Ejectable flight recording system

Abstract

The present application relates to the field of avionics technology for civil aircraft, and in particular to an ejectable flight recording system. The ejectable flight recording system provided in the embodiment of the present application, the application stages of the ejectable flight recording system include the ADT stage and the PFLR stage; the ADT stage includes a processing component, the PFLR stage includes a detachable component, the detachable component includes an emergency positioning transmitter and an antenna, the antenna is connected to the emergency positioning transmitter, and the emergency positioning transmitter is connected to the data management memory and the processing component to realize position reporting and alarming in the ADT stage and the PFLR stage. The ejectable flight recording system provided in the present application uses one emergency positioning transmitter in the ADT stage and the PFLR stage. Such a setting can not only meet the system's requirements for advancing aircraft tracking and monitoring, but also realize the reuse, integration and weight reduction of the emergency positioning transmitter, further saving aircraft costs.

Description

Technical Field

[0001] The present application relates to the field of avionics technology for civil aircraft, and in particular to an ejectable flight recording system. Background Art

[0002] The current air navigation system still has limitations that hinder the timely identification and positioning of distressed aircraft and the implementation of effective search and rescue operations, resulting in delayed or even impossible recovery of flight recorder data from the aircraft involved.

[0003] ICAO member states and the global aviation industry have begun systematically promoting aircraft tracking and monitoring, and have proposed the Global Aeronautical Distress and Safety System (GADSS). GADSS consists of three phases: Aircraft Tracking (AT), Autonomous Distress Tracking (ADT), and Post-Flight Location and Recovery (PFLR). The AT phase, representing normal aircraft operation, requires air carriers to track the position of their aircraft operating over oceanic areas through automatic reporting at least every 15 minutes (4D / 15 tracking). The ADT phase requires all aircraft with a maximum certificated takeoff mass exceeding 5,700 kg, issued for the first time as a single-aircraft airworthiness certificate, to autonomously transmit information enabling the operator to determine their position at least once per minute in the event of distress. The PFLR phase requires all aircraft with a maximum certificated takeoff mass exceeding 27,000 kg and authorized to carry more than 19 passengers, submitting type certification applications to a Contracting State, to be equipped with a device approved by the State of the Operator to recover and promptly provide aircraft recorder data. An Automatic Deployable Flight Recorder (ADFR) is one of the recommended features.

[0004] In related technologies, the specific implementation forms of the two-stage requirements of ADT and PFLR proposed in the GADSS operational concept are relatively independent, which is not conducive to aircraft weight reduction and integration. Summary of the Invention

[0005] The present application provides an ejectable flight recording system that can effectively solve the above or other potential technical problems.

[0006] An embodiment of the present application provides an ejectable flight recording system, wherein the application stages of the ejectable flight recording system include an ADT stage and a PFLR stage; the ADT stage includes a processing component, the PFLR stage includes a detachable component, the detachable component includes an emergency locator transmitter and an antenna, the antenna is connected to the emergency locator transmitter, and the emergency locator transmitter is connected to a data management memory and the processing component to implement position reporting and alarming in the ADT stage and the PFLR stage.

[0007] The ejectable flight recording system provided in an embodiment of the present application has application stages including an ADT stage and a PFLR stage. The ADT stage includes a processing component, and the PFLR stage includes a detachable component. The detachable component includes an emergency locator transmitter and an antenna. The antenna is connected to the emergency locator transmitter, and the emergency locator transmitter is connected to a data management memory and the processing component to implement position reporting and alarming during the ADT and PFLR stages. The ejectable flight recording system provided in the present application uses a single emergency locator transmitter in both the ADT and PFLR stages. This configuration not only meets the system's requirements for aircraft tracking and monitoring, but also enables the reuse, integration, and weight reduction of emergency locator transmitters, further saving aircraft costs.

