CN112133136B

CN112133136B - Aircraft emergency distress signal monitoring system and monitoring method

Info

Publication number: CN112133136B
Application number: CN202010957792.7A
Authority: CN
Inventors: 何龙; 刘翱; 张益�
Original assignee: Second Research Institute of CAAC
Current assignee: Second Research Institute of CAAC
Priority date: 2020-09-11
Filing date: 2020-09-11
Publication date: 2021-06-22
Anticipated expiration: 2040-09-11
Also published as: CN112133136A

Abstract

The application belongs to the technical field of civil aviation safety guarantee, and particularly relates to an aircraft emergency distress signal monitoring system and method; the monitoring system includes: the dual-frequency signal monitoring device can synchronously acquire two emergency signals and perform corresponding processing such as decoding and preliminary judgment on the position of an aircraft involved in an accident; the information comprehensive processing device can correspondingly process the information transmitted by the dual-frequency signal monitoring device to obtain information such as the position and the identity of the aircraft involved in the accident; and the alarm display device can carry out preprocessing on the data transmitted by the information comprehensive processing device, including displaying alarm information. According to the aircraft emergency distress signal monitoring system and method, a localization technical means is provided, so that the all-day real-time monitoring of emergency signals is realized, the running short board in the specific scene of the conventional Cospas-Sarsat is effectively supplemented, and the capacity of acquiring weak signals for analyzing error codes or signals incapable of being received and analyzed in an electromagnetic interference environment is improved.

Description

Aircraft emergency distress signal monitoring system and monitoring method

Technical Field

The application belongs to the technical field of civil aviation safety guarantee, and particularly relates to an aircraft emergency distress signal monitoring system and method.

Background

With the opening of airspace, the positioning and search and rescue after the civil aviation, navigation and transport aircraft are in danger are important problems to be solved by the aviation industry. In recent years, the airplane can not be effectively positioned and quickly rescued when being in distress for many times in China and abroad, and great loss is caused to personnel and property.

Therefore, an Emergency location Transmitter (elet) is developed, which is called as ELT for short; the ELT is one of important systems for ensuring the safety of the airplane, can be activated manually or automatically by collision and water immersion in distress after an emergency occurs, and can emit a distress signal to provide important clues for searching and rescuing and positioning after the aircraft is lost.

At present, the main transmission routes of emergency signals of aircraft are as follows:

1) the 406MHz digital signal from ELT is transmitted to each ground receiving station through a satellite link of a global satellite search and rescue system (Cospas-Sarsat), and then transmitted to a civil aviation operation monitoring center through a corresponding department;

2) from a 121.5MHz homing beacon onboard the aircraft.

However, for the first type of transmission path, because the first type of transmission path is based on the Cospas-Sarsat system, the civil aviation bureau does not have a monitoring means of the civil aviation bureau to acquire the 406MHz emergency signal in the first time, and meanwhile, the signal analyzed by the system is often analyzed incorrectly due to too weak signal, so that the relevant emergency information cannot be determined effectively.

In addition, in the first type of transmission approach, the signal transmitting end ELT is divided into the active position indicating ELT and the passive position indicating ELT, so that the transmitted digital signal sometimes includes the identification and position coding information of the beacon, and sometimes only includes the identification coding information of the beacon, thereby resulting in incomplete related emergency information and failure to perform effective and accurate resolution and identification.

Further, for the second type of transmission route, the emergency signal in the 121.5MHz frequency band is no longer transmitted by the Cospas-Sarsat system since 2009, and currently, only the aircraft at an empty pipe tower or a certain flight altitude and the like can receive the related alarm information, and thus, more related aircraft emergency information cannot be effectively provided. Therefore, the normal and safe operation of civil aviation is influenced by the problems of wrong analysis, timeliness, insufficient effective information and the like of the emergency signal.

Disclosure of Invention

In order to solve at least one of the above technical problems, the present application provides a system and a method for monitoring an emergency distress signal of an aircraft.

In a first aspect, the application discloses an aircraft emergency distress signal monitoring system, which comprises a dual-frequency signal monitoring device arranged at an airport, an information comprehensive processing device and an alarm display device, wherein the dual-frequency signal monitoring device is used for monitoring the emergency distress signal of an aircraft, and the alarm display device is used for displaying the emergency distress signal of the aircraft

The dual-frequency signal monitoring device is used for:

synchronously monitoring emergency signals sent by an aircraft involved in an accident, wherein the emergency signals comprise frequency bands of 121.5MHz and 406 MHz; and

judging the frequency band of the monitored emergency signal; and

when the emergency signal with the frequency band of 121.5MHz exists, judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal; and

when the frequency band of 406MHz is provided with an emergency signal, decoding the frequency band emergency signal to obtain corresponding coding protocol information, wherein the coding protocol information comprises position protocol information or user protocol information; and

when the 406MHz frequency band emergency signal is decoded and only contains user protocol information, judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal; and

transmitting the monitored emergency signal and the corresponding processing result to the outside through a communication network;

the information integrated processing device is used for:

receiving information transmitted by the dual-frequency signal monitoring device through a communication network; and

judging the types of emergency signals in the received information, wherein the types of emergency signals comprise 121.5MHz frequency band emergency signals, 406MHz frequency band emergency signals only containing user protocol information after decoding and 406MHz frequency band emergency signals only containing position protocol information after decoding; and

when the received information is an emergency signal of a 121.5MHz frequency band, carrying out region position matching processing on the synchronously received preliminary direction of the aircraft involved in the accident and the range information of the aircraft involved in the accident to obtain the position and partial identity information of the aircraft involved in the accident, and carrying out matching processing on the partial identity information and an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident;

when the received information is a 406MHz frequency band emergency signal and the corresponding coding protocol information is position protocol information, decoding and extracting the position protocol information to obtain the position information of the aircraft involved in the accident, and simultaneously matching the beacon identity identification information in the position protocol information with an aviation emergency rescue database to obtain the detailed identity information of the aircraft involved in the accident; and

when the received information is a 406MHz frequency band emergency signal and the corresponding coding protocol information is user protocol information, matching beacon identification information in the user protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft concerned, matching the synchronously received initial direction and area range information of the aircraft concerned with the airport map, judging whether the aircraft concerned with the airport surface is in an area nearby the airport surface or an air route area, and performing information fusion and intelligent matching with the detailed identity information of the aircraft concerned with the multi-service system in the area nearby the airport surface or the air route area to obtain situation information of the aircraft concerned with the airport; and

transmitting various processing result data to the outside through a communication network;

the warning display device is used for:

receiving data transmitted by the information comprehensive processing device through a communication network; and

and preprocessing the data, including displaying the alarm information to be displayed in the data.

