RU2615602C1 - Board system of control and regcording of flight information - Google Patents

Abstract

FIELD: physics, measurement equipment.

SUBSTANCE: invention refers to information-measuring engineering and can be used for flight data collection and recording, saving in case of air accidents, as well as for operational monitoring of aircraft systems and equipment. To do this, the system includes a protected onboard storage POS, a maintained protected onboard storage MPOS, an operational onboard storage OOS, saved onboard storage SOS; audio and video data acquisition unit AVDU, wherein each of the units: AVDU, POS, MPOS, OOS, is connected to the onboard aircraft computer network switch via AFDX bus; redundant power supplies RPS, which are connected to each system unit (except for SOS): POS, MPOS, OOS have one RPS unit, and AVDU unit has 3 RPS units; 2 video cameras connected to the AVDU unit, each of which is associated with it through one APINC 818 channel, a microphone that is connected to the VDU unit, and channels of multifunction indicators MFI are connected to the AVDU unit, at that, the AVDU unit output is connected to the SOS unit input, connected to the AVDU unit, the AVDU unit is associated with the MSOS unit, system units, including AVDU, are connected to the common power bus of the aircraft, at that the AVDU unit is connected to data inputs, alarm sensor, which is connected to each system unit and assigned to generate an "Alarm" signal.

EFFECT: invention provides expansion of system functionality by providing backup power, emergency frame transmission backup for flight information recording, monitoring of the aircraft systems information channel status with report development, increasing the inter-unit exchange bandwidth.

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Description

The invention relates to information-measuring equipment and can be used to collect and record flight data (parametric, sound, video information), save this information in case of flight accidents (including above the water surface), as well as for operational control of aviation systems and equipment .

Known technical solution "Data registration system" RF patent No. 2427802, IPC G01D 9/00, publ. August 27, 2011

The device comprises an information collection and processing unit, which consists of an information collection and conversion module, a control module and a flight information processing module, interconnected via an internal bus of the information collection and processing unit, and has information inputs and outputs for connecting to sensors and controlled systems facility, operational on-board drive, protected on-board drive, which consists of a protected drive, a protected drive controller and a sound information processing module interconnected via an internal bus of a secure on-board storage device connected to an information collection and processing unit, wherein the information collection and processing unit is connected by bi-directional serial communication with an operational on-board storage device, in addition, an information collection and processing unit, an operational on-board storage device and a protected the on-board drive is equipped with total operating time modules connected to the internal buses of the respective units.

The disadvantage of the device is limited functionality due to the lack of recording of video information, the impossibility of recording information in the event of a power failure, which leads to insufficient objectivity in the investigation of flight accidents, as well as the low reliability of the system due to the use of an electric cable network between the system units, the inability to search for an emergency recorder in an accident above the water surface.

The technical result of the invention consists in expanding the functionality of the system by providing backup power, reserving the flight information transmission channel, monitoring the state of the information channel of aircraft systems with reporting, increasing the throughput of inter-unit communication and increasing the level of electromagnetic compatibility.

The technical result is achieved by the fact that the on-board system for monitoring and recording flight information contains a secure on-board storage device ZBN, which consists of a power module, a computing module, a controller of a protected drive and a protected drive; SZBN stored protected on-board drive, which consists of a power module, a computing module, a protected drive controller and a stored memory module, consisting of a protected drive and an emergency radio beacon module with GPS / GLONASS module, designed to transmit information about the location of the unit to the COSPAS-SARSAT system ; EBN operational on-board drive, which consists of a power module, a computing module, a removable information storage controller and a removable information storage device; rescue on-board storage RLS, which consists of a power module, a computing module and an internal memory module; the audio and video information collection unit of the BZVI, which consists of a power module, a computing module, an audio information processing module, a video information processing module, an Ethernet channel switch module, interconnected via an Ethernet channel through an Ethernet channel switch module, which is part of the BZVI unit. Each of the blocks: BZVI, ZBN, SZBN, EBN, is connected via the AFDX bus to the switch of the onboard computer network of the aircraft. The system includes backup RIP power sources that are connected to each block of the system (except for RLS): to blocks ZBN, SZBN, EBN one block RIP, and to block BZVI 3 blocks RIP. The system includes video cameras that are connected to the BZVI unit and each of which is connected to it through one ARINC 818 channel. The system includes microphones that are connected to the BVI unit and are designed to transmit sound conditions in the crew cabin. Channels from multifunctional indicators (MFIs) are connected to the BZVI block, intended for transmitting video information displayed on these MFIs to the BZVI block. The output of the BZVI block is connected to the input of the RLS block to provide power to the RLS block, as well as interconnection via the Ethernet channel. The SBN unit is connected to the BZVI unit using a tear-off connector, which provides the ability to eject the SBN unit together with the pilot. The remaining units of the system, including the BZVI unit, are connected to the aircraft’s common power bus through the RIP backup power sources. To the block BZVI connected information inputs designed to receive information from on-board equipment. The system includes an accident sensor, which is connected to each unit of the system and is designed to generate an “Alarm” signal during an impact that occurred, for example, in an accident.