[0008] In an optional embodiment, the ADT stage further includes a sensing information component and a distress trigger conversion module; the PFLR stage further includes a mounting bracket component; the sensing information component is used to sense aircraft status information and send the aircraft status information; the mounting bracket component includes an ejection control module and an ejection separation mechanism, the ejection control module judges the aircraft status information, and when the aircraft status information meets the ejection condition, sends an ejection signal to the ejection separation structure; the detachable component is detachably connected to the mounting bracket component, the ejection separation structure receives the ejection signal, and drives the detachable component to separate from the mounting bracket component; the detachable component also The system comprises a data management memory for receiving and storing flight data and audio data; the distress trigger conversion module receives the distress signal from the processing component and makes a comprehensive judgment based on the distress signal and the trigger logic. If it is judged to be the first distress stage, an activation signal is sent to the emergency locator transmitter to activate the emergency locator transmitter to autonomously transmit information determining the location at a rate of at least once per minute; if it is judged to be the second distress stage, an activation signal is immediately sent to the ejection control module. The ejection control module combines the signal from the sensing information component and makes a comprehensive judgment that it is the crash stage, and then sends an ejection trigger signal to the ejection separation mechanism.

[0009] In an optional embodiment, the sensing information component includes a first impact detection sensor and a first water sensor connected to the fuselage, and the first impact detection sensor and the first water sensor are both connected to the ejection control module for sending first aircraft status information to the ejection control module.

[0010] In an optional embodiment, the number of the first impact detection sensors is three, and the three first impact detection sensors are respectively arranged at the head, belly and tail of the aircraft.

[0011] In an optional embodiment, the mounting bracket assembly further includes a second impact detection sensor and a second water sensor, both of which are connected to the ejection control module for sending second aircraft status information to the ejection control module.

[0012] In an optional embodiment, the ejection control module includes a crash status identifier and a sensor status monitor; the crash status identifier is used to comprehensively judge the first aircraft status information, the second aircraft status information and the activation signal sent by the distress trigger conversion module; the sensor status monitor is used to monitor whether the first impact detection sensor, the second impact detection sensor, the first water sensor and the second water sensor are faulty.

[0013] In an alternative embodiment, the processing component comprises an ADT computer.

[0014] In an optional embodiment, the detachable component further includes a battery module, which is connected to the data management module and is used to provide electrical energy to the data management module.

[0015] In an optional embodiment, the data management memory includes a data management module and an information memory, the data management module is used to receive flight data and audio data, and the information memory is used to store flight data and audio data.

[0016] In an optional embodiment, the antenna includes a Beidou antenna, or the antenna includes a Beidou antenna and a radio antenna.

[0017] Advantages of additional aspects of the present application will be given in part in the following description, and in part will become apparent from the following description, or will be learned through practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] The above and other objects, features and advantages of the embodiments of the present application will become more readily understood through the following detailed description with reference to the accompanying drawings, in which various embodiments of the present application are illustrated by way of example and not limitation, wherein:

[0019] Figure 1 An overall schematic diagram of the ejectable flight recording system provided in an embodiment of the present application;

[0020] Figure 2 This is a schematic diagram of an implementation of an ejectable flight recording system provided in an embodiment of the present application. DETAILED DESCRIPTION

[0021] The following describes in detail embodiments of the present application, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present application, and should not be construed as limiting the present application.

[0022] It should be understood that the following embodiments do not limit the execution order of the steps in the method protected by the present application. The steps of the method of the present application can be executed in any possible order and in a cyclic manner without conflict.

[0023] In the description of this application, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc., indicating the orientation or position relationship, are based on the orientation or position relationship shown in the accompanying drawings, and are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on this application.

[0024] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of the technical features being referred to. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of such features. Throughout the description of this application, "plurality" means at least two, for example, two, three, etc., unless otherwise specifically defined.

[0025] In this application, unless otherwise specified or limited, the terms "mounted," "connected," "connect," "fixed," etc. should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection; direct connection or indirect connection through an intermediate medium; internal communication between two elements or interaction between two elements, unless otherwise specified. Those skilled in the art will understand the specific meanings of the above terms in this application based on specific circumstances.