According to at least one embodiment of the present application, the dual frequency signal monitoring apparatus includes:

the signal monitoring module is used for synchronously monitoring emergency signals sent by the aircraft involved in an accident;

the signal type judging module is used for judging the frequency bands of the emergency signals monitored by the signal monitoring module, wherein the frequency bands comprise the frequency bands of 121.5MHz and 406 MHz;

the signal decoding processing module is used for decoding the frequency band emergency signal to obtain corresponding coding protocol information when the 406MHz frequency band emergency signal is monitored, wherein the coding protocol information comprises position protocol information or user protocol information;

the signal characteristic analysis and tracking module is used for carrying out characteristic analysis on the signal intensity and the incoming wave direction of the monitored emergency signal, judging the distance and the direction of the aircraft involved in the accident, and continuously tracking the signal of the aircraft involved in the accident;

the signal direction and area range calculation module is used for judging the initial direction and the accident-related area range of the accident-related aircraft which sends out the corresponding emergency signal based on the processing result of the signal characteristic analysis and tracking module when the 121.5MHz frequency band emergency signal or the 406MHz frequency band emergency signal which is monitored only contains user protocol information after being decoded;

and the first data transmission module is used for transmitting the monitored emergency signal and the corresponding processing result to the outside through a communication network.

According to at least one embodiment of the present application, the information integrated processing apparatus includes:

the second data transmission module is used for receiving the information transmitted by the dual-frequency signal monitoring device through a communication network and transmitting various processing result data of the information comprehensive processing device to the outside through the communication network;

the information type judging module is used for judging the type of the information received by the second data transmission module, wherein the information type comprises a 121.5MHz frequency band emergency signal, a 406MHz frequency band emergency signal which only contains user protocol information after decoding and a 406MHz frequency band emergency signal which only contains position protocol information after decoding;

the decoding information extraction module is used for decoding and extracting the position protocol information to obtain the position information of the aircraft involved in the accident when receiving the 406MHz frequency band emergency signal only containing the position protocol information after decoding;

the first information matching module is used for matching the beacon identity identification information in the position protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident when receiving the 406MHz frequency band emergency signal only containing the position protocol information after decoding;

the second information matching module is used for matching the beacon identity identification information in the user protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident when receiving the 406MHz frequency band emergency signal which only contains the user protocol information after decoding;

the third information matching module is used for performing area and position matching processing on the synchronously received preliminary position of the aircraft involved in the accident and the range information of the aircraft involved in the accident when an emergency signal of a frequency band of 121.5MHz is received so as to obtain the position and partial identity information of the aircraft involved in the accident, and performing matching processing on the partial identity information and an aviation emergency rescue database so as to obtain the detailed identity information of the aircraft involved in the accident;

the alarm target area judgment module is used for matching the synchronously received initial direction of the aircraft involved in the accident and the range information of the aircraft involved in the accident with a map of an airport when receiving the 406MHz frequency band emergency signal which only contains user protocol information after decoding, and judging whether the aircraft involved in the accident is located in an area near the airport surface or an air route area;

and the fusion matching module is used for performing information fusion and intelligent matching with the corresponding detailed identity information of the aircraft involved in the accident through a multi-service system in an area near an airport scene or an air route area so as to acquire the situation information of the aircraft involved in the accident.

According to at least one embodiment of the present application, the fusion matching module includes:

the first fusion matching unit is used for performing information fusion and intelligent matching on the detailed identity information of the accident-related aircraft, an airport route monitoring system and a communication system when the accident-related aircraft is located in an air route area so as to acquire the position and motion state information of the accident-related aircraft;

and the second fusion matching unit is used for performing information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident and an airport scene monitoring system when the aircraft involved in the accident is located in the area near the airport and the answering machine on the aircraft involved in the accident is in an open state so as to acquire the position information of the aircraft involved in the accident.

According to at least one embodiment of the present application, the second fusion matching unit is further configured to:

when the aircraft involved in the accident is located in the area near the airport and the answering machine on the aircraft involved in the accident is in the off state, the detailed identity information of the aircraft involved in the accident can be subjected to information fusion and intelligent matching with the airport commanding and dispatching system and the airport cooperative decision-making system so as to obtain the position information of the aircraft involved in the accident.

According to at least one embodiment of the present application, the warning display device includes:

the third data transmission module is used for receiving the data transmitted by the information comprehensive processing device through a communication network;

the alarm information display module is used for displaying the alarm information to be displayed;

and the alarm data processing module is used for preprocessing the data received by the third data transmission module, wherein the data preprocessing comprises the step of transmitting alarm information to be displayed in the data to the alarm information display module for displaying.

According to at least one embodiment of the present application, the alarm data processing module includes:

the data storage module is used for storing the received data;

the information classification and statistics module is used for intelligently counting and analyzing the received data according to different types of ELT alarm events and periodically outputting data analysis results to the alarm information display module for display;

the alarm checking and issuing module is used for automatically generating and reporting a checking flow report according to relevant operation regulations of civil aviation and intelligently issuing the data stored in the data storage module to relevant units;

the GIS map display module is used for displaying the position of the emergency signal and the surrounding environment;

and the aviation emergency rescue database updating module is used for being connected with a civil aviation aircraft radio station license management system so as to update the aviation emergency rescue database in real time.

