CN116385913B - Monitoring method and system based on image recognition - Google Patents
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Abstract
The application relates to a monitoring method and a system based on image recognition, which belong to the technical field of electric digital data processing, and aim at the situation that an aircraft is slightly inclined when the aircraft hovers because of external environment factors, the elements of an aircraft power system, historical data corresponding to external environment information, historical data corresponding to external force information and historical data of an external force balance instruction are correlatively bound, so that a technical model for solving the defects is established; the real-time external force information received by the aircraft is used as data input of the model, so that the corresponding real-time external force balance instruction is obtained by matching and is used as data output, and the defects can be overcome by the aircraft power system according to the real-time external force balance instruction. Aiming at the defect that the aircraft shell slightly inclines when the aircraft hovers due to external environment factors, the external environment factors are specifically exemplified by the raining state, so that the influence of raining on the aircraft hovering in the fixed-point image recognition is overcome.
Description
Technical Field
The application belongs to the technical field of electric digital data processing, and particularly relates to a monitoring method, device and system based on image recognition.
Background
At present, an aircraft is utilized to carry out aerial real-time monitoring on an environment pollution area and carry out gas sampling on polluted gas, laboratory gas analysis is convenient, the aircraft can break through the limit of space-time and dead angle-free monitoring, and the efficiency of environment-friendly inspection can be improved through the maneuverability and the rapidity of the aircraft.
Wherein, the aircraft may hover in the air, and related environmental data (such as fixed point image recognition and the like) need to be continuously collected. However, in the process, when the aircraft hovers, the aircraft is slightly inclined due to external environmental factors (such as in rainy days, the aircraft is beaten by rainwater, the volume of the aircraft is large, the stay amount of the rainwater forced to be borne by the aircraft is large, the rainwater does not vertically land, and the like), so that the aircraft cannot perform fixed-point image recognition and the like.
Therefore, a monitoring method, device and system based on image recognition are needed to be designed at present to solve the above problems.
Disclosure of Invention
The application aims to provide a monitoring method, a device and a system based on image recognition, which are used for solving the technical problems in the prior art, such as: the aircraft may hover in the air and continuously acquire relevant environmental data (such as fixed point image recognition and the like). However, in the process, when the aircraft hovers, the aircraft is slightly inclined due to external environmental factors (such as in rainy days, the aircraft is beaten by rainwater, the volume of the aircraft is large, the stay amount of the rainwater forced to be borne by the aircraft is large, the rainwater does not vertically land, and the like), so that the aircraft cannot perform fixed-point image recognition and the like.
In order to achieve the above purpose, the technical scheme of the application is as follows:
the monitoring method based on image recognition comprises the following steps:
s1: judging whether a hover instruction of the aircraft is executed, if yes, judging whether a fixed point image identification instruction of the aircraft is executed, and if yes, entering a step S2;
s2: acquiring external environment information of a current aircraft, and generating real-time external force information of the aircraft in a preset format according to the external environment information;
different external force information borne by the aircraft and external force balance instructions provided by an aircraft power system which are matched with the different external force information one by one are obtained through calculation and analysis of big data of historical statistics, and a plurality of external force balance instructions are constructed into an external force balance instruction library;
s3: mapping the real-time external force information to a matched real-time external force balance instruction through the external force balance instruction library;
s4: and the aircraft power system executes the real-time external force balance instruction.
Further, in step S2, the following is specifically described:
s201: judging whether the external environment of the current aircraft is in a raining state or not, if so, entering step S202;
s202: and generating the real-time external force information according to a preset format according to the condition that the current aircraft is hit by rainwater.
Further, in step S202, first real-time external force information is generated according to the rainfall information and the rainwater direction information of the falling rainwater;
generating second real-time external force information according to the aircraft stress sensing data;
and carrying out matching judgment on the first real-time external force information and the second real-time external force information, if the first real-time external force information and the second real-time external force information are matched, taking the first real-time external force information or the second real-time external force information as the current real-time external force information, otherwise, judging that the current real-time external force information is abnormal.
