RU2771577C1 - Helicopter avionics complex - Google Patents

Abstract

FIELD: aircraft engineering.SUBSTANCE: helicopter’s avionics complex contains a flight and navigation information complex (1) consisting of: a digital computer (2), large-format multifunctional indicators (3, 4), a device for entering navigation parameters (5), a multifunctional control panel (6) with a satellite navigation system (SNS) signal receiver, a course guide (7), low altitude radio altimeter (8), air signal calculator (9), protected onboard storage (10) with an underwater acoustic beacon, navigation and landing equipment (11) VOR/LOC/GS/MB/ADF, an automatic control system (12) with a remote control for operating modes, a microphone device (13), a unit for calculating and converting analog, discrete and digital signals (14), multifunctional indicators (15, 16), an integrated system of backup devices (17) based on a multifunctional electronic indicator, as well as lighting equipment (18) as part of: an alarm unit (19), a light signaling board (20), an alarm board with control (21, 22), a warning alarm board with control (23, 24), radio communication equipment (25) as part of: amplification and switching equipment (26), VHF-UHF-band radio station (27), radio control panel (28), emergency beacon of the international satellite search and rescue system “COSPAS-SARSAT” (29).EFFECT: improved safety of helicopter flights is provided.4 cl, 5 dwg

Description

The invention relates to a set of on-board equipment that provides indication, signaling, navigation, control of general helicopter equipment, helicopter navigation, radio communications, interaction in the air traffic management system and can be used for use as part of civil helicopters flying according to the visual flight rules.

Known Complex of onboard equipment for helicopters and general aviation aircraft (patent RU 2640076, В64С 13/16, published on December 26, 2017), containing a multifunctional indicator (MFI), a main flight instrument (OPP), a combined heading vertical (KB), air pressure receivers, deceleration temperature receiver, signal conversion unit, integrated radio communication system (ISR), alarm and notification display system, set of internal lighting and signaling equipment, wireless user data download device, air traffic control system transponder, emergency and rescue radio beacon, small-sized flight recorder, radio altimeter, automatic radio compass, automatic dependent surveillance transponder, VOR/ILS short-range navigation and landing equipment/marker receiver/automatic radio compass, autopilot connected in a certain way using an information exchange channel. The MFI contains a calculation and generation unit, including an indication and signaling module, software modules for navigation and cartography, as well as warnings of critical modes and early warning of ground proximity, a display module, and a power supply module. OPP contains an LCD indicator, a module for determining the spatial position, a module for converting critical signals. KB contains a main computing module, an attitude module, a module for measuring and calculating air data with a GLONASS/GPS receiver, and a magnetic heading sensor. The ISR contains a radio station unit, an intercom console.

The disadvantages of the Complex of on-board equipment for helicopters and general aviation aircraft are the lack of redundancy of critical system functions, such as displaying the parameters of the spatial orientation of the aircraft and basic flight information, the lack of monitoring the state and serviceability of the systems of the complex and the information exchange channel, as well as the implementation of the functions of calculating, displaying and entering information structurally in one non-redundant block, which reduces the reliability of the complex and the safety of the flight as a whole.

The analogue closest to the invention, taken as a prototype, is the Helicopter on-board equipment complex (patent RU 2652344, G01C 23/00, published on 04/25/2018), containing a navigation computer with a satellite communication receiver, an automatic control system (ACS), an electronic display system , a navigation system that includes a device for determining roll, pitch and a course indicator, an air signal computer, radio equipment, including an automatic radio compass, navigation and landing equipment, radio communication equipment, a low-altitude radio altimeter, a protected on-board storage device, a meteorological radar system, a digital generator maps and a group of backup instruments, including an indicated airspeed indicator, two artificial horizons, a satellite antenna that provides signal transmission to the corresponding input of the navigation calculator and the corresponding input of the digital map generator, moreover, to the satellite receiver A differential correction scheme was introduced into the navigation computer's computer, and a backup air reckoning scheme for the current coordinates of the helicopter's location and automatic flight control along the route was introduced into the flight control computer of the automatic control system.