In a second aspect, the application also discloses an aircraft emergency distress signal monitoring method, which comprises a double-frequency signal monitoring step, an information comprehensive processing step and an alarm display processing step; wherein

The dual-frequency signal monitoring step comprises the following sub-steps:

synchronously monitoring and acquiring emergency signals sent by an aircraft involved in an accident, wherein the emergency signals comprise frequency bands of 121.5MHz and 406 MHz;

judging the frequency band of the monitored emergency signal;

when the emergency signal with the frequency band of 121.5MHz exists, judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal;

when the frequency band of 406MHz is provided with an emergency signal, decoding the frequency band emergency signal to obtain coding protocol information, wherein the coding protocol information comprises position protocol information or user protocol information;

when the 406MHz frequency band emergency signal is decoded and only contains user protocol information, judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal;

the information comprehensive processing step comprises the following substeps:

receiving information transmitted in the dual-frequency signal monitoring step through a communication network;

judging the types of emergency signals in the received information, wherein the types of emergency signals comprise 121.5MHz frequency band emergency signals, 406MHz frequency band emergency signals only containing user protocol information after decoding and 406MHz frequency band emergency signals only containing position protocol information after decoding;

when the received information is a 406MHz frequency band emergency signal and the corresponding coding protocol information is position protocol information, decoding and extracting the position protocol information to obtain the position information of the aircraft involved in the accident, and simultaneously matching the beacon identity identification information in the position protocol information with an aviation emergency rescue database to obtain the detailed identity information of the aircraft involved in the accident;

when the received information is a 406MHz frequency band emergency signal and the corresponding encoding protocol information is user protocol information: firstly, matching beacon identity identification information in user protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident; then, matching the synchronously received preliminary position and area range information of the aircraft involved in the affairs with a map of an airport and/or an airport along-route service station, and judging whether the aircraft involved in the affairs is located in an area near the airport scene or an air route area;

information fusion and intelligent matching are carried out on the multi-service system in the area near the airport scene or the air route area and the detailed identity information of the corresponding accident-related aircraft, so that the situation information of the accident-related aircraft is obtained;

the alarm display processing step includes the following substeps:

receiving the data transmitted in the information comprehensive processing step through a communication network;

According to at least one embodiment of the present application, the sub-step of performing information fusion and intelligent matching with the detailed identity information of the corresponding aircraft involved in the accident through the multi-service system in the area near the airport surface or in the air route area to obtain the situation information of the aircraft involved in the accident specifically includes:

when the aircraft involved in the accident is located in an air route area, carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident, an airport route monitoring system and a communication system so as to obtain the position and motion state information of the aircraft involved in the accident;

when the aircraft involved in the accident is located in the area near the airport, judging the state of the answering machine on the aircraft involved in the accident;

if the answering machine on the aircraft involved in the accident is in an open state, carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident and an airport scene monitoring system so as to obtain the position information of the aircraft involved in the accident;

and if the answering machine on the aircraft involved in the accident is in a closed state, carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident, an airport commanding and dispatching system and an airport cooperative decision-making system so as to obtain the position information of the aircraft involved in the accident.

According to at least one embodiment of the present application, in the alert display processing step, the sub-step of preprocessing the data further includes:

storing the received data;

the received data is intelligently counted and analyzed according to different types of ELT alarm events, and data analysis results are periodically output to an alarm information display module to be displayed;

automatically generating and reporting an inspection flow report according to relevant operation regulations of civil aviation, and intelligently releasing stored data to relevant units;

displaying the position of the emergency signal and the surrounding environment;

and the system is connected with a radio station license management system of the civil aviation aircraft so as to update the aviation emergency rescue database in real time.

The application has at least the following beneficial technical effects:

1) according to the aircraft emergency distress signal monitoring system and method, a localization technical means is provided, so that the all-day real-time monitoring of emergency signals is realized, the running short board in the specific scene of the conventional Cospas-Sarsat is effectively supplemented, and the capacity of acquiring weak signals for analyzing error codes or signals incapable of being received and analyzed in an electromagnetic interference environment is improved;

2) according to the aircraft emergency distress signal monitoring system and method, a linkage framework based on remote monitoring and rear-end intelligent processing is provided, so that the emergency signal can be efficiently captured, and deeper related aircraft information can be timely acquired by matching with an aviation emergency rescue database; then, information fusion and intelligent matching are carried out between a plurality of service systems corresponding to the airport under the multi-scene of the airport and the air route, the accident-related aircraft is quickly positioned, and meanwhile, the states before and after the accident-related aircraft gives an alarm can be tracked and judged, so that a basis is provided for judging whether the alarm is mistaken or not;

3) in the aircraft emergency distress signal monitoring system and method, a closed-loop processing scheme based on signal monitoring, back-end data interaction processing and information statistics, multi-service system fusion linkage and information intelligent release is provided in the system flow design, so that the system is not only beneficial to improving the information acquisition and multi-service department cooperative linkage capacity, but also can provide precious analysis data and technical support for the related management of future emergency alarm, and thus the aviation operation safety is really improved;

4) according to the aircraft emergency distress signal monitoring system and method, the result is intelligently issued to the aviation department, local supervision bureau, district air administration unit and the like of the aircraft concerned in trouble through the alarm processing and display terminal, so that the relay links of the traditional emergency information transmitted from the Cospas-Sarsat to the civil aviation bureau can be effectively reduced, the timeliness is improved, the excessive dependence on the original Cospas-Sarsat system is reduced, and the autonomous control of the system is realized.