The following abbreviations are used throughout the text:

BZVI - block for collecting audio and video information

ZBN - protected on-board drive

SZBN - stored protected on-board drive

EBN - operational on-board storage

СБН - salvage on-board storage

RIP - backup power source

MFIs - Multifunctional Indicators

BO - on-board equipment

SES - aircraft power supply system

AP - accident

SPU - aircraft intercoms

BVS - on-board computer network

LA - aircraft

The invention is illustrated by drawings, where in FIG. 1 is a structural diagram of a device, and FIG. 2 shows the RIP unit.

The on-board system for monitoring and recording flight information contains BZVI (1), ZBN (2), SZBN (3), EBN (4), RNS (5), RIP (6 ... 11), video cameras (12), microphones (13) sensor accidents (14).

The device operates as follows.

The BZVI unit (1) receives video information from the MFI (not indicated in the drawing), parametric information through information inputs from the on-board equipment (not indicated in the drawing), sound from the control system (not indicated in the drawing), and information via the AFDX channel from the BVS LA switch ( not indicated in the drawing).

The power module (1.1) receives the power supply voltage from the SES through the RIP unit (6 ... 8), filters it and converts it to the power necessary for the remaining modules of the unit to work, and also receives a one-time “Emergency” command from the accident sensor (14) and transmits it into the computing module (1.2). The audio information module (1.3) receives the microphone audio information (13), amplifies the signals, sums, digitizes and transmits them to the computing module (1.2). The audio information from the channels coming from the control system, the audio information module (1.3) receives, processes and transmits to the computing module (1.2). Computing module (1.2) receives parametric information from the BO, transmits information to the BO, interacts (receives and transmits information) via the AFDX channel with the BVS LA, receives audio information from the audio information module (1.3), and receives a one-time “Emergency” command from the module power supply (1.1), transfers information to the Ethernet channel switch module (1.4) and interacts through it with the system units (2), (3), (4), (5). The video information processing module (1.5) receives video information from MFIs and video cameras (12) via ARINC 818 channels. The received video information is compressed and transmitted to the Ethernet channel switch module (1.4). The Ethernet channel switch module (1.4) transmits and receives information from system units (2), (3), (4), (5). The connection of the BZVI unit (1) with the system units (2), (3), (4), (5) through the Ethernet channel switch (1.4) is a backup information transfer channel in case there is not enough bandwidth to the AFDX switch to process all the information passing through it. The introduction of redundancy improves device reliability.

The ZBN block (2) receives information via the AFDX channel from the BVS LA switchboard (not indicated in the drawing), parametric, sound, and video information from the BZVI block (1).

The power module (2.1) receives the power supply voltage from the SES through the RIP unit (9), filters it and converts it to the power necessary for the operation of the remaining modules of the unit, and also receives a one-time “Emergency” command from the emergency sensor (14) and transfers it to the module computational (2.2). Computing module (2.2) receives parametric audio and video information from the BZVI unit (1) via the Ethernet optical channel, interacts with the aircraft BVS (receiving and transmitting information) via the AFDX channel, and receives a one-time “Emergency” command from the power module (2.1) , transmits information to the controller module of the protected memory module (2.3), which processes all the received information and transfers it for registration to the protected memory module (2.4). In the protected memory module (2.4), the received information is recorded by zones in accordance with the specified algorithm: the audio information zone, the parametric information zone, the video information zone. The protected memory module (2.4) includes an acoustic radio beacon (2.4.1), which, when it falls into the water, in the event of an accident above the water surface, begins to generate a sound of a certain frequency.