The reason that prevents obtaining the technical result indicated below when using the known Complex of on-board equipment of a helicopter is the low level of equipment integration, the lack of redundancy for the processing and display of navigation information, as well as the inability to monitor the status and serviceability of the systems of the complex and information exchange lines.

The essence of the invention is as follows.

The technical problem solved by the claimed invention is the creation of a complex of on-board radio-electronic equipment of a helicopter in order to improve the safety of helicopter control in solving various problems.

The technical result obtained in the implementation of the invention is expressed

- in increasing the fail-safety of the complex and reducing the load on the crew due to the redundancy of critical functions of the systems, the rational integration of equipment, the implementation of algorithms for complex information processing, centralized monitoring of the state and serviceability of the systems of the complex and information exchange lines,

- in improving the safety of piloting through the use of large-format multifunctional indicators of large size and high resolution, the use of modern principles for the presentation of flight and navigation information, as well as the formation of recommendations for the crew on actions in failure situations,

- in reducing the time of pre-flight preparation, troubleshooting and troubleshooting.

To achieve the technical result, a complex of on-board radio-electronic equipment of a helicopter is proposed, containing a set of equipment elements interconnected by inputs-outputs through information exchange channels, including a flight and navigation information complex 1, which includes at least one large-format multifunctional indicator 3, multifunctional control panel 6, heading vertical 7, low-altitude radio altimeter 8, air signal calculator 9, protected on-board storage device 10 with an underwater acoustic beacon, microphone device 13, block for calculating and converting analog, discrete and digital signals 14, multifunctional indicators 15 , 16, radio communication equipment 25, containing amplification and switching equipment 26, radio station 27, radio control panel 28, in accordance with the claimed invention, characterized in that the complex a digital calculator 2, an integrated system of backup devices 17, a device for entering navigation parameters 5 are introduced, in addition, the complex includes lighting equipment 18, containing an alarm unit 19, a light signaling board 20, at least one alarm board with control 21, at least one a warning signal board with control 23, an emergency beacon 29 of the international satellite search and rescue system, while the said heading vertical 7 is interconnected by inputs and outputs via information exchange channels with a digital computer 2, wide-format multifunctional indicators 3, 4, a multifunctional control panel 6, said airborne computer signals 9 is interconnected by inputs-outputs via information exchange channels with a digital calculator 2, heading vertical 7, large-format multifunctional indicators 3, 4, said device for inputting navigation parameters 5 is interconnected by inputs-outputs mi through the channels of information exchange with the air signal computer 9, the digital computer 2, the multifunctional control panel 6, the integrated system of backup devices 17, the said digital computer 2 is interconnected by inputs and outputs through the information exchange channels with the air signal computer 9, the radio altimeter of low altitudes 8, multifunctional control panel 6, widescreen multifunctional indicators 3, 4, an integrated system of backup devices 17, a calculation and conversion unit 14, a device for entering navigation parameters 5, an emergency radio beacon 29, the said multifunctional control panel 6 is interconnected by inputs and outputs via information exchange channels with a radio station 27, digital calculator 2, widescreen multifunctional indicators 3, 4, said low-altitude radio altimeter 8 is interconnected by inputs-outputs via information exchange channels with digital calculator 2, widescreen multifunctional and indicators 3, 4, the mentioned integrated system of backup devices 17 is interconnected by inputs-outputs via information exchange channels with a digital calculator 2, the said protected on-board storage device 10 is interconnected by inputs-outputs via information exchange channels with amplification and switching equipment 26 and a microphone device 13.

At the same time, navigation and landing equipment 11 was introduced into the complex, which is interconnected by inputs-outputs through information exchange channels with a digital computer 2, large-format multifunctional indicators 3, 4, and amplification and switching equipment 26.

Also, the complex introduced an automatic control system 12 with a control panel for operating modes of the automatic control system, which is interconnected by inputs and outputs via information exchange channels with the heading vertical 7, an air signal computer 9, a digital computer 2, a low-altitude radio altimeter 8, an integrated system of backup instruments 17.

In addition, a scheme for centralized control of the state and serviceability of the systems of the complex and information exchange lines was introduced into the complex.

