RU2530701C1 - Integrated system of flight info acquisition, control, processing and recording - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises the following extra units: control board as mixer of audio signals from first and second astatic radio range mikes for transmission and registration in front and rear onboard multipurpose protected integrators and as Ethernet network commutator. Whereto connected are front and rear multipurpose protected onboard integrators, video camera, combined flight data acquisition unit and wireless data transfer unit. It has at least one high-speed data exchange channel to transmit video signal from multipurpose indicators to combined flight data acquisition unit and, further, to front and rear onboard multipurpose protected integrators via onboard circuit.

EFFECT: higher reliability and perfected control.

6 cl, 1 dwg

Description

FIELD OF THE INVENTION

The invention relates to the field of aviation technology and is intended for use in on-board systems for collecting, controlling, processing and recording audio, voice and video information, as well as digital parametric information by recording it in protected on-board drives of the aircraft.

State of the art

All modern aircraft are equipped with systems designed to collect, process and analyze flight information, which allows continuously, throughout the flight, recording elements of the flight path, crew actions, equipment operation and signals about failures or abnormal operation modes of both individual units and units of the aircraft, and in the aircraft as a whole, and subsequently, in cameral conditions, process and analyze flight information. Saving flight data is necessary for possible use by the crew during the flight and in the event of an accident investigation in order to determine the causes and prerequisites for it.

A wide range of systems for collecting, processing and recording flight information is known in the art. All these systems share a common property: the presence of sensors of the state of the monitoring object, which convert the measured value into an electrical signal; switches that sequentially or in decreasing order of priority connect sensors to information transmission channels; converters encoding analog information into discrete; information storage and storage devices (on-board information storage devices).

From the publication of patent US 6735505 B2, IPC G11B 5/02, publ. 05/11/2004, a known system for recording flight information and voice information containing means for monitoring flight parameters, detecting emergency situations and transmitting data to ground-based air traffic control stations.

The prior art also knows a system for recording events on board a vehicle, in particular an aircraft (see publication of US patent 7356336 B2, IPC H04Q 7/20, published 08.04.2008), containing a set of modules, communication buses and a wireless controller designed for receiving and recording current data from modules, taking into account their comparison with the standard characteristics and parameters of these modules stored in the database.

In the patent for utility model RU 68725 U1, IPC G06F 3/06, publ. 11/27/2007 a system for recording parametric flight information is disclosed, comprising a flight information collection unit connected to a control panel, sensors, and also with an on-board protected drive connected to a speed signaling device, the digital flight information collection unit being connected to an operational flight information storage device connected to remote control. This system provides the recording of parametric flight information in digital form on the corresponding unit for collecting flight information, however, this system does not provide for the collection and recording of sound, voice and video information.

There is also known a system for displaying and recording flight information on the application US 2011/0125349 A1, IPC B64D 45/00, publ. 05/26/2011, including sensors for collecting data on the state of the aircraft, a video camera installed in the cockpit for receiving visual information, a device for storing data from sensors and a video camera, and a control device, the feature of which is automatic dynamic adjustment of the resolution and recording frequency of data from the video camera and sensors in depending on the speed and extent of change of this data.

From the publication of patent US 6721640 B2, IPC G01M 17/00, publ. 04/13/2004 (see abstract, Fig. 1), an integrated system for collecting, controlling, processing and recording flight information is known, which, by its totality of features, is the closest analogue of the present invention. This system, selected as a prototype of the present invention, contains protected on-board storage of parametric, sound and visual information, microphones and zone cameras located in the cockpit, a switched on-board communication network, a combined flight data collection unit, equipped with input ports for receiving data from a set of sensors installed in aircraft systems and aircraft equipment, and output ports for transmitting data to protected on-board drives and telemetry devices oystvo designed to transmit data from the aircraft to the ground-based facilities.

In a system defined as a prototype, in a switched on-board communication network, the information exchange channel is made in the form of a single transmitting data bus ARINC 429, which is one of a number of specifications developed by the Airlines Electronic Engineering Committee and widely used in avionics.

In accordance with ARINC 429, a data bus specification is defined that enables the transmission and reception of data between elements of avionics on-board electronic equipment at one of three speeds: 12.5 Kbps, 50 Kbps or 100 Kbps. The ARINC 429 specification also defines other parameters, including the type of wiring, the level of electrical voltage, the coding used, and the distribution of labels, established discrete data word formats, and file transfer protocols.

