Data monitoring method and medium
A data monitoring method and a data monitoring medium. The method has: acquiring current vibration data of a target flight device in real time; Determining an anomaly protection strategy of the target flight device based on the current vibration data; The target flight equipment is controlled to execute corresponding operations according to an abnormality protection strategy. Embodiments of the invention, by acquiring the current vibration data of the target flight equipment in real time, determining an anomaly protection strategy of the target flight device based on the current vibration data.
1. A data monitoring method comprising:
acquiring a current vibration data of a target flight device in real time;
determining an abnormal protection strategy of the target flight device according to the current vibration data;
controlling the target flight device to execute a corresponding operation according to the abnormal protection policy; and
wherein each necessary part of the target flight device is configured with a vibration sensor;
wherein the necessary part comprises a motor engine mounting position, installing position of a navigation system, a steering engine mounting position, a wing mounting position, and a vertical tail mounting position.
2. The method according to claim 1 , wherein the step of acquiring the current vibration data of the target flight device in real time comprises:
receiving the current vibration data sent by the vibration sensor in real time; or
receiving the current vibration data sent by the vibration sensor through a health monitoring system in real time.
3. The method according to claim 1 , wherein the step of determining the abnormal protection strategy of the target flight device according to the current vibration data comprises:
determining a current fault degree and a current fault position of the target flight device according to the current vibration data and a preset vibration threshold; and
determining the abnormal protection strategy of the target flight device according to the current fault degree and the current fault position.
4. The method according to claim 3 , wherein the preset vibration threshold comprises:
a first preset vibration threshold value and a second preset vibration threshold value, and the first preset vibration threshold value is less than the second preset vibration threshold value;
according to the current vibration data and the preset vibration threshold to determine the current fault degree and the current fault position of the target flight device, comprising respectively comparing a result of the current vibration data with the first preset vibration threshold value and the second preset vibration threshold value;
under the condition that the current vibration data is greater than the first preset vibration threshold and less than the second preset vibration threshold value, the current fault degree of the target flight device is mild fault;
under the condition that the current vibration data is greater than the second preset vibration threshold value, the current fault degree of the target flight device is severe fault;
determining the current fault position of the target flight device according to the mounting position of the vibration sensor corresponding to the current vibration data greater than the preset vibration threshold value.
5. The method according to claim 3 , wherein the step of determining the abnormal protection strategy of the target flight device according to the current fault degree and the current fault position comprises one of the following:
when the current fault degree is mild fault, and the current fault position is a non-necessary position, determining the abnormal protection strategy of the target flight device is fault voice prompt;
when the current fault degree is mild fault, and the current fault position is a necessary position, determining the abnormal protection strategy of the target flight device is maintenance fault part;
when the current fault degree is severe fault, and the current fault position is the necessary position, determining the abnormal protection strategy of the target flight device is closing the fault part.
6. The method according to claim 1 , wherein a configuration mode of the vibration sensor comprises one of the following: a) integrated on the motor control system, and b) integrated on the steering engine control system.
7. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 1 .
8. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 2 .
9. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 3 .
10. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 4 .
11. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 5 .
12. A non-transitory computer readable storage medium, wherein the computer readable storage medium is stored with computer instructions, wherein the computer instructions cause the processor to perform the data monitoring method according to claim 6 .