The cause-and-effect relationships of the features of the invention with the technical result are expressed as follows. The use of large-format multifunctional displays ensures the simultaneous display of flight, navigation and signaling information to each crew member, including recommendations for actions in case of failure situations, as well as information on the operation parameters of the power plant and transmission, which makes it possible to reduce the load on the crew by eliminating the need to switch attention between different means of indication.

The use of an integrated system of backup instruments, which autonomously generates and displays the main flight information, ensures the safe completion of the flight in the event of a failure of the main computing systems and indication means.

The implementation of the function of centralized control of the state and serviceability of the systems of the complex and information exchange lines by carrying out the following types of control: continuous automatic and ground extended is aimed at improving flight safety, since it allows both pre-flight control and continuous control in flight without the crew intervening in the performance of the main functions of helicopter systems.

The implementation of the invention ensures the fulfillment of high requirements for the accuracy and reliability of the information required for indication to the crew due to the complex processing of flight and navigation information, a reduction in the time for pre-flight preparation, troubleshooting and troubleshooting is achieved.

The implementation of the invention provides a reduction in the load on the crew due to the simultaneous display on widescreen multifunctional indicators 3, 4 of various combinations that the crew selects, flight, navigation, digital cartographic information, information about the operation parameters of the power plant and transmission, signal information.

The implementation of the invention provides a reduction in the load on the crew by providing prompt input of information about the type of barrocorrection, the given value of the dangerous altitude, the given ground angle and the given course using the device 5 for entering navigation parameters.

The implementation of the invention improves the ergonomic characteristics of the information and control field of the cockpit and reduces the load on the crew by providing control of various types of displaying information about the state of the general helicopter equipment using operational controls on the multifunctional indicators 15, 16.

The implementation of the invention provides a reduction in the weight of the equipment, improving the ergonomic characteristics of the information and control field of the cockpit and reducing the load on the crew through the use of an electronic integrated system of standby devices 17, which implements the functions of a large group of electromechanical standby devices.

The implementation of the invention provides a reduction in the weight of the equipment and optimization of the layout of the cockpit due to the use of separate devices as part of the lighting equipment: an alarm unit 19 and a light signaling board 20.

The implementation of the invention provides an increase in the reliability and safety of the flight through the implementation of backup control of the settings of the radio equipment using the multifunctional control panel 6.

The implementation of the invention improves the ergonomic characteristics of the information and control field of the cockpit, reduces the burden on the crew and improves flight safety through the use of a multifunctional control panel 6 with an integrated keyboard for entering digital and symbolic information, a module for loading from a removable carrier of an aeronautical database (AN DB), digital terrain map (DTM) and flight plans.

The implementation of the invention provides for the implementation of the function of centralized control of the state and serviceability of the systems of the complex and information exchange lines. All received information from the interfaced sensor systems is controlled for reliability using built-in hardware control: on the basis of parity, the duration of the pause between words and the number of bits (bits) in the information word, as well as software control: on the content of the matrix-state code, update time information words, tolerance control of input parameters from two or more homogeneous sensor systems, echo control, checking information for belonging to the range of permissible values, checking for monotonicity of parameter changes, control of changes in cyclic counter values.

The invention is illustrated by drawings:

fig. 1 is a functional diagram of the helicopter avionics complex;

fig. 2 - the general structure of the frame on the widescreen display;

fig. 3 is a general view of a complex frame of flight and navigation information (PNT) on a widescreen display;

fig. 4 - general view of the equipment control frame (CONTR) on a widescreen display;

fig. 5 - general view of the frame on the electronic indicator of the integrated system of standby devices (ISRP).