Further, when the current real-time external force information is judged to be abnormal;
acquiring corresponding matched real-time raining data through real-time weather table data according to the current geographic position information of the aircraft;
generating third real-time external force information according to the real-time raining data;
respectively carrying out matching judgment on the first real-time external force information and the second real-time external force information and the third real-time external force information, and respectively generating a first matching degree and a second matching degree;
if the first matching degree is higher than the second matching degree, the first real-time external force information is used as the current real-time external force information;
and if the first matching degree is lower than the second matching degree, taking the second real-time external force information as the current real-time external force information.
Further, in generating the second real-time external force information according to the aircraft stress sensing data, the method specifically comprises the following steps:
the first stress detection sensors are uniformly distributed on the surface of the aircraft shell in a fixed mode at intervals of two adjacent pairs;
generating the second real-time external force information according to the aircraft stress sensing data detected by the first stress detection sensors;
the first stress detection sensors are distributed in a uniform array at the centers of two adjacent intervals, and the second stress detection sensors are distributed in a uniform array at the centers of two adjacent intervals; the plurality of second detection sensors are in a closed state;
when the first matching degree is higher than the second matching degree;
starting the plurality of second detection sensors, and taking external force information generated by the aircraft stress sensing data detected by the second stress detection sensors as a detection standard;
if the second real-time external force information is matched with the inspection standard, the first stress detection sensors work normally;
and if the second real-time external force information is not matched with the inspection standard, the first stress detection sensors work abnormally.
Further, in step S3, if the real-time external force information cannot be mapped to the matched real-time external force balance instruction through the external force balance instruction library;
in step S2, generating real-time external force information received by the aircraft in a second preset format according to the external environment information;
in step S3, the integrated data identification processing end corresponding to the preset format and used for executing the mapping of the real-time external force information to the matched real-time external force balance instruction through the external force balance instruction library is replaced by the integrated data identification processing end corresponding to the second preset format.
And the monitoring device based on image recognition is used for carrying out data monitoring according to the monitoring method based on image recognition.
The monitoring system based on image recognition is used for carrying out data monitoring according to the monitoring method based on image recognition.
An electronic device comprising a processor and a memory for storing executable commands of the processor, the processor implementing the image recognition based monitoring method as described above by running the executable commands.
A storage medium having stored thereon a computer program which when executed performs a method of monitoring based on image recognition as described above.
Compared with the prior art, the application has the following beneficial effects:
the technical model for solving the defects is established by performing relevance binding on elements of an aircraft power system, historical data corresponding to external environment information, historical data corresponding to external force information and historical data of an external force balance instruction aiming at the defect that the aircraft is slightly inclined when the aircraft hovers due to external environment factors when the aircraft hovers; the real-time external force information received by the aircraft is used as data input of the model, so that the corresponding real-time external force balance instruction is obtained by matching and is used as data output, and the defects can be overcome by the aircraft power system according to the real-time external force balance instruction. Aiming at the defect that the aircraft shell slightly inclines when the aircraft hovers due to external environment factors, the external environment factors are specifically exemplified by the raining state, so that the influence of raining on the aircraft hovering in the fixed-point image recognition is overcome.
Drawings
Fig. 1 is a schematic flow chart of the steps in embodiment 1 of the present application.
Fig. 2 is a schematic diagram of data input for rainy conditions according to embodiment 1 of the present application.
Fig. 3 is a flow chart of the steps in embodiment 2 of the present application.
Fig. 4 is a flow chart of the steps in embodiment 3 of the present application.
Fig. 5 is a flow chart of the steps in embodiment 4 of the present application.
Fig. 6 is a distribution diagram of a force sensor array according to embodiment 4 of the present application.