Block SZBN (3) receives information on the AFDX channel from the switch of the on-board computer network of the aircraft (not indicated in the drawing), parametric, sound and video information from the block BZVI (1).

The power module (3.1) receives the power supply voltage from the SES through the RIP unit (10), filters it and converts it to the power necessary for the operation of the remaining modules of the unit, and also receives a one-time “Emergency” command from the emergency sensor (14) and transfers it to the module computational (3.2). Computing module (3.2) receives parametric audio and video information from the BZVI unit (1) via the optical Ethernet channel, interacts (receives and transmits information) via the AFDX channel with the BVS LA, and receives a one-time “Emergency” command from the power module (3.1) , transmits information to the controller module of the protected memory module (3.3), which processes all the received information and transfers it to the stored memory module (3.4), which in turn consists of a protected memory module (3.4.1) and an emergency beacon module (3.4.2 ) The stored memory module (3.4) is intended for separation from the SZBN block in the event of an accident over a water surface. The separation is due to the operation of sensors that determine that the unit is in the water. The protected unit of the memory module (3.4.1) receives and registers information by zones in accordance with a predetermined algorithm: an audio information zone, a parametric information zone, a video information zone. The emergency beacon module (3.4.2) is a device designed to transmit information about the location of the unit to the COSPAS-SARSAT system. The emergency beacon module (3.4.2) also includes a GPS / GLONASS receiver, which provides more accurate coordinates for the location of the separated stored memory module (3.4). The emergency beacon module (3.4.2) is turned on when the stored memory module (3.4) is separated from the SZBN block by turning on the internal power source (not indicated in the drawing).

The EBN unit (4) receives information via the AFDX channel from the BVS LA switch (not indicated in the drawing), parametric, sound, and video information from the BZVI unit (1).

The power supply module (4.1) receives the power supply voltage from the SES through the RIP unit (11), filters it and converts it to the power necessary for the operation of the remaining modules of the unit, and also receives a one-time “Emergency” command from the emergency sensor (14) and transfers it to the module computational (4.2). Computing module (4.2) receives parametric, audio and video information from the BZVI unit (1) via the Ethernet optical channel, interacts (receives and transmits information) via the AFDX channel with the BVS LA, and receives a one-time “Emergency” command from the power module (4.1 ), transmits the information to the controller module of the removable storage device (4.3), which processes all the received information and transfers it to the removable storage device (4.4). The removable storage device (4.5) receives information from the controller module of the removable storage device (4.3) and registers the zones according to the specified algorithm: the audio information zone, the parametric information zone, the video information zone. A removable storage device for information from the EBN unit is designed for more efficient processing of flight information.

The SBN block (5) receives information via the AFDX channel from the BVS LA switch (not indicated in the drawing), parametric, sound, and video information from the BZVI block (1).

The power module (5.1) receives the power supply voltage from the power module (1.1) of the BZVI unit (1), filters it and converts it to the power necessary for the operation of the remaining modules of the unit, and also receives a one-time “Emergency” command from the power module (1.1) of the BZVI unit (1) and transfers it to the computational module (5.2). Computing module (5.2) receives parametric audio and video information from the BZVI unit (1) via the Ethernet electric channel, interacts with the on-board equipment (receive and transmit) via the AFDX channel, and receives a one-time “Emergency” command from the power module (5.1), transfers information to the internal memory module (5.3), which processes and registers all received information. The internal memory module (5.3) receives information from the computational module (5.2) and registers by zones in accordance with the specified algorithm: the audio information zone, the parametric information zone, the video information zone. The SBN block (5) is intended for bailout together with the pilot in the event of an accident. This function of the SBN block is intended for more efficient processing of the registered information in the case of an AP, until a protected on-board drive ZBN and a stored protected on-board drive SZBN are found.