The helicopter avionics complex (Fig. 1) contains the following equipment, interconnected by inputs and outputs via the information exchange channel, and is designed to perform interconnected operational functions:

- flight and navigation information complex 1 consisting of:

- digital calculator 2,

- widescreen multifunctional indicators 3, 4,

- navigation parameters input device 5,

- multifunctional control panel 6 with satellite navigation system (SNS) signal receiver,

- course vertical 7,

- low altitude radio altimeter 8,

- air signal calculator 9,

- protected on-board drive 10 with an underwater acoustic beacon,

- navigation and landing equipment 11 VOR/LOC/GS/MB/ADF,

- automatic control system 12 (ACS), including a control panel for the operation modes of the ACS,

- microphone device 13;

- block for calculating and converting analog, discrete and digital signals 14;

- multifunctional indicators 15, 16;

- an integrated system of backup devices 17 based on a multifunctional electronic indicator;

- lighting equipment 18, consisting of:

- alarm block 19,

- signaling board 20,

- alarm board with control 21, 22;

- warning signal board with control 23, 24;

- radio communication equipment 25 consisting of:

- amplification and switching equipment 26,

- radio station MV-UHF band 27,

- radio control panel 28;

- emergency beacon of the international satellite search and rescue system "KOSPAS-SARSAT" 29.

The functional diagram of the helicopter avionics complex (Fig. 1) shows the communication channels between the elements of the complex: 30 - electrical line for transmitting discrete signals (one-time commands), 31 - digital code line; 32 - electrical transmission line of analog signals; 33 - electric line for the transmission of sound signals. Mentioned communication channels 30, 31, 32, 33 are channels of information exchange. The types of communication channels through which information exchange is carried out between each specific type of equipment from the complex are indicated in the diagram in Fig. one.

The flight and navigation information complex 1 includes a digital calculator 2, two widescreen multifunctional indicators 3, 4, a device for entering navigation parameters 5, a multifunctional control panel 6 with a SNS receiver, a heading vertical 7, a low-altitude radio altimeter 8, an air signal computer 9, a protected airborne drive 10, navigation and landing equipment 11 VOR/LOC/GS/MB/ADF, automatic control system 12, microphone device 13.

The integrated system of backup devices 17 includes a multifunctional indicator-calculator, a magnetic heading sensor and an airflow stagnation temperature sensor.

The composition of the lighting equipment 18 includes an alarm unit 19, a light signaling board 20, an alarm board with control 21, 22, a warning alarm board with control 23, 24.

The radio communication equipment 25 includes amplification and switching equipment 26, a MV-UHF radio station 27, a radio communication control panel 28, an emergency radio beacon 29 of the international satellite search and rescue system KOSPAS-SARSAT.

In the cockpit there are two large-format multifunctional indicators 3, 4, a device for entering navigation parameters 5, a multifunctional control panel 6, a control panel for operating modes from the ACS 12, a microphone device 13, two multifunctional indicators 15, 16, a multifunctional electronic indicator from the ISRP 17 , light signaling board 22, alarm board with control 21, 22, warning alarm board with control 23, 24, radio control panel 28.

A significant difference of the avionics complex is the implementation on a widescreen multifunctional indicator (MFD) of simultaneous indication of several zones containing the following information:

- zone of indication of signatures of names of functional buttons;

- zone of indication of signatures of names of multifunctional buttons;

- area for displaying graphic information of the main frame: flight, navigation, cartographic;

- zone for displaying graphical information of the auxiliary frame: parameters of general helicopter equipment or navigational flight plan;

- zone for displaying text information messages: emergency, warning and notification messages, as well as recommendations for the crew.

The general structure of the frame on the widescreen display is shown in Fig. 2.

In the upper part of the screen there are function buttons for selecting display frames, buttons for adjusting the brightness of the image and buttons for scrolling through information messages.

At the bottom of the screen are multi-functional buttons, the purpose of which changes depending on the displayed frame.

Depending on the selected format control button, the main frame may display:

- a complex frame of flight and navigation information (PNT);

- navigation information frame (NVG);

- a frame for monitoring the state of on-board radio-electronic equipment (CONTR).

The auxiliary frame is designed for optimal and timely access to the following information for the crew:

- alarm text emergency and warning information;

- information about the operation of the power plant and transmission;

- information about the current route (navigator's flight plan).

Switching the information presentation format in the auxiliary frame is performed using the multifunctional buttons MOVE and MARCH, located at the bottom of the screen.

A general view of the complex frame of flight and navigation information on a widescreen display is shown in Fig. 3.