Drawings

FIG. 1 is a block diagram of an aircraft emergency distress signal monitoring system according to the present application;

FIG. 2 is a flow chart (including a module structure diagram) of a dual-frequency signal monitoring step in the aircraft emergency distress signal monitoring method of the present application;

FIG. 3 is a block diagram of an integrated information processing device in the method for monitoring an aircraft emergency distress signal according to the present application;

FIG. 4 is a flowchart illustrating the steps of information integration processing in the method for monitoring an aircraft emergency distress signal according to the present application;

fig. 5 is a block diagram of an alarm display device in the aircraft emergency distress signal monitoring system according to the present application.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

The aircraft emergency distress signal monitoring system and the monitoring method of the present application are further described in detail with reference to fig. 1 to 5.

In a first aspect, the application discloses an aircraft emergency distress signal monitoring system; as shown in fig. 1, the monitoring system may include a dual-frequency signal monitoring apparatus 100 (see the dual-frequency signal monitoring station in fig. 1), an information integrated processing apparatus 200 (see the information processing and service system linkage center in fig. 1), and an alarm display apparatus 300 (see the alarm information processing display center in fig. 1) at an airport.

Further, as shown in fig. 2, the dual-band signal monitoring apparatus 100 may further include a signal monitoring module 101, a signal type determining module 102, a signal decoding processing module 103, a signal characteristic analyzing and tracking module 104, a signal direction and area range calculating module 105, and a first data transmission module 106.

Specifically, the signal monitoring module 101 is configured to perform synchronous monitoring on emergency signals sent by the aircraft involved in an accident, where the emergency signals include frequency bands of 121.5MHz and 406 MHz. It should be noted that the types of emergency signals that may be sent by different types of aircraft involved in an accident are different, for example, when an ELT alarm device on the aircraft is triggered, emergency signals in the 121.5MHz frequency band and the 406MHz frequency band may be sent at the same time; for the case of simultaneously monitoring the emergency signals of the 121.5MHz frequency band and the 406MHz frequency band, the 121.5MHz frequency band and the 406MHz frequency band are respectively processed according to corresponding processing modes (which will be described in detail later).

The signal type determining module 102 is configured to determine a frequency band of the emergency signal monitored by the signal monitoring module 101, where the frequency band includes the above 121.5MHz frequency band or 406MHz frequency band, or both the 121.5MHz frequency band and the 406MHz frequency band.

The signal decoding processing module 103 is configured to, when a 406MHz frequency band emergency signal is monitored, decode the monitored 406MHz frequency band emergency signal to obtain coding protocol information corresponding to the 406MHz frequency band emergency signal, where the coding protocol information includes position protocol information or user protocol information.

The signal characteristic analyzing and tracking module 104 is configured to perform characteristic analysis on the signal strength and the incoming wave direction of the monitored emergency signal, determine the distance and the direction of the aircraft involved in the accident, which sends the corresponding emergency signal, and continuously track the signal of the aircraft involved in the accident.

The signal direction and area range calculation module 105 is configured to, when the 121.5MHz frequency band emergency signal is monitored or the 406MHz frequency band emergency signal is monitored and decoded and then only contains user protocol information, determine a preliminary direction and an area range of an aircraft involved in an accident that sends a corresponding emergency signal based on a processing result of the signal characteristic analysis and tracking module 104.

The first data transmission module 106 is configured to transmit the monitored emergency signal and the corresponding processing result (including the decoded information and the determined preliminary position of the aircraft involved in the event and the information about the area of the aircraft involved in the event) to the outside through a communication network.

In summary, the whole operation process of the dual-frequency signal monitoring apparatus 100 can be divided into two stages; in the first stage, the front-end dual-standard signal monitoring module monitors the frequency bands of 121.5MHz and 406MHz in real time and judges whether signal capture exists in real time. In the second stage, after any signals of the two frequency bands are captured, corresponding emergency response and receiving processing modes are given. Wherein, dual-frequency signal monitoring devices 100 has still possessed the preliminary judgement of radio signal position except that can provide the monitoring and the decoding of emergency signal, only has 121.5MHz to receive and receives the condition of not taking positional information in the 406MHz signal, also can possess preliminary position and the regional scope of concerning affairs and confirm, improves emergency signal in time discovers and triggers the quick investigation ability of interfering signal by mistake.

Further, the integrated information processing device 200 serves as a core of the aircraft emergency distress signal monitoring system, and can be responsible for flow processing control of alarm information, linkage of airport multi-service systems and intelligent target information matching.

Specifically, as shown in fig. 3, the information integrated processing apparatus 200 may include a second data transmission module 201, an information type determination module 202, a decoded information extraction module 203, a first information matching module 204, a second information matching module 205, a third information matching module 206, an alarm target area determination module 207, and a fusion matching module 208.

The second data transmission module 201 is configured to receive information transmitted by the dual-frequency signal monitoring device 100 through a communication network, and transmit various processing result data performed by the information comprehensive processing device 200 to the outside through the communication network; the various processing result data includes position information of the aircraft involved in the accident, identity information of the aircraft involved in the accident, information that the aircraft involved in the accident is located in an area near an airport surface or an air route area, situation information of the aircraft involved in the accident, and the like, which will be described later.

The information type determining module 202 is configured to determine the type of the information received by the second data transmission module 201, where the information type includes a 121.5MHz frequency band emergency signal, a 406MHz frequency band emergency signal that only includes user protocol information after decoding, and a 406MHz frequency band emergency signal that only includes location protocol information after decoding.

The decoding information extraction module 203 is configured to, when receiving the 406MHz frequency band emergency signal which only includes the position protocol information after decoding, perform decoding extraction processing on the position protocol information therein, and obtain the position information of the aircraft involved in the accident.

The first information matching module 204 is configured to, when receiving a 406MHz frequency band emergency signal that only includes the location protocol information after decoding, perform matching processing according to the beacon identity identification information in the location protocol information and the aviation emergency rescue database, and obtain detailed identity information of the aircraft involved in the accident.

The second information matching module 205 is configured to, when receiving a 406MHz frequency band emergency signal that only includes user protocol information after decoding, perform matching processing on beacon identity identification information in the user protocol information and an aviation emergency rescue database, and obtain detailed identity information of the aircraft involved in the accident.

