RU2640076C2 - Complex of onboard equipment of general aviation helicopters and aircrafts - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: complex of onboard equipment of general aviation (GA) helicopters and aircrafts contains a multifunctional indicator (MFI), a basic flight instrument (BFI), a combined attitude-and-heading reference system (AHRS), air pressure receivers, a braking temperature receiver, a signal conversion unit, an integrated radio communication system (IRCS), alarm and notification signalling panel system, a set of internal lighting and light-signal equipment, a device for wireless user data downloading, an air traffic control transponder, a search-and-rescue radio beacon, small-sized on-board recorder, height finder, automatic radio compass, automatic dependent surveillance transponder, VOR/ILS short-range navigation and landing equipment set, equipment set of a marker receiver/automatic radio compass, an automatic pilot system connected in a certain way by means of an information exchange channel. MFI contains a computing and forming unit, including a display and alarm module, software modules of navigation and cartography, as well as prevention of critical conditions and early warning of ground proximity, a display module, power module. The BFI contains an LCD indicator, an attitude module, a critical signal conversion module. The AHRS contains a main computer module, an attitude module, a module for measuring and computing air data with a GLONASS/GPS receiver, and a magnetic direction sensor. The IRCS contains a radio station unit, an intercommunication control panel.EFFECT: increase of piloting safety and efficiency in the use of general-purpose helicopters and aircraft.6 cl, 2 dwg

Description

The invention relates to universal airborne electronic equipment (avionics), providing measurement and indication to the crew of the aircraft (LA) of flight parameters, signaling the limiting and critical flight modes and operation of units and systems of aircraft, navigation, equipment control, radio communications, registration of flight data, monitoring of technical the state of aircraft onboard systems.

There is a general aviation class, which includes helicopters and airplanes, characterized by a small take-off weight and a small number of passengers carried, which in turn imposes special requirements on weight and size characteristics, energy consumption and the cost of avionics and its operation.

Today, there is a tendency for generations of avionics and helicopter avionics and aircraft to be replaced by highly integrated digital systems built on the basis of common computing resources platforms instead of disparate electronic units, as well as on the principles of a “glass cabin”, i.e. use of multifunction displays instead of traditional separate electromechanical devices.

This trend, as well as the specifics of general aviation, imposes requirements to ensure the maximum level of integration of onboard equipment functions with a minimum number of avionics hardware units.

Known on-board flight and navigation system for helicopters, described in RF patent No. 2204504, IPC B64C 13/16, G01C 23/00, 07/08/2002, adopted as a prototype, containing in its composition interconnected navigation system, helicopter control system, display system, an on-board computer that performs the functions of setting source data, generating and correcting motion parameters, a system for converting analog and discrete information, an integrated information generation device, and a pairing device.

The disadvantages of the known invention adopted for the prototype are:

- the structure of the complex is based on the concept of federal centralized architecture (FCA), i.e. the complex is a set of individual components (KI) that perform a specific function in the avionics of a helicopter and are interconnected by many different channels (interfaces) of information reception / transmission,

- a large number of cross information links between the KI complex,

- relatively high indicators of mass and overall characteristics,

- functional limitation and limited application, determined by the rigidly fixed structure of the complex.

The proposed complex of on-board equipment for helicopters and general aviation aircraft BWC AON aircraft is aimed at improving the technical and operational characteristics of helicopters and AON aircraft by increasing the degree of integration of avionics functions in the optimal number of avionics hardware units.