A modern aircraft has a large number of aircraft systems and aircraft equipment with a wide variety of sensors, while the requirements for speed and volume of information exchange with which differ significantly. The use of only one transmitting data bus in accordance with the ARINC 429 specification in the aircraft’s switched on-board communications network in a solution defined as a prototype of the invention leads to a limitation of controllability and, as a result, to a decrease in flight reliability and safety.

SUMMARY OF THE INVENTION

The aim of the invention is to increase the efficiency of operation of the aircraft and reduce the cost of its maintenance and repair.

The goal is achieved in an integrated system for collecting, controlling, processing and recording flight information (1), and the system contains:

at least one zone video camera (4) located in the cockpit, as well as the first (5) and second (6) non-directional zone microphones;

switched on-board network (7) for transmission and registration in the front (2) and rear (3) multipurpose protected on-board data storage devices from the avionics system and on-board maintenance system, said network (7) including a switch (15);

a combined unit (8) for collecting flight data for receiving data from aircraft systems and equipment, as well as connected to the switch (15) of the aforementioned network (7) with the main and backup channels (16) of information exchange; moreover, the switch (15) of the switched on-board network (7) is connected by a pair of primary and backup channels (18) of information exchange to the front (2) and rear (3) multipurpose protected on-board drives, respectively;

at the same time, the following are additionally introduced into the system:

a control panel (10), providing, in particular, the functions of a mixer of audio signals from the first (5) and second (6) omnidirectional zone microphones for subsequent transmission and registration in the front (2) and rear (3) multipurpose protected on-board drives, as well as functions of the Ethernet network switch, to which the front (2) and rear (3) multipurpose protected on-board drives, a video camera (4) are connected, as well as a combined unit (8) for collecting flight data and a wireless unit (11) for transmitting data, and the wireless unit ( 11) connect data It is connected to the combined unit (8) for collecting flight data and provides wireless transmission of stored flight data from the front (2) and rear (3) multifunctional protected on-board drives to the ground post;

at least one high-speed data exchange channel (13) through which a video signal is transmitted from multi-function indicators to a combined unit (8) for collecting flight data for conversion and subsequent transmission through the network of a switched on-board network (7) to the front (2) and rear (3) ) multipurpose protected on-board drives.

The technical result of the invention is to increase reliability and improve the suitability of an integrated system for collecting, controlling, processing and recording flight information.

The specified technical result is achieved in the proposed integrated system for collecting, monitoring, processing and recording flight information, containing at least one zone video camera (4) located in the cockpit, as well as the first (5) and second (6) non-directional zone microphones; switched on-board network (7) for transmission and registration in the front (2) and rear (3) multipurpose protected on-board data storage systems from avionics systems and on-board maintenance systems, said switched on-board network (7) including a network switch (15); a combined unit (8) for collecting flight data to receive information exchange via channel (9), in an embodiment of the invention corresponding to the ARINC 429 specification, data from aircraft systems and equipment, and also connected to the switch (15) of the switched on-board network (7) with the main and backup channels (16) of information exchange of the switched on-board network (7); moreover, the switch (15) of the switched on-board network is connected by a pair of main and backup channels (18) of the information exchange of the network (7) to the front (2) and rear (3) multipurpose protected on-board drives, respectively; at the same time, the control panel (10) is additionally included in the system, providing, in particular, the functions of a mixer of audio signals from the first (5) and second (6) non-directional zone microphones for subsequent transmission and registration in the front (2) and rear (3) multipurpose protected on-board drives, as well as the functions of the Ethernet network switch, to which the front (2) and rear (3) multipurpose protected on-board drives, a video camera (4), as well as a combined flight data collection unit (8) and a wireless transmission unit (11) are connected data, and b sprovodnoy unit (11) connected to the data combined unit (8) collecting flight data and provides wireless transmission of the stored flight data from the front (2) and rear (3) protected multifunctional board drives Ground post; at least one data exchange channel (13), in an embodiment corresponding to the ARINC 818 specification, through which a video signal from multifunctional indicators is transmitted to the combined unit (8) for collecting flight data for conversion and subsequent transmission through the network, in an embodiment corresponding to the ARINC 664 specification (16, 15, 18), front (2) and rear (3) multi-purpose protected on-board drives.