Each RIP unit (6 ... 11) shown in FIG. 1, works identically. Further, the principle of operation is considered on the example of one RIP unit (6) shown in FIG. 2. The RIP unit (6) receives power from the SES of the aircraft, converts it and accumulates it internally to provide power to the system units in the event of a power failure from the SES. The RIP unit can be powered from 2 voltages of the aircraft power supply system (SES):

- from a direct current voltage of 27 volts. In this case, in normal operation, the RIP passes a constant current of the on-board network through itself to the system units, without correcting it, but at the same time charging the internal energy source;

- from an alternating current network of 115 volts. In this case, the RIP converts alternating current into direct current, which goes into the blocks of the network, and also charges the internal energy source.

Power from the SES of the aircraft is supplied to the power supply module of the RIP (6.1), which filters electromagnetic interference of both SES and its own modules. The voltage from the output of the RIP power supply module (6.1) is supplied to the control, switching, and charge module (6.2). The outputs of the control module, switching and charge (6.2), carry out the electric charge of the energy storage device (6.3). The control, switching and charge module (6.2) also performs the function of measuring the voltage on the energy storage device (6.3) in order to control charge-discharge processes. When connecting power to the SES LA RIP through the control, switching and charge module (6.2), it starts the charge function of the energy storage device (6.3). At the end of the charge, the control, switching and charge module (6.2) switches to charge maintenance mode to compensate for the self-discharge of the energy storage device (6.3). In the event of a power failure event from the aircraft SES, the control, switching and charge module (6.2) switches the output of the energy storage device to the output of the RIP unit (6) to provide power to the unit connected to it. When the energy storage device is completely discharged, the RIP will disconnect power from the connected unit. In the event of power supply recovery from the SES of the aircraft, the RIP will restore power from the SES of the aircraft and re-charge the energy storage device (6.3).

The on-board flight information monitoring and recording system allows you to expand the functionality of the flight information recording system by introducing an additional unit providing backup power to the system units, by redundant the flight information transmission channel, by monitoring the status of the information channel of aircraft systems, and by increasing the level of electromagnetic system compatibility due to the implementation of inter-unit optical communication channels.

Claims (1)

On-board monitoring and recording system of flight information, characterized in that it contains a secure on-board storage device ZBN, which consists of a power module, a computing module, a controller of a protected drive and a protected drive; a stored protected on-board drive SZBN, which consists of a power module, a computing module, a controller and a stored memory module, consisting of a protected drive and an emergency radio beacon module with a GPS / GLONASS module, designed to transmit information about the location of the unit to the COSPAS-SARSAT system; EBN operational on-board drive, which consists of a power module, a computing module, a removable information storage controller and a removable information storage device; rescue on-board storage RLS, which consists of a power module, a computing module and an internal memory module; an audio and video information collection unit BZVI, which consists of a power module, a computational module, an audio information processing module, a video information processing module, an Ethernet channel switch module, interconnected via an Ethernet channel through an Ethernet channel switch module, which is a part of the BZVI unit, each from the blocks: BZVI, ZBN, SZBN, EBN, connected via the AFDX bus to the switch of the onboard computer network of the aircraft; redundant RIP power supplies that are connected to each block of the system, except for the SBN block, namely: to the ZBN, SZBN, EBN blocks for one RIP block, and to the BZVI block 3 of the RIP block; video cameras that are connected to the BZVI block and each of which is connected to it through one ARINC 818 channel, microphones that are connected to the BZVI block, channels from multifunctional MFI indicators are connected to the BZVI block, intended for transmission of video information to the BZVI block, while the block output The BZVI is connected to the input of the RLS unit to provide power to the RLS unit and to transmit the Crash command to it, as well as the Ethernet link, the RLS unit is connected to the BZVI unit using a tear-off connector, which allows catapults can be opened to the SBN unit together with the pilot, the system blocks, including the BZVI block, are connected to the aircraft’s power supply system through the blocks of redundant power supplies, and the BZVI block has information inputs for receiving information from the onboard equipment, an accident sensor that is connected to each the system block, in addition to the RLS block, and is designed to generate an “Alarm” signal.

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