[0026] In the description of this specification, the description with reference to the terms "one embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and features of different embodiments or examples without contradiction.

[0027] The current air navigation system still has limitations, which hinder the timely identification and positioning of distressed aircraft and the implementation of effective search and rescue operations, resulting in delayed or even impossible recovery of flight recorder data from the aircraft involved.

[0028] ICAO member states and the global aviation industry have begun systematically promoting aircraft tracking and monitoring, and have proposed the Global Aeronautical Distress and Safety System (GADSS). GADSS consists of three phases: Aircraft Tracking (AT), Autonomous Distress Tracking (ADT), and Post-Flight Location and Recovery (PFLR). The AT phase, representing normal aircraft operation, requires air carriers to track the position of their aircraft operating over oceanic areas through automatic reporting at least every 15 minutes (4D / 15 tracking). The ADT phase requires all aircraft with a maximum certificated takeoff mass exceeding 5,700 kg, issued for the first time as a single-aircraft airworthiness certificate, to autonomously transmit information enabling the operator to determine their position at least once per minute in the event of distress. The PFLR phase requires all aircraft with a maximum certificated takeoff mass exceeding 27,000 kg and authorized to carry more than 19 passengers, submitting type certification applications to a Contracting State, to be equipped with a device approved by the State of the Operator to recover and promptly provide aircraft recorder data. An Automatic Deployable Flight Recorder (ADFR) is one of the recommended features. In related technologies, the specific implementation forms of the two-stage requirements of ADT and PFLR proposed in the GADSS operational concept are relatively independent, which is not conducive to aircraft weight reduction and integration.

[0029] Research has found that the implementation plan for the ADT stage is based on the emergency locator transmitter (ELT-DT) for distress tracking, and one of the implementation plans for the PFLR stage is ADFR, which also includes an ELT. There is functional overlap in the ELTs involved in the two stages, resulting in a large number of ELTs on board, which is not conducive to aircraft weight reduction and integration.

[0030] Secondly, the current positioning information of the ELT on board mainly comes from GNSS. On July 31, 2020, the Beidou-3 global satellite navigation system was officially launched, which also marked the completion and start of trial operation of the Beidou international search and rescue system. In order to realize the autonomous control of domestic civil aircraft, it is possible to consider using Beidou beacons for emergency positioning of ejectable flight recorders and realize the integration of radio beacons and Beidou positioning beacons.

[0031] This application addresses the problems of low survival rate, difficulty in search and salvage, and high cost of traditional black boxes after maritime or extreme aviation accidents. It proposes a new ejectable flight recorder system that meets the ADT and PFLR requirements of the GADSS operational concept.

[0032] In view of this, an embodiment of the present application provides an ejectable flight recording system, wherein the application stages of the ejectable flight recording system include an ADT stage and a PFLR stage; the ADT stage includes a processing component, and the PFLR stage includes a detachable component, wherein the detachable component includes an emergency locator transmitter and an antenna, wherein the antenna is connected to the emergency locator transmitter, and the emergency locator transmitter is connected to a data management memory and the processing component to implement position reporting and alarming in the ADT stage and the PFLR stage. The ejectable flight recording system provided in the present application uses a common emergency locator transmitter in the ADT stage and the PFLR stage. Such an arrangement can not only meet the system's requirements for advancing aircraft tracking and monitoring, but also achieve the reuse, integration, and weight reduction of the emergency locator transmitter, further saving aircraft costs.

[0033] Please refer to Figure 1 and Figure 2 The ejectable flight recording system provided in the embodiment of the present application has application stages including an ADT stage and a PFLR stage; the ADT stage includes a processing component, the PFLR stage includes a detachable component, the detachable component includes an emergency positioning transmitter and an antenna, the antenna is connected to the emergency positioning transmitter, the emergency positioning transmitter is connected to a data management memory and the processing component to realize position reporting and alarming in the ADT stage and the PFLR stage.