Another significant difference of the on-board radio-electronic equipment complex is the implementation on a wide-format multifunctional display of the frame for monitoring the CONTR state of the on-board equipment and controlling the equipment control function (Fig. 4).

The advanced equipment control feature is only available when the helicopter is on the ground and is not available after takeoff.

The CONTR frame is designed to display:

- state of equipment of the avionics complex;

- state of communication lines, display of unreliable information;

- carrying out extended control of equipment during ground pre-flight preparation and maintenance of the complex.

The COUNTER frame is called by pressing the COUNTER functional button on the button frame of the multifunctional indicator.

In the left part of the frame, a zone with an enlarged list of systems is highlighted. The following color coding of the names of the systems has been applied:

- green color - the system and the units included in it are operational, the input communication lines from the interfaced equipment are operational, the received information is reliable,

- red color - failures of the system and/or incoming units have been detected, failures of input communication lines have been detected, false information has been received.

The central part of the frame displays information about the state of the selected system: the full name of the system; integral state of the system; the content of the status words issued by the selected system; the version and checksum of the firmware of the selected system.

To carry out ground extended control of the complex in the CONTROL frame, it is necessary to press the FULL multifunctional button. At the same time, in the central part of the screen in the zone of the integral state of the complex, the inscription "CHECKING IN PROGRESS" and the time remaining until the end of extended monitoring are displayed. In the process of advanced control, the message field, located on the right side of the frame, displays information about the passage of control in the form of messages about detected system malfunctions, inaccurate information and communication lines, as well as text messages.

To carry out an extended control of a specific system in the CONTR frame, use the arrows to select the appropriate system and press the INDIV softkey.

The next significant difference of the avionics complex is the introduction of an integrated system of standby instruments into its composition.

The integrated system of backup instruments based on a multifunctional electronic indicator is designed to determine and display the parameters of the spatial position of the helicopter, airspeed, navigation parameters, parameters of radio navigation and landing aids, the common pitch and rotational speed of the main rotors.

In accordance with the requirements of AP-29 (D29.2.10) and GOST 19340, in the cockpit of the helicopter, when using on-screen indicators, backup instruments must be installed, the composition and characteristics of which ensure the safe continuation of the flight and landing in accordance with the flight manual in the event of a complete loss of information on main screen indicators, including in case of failure of the main sources of the power supply system.

The integrated system of backup instruments as a backup source of information provides measurement, calculation and output to its own electronic indicator and to the interfaced equipment of the parameters of the spatial position of the helicopter and the altitude and speed parameters based on information received from the built-in sensors.

The general view of the frame on the electronic indicator of the integrated system of redundant devices is shown in Fig. 5.

The electronic indicator of the integrated system of standby instruments provides display of the following measured parameters of the spatial position of the helicopter, altitude, speed and other parameters: roll angle; pitch angle; angle heading gyromagnetic; instrument speed; true speed; vertical speed; barometric altitude; lateral overload; geometric height (according to information from the radio altimeter); rotor speed (according to information from the general helicopter equipment sensor); common rotor pitch (according to information from the block for calculating and converting analog, discrete and digital signals); heading angles of the radio station ARK, VOR (according to information from the onboard receiver of signals of radio technical means (RTS); heading angles ILS (according to information from the onboard receiver of signals RTS).

The avionics complex of the helicopter operates as follows (Fig. 1).

Heading vertical 7 generates information about the spatial position of the helicopter: true heading angle, roll angle, pitch angle, as well as information about accelerations, overloads and angular velocity components, which is output to the digital computer 2 through the appropriate information exchange channels, widescreen multifunctional indicators 3, 4, multifunctional control panel 6, automatic control system 12.

The digital calculator 2 provides information on the modes of operation, given coordinates and the heading of the helicopter to the heading vertical 7 through the corresponding channels of information exchange.

The multifunctional control panel 6 outputs a time stamp signal and satellite navigation system (SNS) data to the heading vertical 7 through the appropriate information exchange channels.