In one embodiment of the invention, the communication channel transmission line, in the embodiment corresponding to the ARINC 818 specification, is made in the form of a fiber-optic communication channel channel, and the transmission lines of the mentioned Ethernet network in the embodiment are made in the form of a shielded twisted pair cable (12, 22 )

Also, in an embodiment of the invention, the front (2) and rear (3) protected on-board drives of parametric, sound and visual information are connected to the corresponding uninterruptible power supply device (19, 20).

In yet another embodiment, the control panel (10) of the proposed system is integrated in the integrated ceiling panel in the cockpit.

In yet another embodiment of the invention, the control panel (10) comprises an Ethernet port for connecting a portable computer device (e.g., laptop or tablet) (not shown).

Brief Description of the Drawings

The invention is further illustrated by specific examples of its implementation with reference to the accompanying drawing, which shows a block diagram of an integrated system for collecting, controlling, processing and recording flight information (Fig. 1).

The implementation of the invention

The integrated system (1) for collecting, controlling, processing and recording flight information, shown in FIG. 1, contains a front (2) multi-purpose protected on-board storage of parametric, sound and visual information installed in the nose of the aircraft, and a rear (3) multi-purpose protected on-board storage of parametric, sound and visual information located in the rear of the aircraft. The system also contains a zone video camera (4) installed in the cockpit, a first (5) and a second (6) omnidirectional zone microphones, a switched on-board communication network (7), a combined flight data collection unit (8) connected to sensors installed in aircraft systems and equipment of the aircraft, using the information exchange channel (9) corresponding to the ARINC 429 specification, the transmission line of which in the embodiment of the invention is made in the form of a shielded twisted pair cable, and to the control panel (10) and the wireless unit (11) data transmission - using the channel (12) information exchange that meets the requirements of the Ethernet network (IEEE 802.3 standard), the transmission line of which in the embodiment of the invention is made in the form of a shielded twisted pair.

Multifunction flight navigation displays are connected to the combined flight data collection unit (8) using a broadband, high-speed data exchange channel (13) corresponding to the ARINC 818 specification, the transmission line of which is made in the form of a fiber-optic communication line, and a three-axis unit (14) linear acceleration sensors, as well as a switch (15) of a communication network that complies with the ARINC 664 specification, using an information exchange channel (16) that complies with the ARINC 664 specification, the transmission line of which is in one of the embodiments of the invention is made in the form of a shielded twisted pair.

Power supply to the combined unit (8) for collecting flight data is carried out from a twofold redundant DC source (17).

Protected on-board drives of parametric, sound and visual information 2 and 3 are connected to the switch (15) of the switched on-board communication network (7) that complies with the ARINC 664 specification, using two identical communication channels 18, in the embodiment of the invention corresponding to the ARINC 664 specification, lines the transmission of which is made in the form of a fiber optic communication line.

Power supply of the first (2) and second (3) protected on-board drives of parametric, sound and visual information is carried out from the DC network through the front (19) and rear (20) uninterruptible power supply devices of the drives, respectively.

Voice and sound information from the first (5) and second (6) omnidirectional zone microphones is transmitted to the control panel (10), digitized in it and then transmitted to the front (2) and rear (3) protected on-board drives of parametric, audio and visual information through the corresponding communication channel (21), the transmission lines of which in the embodiment of the invention are made in the form of a shielded twisted pair.

The signal from the video camera (4) is fed to the front (2) and rear (3) protected on-board drives of parametric, sound and visual information through the control panel (10) via Ethernet channels.

The present integrated system for collecting, controlling, processing and recording flight information, shown in figure 1, performs the following functions of audio and video surveillance, registration and automatic data collection, in particular:

- reception and processing of voice / sound information about crew negotiations via internal, external radio channels and zonal microphones in the cockpit;

- receiving messages on the digital channel "board-to-board-board" in the "dispatcher - pilot" mode;

- receiving video signals from flight navigation displays and zone video cameras (4) in the cockpit;

- registration of audio and visual data on solid-state multipurpose protected on-board drives;

- preservation of accumulated flight data in the event of an accident to determine the causes and prerequisites for it.