To achieve a technical result, which is to increase the safety of piloting and the efficiency of the use of helicopters and AON aircraft, to increase technical excellence, the reliability of the complex, a complex of on-board equipment for helicopters and general aviation aircraft is proposed, containing

multifunctional MFI indicator, consisting of a unit for calculating and forming BVF, a display module (color) MDC, a power supply module for MPI, interacting with each other, and the block for calculating and forming BVF contains n-program modules, including an operating system, an input-output module, a control module etc., as well as a software module for indicating and signaling, a software module for navigation and cartography,

software module for warning critical modes, software module for early warning of the proximity of the earth, and containing mode controls located on its front panel with built-in backlight,

the main flight control device of the OPP, which consists of the LCD indicator itself, the module for determining the spatial position and measuring the air data of the MPP and the critical signal conversion module MPKS

combined KB vertical line, consisting of a main computing module, a spatial position module, an air data measurement and calculation module with a GLONASS / GPS receiver, a magnetic heading sensor interacting with each other,

LDPE air pressure receivers,

braking temperature receiver

BTS signal conversion unit,

an integrated radio communication system of the ISR, consisting of a radio station unit, including a voice alert module and an intercom module, intercom panels,

STAUS alarm and notification alarm system,

a set of internal lighting and light-signaling equipment, consisting of a light-signal board, a light-signal board with control, a lighting adjustment unit, a brightness mode controller,

air traffic control system transponder,

emergency rescue beacon,

small-sized on-board recorder of ICBMs,

device for wireless loading of user data,

radio altimeter

ARC automatic radio compass, automatic dependent surveillance transponder, VOR / ILS short-range navigation and landing equipment set / marker receiver / automatic radio compass, autopilot,

information exchange channel.

In FIG. 1 shows a block diagram of the proposed complex.

The complex of onboard equipment for helicopters and general aviation aircraft contains:

multifunctional indicator MFI 1, consisting of a unit for calculating and forming BVF 2, including n-software modules containing a software module for indicating and signaling 3, a software module for navigation and cartography 4, a software module for warning critical modes 5, a software module for early warning of proximity to the earth 6, as well as a display module (color) MDC 7 and power supply module MPI 8,

the main flight instrument OPP 9, consisting of an LCD indicator 10, a module for determining the spatial position and measurement of air data MPP 11 and the critical signal conversion module MPKS 12,

Combined vertical line KB 13, consisting of the main computing module 14, spatial position module 15, measurement and calculation module for air data with a GLONASS / GPS 16 receiver, magnetic heading sensor KMT 17,

PVD air pressure receivers 18,

braking temperature receiver 19, BPS 20 signal conversion unit,

an integrated radio communication system ISR 21, consisting of a radio station unit 22, including an intercom module 23 and a voice announcement module 24, and internal communication panels 25,

alarm and notification alarm system STAUS 26, consisting of an alarm and notification alarm panel,

set of internal lighting and signaling equipment STO 27, consisting of a light-signal panel, a light-signal panel with control, a lighting adjustment unit, a brightness mode controller,

a device for wireless loading of user data 28, consisting of a unit and an antenna,

the transponder of the ATC system 29, consisting of a transmitter unit and antennas,

emergency rescue beacon 30, consisting of an automatic stationary radio beacon and a portable emergency rescue beacon;

small-sized on-board recorder MBR 31, consisting of a unit, a control panel, a microphone dynamic device,

radio altimeter 32,

ARC 33 automatic radio compass,

transponder automatic dependent surveillance 34, consisting of the actual block,

a set of short-range navigation and landing equipment VOR / ILS / marker receiver / automatic radio compass 35,

autopilot 36, consisting of a control computer and drive mechanisms,

information exchange channel 37, which is a combination of digital and analog data lines that combine the equipment included in the complex.

In FIG. 2 shows the front panel of the multifunctional indicator MFI 1, where

38 - mode control elements;

The complex of onboard equipment for helicopters and general aviation aircraft provides:

- the formation and continuous display of the crew of the helicopter (airplane) flight and navigation information;

- operational management of the display of information on MFI 1 and OPP6;

- two-way radio communication within the direct radio-visibility of crew members with ground-based air traffic control services;

- internal telephone communication between crew members;

- listening to sound signals of medium-wave drive and broadcast radio stations;

- automatic transmission of distress signals in the event of a helicopter (airplane) accident or emergency landing;

- manual and automated (at pre-set frequencies) tuning of radio communication and radio navigation equipment;

- navigation support for helicopter (airplane) flight;

- monitoring the state of the power plant of the helicopter (aircraft);

- the formation and storage of information about failures of helicopter (airplane) systems, about exceeding operational limitations of the engine and onboard equipment parameters, as well as the issuance of this information on the ground to maintenance personnel;

- collection, formation and registration of an array of flight information, as well as audio information about the negotiations between the crew and passengers in a secure on-board recorder.