[0034] The ejectable flight recording system provided in an embodiment of the present application has application stages including an ADT stage and a PFLR stage. The ADT stage includes a processing component, and the PFLR stage includes a detachable component. The detachable component includes an emergency locator transmitter and an antenna. The antenna is connected to the emergency locator transmitter, and the emergency locator transmitter is connected to a data management memory and the processing component to implement position reporting and alarming during the ADT and PFLR stages. The ejectable flight recording system provided in the present application uses a single emergency locator transmitter in both the ADT and PFLR stages. This configuration not only meets the system's requirements for aircraft tracking and monitoring, but also enables the reuse, integration, and weight reduction of emergency locator transmitters, further saving aircraft costs.

[0035] It should be noted that the functions of the emergency locator transmitter ELT-DT include radio beacon transmission function (121.5MHz and 406MHz), detection, maintenance functions, etc. It receives signals from the distress trigger conversion module, such as time, location information, activation signals, etc., and realizes the position reporting and alarm functions of the two stages of ADT and PFLR through the antenna.

[0036] It should also be noted that the functional components between the ADT stage and the PFLR stage can cooperate with each other to achieve the operating purpose of each stage. The structural distinction does not mean that the functional components are isolated from each other.

[0037] In an optional exemplary embodiment, the ADT stage further includes a sensing information component and a distress trigger conversion module; the PFLR stage further includes a mounting bracket assembly; the sensing information component is used to sense aircraft status information and send the aircraft status information; the mounting bracket assembly includes an ejection control module and an ejection separation mechanism, the ejection control module receives the aircraft status information; the detachable component is detachably connected to the mounting bracket assembly, the ejection separation structure receives the ejection signal, and drives the detachable component to detach from the mounting bracket assembly; the detachable component also includes a data management memory, the data management memory Used to receive and store flight data and audio data; the distress trigger conversion module receives the distress signal from the processing component and makes a comprehensive judgment based on the distress signal and the trigger logic. If it is judged to be the first distress stage, an activation signal is sent to the emergency locator transmitter to activate the emergency locator transmitter to autonomously transmit information determining the location at a rate of at least once per minute; if it is judged to be the second distress stage, an activation signal is immediately sent to the ejection control module. The ejection control module combines the aircraft status information of the sensing information component and makes a comprehensive judgment to determine that it is the crash stage, and then sends an ejection trigger signal to the ejection separation mechanism.

[0038] It should be noted that, specifically, in this embodiment, the ADT stage also includes a sensing information component and a distress trigger conversion module; the PFLR stage also includes a mounting bracket component. The sensing information component is used to sense aircraft status information and send the aircraft status information, that is, when the sensing information component senses the crash status information, it can send the aircraft status information to the ejection control module; the distress trigger conversion module receives the distress signal from the processing component, and makes a comprehensive judgment based on the distress signal and the trigger logic. If it is judged to be the first distress stage, that is, the general danger stage, which belongs to the ADT stage and no crash will occur, an activation signal is sent to the emergency locator transmitter to activate the emergency locator transmitter to autonomously transmit the information on the determined location at a rate of at least once per minute; if it is judged to be the second distress stage, If the aircraft is in a dangerous stage, that is, a serious dangerous stage (about to fall to the ground or into the sea), and a crash is about to occur, an activation signal is immediately sent to the ejection control module. The ejection control module combines the aircraft status information of the sensing information component and comprehensively judges that it is a crash stage. Then, an ejection trigger signal is sent to the ejection separation mechanism. The ejection separation mechanism receives the ejection signal and can drive the detachable component to separate from the mounting frame component. The data management memory in the detachable component is used to receive and store flight data and audio data. After the detachable component is ejected, it can send positioning and alarm information and protect the data management memory at the same time.

[0039] Specifically, when the aircraft is flying normally, flight data and audio data are received through the data bus and written into the data management memory; when the aircraft crashes, the detachable components automatically separate from the fuselage, rely on the automatic structural and external characteristics of the detachable components to slow down and then fall to the ground or into the water, rely on their own buoyancy to float on the sea surface, and the internal emergency locator transmitter starts working, and the antenna connected to the emergency locator transmitter transmits a distress signal to guide the search and rescue forces to the crash site.