The third information matching module 206 is configured to, when the 121.5MHz frequency band emergency signal is received, perform area location matching processing on the synchronously received preliminary location of the aircraft involved in the event and the information about the area range involved in the event (that is, the location and the area information determined by the signal location and area range calculation module 105) to obtain the location and partial identity information of the aircraft involved in the event that the 121.5MHz frequency band emergency signal is sent, and then perform matching processing on the partial identity information and the aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the event. It should be noted that, the partial identity information and the detailed identity information are referred to each other, that is, the information type in the partial identity information is smaller than the information type in the detailed identity information, but the specific types of the partial identity information and the detailed identity information are not limited at this time, and may be changed according to the data amount in the database, which is not described here.

The alarm target area determination module 207 is configured to, when receiving the decoded 406MHz frequency band emergency signal only including the user protocol information, perform matching processing on the synchronously received preliminary position and area range information of the aircraft involved in the event and a map of an airport (except the airport, in other embodiments, the information may also include an along-route service station or an individual along-route service station), and determine whether the aircraft involved in the event is located in an area near an airport surface or an air route area.

The fusion matching module 208 is configured to perform information fusion and intelligent matching on the multi-service system in the area near the airport surface or in the air route area, which is determined by the above-mentioned alarm target area determination module 207, and the detailed identity information of the aircraft involved in the accident (that is, the 406MHz frequency band emergency signal only including the user protocol information is sent out), so as to obtain situation information of the aircraft involved in the accident.

In addition, for the three alarm signals including the 121.5MHz frequency band emergency signal and the 406MHz frequency band emergency signal, the following further explanation is adopted by different processing means:

1) for the first warning signal (i.e. the emergency signal in the frequency band of 121.5 MHz), since the warning signal does not include the location information and the corresponding beacon identification information, the dual-frequency signal monitoring device 100 determines the preliminary direction and the area range of the trouble related area, and then the warning signal is linked with the information comprehensive processing device 200, the area location matching is performed through the multi-service system in the area, the trouble related aircraft is determined through matching and troubleshooting, the location and part of the identity information of the aircraft are obtained, and the detailed information of the state, the navigation department information, the flight number, the aircraft responder code and the like of the trouble related aircraft is obtained through matching the part of the identity information with the aviation emergency rescue database.

2) For the second kind of warning signal (i.e. the 406MHz frequency band emergency signal which contains only the user protocol information after decoding), since the warning signal does not contain the position information, it is necessary to determine the position or the area range of the aircraft involved by other auxiliary means. Firstly, a beacon identification code in an alarm signal is matched with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident, then the direction and the area range of the aircraft involved in the accident are calculated through a received signal strength value (RSSI) and an incoming wave direction of the dual-frequency signal monitoring device 100, and the aircraft involved in the accident is matched with a map of an airport to judge whether the position of the aircraft involved in the accident is located in an area near the airport scene or an air route.

3) For the third warning signal (i.e. the 406MHz frequency band emergency signal containing the location protocol information after decoding), since the location protocol contains both the beacon identification information and the location information, the location information can be directly decoded and extracted. Then, the beacon identification information in the alarm signal is matched with an aviation emergency rescue database, and detailed information (namely identity information) of the state, the driver information, the flight number, the aircraft responder code and the like of the aircraft involved in the accident is obtained. And finally, the data is transmitted to an alarm display device 300 at the rear end to display and release the position, the target direction, the distance, the identity and the like of the GIS map.

Further, the fusion matching module 208 can perform corresponding information fusion and intelligent matching processing according to different specific areas (i.e. air route areas or areas near airports); specifically, as shown in fig. 3, the fusion matching module 208 may include a first fusion matching unit 2081 and a second fusion matching unit 2082, and the processing of the first fusion matching unit 2081 and the second fusion matching unit 2082 for different regions includes the following three ways:

1) when the aircraft involved in the accident is located in the air route area, the detailed identity information of the aircraft involved in the accident is linked with the airport route monitoring system and the communication system through the first fusion matching unit 2081, and then information fusion and intelligent matching are carried out on the detailed identity information and the system, so that situation information such as the position and the motion state information of the aircraft involved in the accident can be obtained. As shown in fig. 1 and 4, the communication system includes, but is not limited to: wide area multipoint positioning system, Aircraft Communication Addressing and Reporting System (ACARS), aeronautical surveillance radar (ARSR), and aeronautical ADS-B system.

2) When the aircraft involved in the accident is located in the air route area and the transponder on the aircraft involved in the accident is in an open state, the second fusion matching unit 2082 is used for carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident and an airport scene monitoring system so as to obtain the position information of the aircraft involved in the accident. As shown in fig. 1 and 4, the airport surface monitoring system includes, but is not limited to, the following mainstream systems: a scene ADS-B system, a scene multipoint positioning system, a field monitoring secondary radar, an A-CDM system and an A-SMGCS system.

3) When the aircraft involved in the accident is located in the air route area and the answering machine on the aircraft involved in the accident is in the closed state, the second fusion matching unit 2082 is used for conducting information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident, the airport command and scheduling system and the airport collaborative decision-making system, and obtaining information such as a flight plan and an airport number of the aircraft involved in the accident, so that management personnel can be assisted to quickly locate the stop position of the aircraft, and finally the position information of the aircraft involved in the accident is obtained.

Further, as shown in fig. 5, the above-mentioned alarm display device 300 of the present application may include a third data transmission module 301, an alarm information display module 302, and an alarm data processing module 303.

Specifically, the third data transmission module 301 is configured to receive data transmitted by the information integrated processing device 200 through the communication network, where the data includes the aforementioned location information of the aircraft involved in the accident, the identity information of the aircraft involved in the accident, information that the aircraft involved in the accident is located in an area near an airport surface or an air route area, and situation information of the aircraft involved in the accident.

The warning information display module 302 is configured to display warning information to be displayed; the alarm information to be displayed may include the ELT type of the aircraft involved in the event, the number of alarms, the airline company involved in the event, the distribution of the event area, and the like.