To ensure the listed audio and video surveillance functions, the following blocks are involved that are part of the claimed system:

- combined flight data collection unit (8);

- front (2) and rear (3) multipurpose protected on-board drives of parametric, sound and visual information;

- control panel (10);

- the first (5) and second (6) zone microphones;

- zone video camera (4);

- front (19) and rear (20) uninterruptible power supply drives.

Temporary synchronization of all parametric, audio and visual data is provided by the combined unit (8) for collecting flight data.

Front (2) and rear (3) protected on-board drives are designed for registration:

- information about crew negotiations;

- messages transmitted via land-to-ground exchanges in the dispatcher-pilot mode;

- video images of display formats from flight navigation displays and the cockpit camera.

Front (2) and rear (3) protected on-board drives record the following information:

- messages received and transmitted by the crew via airborne communications radios;

- negotiations in the cockpit between crew members;

- negotiations in the cockpit between crew members by means of internal communications;

- sound recognition signals of ground-based navigation and landing radio equipment received in the headphones of crew members or loudspeakers installed in the cockpit;

- voice data of passenger notification by flight crew members through loud-speaking communication equipment.

Front (2) and rear (3) multi-purpose protected on-board drives are multi-channel. The voice / sound information recorded by the drives is recorded on the carrier in the following order:

- to the first channel - from the headset used at the workplace of the first pilot (not shown);

- to the second channel - from the headset used at the workplace of the second pilot (not shown);

- to the third channel - from the headset used at the workplace of the third crew member (not shown);

- to the fourth channel - a mixed signal from the first (5) and second (6) non-directional zone microphones installed in the cockpit.

In the front (2) and rear (3), it is possible to register video images of the display formats from the flight and navigation displays, the signal from which through the data exchange channels complying with the ARINC-818 specification, enters the combined unit (8) for collecting flight data, where it is converted for subsequent transmissions through a network that complies with the ARINC-664 specification, through the switch of this network to the front (2) and rear (3) multifunctional protected on-board drives, which also record video from the video camera (4) of the cab ipazha, through which the signal from the Ethernet network is supplied to the control panel (10), wherein transformed (is compressed) and further through the Ethernet network is transmitted to said front (2) and rear (3) Storage and stored therein.

The data recording mode in the front (2) drives and the rear (3) multipurpose protected drives is provided automatically according to the following specified control logic in terrestrial conditions: switching on - before starting the engines, switching off - after ten minutes after the engines are stopped, and continuous recording for the entire flight, and disabling data recording in the front (2) and rear (3) multipurpose protected drives in flight is excluded.

The system includes a control panel (10) installed on an integrated ceiling panel in the cockpit, providing:

- authorized removal of audio and video recordings;

- control listening and viewing fragments of audio information recording through the headset during checks of the front (2) and rear (3) registrars;

- viewing control video information through a connected laptop (not shown) when checking the front (2) and rear (3) recorders;

- preliminary amplification and mixing of signals from zonal microphones with stepwise adjustment of the output signal gain;

- conversion of the signal from the cameras if they are installed in the cockpit.

The front (2) and rear (3) multipurpose protected on-board drives are installed in the sealed fuselage zone at the top of the cockpit and tail compartments and ensure the safety of the accumulated flight data under adverse effects of destructive factors in the event of a flight accident.

The cases of the front (2) and rear (3) drives have reflective stripes, bright orange color and the inscriptions in Russian “EMERGENCY RECORDER” and “DO NOT OPEN”, duplicated in English, “FLIGHT RECORDER” and “DO NOT OPEN”, respectively. Also, sonar beacons are installed on the front (2) and rear (3) drives, providing detection at a depth underwater.

The front (2) and rear (3) drives are powered by non-disconnecting buses of the DC electrical supply system with a nominal voltage of 28 V. To ensure uninterrupted power in the front (2) and rear (3) protected on-board drives of parametric, audio and visual information are provided front (19) and rear (20) uninterruptible power supply drives. The front (19) and rear (20) uninterruptible power supply devices of the drives also provide a limitation of the registration time in the event of a power failure during an accident for no more than 10 minutes.

The solid-state memory of the front (2) and rear (3) protected on-board drives of parametric, sound and visual information stores the recorded voice / sound and visual information about at least the last two hours of registration.