[0040] In an optional exemplary embodiment, the sensing information component includes a first impact detection sensor and a first water sensor connected to the fuselage, and the first impact detection sensor and the first water sensor are both connected to the ejection control module for sending first aircraft status information to the ejection control module.

[0041] It should be noted that the first impact detection sensor is used to sense the impact acceleration signal. When the impact acceleration reaches certain conditions, it outputs an impact effective switching signal. The first impact detection sensor receives the threshold adjustment signal sent by the ejection recorder mounting bracket, and adjusts the sensor threshold and trigger when the distress level changes. The first water sensor is developed using the conductive properties of water. The first water sensor mainly includes a base, a positive conductive sheet, and a negative conductive sheet. A voltage is applied to the positive and negative conductive sheets of the first water sensor. When the first water sensor is not immersed in water, no current will flow between the electrodes. When the first water sensor is immersed in water, the current flows from the positive conductive sheet through the wire ions in the water to the negative conductive sheet. This determines whether the first water sensor is like water, and then determines whether the body has fallen into the water.

[0042] In an optional exemplary embodiment, there are three first impact detection sensors, and the three first impact detection sensors are respectively arranged at the head, belly, and tail of the aircraft.

[0043] It should be noted that there are three first impact detection sensors, which are respectively arranged at the head, belly and tail of the aircraft. They can accurately detect the head, belly and tail of the aircraft to better judge whether the aircraft is about to crash.

[0044] In an optional exemplary embodiment, the mounting bracket assembly further includes a second impact detection sensor and a second water sensor, both of which are connected to the ejection control module for sending second aircraft status information to the ejection control module.

[0045] It should be noted that the mounting bracket assembly also includes a second impact detection sensor and a second water sensor, and the second impact detection sensor and the second water sensor are both connected to the ejection control module. That is, the second impact detection sensor and the second water sensor are arranged in the mounting bracket assembly, which is convenient for comprehensively judging from multiple angles whether the aircraft is facing a crash state, and is used to send second aircraft status information to the ejection control module, so that the ejection control module can make accurate judgments by combining more factors.

[0046] In an optional exemplary embodiment, the ejection control module includes a crash status identifier and a sensor status monitor; the crash status identifier is used to comprehensively judge the first aircraft status information, the second aircraft status information and the activation signal sent by the distress trigger conversion module; the sensor status monitor is used to monitor whether the first impact detection sensor, the second impact detection sensor, the first water sensor and the second water sensor are faulty.

[0047] It should be noted that the crash status identifier has a crash status identification function. It receives the processing component, the first aircraft status information and the second aircraft status information, and outputs an ejection signal when the aircraft is about to crash and the ejection conditions are met.

[0048] It should also be noted that the sensor status monitor has a sensor status monitoring function, which receives outputs of the first impact detection sensor, the second impact detection sensor, the first water sensor and the second water sensor, and determines whether the above sensors are faulty.

[0049] In an alternative exemplary embodiment, the processing component comprises an ADT computer.

[0050] It should be noted that in this embodiment, the ADT computer outputs time, positioning, and distress signals to the distress trigger conversion module through the signals of each system on the AFDX receiver according to its own distress event detection and triggering logic, providing it with a basis for judging the distress position sending trigger and ejection trigger.

[0051] AFDX (Avionics Full Duplex Switched Ethernet) is a standard protocol for data exchange between subsystems in avionics systems, defining electrical characteristics. It is an adaptive modification of the industry-standard Ethernet communication protocol, offering significantly higher reliability, greater adaptability to harsh environments, and enhanced real-time performance.

[0052] In an optional exemplary embodiment, the detachable component further includes a battery module, which is connected to the data management module and is used to provide power to the data management module and the emergency locator transmitter.

[0053] It should be noted that the detachable component also includes a battery module, which is connected to the data management module and is used to provide power to the data management module and the emergency positioning transmitter, thereby ensuring that the emergency positioning transmitter sends positioning information and the antenna transmits a distress signal to guide the search and rescue forces to the accident site.