The air signal computer 9 outputs information about the altitude and speed parameters of the helicopter to the digital computer 2, heading vertical 7, widescreen multifunctional indicators 3, 4, and automatic control system 12 via the appropriate information exchange channels.

The input device for navigation parameters 5 generates and, through the appropriate channels of information exchange, issues information about the type of barrocorrection, the set value of the dangerous height, the set ground angle and the set course to the air signal computer 9, the digital computer 2, the multifunctional control panel 6, the integrated system of backup devices 17.

The digital calculator 2 generates and, through the appropriate information exchange channels, issues a one-time command "Advanced control" to the air signal computer 9, the low-altitude radio altimeter 8, and the automatic control system 12.

The multifunctional control panel 6 generates and, through the appropriate channels of information exchange, issues the information necessary to control and monitor the state of the equipment of the complex, data from the receiver of the satellite navigation system (SNS), route information and route navigation parameters to the digital computer 2.

The multifunctional control panel 6 provides input and, through the appropriate channels of information exchange, issues external radio control parameters to the radio station 27 of the MV-UHF band, in response to which it receives a status word from the radio station 27 of the MV-UHF band.

The digital calculator 2, through the appropriate channels of information exchange, outputs for indication the calculated navigation parameters of the movement, as well as alarm text emergency, warning and notifying information to the multifunctional control panel 6 and widescreen multifunctional indicators 3, 4.

The digital calculator 2 outputs data on deviation corrections, reference pressure and control commands to the integrated system of backup devices 17 through the appropriate information exchange channels.

The multifunctional control panel 6 provides for loading from a removable media and transferring cartographic data, a standard aeronautical database, a database of artificial obstacles, user databases, as well as issuing calculated navigation motion parameters to widescreen multifunctional indicators 3, 4.

The low-altitude radio altimeter 8 generates and, through the appropriate information exchange channels, provides information about the current true flight altitude to the digital computer 2, widescreen multifunctional displays 3, 4, automatic control system 12.

The digital calculator 2 generates and issues a one-time command "Turn off radio altimeter radiation" to the low-altitude radio altimeter 8 through the appropriate information exchange channels.

The digital calculator 2 generates and through the appropriate channels of information exchange issues a one-time command "Maximum allowable flight speed" to the calculation and conversion unit 14, which is transmitted to the alarm unit 19.

The digital calculator 2 generates and, through the appropriate information exchange channels, issues a one-time command "Dangerous height" to the calculation and conversion unit 14, which outputs the corresponding sound signal to the amplification and switching equipment 26.

A low-altitude radio altimeter 8, a radio control panel 28, a MV-UHF radio station 27, amplification and switching equipment 26 form and, through the appropriate information exchange channels, issue the corresponding one-time “Healthy” commands to the digital calculator 2 and the calculation and conversion unit 14.

The alarm block 19 generates and outputs three types of sound signals through the appropriate information exchange channels: “Buzzer”, “HV speeds are Small”, “HV speeds are Great” to the amplification and switching equipment 26.

The automatic control system 12 generates and, through the appropriate channels of information exchange, issues information for indicating the set values and director signals, about the current state of the set modes to the digital calculator 2 and widescreen multifunctional indicators 3, 4.

The VOR/LOC/GS/MB/ADF 11 navigation and landing equipment generates and outputs information from the ADF (heading angle of the radio station, receipt of the operating frequency) and from VIR (VOR azimuth, course deviation, glide path deviation, signals) through the appropriate information exchange channels. flight of marker beacons, receipt of the operating frequency) into the digital calculator 2 and large-format multifunctional indicators 3, 4.

The digital calculator 2 on the appropriate channels of information exchange provides information about the modes of operation and tuning frequencies to the navigation and landing equipment 11 VOR/LOC/GS/MB/ADF.

Navigation and landing equipment 11 VOR / LOC / GS / MB / ADF generates and outputs audio signals from ADF (identification signal for driving and broadcasting stations) and from VIR (signal "Identification" of localizers VOR / ILS and passage of marker beacons) through the appropriate information exchange channels ), as well as audio signals of three types: ADF OUT, Marker, VOR/LOC to amplification and switching equipment 26.