Monitoring the status of the integrated system for collecting, controlling, processing and recording flight information in general and registration means in particular is provided by built-in monitoring tools, with the issuance of information to the aircraft’s on-board monitoring and maintenance systems with simultaneous registration on protected and operational on-board drives. Information on the status of registration tools on the monitor of the on-board maintenance system in the cockpit in the form of a page and in the form of messages (instructions).

The wires of the power supply circuits of the registration means have coordinated circuit breakers that prevent them from overheating in the event of a short circuit.

In the proposed integrated system for the collection, control, processing and registration of flight data, the registration function is carried out by means of registration of parametric information that provides:

- collection of parametric information from aircraft systems and aircraft equipment;

- recording on a solid-state on-board protected drive of mandatory flight data in accordance with applicable requirements;

- saving the accumulated flight data in the memory of the protected drive in the event of an accident or accident;

- registration of an expanded set of flight data and reports on identified events of flight control of the aircraft on solid state drives with quick access.

The means of recording the parametric information of the proposed integrated system for collecting, monitoring, processing and recording flight data include a combined unit (8) for collecting flight data, front (2) and rear (3) protected on-board drives, a three-axis block (14) of linear acceleration sensors, and also a unit (11) for wireless data transmission.

The combined flight data collection unit (8) as part of the registration means provides the reception of a mandatory set of data for recording to a solid-state protected drive; processing and distribution of data streams for transmission to a secure and operational on-board storage; formation of the structure of parametric data arrays for registration on protected on-board drives; formation of a time scale (with reference to astronomical time) and the transfer of its values for registration on all storage devices of parametric, sound and visual data.

In an embodiment of the present invention, the combined unit (8) for collecting flight data incorporates an integrated operational easy-to-access drive with quick access and is installed in the sealed part of the fuselage in the compartment of the avionics.

Power supply to the combined unit (8) for collecting flight data is carried out from non-disconnectable buses of the DC power supply system with a nominal voltage of 28 V.

Front (2) and rear (3) multipurpose protected on-board drives are designed for synchronized recording of parametric data and voice / sound / video information.

The list of parametric data recorded by the front (2) and rear (3) multipurpose protected drives complies with current regulatory requirements and includes the following parameters:

- service parameters (astronomical time, aircraft number, flight date flight number, etc.);

- parameters characterizing the movement of the aircraft;

- parameters characterizing the position of the controls;

- parameters characterizing the state of the power plant;

- parameters characterizing the state of systems and equipment.

Ground copying of registered in the front (2) and rear (3) multipurpose protected flight data storage devices, when operating on an airplane, is performed through a network interface that complies with the IEEE 802.3 group standard (Ethernet network standard, which provides data reception and transmission at speeds of 10 or 100 Mbit / s) using the firmware provided by the manufacturer of the mentioned front (2) and rear (3) multipurpose protected drives.

Post-flight data processing of the front (2) and rear (3) drives is carried out using the flight safety analysis program of an aircraft type "AirFASE®" or similar.

Front (2) and rear (3) multipurpose protected on-board drives ensure the safety of accumulated flight data in case of adverse effects of destructive factors in the event of a flight accident in accordance with the requirements of the specifications TSO-123b, TSO-124b and ED-112.

The solid state memory of the front (2) and rear (3) drives stores the recorded parametric information of at least 25 of the last 25 hours of data recording.

The registration mode of parametric data in the front (2) and rear (3) multipurpose protected drives is provided automatically according to the specified control logic. In terrestrial conditions, the registration is enabled before the engines start, and the shutdown is after five minutes after the engines are stopped. In flight, data is recorded continuously throughout the flight, and disabling registration in the front (2) and rear (3) multipurpose protected drives in flight is excluded.

The system includes a control panel (10), which is installed on an integrated ceiling panel in the cockpit.

The three-axis block of linear acceleration sensors (14) is designed to measure accelerations along the X, Y, Z axes with the issuance of electrical signals to the combined block (8) of flight data collection.

A three-axis block (14) of linear acceleration sensors is installed in the region of the center of mass of the aircraft.

The combined flight data collection unit (8) also has a built-in solid-state operational storage with quick access. This operational drive is designed to register a copy of the required data file of the front (2) and rear (3) multipurpose protected drives and data with reports on flight monitoring of aircraft status information

Unit 8 operational storage data can be transmitted via cellular communication channels or the IEEE 802.11 group Wi-Fi interface (standard) via wireless data transmission unit (11) for ground processing by the aircraft operator company automatically or by a signal from the cockpit, provided completion is completed flight, taxiing to the parking lot and opening the doors of the aircraft.