The alarm data processing module 303 is configured to pre-process the data received by the third data transmission module 301, where the pre-process includes transmitting alarm information to be displayed in the data to the alarm information display module 302 for displaying.

Further, the alarm data processing module 303 may pre-process the data, and may select multiple types as needed, in addition to transmitting the alarm information to be displayed in the data to the alarm information display module 302 for display; as shown in fig. 5, in this embodiment, it is further preferable that the alarm data processing module 303 may include a data storage module 3031, an information classification and statistics module 3032, an alarm checking and issuing module 3033, a GIS map display module 3034, and an aviation emergency rescue database updating module 3035.

Specifically, the data storage module 3031 is configured to store the received data; the information classification and statistics module 3032 is configured to perform intelligent statistics and analysis on the received data according to different types of ELT alarm events, and periodically output a data analysis result to the alarm information display module 302 for display; the alarm checking and issuing module 3033 is used for automatically generating and reporting a checking flow report according to relevant operation regulations of civil aviation, and intelligently issuing the data stored in the data storage module 3031 to relevant units; a GIS map display module 3034, configured to display the location and the surrounding environment of the emergency signal; and the aviation emergency rescue database updating module 3035 is used for connecting with a civil aviation aircraft radio station license management system to update the aviation emergency rescue database in real time.

To sum up, the alarm data processing module 303 can have at least the following four main functions through the linkage of the modules:

1) the results output by the information integrated processing device 200 are processed and stored, and the results are intelligently distributed to relevant units, such as the aviation department of the concerned aircraft, the local supervision bureau, the district air administration unit, the airport unit where the aircraft stops, and the like.

2) And feeding back the processed result to the alarm information display module 302 for display.

3) And after carrying out intelligent statistics and analysis on the ELT alarm event, periodically outputting data analysis results including ELT types, alarm quantity, event-related airline companies, event area distribution and the like of the event-related aircraft.

4) The method keeps synchronization with an aviation emergency rescue database, and ensures timely updating of an aircraft information data source.

Finally, the above-mentioned various existing service systems involved in the information fusion and intelligent matching process of the fusion matching module 208 are further explained as follows:

1) secondary radar for field monitoring

In the field monitoring secondary radar positioning technology, an interrogation radar of an airport surface transmits an interrogation signal to the airport surface in a certain mode, a transponder mounted on an airplane receives the interrogation signal, processes and decodes the interrogation signal to send a reply signal back to a ground interrogation radar, and the ground interrogation radar obtains the reply signal and then decodes the reply signal to obtain information such as the position, the height and the like of the airplane.

2) ADS-B positioning system

The ADS-B positioning is broadcast information sent by a ground ADS-B receiver-borne ADS-B device, and the broadcast information contains various information such as airplane satellite positioning and airplane labels, so that the airplane position is obtained.

3) Wide area multipoint positioning system/scene multipoint positioning system

The multipoint positioning technology mainly utilizes a plurality of receiving stations to receive the same response signal transmitted by a target, and realizes target positioning by calculating the arrival time difference of signals received by each receiving station. According to different application scenes, the multipoint positioning system can be divided into two types: airport surface multipoint positioning systems and wide area multipoint positioning systems. The former is mainly applied to airport scene to monitor the aircrafts on the scene; while the latter applies to approach or route.

4) A-SMGCS system

The English language of the A-SMGC System is called (Advanced Surface Movement Guidance Control System) as an Advanced scene activity Guidance Control System. The A-SMGCS system mainly realizes the control of the airplane and the vehicle of the airport scene activity through the functions of monitoring, controlling, routing planning and guiding so as to improve the efficiency and the safety of the scene activity under various operating conditions. The ASMGCS system greatly improves the scene operation efficiency and ensures the safe production of civil aviation operation.

5)A-CDM

An airport collaborative decision making system (a-CDM) is an operational mode in which entities such as airports, air traffic controllers, airlines, etc. share and process data in a more efficient, transparent manner. The system is characterized in that each participant shares data to an A-CDM information platform, and the data information of each participant is integrated through the system, so that cooperative decision among units such as airports, air traffic control units, airlines and the like taking 'airports' as centers is realized, the operating efficiency and quality of the airports are improved, and the aim of greatly improving the overall operating efficiency on the premise of normal operation of flights is finally achieved.

6) Airway surveillance radar

The route surveillance radar is a long-range air traffic surveillance radar working by using a primary radar principle. The range is about 460km (250n mile) and is used to monitor the aircraft on the route, to keep track of the aircraft, and to check the spacing maintained between adjacent aircraft.

7) Aircraft Communication Addressing and Reporting System (ACARS)

The ACARS data chain system realizes data message transmission between the airplane and the ground through three digital communication sub-links of very high frequency radio communication, high frequency radio communication and satellite communication of airplane airborne equipment and ground-air data communication service providers, establishes connection between the airplane and ground terminal users and realizes data communication between the ground system and the airplane.

8) Command dispatching system (AOC)

The AOC, namely the operation command center of the airport, sends out various instructions in time like the brain of the airport: and dispatching and coordinating all the guarantee departments of the ground, the engineering and the like of the airport to make guarantee service for all flights. Such as after a flight has fallen, at what flight stop, etc., may all need to be scheduled via the command at the AOC.

In a second aspect, the application also discloses an aircraft emergency distress signal monitoring method, which mainly comprises a dual-frequency signal monitoring step S10, an information comprehensive processing step S20 and an alarm display processing step S30. It should be noted that, in the aircraft emergency distress signal monitoring method of the present application, hardware and module systems related to the aircraft emergency distress signal monitoring method may be, but are not limited to, implemented by using any one of the aircraft emergency distress signal monitoring systems described in the first aspect, and may also be implemented by using other systems that can use the same function.

Specifically, the dual-frequency signal monitoring step S10 includes the following sub-steps:

step S101, synchronously monitoring and acquiring emergency signals sent by the aircraft involved in the accident, wherein the emergency signals comprise frequency bands of 121.5MHz and 406 MHz.