Detailed Description
The following description of the embodiments of the present application will be made more fully with reference to the accompanying drawings, in which 1-6 are shown, it being apparent that the embodiments described are merely some, but not all embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
Example 1:
in the prior art, an aircraft may hover in the air, and related environment data (such as fixed point image recognition and the like) need to be continuously collected. However, in the process, when the aircraft hovers, the aircraft is slightly inclined due to external environmental factors (such as in rainy days, the aircraft is beaten by rainwater, the volume of the aircraft is large, the stay amount of the rainwater forced to be borne by the aircraft is large, the rainwater does not vertically land, and the like), so that the aircraft cannot perform fixed-point image recognition and the like.
As shown in fig. 1, a monitoring method based on image recognition is provided, which includes the following steps:
the monitoring method based on image recognition comprises the following steps:
s1: judging whether a hover instruction of the aircraft is executed, if yes, judging whether a fixed point image identification instruction of the aircraft is executed, and if yes, entering a step S2;
s2: acquiring external environment information of a current aircraft, and generating real-time external force information of the aircraft in a preset format according to the external environment information;
different external force information borne by the aircraft and external force balance instructions provided by an aircraft power system which are matched with the different external force information one by one are obtained through calculation and analysis of big data of historical statistics, and a plurality of external force balance instructions are constructed into an external force balance instruction library;
s3: mapping the real-time external force information to a matched real-time external force balance instruction through the external force balance instruction library;
s4: and the aircraft power system executes the real-time external force balance instruction.
In the scheme, aiming at the defect that the aircraft is slightly inclined when the aircraft hovers due to external environment factors, correlation binding is carried out on elements of the aircraft power system, historical data corresponding to external environment information, historical data corresponding to external force information and historical data of an external force balance instruction, so that a technical model for solving the defect is established; the real-time external force information received by the aircraft is used as data input of the model, so that the corresponding real-time external force balance instruction is obtained by matching and is used as data output, and the defects can be overcome by the aircraft power system according to the real-time external force balance instruction.
As shown in fig. 2, in step S2, the following is further specific:
s201: judging whether the external environment of the current aircraft is in a raining state or not, if so, entering step S202;
s202: and generating the real-time external force information according to a preset format according to the condition that the current aircraft is hit by rainwater.
According to the scheme, aiming at the defect that the aircraft shell is slightly inclined when the aircraft hovers due to the external environment factors, the external environment factors are specifically exemplified by the raining state, so that the influence of raining on the aircraft hovering in the fixed-point image recognition is overcome.
Example 2:
as shown in fig. 3, further, in step S202, first real-time external force information is generated according to the rainfall amount information and the rainwater direction information of the falling rainwater; taking external environment information of the aircraft as a reference standard; generating second real-time external force information according to the aircraft stress sensing data; taking actual stress information of the aircraft body as a reference standard;
and carrying out matching judgment on the first real-time external force information and the second real-time external force information, if the first real-time external force information and the second real-time external force information are matched, taking the first real-time external force information or the second real-time external force information as the current real-time external force information, otherwise, judging that the current real-time external force information is abnormal.
In the above scheme, the real-time external force information of the aircraft is generated according to the external environment information, and this step is extremely critical, and as data input, the error influence on the whole process may be caused to the greatest extent directly; therefore, the real-time external force information of the external environment information generating aircraft is divided into two different modes, and an inspection scheme is formed mutually, so that the accuracy of data input is ensured.
Example 3:
as shown in fig. 4, further, on the basis of embodiment 2, when it is determined that the current real-time external force information is abnormal;
acquiring corresponding matched real-time raining data through real-time weather table data according to the current geographic position information of the aircraft;
generating third real-time external force information according to the real-time raining data;
respectively carrying out matching judgment on the first real-time external force information and the second real-time external force information and the third real-time external force information, and respectively generating a first matching degree and a second matching degree;
if the first matching degree is higher than the second matching degree, the first real-time external force information is used as the current real-time external force information;
and if the first matching degree is lower than the second matching degree, taking the second real-time external force information as the current real-time external force information.
In the above-mentioned scheme, when it is determined that the current real-time external force information generates an abnormality, it is not clear which mode of data input is abnormal; therefore, a third way of generating real-time external force information is designed, i.e. obtained by means of weather table data; the third generation real-time external force information is used as a reference standard, so that the first two modes for generating the real-time external force information are clarified.