[0054] In an optional exemplary embodiment, the data management memory includes a data management module and an information memory, the data management module is used to receive flight data and audio data, and the information memory is used to store the flight data and audio data.

[0055] It should be noted that the data management memory includes a data management module and an information memory. The data management module is used to receive flight data and audio data, and the information memory is used to store flight data and audio data. For example, the information memory can store various types of data and provide crash protection for each type of stored data.

[0056] It should also be noted that the main functions of the data management module include: power conversion and management, Ethernet bus communication, data storage management, RS-422 bus communication, status monitoring and status recording functions.

[0057] In an optional exemplary embodiment, the antenna includes a Beidou antenna, or the antenna includes a Beidou antenna and a radio antenna.

[0058] It should be noted that the antenna provided in the embodiment of the present application can be a Beidou antenna, or the antenna can include a Beidou antenna and a radio antenna, thereby ensuring the security and stability of information transmission.

[0059] It should also be noted that the ejectable flight recorder system provided in this application can meet the GADSS operational requirements proposed by the International Civil Aviation Organization (ICAO) and simultaneously implement Beidou positioning on domestically produced civil aircraft. By integrating the ADT computer, distress trigger conversion module, ELT-DT, and ADFR, the system achieves the functional requirements of both the ADT and PFLR phases, embodying the highly integrated nature of civil aircraft and contributing to aircraft weight reduction. It also addresses the current problems of low survival rates, difficulty in search and salvage, and high costs associated with traditional black boxes on civil aircraft following maritime or extreme aviation accidents.

[0060] In order to further understand the operating principle of the ejectable flight recording system provided by this application, the working process of the ejectable flight recording system is described as follows:

[0061] Startup working mode: After the ejectable flight recorder system is powered on, it enters the startup mode, completes the startup self-test of each module, stores the test results in the status word, and reports them to the onboard avionics system;

[0062] Recording working mode: After the ejection flight recording system completes the startup work, it enters the recording working mode. In the recording working mode, the flight data is received through the high-speed serial bus interface, the cockpit audio signal is collected through the audio interface, and various types of data are stored in the information memory in the crash protection storage unit; the acceleration signal and the water entry signal are detected by the first impact detection sensor, the second impact detection sensor, the first water sensor and the second water sensor, and sent to the ejection control module in real time. At the same time, the ADT computer receives the signals of various systems on the AFDX receiver in real time, and after its own distress event detection and trigger logic processing, sends the corresponding signal to the distress trigger conversion module and the ejection control module to provide them with a basis for judgment;

[0063] Maintenance Mode: The data management module of the ejectable flight recorder system enters maintenance mode upon receiving a maintenance command. It receives maintenance commands from maintenance equipment via the Ethernet bus interface and performs maintenance operations such as data unloading, configuration loading, program loading, and radio testing on the recorder system. It enters recording mode upon receiving a recording status command while in maintenance mode or when the maintenance bus is idle.

[0064] Distress Alert Mode: When the ejectable flight recorder is in recording mode and a distress condition is met, it enters distress alert mode. The ADT computer and distress trigger conversion module output a start-locating signal. This start-locating signal activates the ELT-DT in the ejection recorder. When the distress condition is resolved while in distress alert mode, the system enters recording mode.

[0065] Ejection Separation Mode: When the ejection conditions are met while the ejectable flight recorder is in distress mode, the system enters ejection separation mode. The ejection control module within the ejection recorder mounting bracket outputs an ejection signal. This signal activates the ejection separation mechanism, disconnecting the ejection recorder's electrical and mechanical connections and simultaneously generating thrust to eject the ejection recorder from the aircraft.

[0066] Survival recovery mode: The ejectable flight recording system enters the survival recovery mode after completing the jettison and separation. The ejection recording system lands on the ground or floats on the sea surface through deceleration and impact-resistant structure to protect the internal data. The ELT-DT in the ejection recording system continues to work according to the positioning workflow to achieve radio positioning.