And S102, judging the frequency band of the monitored emergency signal, wherein the frequency band is judged to be a 121.5MHz frequency band or a 406MHz frequency band or both the frequency bands.

S103, when the emergency signal with the frequency band of 121.5MHz exists, judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal;

and when the frequency band of 406MHz is provided with the emergency signal, decoding the frequency band emergency signal to obtain coding protocol information, wherein the coding protocol information comprises position protocol information or user protocol information.

And S104, judging the type of the decoded information, and judging the initial position and the area range of the accident-related aircraft which sends the corresponding emergency signal when the 406MHz frequency band emergency signal only contains user protocol information after decoding.

Step S105, transmitting the monitored emergency signal and the corresponding processing result to the outside through a communication network;

similarly, the information integrating process step S20 may include a plurality of sub-steps:

step S201, receiving the information transmitted in the dual frequency signal monitoring step through the communication network.

Step S202, judging the types of emergency signals in the received information, wherein the types of emergency signals include emergency signals in a 121.5MHz frequency band, emergency signals in a 406MHz frequency band which only contain user protocol information after decoding, and emergency signals in the 406MHz frequency band which only contain position protocol information after decoding.

And S203, when the received information is an emergency signal of the frequency band of 121.5MHz, performing area position matching processing on the synchronously received preliminary direction of the aircraft involved in the accident and the range information of the area involved in the accident to obtain the position and partial identity information of the aircraft involved in the accident, and performing matching processing on the partial identity information and an aviation emergency rescue database to obtain the detailed identity information of the aircraft involved in the accident.

Step S204, when the received information is a 406MHz frequency band emergency signal and the corresponding coding protocol information is position protocol information, decoding and extracting the position protocol information to obtain the position information of the aircraft involved in the accident, and meanwhile, matching beacon identity identification information in the position protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident;

when the received information is a 406MHz frequency band emergency signal and the corresponding encoding protocol information is user protocol information: firstly, matching beacon identity identification information in user protocol information with an aviation emergency rescue database to obtain detailed identity information of an aircraft involved in an accident; and then, matching the synchronously received preliminary position and area range information of the aircraft involved in the accident with a map of an airport, and judging whether the aircraft involved in the accident is located in an area near the airport scene or an air route area.

And S205, performing information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident through the multi-service system in the area near the airport scene or the air route area judged in the step S204, so as to obtain the situation information of the aircraft involved in the accident.

In addition, in step S205, corresponding information fusion and intelligent matching processing can be performed according to the specific area (that is, the air route area or the area near the airport); specifically, step S205 can be further divided into the following steps:

s2051, whether the aircraft involved in the accident is located in the air route area or the area near the airport is judged.

And S2052, when the aircraft involved in the accident is located in the air route area, carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident, the airport route monitoring system and the communication system so as to obtain the position and motion state information of the aircraft involved in the accident.

and if the answering machine on the aircraft involved in the accident is in a closed state, carrying out information fusion and intelligent matching on the detailed identity information of the aircraft involved in the accident, the airport commanding and dispatching system and the airport cooperative decision system so as to obtain the position information of the aircraft involved in the accident.

Step S206, transmitting the various processing result data performed in the above steps to the outside through a communication network. The various processing result data may include position information of the aircraft involved in the event, identity information of the aircraft involved in the event, information that the aircraft involved in the event is located in an area near an airport surface or an air route area, situation information of the aircraft involved in the event, and the like.

Similarly, the alarm display processing step S30 may include multiple sub-steps:

step S301, receiving the data transmitted in the information integrating process step through the communication network.

Step S302, preprocessing the data, including displaying the alarm information to be displayed.

In step S302, the data is preprocessed, and multiple processing manners may be selected as needed, and in this embodiment, the following processing steps are preferably included:

and step S3021, storing the received data.

And step S3022, intelligently counting and analyzing the received data according to different types of ELT alarm events, and periodically outputting data analysis results to an alarm information display module for display.

And S3023, automatically generating and reporting a checking process report according to the relevant operation regulations of civil aviation, and intelligently releasing the stored data to relevant units.

And step S3024, displaying the position of the emergency signal and the surrounding environment.

And S3025, connecting the station license management system with the civil aviation aircraft station license management system to update the aviation emergency rescue database in real time.

It should be noted that, although the various preprocessing steps performed on the data in step S302 are arranged according to the numbering sequence, in other preferred embodiments, the sequence of the preprocessing steps may be appropriately adjusted as needed, and details are not described here.

In summary, the aircraft emergency distress signal monitoring system and method of the present application have at least the following advantages:

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. The aircraft emergency distress signal monitoring system is characterized by comprising a dual-frequency signal monitoring device (100) arranged at an airport, an information comprehensive processing device (200) and an alarm display device (300), wherein the alarm display device (300) is arranged at the airport

The dual-frequency signal monitoring device (100) is configured to:

judging the frequency band of the monitored emergency signal; and

the information integrated processing apparatus (200) is configured to:

receiving information transmitted by the dual-frequency signal monitoring device (100) through a communication network; and

the alert display apparatus (300) is configured to:

receiving data transmitted by the information integrated processing device (200) through a communication network; and

2. Aircraft emergency distress signal monitoring system according to claim 1, characterized in that the dual frequency signal monitoring device (100) comprises:

the signal monitoring module (101) is used for synchronously monitoring emergency signals sent by the aircraft involved in an accident;

the signal type judging module (102) is used for judging the frequency bands of the emergency signals monitored by the signal monitoring module (101), wherein the frequency bands comprise the frequency bands of 121.5MHz and 406 MHz;

the signal decoding processing module (103) is used for decoding the frequency band emergency signal when the 406MHz frequency band emergency signal is monitored, and acquiring corresponding coding protocol information, wherein the coding protocol information comprises position protocol information or user protocol information;

the signal characteristic analysis and tracking module (104) is used for carrying out characteristic analysis on the signal intensity and the incoming wave direction of the monitored emergency signal, judging the distance and the direction of the aircraft involved in the accident, and continuously tracking the signal of the aircraft involved in the accident;

the signal direction and area range calculation module (105) is used for judging the initial direction and the accident-related area range of the accident-related aircraft which sends out the corresponding emergency signal based on the processing result of the signal characteristic analysis and tracking module (104) when the 121.5MHz frequency band emergency signal or the 406MHz frequency band emergency signal which is monitored is decoded and only contains user protocol information;

and the first data transmission module (106) is used for transmitting the monitored emergency signals and the corresponding processing results to the outside through a communication network.