Multifunctional indicator MFI 1, consisting of a unit for calculating and forming BVF 2 interacting with each other, including n-program modules containing a software module for indicating and signaling 3, a software module for navigation and cartography 4, a software module for warning critical modes 5, a software module for early warning of proximity Earth 6, as well as the display module MDC 7 and the power supply module MPI 8, performs:

- solving navigation and flight control problems;

- management of operating modes and tuning of complex systems;

- indication of the state parameters of the onboard equipment and engine (s);

- indication of complex unit failures;

- indication of flight and navigation parameters (roll angles, pitch; magnetic course; lateral sliding; instrument, vertical speed; absolute, relative barometric altitude; radio altitude; ARC course);

- selection of information frames for display, data entry;

- display of notification and alarm messages;

- adjusting the brightness of the displayed information.

The unit for calculating and forming BVF 2, including n-program modules containing a program module for indicating and signaling 3, a program module for navigation and cartography 4, a program module for warning critical modes 5, a program module for early warning of ground proximity 6, as well as an operating system, input module - output, equipment control module, etc., is a platform of common computing resources and ensures the functioning of all software modules included in it, as well as receives and issues information interface signals to the interfaced equipment, image formation for transmission to MDC7.

The display module MDC 7 displays the received video information on the LCD screen, polls the current state of the mode control elements 38, and also provides information on their status in the BVF 2.

MPI 8 power supply module provides uninterrupted power supply to BVF 2, MDC 7.

The mode control elements 38 are located on the front panel of the MFI 1 and include a sufficient number of buttons and controllers in the form of push-buttons. The mode control elements 38 in the form of buttons having a built-in backlight call the complex functions, control information display modes, and operating modes of adjacent systems.

The control elements 38 in the form of a pressure ratchet, for example, adjust the brightness of the LCD screen MFI 1, the setting values, for example, atmospheric pressure, frequency settings of the radio equipment.

Block BVF 2 provides reception and issuance of one-time commands (RC) from helicopter (aircraft) sensors, as well as interaction with avionics.

A feature of this indicator MFI 1 is that the BVF 2 unit, which is part of it, is a platform of common computing resources and provides the functions of the main computer and algorithmic processing, as well as the management and processing of input information, thereby integrating the onboard computer and indicator . This is ensured by the fact that the BVF-2 unit contains many independent applied software applications, including the introduced navigation and cartography software module 4, developed in accordance with real-time requirements, thereby allowing the equipment included in this complex to be integrated and many BWC functions integrated.

MFI 1 interacts with OPP 9, KB 13, BPS 20, ISR 21, STAUS 26, transponder ATC 29, emergency rescue beacon 30, ICBM 31, radio altimeter 32, ARC 33, automatic dependent transponder 34, a set of short-range navigation equipment and landing VOR / ILS / marker receiver / automatic radio compass 35, autopilot 36 through the channel of information exchange 37.

The primary flight control device OPP 9, consisting of an LCD indicator 10, a module for determining the spatial position and measurement of air data MPP 11 and a critical signal conversion module MPKS 12, receives and displays basic flight and navigation information, such as instrument and true airspeed, vertical speed, relative barometric altitude, lateral glide, roll, pitch, signaling the way out of the specified level, as well as autonomous measurement, calculation and display of altitude critical flight parameters and spatial position of the aircraft in case of failure of the main channel for measuring flight and navigation parameters, namely KB 13.