Example 4:
as shown in fig. 5, further, in generating the second real-time external force information according to the aircraft stress sensing data on the basis of embodiment 2, the specific steps are as follows:
the first stress detection sensors are uniformly distributed on the surface of the aircraft shell in a fixed mode at intervals of two adjacent pairs;
generating the second real-time external force information according to the aircraft stress sensing data detected by the first stress detection sensors;
wherein, the centers of the two adjacent intervals of the first stress detection sensors are uniformly distributed with a plurality of second detection sensors (as shown in figure 6); the plurality of second detection sensors are in a closed state;
when the first matching degree is higher than the second matching degree;
starting the plurality of second detection sensors, and taking external force information generated by the aircraft stress sensing data detected by the second stress detection sensors as a detection standard;
if the second real-time external force information is matched with the inspection standard, the first stress detection sensors work normally;
and if the second real-time external force information is not matched with the inspection standard, the first stress detection sensors work abnormally.
In the above scheme, when the first matching degree is higher than the second matching degree, generating a second real-time external force information to generate an abnormal condition; according to the scheme, through designing two complementary stress detection sensor arrays, the two complementary stress detection sensor arrays are used as accurate judgment and detection for abnormal conditions of second real-time external force information, if the real-time external force information generated by the two complementary stress detection sensor arrays is the same, the second real-time external force information is judged to be normal, the first real-time external force information is indirectly judged to be abnormal, and if the real-time external force information generated by the two complementary stress detection sensor arrays is different, the second real-time external force information is judged to be abnormal, and the first real-time external force information is indirectly judged to be normal.
Example 5:
considering that the data processing pressure of the data processing integrated end of the aircraft is high, the number of data collectors of the aircraft is extremely huge; therefore, compared to the data collector, the aircraft data processing integration end is likely to generate operation errors.
Further on the basis of embodiment 1, in step S3, if the real-time external force information cannot be mapped to the matched real-time external force balance command through the external force balance command library;
in step S2, generating real-time external force information received by the aircraft in a second preset format according to the external environment information;
in step S3, the integrated data identification processing end corresponding to the preset format and used for executing the mapping of the real-time external force information to the matched real-time external force balance instruction through the external force balance instruction library is replaced by the integrated data identification processing end corresponding to the second preset format.
In the above scheme, by matching the data input of different preset formats with the integrated data identification processing end capable of identifying the data of different preset formats, it can be effectively checked that the real-time external force information cannot be mapped to the matched real-time external force balance instruction through the external force balance instruction library is caused by the operation error of the integrated data identification processing end.
Example 6:
it is contemplated that the aircraft hull may be relatively bulky and that uneven amounts of water in the aircraft hull may cause aircraft hover imbalance when the direction of rain is not perpendicular to the aircraft hull.
Further, on the basis of embodiment 3, the real-time water accumulation amount of the aircraft shell is detected, so that water accumulation amount distribution information of the aircraft shell is obtained, the distribution situation of the water accumulation amount pressure borne by the aircraft shell is judged according to the water accumulation amount distribution information, and the distribution situation of the water accumulation amount pressure is analyzed to obtain additional power which is required to be provided by the aircraft power system on the basis of the real-time external force balance instruction (the additional power is used for balancing aircraft hovering unbalance caused by uneven water accumulation amount of the aircraft shell).
And the monitoring device based on image recognition is used for carrying out data monitoring according to the monitoring method based on image recognition.
The monitoring system based on image recognition is used for carrying out data monitoring according to the monitoring method based on image recognition.
An electronic device comprising a processor and a memory for storing executable commands of the processor, the processor implementing the image recognition based monitoring method as described above by running the executable commands.
A storage medium having stored thereon a computer program which when executed performs a method of monitoring based on image recognition as described above.
The above is a preferred embodiment of the present application, and all changes made according to the technical solution of the present application belong to the protection scope of the present application when the generated functional effects do not exceed the scope of the technical solution of the present application.
