight are identified and predicted by using an abnormal states of flight identification and prediction system according to any one of claims 1 to 6.
8. A storage medium having stored thereon a computer program which when executed performs a method of identifying and predicting a flight anomaly condition as claimed in claim 7.
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| CN117647285A (en) * | 2024-01-30 | 2024-03-05 | 四川川能智网实业有限公司 | Equipment operation monitoring system and method based on industrial Internet of things |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117268477A (en) * | 2023-11-22 | 2023-12-22 | 四川长虹云数信息技术有限公司 | Novel agricultural collector |
| CN117647285A (en) * | 2024-01-30 | 2024-03-05 | 四川川能智网实业有限公司 | Equipment operation monitoring system and method based on industrial Internet of things |
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