CN-121999588-A - Emergency position indicating transmitter false triggering prevention method and system based on multi-sensor fusion

CN121999588ACN 121999588 ACN121999588 ACN 121999588ACN-121999588-A

Abstract

The invention discloses an emergency position indicating transmitter false triggering prevention method and system based on multi-sensor fusion, which are characterized in that a monitoring window is started after G value exceeds limit, multi-sensor information is introduced to carry out comprehensive judgment, false judgment caused by only depending on a single G value is avoided, the false triggering rate is obviously reduced, the ELT is updated from a simple impact detector to an intelligent flight state judging device, the characteristics of a real crash scene are more met, the reliability of distress signals is improved, and the accident identification accuracy is improved.

Inventors

PAN CHAO
ZHU HAO
GUO ZICHEN
XU LINFENG

Assignees

龙兴(杭州)航空电子有限公司

Dates

Publication Date: 20260508
Application Date: 20260409

Claims (10)

1. An emergency position indicating transmitter false triggering prevention method based on multi-sensor fusion is characterized by comprising the following steps: Step S1, data monitoring and acquisition, namely monitoring G value signals output by an accelerometer arranged in an emergency position indication transmitter in real time; Step S2, G value judgment, when the G value signal exceeds a preset threshold value, starting a monitoring window with a duration; S3, analyzing multi-source data, and synchronously acquiring and analyzing multi-source sensor data from an aircraft system in a monitoring window; And S4, judging the triggering condition, namely judging whether the real accident triggering condition of the emergency position indicating transmitter is met according to the multi-source sensor data, if so, sending a distress signal, otherwise, judging that the emergency position indicating transmitter is not activated as a false triggering event.
2. The method for preventing false triggering of the emergency position indicating transmitter based on the multi-sensor fusion according to claim 1, wherein the data is monitored and collected in the step S1 by the following means: And setting a preset threshold value in the system, and continuously sensing linear acceleration of the aircraft in three directions of XYZ by using a triaxial accelerometer in the emergency position indicating transmitter, wherein an original output signal of the accelerometer is a G value.
3. The method for preventing false triggering of an emergency position indicating transmitter based on multi-sensor fusion according to claim 1, wherein the step S2 is implemented by: after the abnormal impact is detected initially, auxiliary information from other systems of the aircraft is collected and analyzed, the authenticity of time is comprehensively judged, and a buffer monitoring window is provided.
4. The method for preventing false triggering of an emergency position indicating transmitter based on multi-sensor fusion according to claim 1, wherein the multi-source data is analyzed in the step S3 by the following means: A1, checking the validity of data, checking an SSM field of the data, and entering a fault safety logic if a problem occurs according to any key parameter of the field; a2, judging whether the power state is abnormal, judging whether the main power voltage is lower than a failure threshold value, if yes, recording a time stamp; and step A3, judging the abnormal state of the aircraft, calculating attitude parameters in real time, judging whether the aircraft exceeds the limit, analyzing the combined characteristics of the flight state of the aircraft, and identifying a typical accident mode.
5. The method for preventing false triggering of the emergency position indicating transmitter based on the multi-sensor fusion according to claim 1, wherein the actual accident triggering condition in the step S4 is as follows: a. the main supply voltage is below the failure threshold and the duration exceeds a first time threshold T1; b. the aircraft attitude parameters are abnormal and the duration exceeds a second time threshold T2; c. Airspeed and altitude drop sharply, or all engine thrust is lost, and the state duration exceeds a third time threshold T3.
6. The method for preventing false triggering of an emergency position indicating transmitter based on multi-sensor fusion according to claim 1, wherein the method further comprises the following steps: s5, training an unsupervised anomaly detection model by using historical normal flight data, and constructing a minimum feature set; s6, inputting the real-time multi-source sensor data into an anomaly detection model to obtain anomaly scores; and S7, when the rule judges that the triggering condition is met and the abnormal score exceeds a preset threshold value, activating the emergency position indicating transmitter.
7. The method for preventing false triggering of an emergency position indicating transmitter based on multi-sensor fusion according to claim 6, wherein the unsupervised anomaly detection model in step S5 is trained by using an isolated forest algorithm and is converted into a lightweight rule engine before deployment, and the lightweight rule engine is embedded into a microcontroller unit of the emergency position indicating transmitter in the form of a C language source code.
8. The method for preventing false triggering of an emergency position indicating transmitter based on multi-sensor fusion according to claim 1, wherein the step S6 is implemented by: And triggering a monitoring window when the G value exceeds the limit, synchronously collecting key parameters in the minimum feature set, carrying out standardized processing on data, matching data distribution during model training, inputting the processed data into an embedded isolation forest model, and outputting an anomaly score.
9. An emergency position indicating transmitter false triggering prevention system based on multi-sensor fusion adopts the method for false triggering prevention of the emergency position indicating transmitter based on multi-sensor fusion as set forth in any one of claims 1-8, and is characterized by comprising an acceleration monitoring module, an impact time detection and window starting module, a multi-source sensor data fusion analysis module, an accident triggering condition judgment module, an unsupervised abnormality detection module and a dual verification activation control module; the acceleration monitoring module is used for collecting G value signals output by a built-in triaxial accelerometer of the emergency position indicating transmitter in real time and preliminarily judging whether abnormal impact occurs or not; The impact time detection and window starting module is used for starting a multi-source data fusion analysis flow when the G value exceeds a preset threshold value; The multisource sensor data fusion analysis module is used for synchronously acquiring and comprehensively analyzing sensor data from a plurality of systems of the aircraft in a monitoring window, so that the accident judgment accuracy is improved; the accident triggering condition judging module is used for judging whether the real accident triggering condition is met or not based on a preset multi-condition logic; The unsupervised anomaly detection module is used for identifying a potential complex or unknown accident mode in a data driving mode as the supplement of traditional rule judgment, and further inhibiting false triggering; and the dual-verification activation control module is used for finally activating the emergency position-indicating transmitter to send a distress signal when the traditional rule judges that the trigger condition is met and the abnormal score exceeds a preset threshold value.
10. The emergency position indicating transmitter false triggering prevention system based on multi-sensor fusion according to claim 9, wherein the multi-source sensor data fusion analysis module comprises a data validity verification unit, a power state monitoring unit and an aircraft gesture recognition unit; A data validity checking unit for checking SSM fields in sensor data from the aircraft system; The power state monitoring unit is used for judging whether the main power voltage is lower than a failure threshold value or not and recording an abnormal time stamp; The aircraft attitude identification unit is used for calculating attitude parameters in real time, judging whether the attitude parameters exceed the limit, and identifying a typical accident mode by combining the flight state combination characteristics; the unsupervised anomaly detection model module comprises a model training unit and a real-time anomaly scoring unit; The model training unit is used for training an unsupervised anomaly detection model by using historical normal flight data and constructing a minimum feature set; and the real-time anomaly scoring unit is used for inputting the real-time multisource sensor data into the embedded model and outputting an anomaly score.