The digital calculator 2 generates and, through the appropriate information exchange channels, issues control commands and parametric information to the heading vertical 7, the automatic control system 12, the air signal computer 9, the low-altitude radio altimeter 8, the navigation and landing equipment VOR / LOC / GS / MB / ADF 11, navigation parameters input device 5, emergency beacon "KOSPAS-SARSAT" 29.

The integrated system of backup instruments 17 generates and through the appropriate channels of information exchange issues information about the values of the angles of spatial orientation, instrumental and ground speeds, barometric altitude, vertical barometric speed, rotor speed and status data to the digital computer 2 and automatic control system 12.

The amplification and switching equipment 26 and the microphone device 13, through the appropriate channels of information exchange, output for registration audio signals of the conversations of the crew and subscribers in the transport cabin, the sound environment in the cockpit to the protected on-board storage 10.

The complex includes an automatic control system 12 with a control panel for operating modes of the automatic control system, which is interconnected by inputs and outputs via information exchange channels with the heading vertical 7, an air signal computer 9, a digital computer 2, large-format multifunctional indicators 3, 4, a low-altitude radio altimeter 8 , an integrated system of backup devices 17.

The avionics complex of the helicopter complies with the requirements of AP-29 to ensure flights according to the rules of visual flight with a crew consisting of one or two pilots, while the ability to control both one and two pilots, day and / or night, is implemented. At the same time, the complex remains fully operational and ensures safe flight performance even when the following optional equipment from the complex is dismantled on a helicopter: navigation and landing equipment 11 VOR / LOC / GS / MB / ADF, automatic control system 12 and equipment of the co-pilot's workplace - a wide-format multifunctional display 4, an alarm board with control 22 and a warning alarm board with control 24.

Thus, the developed complex of on-board radio-electronic equipment (avionics) of the helicopter ensures the fulfillment of the following functional requirements:

- flights without restrictions on the geographical position of the helicopter;

- route flights - on domestic and international air routes or local air lines (IL);

- cross-country flights - on predetermined (programmed) routes outside air routes and international lines using ground RTS;

- route flights - on air routes or MVL and beyond them;

- aerodrome flights - in the area of the aerodrome, including maneuvering along the standard routes of departure (SID) and arrival (STAR);

- non-precision approach to airfields and landing sites not equipped with RTS, including the method of area navigation using satellite navigation systems (SNS) in manual control mode (in the basic configuration);

- instrument approach and landing on airfields equipped with RTS (VOR, ILS, MRKR) in automated and manual control modes (with optional equipment).

The complex of onboard radio-electronic equipment (avionics) of the helicopter provides the solution of the following tasks:

- flight navigation support by determining the geographic coordinates of the helicopter and its movement parameters using various navigation aids, including the GPS/GLONASS/GALILEO satellite navigation system, with indication of the helicopter's location to the crew;

- formation and display of flight and navigation information in symbolic and textual form on multifunctional indicators (MFI), multifunctional control panel (MFPU) and integrated system of standby instruments (ISRP);

- control, formation and display of information on the state of the power plant (PS) and information on the state of general helicopter equipment (HVO);

- formation, signaling and indication of notification, warning and emergency messages in the form of text messages on the MFI, sound tones and light indication on the light signal boards;

- operational manual input of the specified values of flight parameters and units of their measurement;

- centralized control of onboard radio navigation equipment;

- reading and displaying the current local time, UTC time and flight time;

- collection, registration and storage of an array of sound and digital parametric flight information in a secure flight recorder;

- providing helicopter crew members with internal voice communication, external voice communication in the VHF band, as well as listening to sound signals from radio navigation systems and warning signals about the failure of helicopter systems and the achievement of limit flight parameters;

- control of radio communication equipment (RSO) with display of operating modes and frequencies of equipment settings;

- transmission of a distress signal in the "COSPAS-SARSAT" system to determine the location of the helicopter in the event of a flight accident;

- automatic and automated continuous and periodic monitoring of the technical condition, parameters and modes of operation of equipment, communication lines with the issuance of monitoring results for indication and on-board recording facilities;