[0067] Finally, it should be noted that the above implementation modes are only used to illustrate the technical solutions of the present application, rather than to limit them. Although the present application has been described in detail with reference to the aforementioned implementation modes, ordinary technicians in this field should understand that they can still modify the technical solutions described in the aforementioned implementation modes, or replace some or all of the technical features therein with equivalents. However, these modifications or replacements do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the implementation modes of the present application.

[0068] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable manner without contradiction. To avoid unnecessary repetition, this application will not further describe various possible combinations.

Claims

1. An ejectable flight recording system, characterized in that: The application phases of the ejectable flight recorder system include an ADT phase and a PFLR phase; the ADT phase includes a processing component, the PFLR phase includes a detachable component, the detachable component includes an emergency locator transmitter and an antenna, the antenna is connected to the emergency locator transmitter, and the emergency locator transmitter is connected to a data management memory and the processing component to implement position reporting and alarming in the ADT phase and the PFLR phase; The ADT stage also includes a sensing information component and a distress trigger conversion module; the PFLR stage also includes a mounting frame component; The information sensing component is used to sense aircraft status information and send the aircraft status information; The mounting frame assembly includes an ejection control module and an ejection separation mechanism, wherein the ejection control module receives the aircraft status information; The detachable component is detachably connected to the mounting frame assembly, and the ejection separation mechanism receives an ejection signal and drives the detachable component to separate from the mounting frame assembly; The detachable assembly further includes a data management memory configured to receive and store flight data and audio data; The distress trigger conversion module receives the distress signal from the processing component and makes a comprehensive judgment based on the distress signal and the trigger logic. If it is determined to be the first distress stage, it sends an activation signal to the emergency locator transmitter to activate the emergency locator transmitter to autonomously transmit the information determining the location at a rate of at least once per minute. If it is determined to be the second distress stage, it immediately sends an activation signal to the ejection control module. The ejection control module combines the aircraft status information from the sensing information component and makes a comprehensive judgment that it is the crash stage, and then sends an ejection trigger signal to the ejection separation mechanism. The ADT refers to autonomous distress tracking, and the PFLR refers to post-flight location and recovery.

2. The ejectable flight recording system according to claim 1, characterized in that: The sensing information component includes a first impact detection sensor and a first water sensor connected to the aircraft body. The first impact detection sensor and the first water sensor are both connected to the ejection control module and are used to send first aircraft status information to the ejection control module.

3. The ejectable flight recording system according to claim 2, characterized in that: There are three first impact detection sensors, which are respectively arranged at the head, belly and tail of the aircraft.

4. The ejectable flight recording system according to claim 2, characterized in that: The mounting bracket assembly further includes a second impact detection sensor and a second water sensor, both of which are connected to the ejection control module and configured to send second aircraft status information to the ejection control module.

5. The ejectable flight recording system according to claim 4, characterized in that: The ejection control module includes a crash state identifier and a sensor state monitor; the crash state identifier is used to comprehensively determine the first aircraft state information, the second aircraft state information and the activation signal sent by the distress trigger conversion module; The sensor status monitor is used to monitor whether the first impact detection sensor, the second impact detection sensor, the first water sensor, and the second water sensor are faulty.

6. The ejectable flight recording system according to claim 1, wherein: The processing component includes an ADT computer.

7. The ejectable flight recording system according to any one of claims 2 to 6, characterized in that: The data management memory includes a data management module and an information memory. The detachable component also includes a battery module. The battery module is connected to the data management module and is used to provide power to the data management module and the emergency locator transmitter.

8. The ejectable flight recording system according to any one of claims 2 to 6, characterized in that: The data management memory includes a data management module and an information memory. The data management module is used to receive flight data and audio data, and the information memory is used to store flight data and audio data.

9. The ejectable flight recording system according to any one of claims 2 to 6, characterized in that: The antenna includes a Beidou antenna, or the antenna includes a Beidou antenna and a radio antenna.

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