Description

Emergency position indicating transmitter false triggering prevention method and system based on multi-sensor fusion Technical Field The invention relates to the field of aviation avionics, in particular to an anti-false triggering method and system of an emergency position indicating transmitter based on multi-sensor fusion. Background The existing emergency position indicating transmitter ELT is started accidentally even in a non-emergency situation, and sends an error distress signal to a satellite, so that search and rescue resources are wasted and aviation communication is interfered. At present, false triggering of the ELT is mainly caused by human misoperation or equipment faults, for example, a machine set or a maintenance personnel touches an ELT switch by mistake during inspection and maintenance, or is not reset in time after a battery is replaced, or a G value sensor of the ELT is triggered by shock waves during disassembly or other equipment maintenance, part of the ELT can be activated due to design defects during the power-on/power-off process of an aircraft, and the false triggering of the ELT is very frequent. In view of the foregoing, there is a need for an anti-false triggering method and system for an emergency position indicating transmitter based on multi-sensor fusion to solve the shortcomings in the prior art. Disclosure of Invention Aiming at the defects of the prior art, the invention provides an emergency position indicating transmitter false triggering prevention method and system based on multi-sensor fusion, and aims to solve the problems. In order to achieve the purpose, the invention provides the technical scheme that the method for preventing false triggering of the emergency position indicating transmitter based on multi-sensor fusion comprises the following steps: Step S1, data monitoring and acquisition, namely monitoring G value signals output by an accelerometer arranged in an emergency position indication transmitter in real time; Step S2, G value judgment, when the G value signal exceeds a preset threshold value, starting a monitoring window with a duration; S3, analyzing multi-source data, and synchronously acquiring and analyzing multi-source sensor data from an aircraft system in a monitoring window; And S4, judging the triggering condition, namely judging whether the real accident triggering condition of the emergency position indicating transmitter is met according to the multi-source sensor data, if so, sending a distress signal, otherwise, judging that the emergency position indicating transmitter is not activated as a false triggering event. Optionally, the data is monitored and collected in step S1 by the following means: And setting a preset threshold value in the system, and continuously sensing linear acceleration of the aircraft in three directions of XYZ by using a triaxial accelerometer in the emergency position indicating transmitter, wherein an original output signal of the accelerometer is a G value. Optionally, the step S2 is implemented by: after the abnormal impact is detected initially, auxiliary information from other systems of the aircraft is collected and analyzed, the authenticity of time is comprehensively judged, and a buffer monitoring window is provided. Optionally, the multi-source data is analyzed in step S3 by: A1, checking the validity of data, checking an SSM field of the data, and entering a fault safety logic if a problem occurs according to any key parameter of the field; a2, judging whether the power state is abnormal, judging whether the main power voltage is lower than a failure threshold value, if yes, recording a time stamp; and step A3, judging the abnormal state of the aircraft, calculating attitude parameters in real time, judging whether the aircraft exceeds the limit, analyzing the combined characteristics of the flight state of the aircraft, and identifying a typical accident mode. Optionally, the actual accident triggering condition in step S4 is: a. the main supply voltage is below the failure threshold and the duration exceeds a first time threshold T1; b. the aircraft attitude parameters are abnormal and the duration exceeds a second time threshold T2; c. Airspeed and altitude drop sharply, or all engine thrust is lost, and the state duration exceeds a third time threshold T3. Optionally, the method further comprises the steps of: s5, training an unsupervised anomaly detection model by using historical normal flight data, and constructing a minimum feature set; s6, inputting the real-time multi-source sensor data into an anomaly detection model to obtain anomaly scores; and S7, when the rule judges that the triggering condition is met and the abnormal score exceeds a preset threshold value, activating the emergency position indicating transmitter. Optionally, the unsupervised anomaly detection model in step S5 is trained by using an isolated forest algorithm, and is converted into a lightweight rule engine before d