Information on the status of the registration means is displayed on the monitor of the aircraft monitoring and maintenance systems in the cockpit in the form of a page and in the form of messages (instructions).

The wires of the power circuits of all units of the declared integrated collection, control, processing and recording of flight data have coordinated circuit breakers that prevent them from overheating in the event of a short circuit.

The automatic flight data collection function is provided by automatic flight data collection equipment designed to collect and convert parametric information from aircraft systems and equipment for mandatory registration to the front (2) and rear (3) multi-purpose protected on-board drives; collection and conversion of an expanded set of flight data for monitoring (monitoring) the state of the aircraft;

express analysis according to a given logic in flight of incoming parametric data from aircraft systems and equipment with the identification of failure events, malfunctions and deviations in their work;

generating and transmitting output data with packets with reports and parameters, according to detected events during automated express analysis, to the interfaced equipment (ACARS, on-board printer, operational storage with quick access and service system).

For automatic flight data collection, a combined flight data collection unit (8) is used, which provides reception of parametric data from aircraft systems and aircraft equipment in the form of digital signals transmitted via a communication channel, in an embodiment of the invention corresponding to the ARINC 429 specification, as well as digital signals, transmitted over an information exchange channel, in one embodiment of the present invention in accordance with the ARINC 664 specification.

Due to the use of a combined flight data collection unit, a control panel, zonal microphones, video cameras, and various specifications of data transmission channels and information exchange channels that meet the requirements for speed and volume of information received from the cockpit, from aircraft systems and aircraft equipment, high controllability is achieved and reliability.

Industrial applicability

The invention is intended for use in the aviation industry in the design and manufacture of modern and promising passenger aircraft, providing high reliability and flight safety during the mass transportation of air passengers in various conditions.

All technical means and the software providing their work, the application of which is provided for by the invention, are developed and produced both by domestic industrial enterprises and by leading companies in foreign countries.

The interaction of means envisaged by the invention is realized in known processes for various purposes in the field of aircraft manufacturing. In the manufacturing process of all devices included in the control system of general aircraft equipment and aircraft systems, standard, standard industrial equipment, known materials and components can be used.

Claims (6)

1. An integrated system for collecting, controlling, processing and recording flight information, containing
at least one zonal video camera located in the cockpit, as well as the first and second non-directional zonal microphones;
a switched on-board network for transmitting and registering in the front and rear multipurpose protected on-board data storage devices from an avionics system and an on-board maintenance system, said network including a switch;
a combined unit for collecting flight data to receive data from aircraft systems and equipment, as well as the main and backup communication channels connected to the switch of the mentioned network; moreover, the commutator of the switched on-board network is connected by a pair of primary and backup channels of information exchange, respectively, to the front and rear multipurpose protected on-board drives;
characterized in that the system further comprises:
a control panel that provides, in particular, the functions of a mixer of audio signals from the first and second omnidirectional zone microphones for subsequent transmission and registration in the front and rear multipurpose protected on-board drives, as well as the functions of the Ethernet network switch, to which the front and rear multipurpose protected on-board drives are connected , a video camera, as well as a combined unit for collecting flight data and a wireless unit for transmitting data, and the wireless unit for transmitting data is connected to the combined unit flight data collection and provides wireless transmission of stored flight data from the front and rear multi-function protected on-board drives to the ground post;
at least one high-speed data exchange channel through which a video signal is transmitted from multi-function indicators to a combined flight data collection unit for conversion and subsequent transmission through a switched on-board network to the front and rear multi-purpose protected on-board drives. 2. The system according to claim 1, characterized in that the transmission line of the high-speed data exchange channel is made in the form of a fiber optic communication line. 3. The system according to claim 1, characterized in that the front and rear protected on-board drives of parametric, sound and visual information are connected to the corresponding uninterruptible power supply device. 4. The system according to claim 1, characterized in that the transmission lines of said Ethernet network are made in the form of a shielded twisted pair cable. 5. The system according to claim 1, in which the control panel is integrated in the integrated ceiling panel in the cockpit. 6. The system according to claim 1, characterized in that a portable computer device is additionally connected to said Ethernet network transmission line control panel.