- automated execution of procedures for pre-flight preparation, maintenance and control in ground conditions;

- manual and automated correction of helicopter location coordinates using VOR beacons with indication to the crew;

- piloting and control of a helicopter in automated, director and combined control modes, as well as ensuring stabilization of the helicopter in heading, roll, pitch and barometric altitude;

- displaying the navigation and planning situation against the background of a digital map of the area (DTM);

- automated loading and storage of a standard aeronautical database (ANBD), a database of artificial obstacles, a database of two-dimensional digital cartographic information (TsKI), a database of a digital matrix of heights;

- diagnostics of the helicopter transmission by timely detection of pre-failure conditions during the installation of the on-board diagnostic system of the HUMS type;

- determination and display to the crew of the configuration of the installed equipment.

Claims (4)

1. A complex of on-board electronic equipment of a helicopter, containing a set of equipment elements interconnected by inputs-outputs via information exchange channels, including a flight and navigation information complex (1), which includes at least one widescreen multifunctional indicator, multifunctional control panel (6), heading vertical (7), low-altitude radio altimeter (8), air signal computer (9), protected on-board storage device (10) with an underwater acoustic beacon, microphone device (13), block for calculating and converting analog , discrete and digital signals (14), multifunctional indicators (15, 16), radio communication equipment (25) containing amplification and switching equipment (26), a radio station (27), a radio communication control panel (28), characterized in that the composition of the complex, a digital computer (2) was introduced, an integrated backup system x instruments (17), a device for entering navigation parameters (5), in addition, the complex includes lighting equipment (18) containing an alarm unit (19), a light signaling board (20), at least one alarm board with control, at least at least one warning signal board with control, an emergency radio beacon (29) of the international satellite search and rescue system, while the said heading vertical (7) is interconnected by inputs and outputs via information exchange channels with a digital computer (2), widescreen multifunctional indicators (3, 4) , multifunctional control panel (6), said air signal calculator (9) is interconnected by inputs-outputs via information exchange channels with a digital calculator (2), vertical heading (7), widescreen multifunctional indicators (3, 4), said device for inputting navigation parameters ( 5) is interconnected by inputs-outputs through information exchange channels with an air signal calculator (9), a digital calculator (2), a multifunctional control panel (6), an integrated system of backup devices (17), the mentioned digital calculator (2) is interconnected by inputs and outputs via information exchange channels with an air signal calculator (9), low-altitude radio altimeter (8), multifunctional control panel (6), widescreen multifunctional displays (3, 4), integrated system of backup instruments (17), calculation and conversion unit (14), navigation parameters input device (5), emergency radio beacon ( 29), the mentioned multifunctional control panel (6) is interconnected by inputs-outputs via information exchange channels with the radio station (27), digital calculator (2), widescreen multifunctional indicators (3, 4), the mentioned low-altitude radio altimeter (8) is interconnected by inputs-outputs through information exchange channels with a digital calculator (2), wide-format multifunctional indicators (3, 4), said integrated system of backup devices (17) is interconnected by inputs-outputs via information exchange channels with a digital calculator (2), said protected on-board storage (10) is interconnected by inputs-outputs via information exchange channels with amplification and switching equipment (26) and a microphone device (13). 2. The complex of on-board radio-electronic equipment of the helicopter according to claim 1, characterized in that the complex includes navigation and landing equipment (11), which is interconnected by inputs and outputs via information exchange channels with a digital computer (2), large-format multifunctional indicators (3, 4 ), amplification and switching equipment (26). 3. The complex of on-board radio-electronic equipment of the helicopter according to claim 1, characterized in that the complex includes an automatic control system (12) with a control panel for operating modes of the automatic control system, which is interconnected by inputs and outputs via information exchange channels with the heading vertical (7), a computer air signals (9), digital calculator (2), large-format multifunctional displays 3, 4, low-altitude radio altimeter (8), integrated system of backup instruments (17). 4. The complex of on-board electronic equipment of the helicopter according to claim 1, characterized in that the complex has a scheme for centralized control of the state and serviceability of the systems of the complex and information exchange lines.

Images