Claims (5)
1. The monitoring method based on image recognition is characterized by comprising the following steps of:
s1: judging whether a hover instruction of the aircraft is executed, if yes, judging whether a fixed point image identification instruction of the aircraft is executed, and if yes, entering a step S2;
s2: acquiring external environment information of a current aircraft, and generating real-time external force information of the aircraft in a preset format according to the external environment information;
different external force information borne by the aircraft and external force balance instructions provided by an aircraft power system which are matched with the different external force information one by one are obtained through calculation and analysis of big data of historical statistics, and a plurality of external force balance instructions are constructed into an external force balance instruction library;
s3: mapping the real-time external force information to a matched real-time external force balance instruction through the external force balance instruction library;
s4: executing the real-time external force balance instruction by an aircraft power system;
in step S2, the specific steps are as follows:
s201: judging whether the external environment of the current aircraft is in a raining state or not, if so, entering step S202;
s202: generating the real-time external force information according to a preset format according to the condition that the current aircraft is hit by rainwater;
in step S202, first real-time external force information is generated according to rainfall information and rainwater direction information of rainwater falling;
generating second real-time external force information according to the aircraft stress sensing data;
and carrying out matching judgment on the first real-time external force information and the second real-time external force information, if the first real-time external force information and the second real-time external force information are matched, taking the first real-time external force information or the second real-time external force information as the current real-time external force information, otherwise, judging that the current real-time external force information is abnormal.
2. The image recognition-based monitoring method according to claim 1, wherein when it is determined that the current real-time external force information generates an abnormality;
acquiring corresponding matched real-time raining data through real-time weather table data according to the current geographic position information of the aircraft;
generating third real-time external force information according to the real-time raining data;
respectively carrying out matching judgment on the first real-time external force information and the second real-time external force information and the third real-time external force information, and respectively generating a first matching degree and a second matching degree;
if the first matching degree is higher than the second matching degree, the first real-time external force information is used as the current real-time external force information;
and if the first matching degree is lower than the second matching degree, taking the second real-time external force information as the current real-time external force information.
3. The method for monitoring based on image recognition according to claim 1, wherein the generating of the second real-time external force information based on the aircraft stress sensing data comprises the following steps:
when the current real-time external force information is judged to be abnormal;
acquiring corresponding matched real-time raining data through real-time weather table data according to the current geographic position information of the aircraft;
generating third real-time external force information according to the real-time raining data;
respectively carrying out matching judgment on the first real-time external force information and the second real-time external force information and the third real-time external force information, and respectively generating a first matching degree and a second matching degree;
the first stress detection sensors are uniformly distributed on the surface of the aircraft shell in a fixed mode at intervals of two adjacent pairs;
generating the second real-time external force information according to the aircraft stress sensing data detected by the first stress detection sensors;
the first stress detection sensors are distributed in a uniform array at the centers of two adjacent intervals, and the second stress detection sensors are distributed in a uniform array at the centers of two adjacent intervals; the plurality of second detection sensors are in a closed state;
when the first matching degree is higher than the second matching degree;
starting the plurality of second detection sensors, and taking external force information generated by the aircraft stress sensing data detected by the second stress detection sensors as a detection standard;
if the second real-time external force information is matched with the inspection standard, the first stress detection sensors work normally;
and if the second real-time external force information is not matched with the inspection standard, the first stress detection sensors work abnormally.
4. The method for monitoring based on image recognition according to claim 1, wherein in step S3, if the real-time external force information cannot be mapped to the matched real-time external force balance command through the external force balance command library;
in step S2, generating real-time external force information received by the aircraft in a second preset format according to the external environment information;
in step S3, the integrated data identification processing end corresponding to the preset format and used for executing the mapping of the real-time external force information to the matched real-time external force balance instruction through the external force balance instruction library is replaced by the integrated data identification processing end corresponding to the second preset format.
5. Image recognition based monitoring system, characterized in that the image recognition based monitoring system is used for data monitoring according to the image recognition based monitoring method according to any of claims 1-4.
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