3. Aircraft emergency distress signal monitoring system according to claim 1, characterized in that the information integrated processing device (200) comprises:

the second data transmission module (201) is used for receiving the information transmitted by the dual-frequency signal monitoring device (100) through a communication network and transmitting various processing result data performed by the information comprehensive processing device (200) to the outside through the communication network;

an information type judging module (202) for judging the type of the information received by the second data transmission module (201), wherein the information type includes a 121.5MHz frequency band emergency signal, a 406MHz frequency band emergency signal only containing user protocol information after decoding, and a 406MHz frequency band emergency signal only containing location protocol information after decoding;

the decoding information extraction module (203) is used for decoding and extracting the position protocol information to obtain the position information of the aircraft involved in the accident when receiving the 406MHz frequency band emergency signal only containing the position protocol information after decoding;

the first information matching module (204) is used for matching the beacon identity identification information in the position protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident when a 406MHz frequency band emergency signal which only contains the position protocol information after decoding is received;

the second information matching module (205) is used for matching the beacon identity identification information in the user protocol information with an aviation emergency rescue database to obtain detailed identity information of the aircraft involved in the accident when receiving the 406MHz frequency band emergency signal which only contains the user protocol information after decoding;

the third information matching module (206) is used for performing region and position matching processing on the synchronously received preliminary position of the aircraft involved in the accident and the information of the range of the area involved in the accident when the emergency signal of the frequency band of 121.5MHz is received so as to obtain the position and partial identity information of the aircraft involved in the accident, and performing matching processing on the partial identity information and an aviation emergency rescue database so as to obtain the detailed identity information of the aircraft involved in the accident;

the alarm target area judgment module (207) is used for matching the synchronously received preliminary direction and the information of the area range of the accident-related aircraft with the map of the airport when receiving the 406MHz frequency band emergency signal which only contains the user protocol information after decoding, and judging whether the accident-related aircraft is located in the area near the airport surface or the air route area;

and the fusion matching module (208) is used for performing information fusion and intelligent matching with the detailed identity information of the corresponding aircraft involved in the accident through a multi-service system in an area near an airport scene or an air route area so as to acquire the situation information of the aircraft involved in the accident.

4. The aircraft emergency distress signal monitoring system of claim 3, wherein the fusion matching module (208) comprises:

the first fusion matching unit (2081) is used for carrying out information fusion and intelligent matching on the detailed identity information of the accident-related aircraft, an airport airway monitoring system and a communication system when the accident-related aircraft is located in an airway area so as to obtain the position and motion state information of the accident-related aircraft;

and the second fusion matching unit (2082) is used for carrying out information fusion and intelligent matching on the detailed identity information of the aircraft and an airport scene monitoring system when the aircraft is located in the area near an airport and the transponder on the aircraft is in an open state so as to acquire the position information of the aircraft.

5. The aircraft emergency distress signal monitoring system according to claim 4, wherein the second fused matching unit (2082) is further configured to:

6. Aircraft emergency distress signal monitoring system according to claim 5, characterized in that the alert display device (300) comprises:

a third data transmission module (301) for receiving data transmitted by the information integrated processing apparatus (200) through a communication network;

the alarm information display module (302) is used for displaying the alarm information to be displayed;

and the alarm data processing module (303) is used for preprocessing the data received by the third data transmission module (301), wherein the preprocessing comprises the step of transmitting the alarm information to be displayed in the data to the alarm information display module (302) for displaying.

7. The aircraft emergency distress signal monitoring system of claim 6, wherein the alarm data processing module (303) comprises:

a data storage module (3031) for storing the received data;

the information classification and statistics module (3032) is used for carrying out intelligent statistics and analysis on the received data according to different types of ELT alarm events and outputting data analysis results to the alarm information display module (302) for display at regular intervals;

the alarm checking and issuing module (3033) is used for automatically generating and reporting a checking flow report according to relevant operation regulations of civil aviation and intelligently issuing the data stored in the data storage module (3031) to relevant units;

the GIS map display module (3034) is used for displaying the position of the emergency signal and the surrounding environment;

and the aviation emergency rescue database updating module (3035) is used for connecting with a civil aviation aircraft radio station license management system so as to update the aviation emergency rescue database in real time.

8. An aircraft emergency distress signal monitoring method, which is characterized in that the aircraft emergency distress signal monitoring system according to any one of claims 1 to 7 is adopted, and comprises a double-frequency signal monitoring step, an information comprehensive processing step and an alarm display processing step; wherein

The dual-frequency signal monitoring step comprises the following sub-steps:

judging the frequency band of the monitored emergency signal;

when the frequency band emergency signal with 406MHz is available, decoding the frequency band emergency signal to obtain coding protocol information, wherein the coding protocol information comprises position protocol information or user protocol information;

the information comprehensive processing step comprises the following substeps:

the alarm display processing step includes the following substeps:

9. The aircraft emergency distress signal monitoring method according to claim 8, wherein the substep of performing information fusion and intelligent matching with detailed identity information of a corresponding accident-related aircraft through a multi-service system in an area near the airport surface or an air route area to acquire situation information of the accident-related aircraft specifically comprises:

10. The aircraft emergency distress signal monitoring method of claim 8, wherein in the alert display processing step, the sub-step of pre-processing the data further comprises:

storing the received data;