The following parameters are displayed on LCD indicator 10: gyromagnetic course, automatic radio compass (ARC) course, roll, pitch, instrument and true speed, vertical speed; relative barometric altitude, radio height; side glide; outdoor temperature; total pitch and rotor speed.

The integrated MPP 11 performs autonomous measurement, calculation and display of altitude-speed flight parameters and the spatial position of the helicopter (aircraft) in the event of a failure of the main channel for measuring flight and navigation parameters, namely KB 13.

The built-in MPKS 12 autonomously receives and converts analog signals from sensors of the carrier system (for helicopters) or power plants (for airplanes) to provide backup display of critical parameters information.

OPP 9 receives information from KB 13 and BPS 20 and interacts with MFI 1 through the information exchange channel 37.

The combined horizontal line KB 13, consisting of the main computing module 14, the spatial position module 15, the air data measurement and calculation module with the GLONASS / GPS 16 receiver, and the KMT 17 magnetic course sensor performs:

- measurement, calculation and delivery to consumers of the parameters of the spatial position of the helicopter (aircraft), carried out by means of the module spatial position 15;

- measurement, calculation and delivery to consumers of altitude and speed parameters of a helicopter (airplane) by means of the main computing module 14 and by means of the measurement and calculation module of air data with a GLONASS / GPS 16 receiver;

- receiving information by means of a module for measuring and calculating air data with a GLONASS / GPS 16 receiver, converting and issuing to the consumers the navigation parameters of a helicopter (airplane) from the GLONASS / GPS satellite navigation system;

- the issuance to consumers of the values of the spatial position and navigation parameters of the object, calculated using information from their own sensors (linear acceleration sensors, angular velocity sensors), KMT 17, air pressure receivers PVD 18 and information from the GLONASS / GPS SNA.

A feature of this combined vertical line is that it includes a module for measuring and calculating air data with a GLONASS / GPS 16 receiver, which allows KB 13 to work in combination mode.

KB 13 through the information exchange channel 37 interacts with IFI 1 and OPP 9.

The air pressure receivers LDPE 18 carry out the perception and transmission in KB 13 and MPP 11, included in the OPP 9, of the full and static air pressure. The peculiarity of the LDPE is that they provide a device that generates a heating failure signal for each LDPE. LDPE receivers are installed on the right and left side of a helicopter (airplane).

The receiver of the braking temperature 19 carries out the perception and transmission in KB 13 and MPP 11, included in the OPP 9, the braking temperature of the air flow.

The signal conversion unit BPS 20, performs:

- reception and digitalization of discrete signals from onboard sensors of a helicopter (airplane);

- the issuance of information in the form of a serial binary code on the channel of information exchange 37;

- the issuance of information about their own health in IFI 1.

BPS 20 provides uninterrupted power to the braking temperature receiver 19.

BPS 20 interacts with MFI 1 and OPP 9 through the information exchange channel 37.

The integrated radio communication system ISR 21, consisting of a radio station block 22, including a speaker unit 23 and a voice announcement module 24, and intercom panels 25 performs:

- through an intercom module 23 and a voice alert module 24, an external two-way simplex telephone radio communication to one of the aircraft pilots (with the possibility of listening to conversations by another pilot);

- through the block of the radio station 21 external two-way simplex radio communication for one of the pilots through an additional radio station;

- by means of the radio station unit 22 and the internal communication panels 25, internal telephone communication in the SPU mode (aircraft intercom) (conference communication) between two pilots and one passenger with volume control;

- through the block of the radio station 22 and the voice alert module 24 listening to each of the two pilots:

- signals from radio navigation devices with volume control;

- signals from sensors of special signals;

- voice messages;

- signals of marker beacons from the built-in marker receiver.

ISR 21 interacts with MFI 1, STAUS 26 through the information exchange channel 37.

The alarm and notification alarm system STAUS 26, consisting of an alarm and notification alarm panel, independently of MFI 1 and OPP 9, provides the crew with alarm and warning alarm information about the state of helicopter (aircraft) systems and units in the form of light and sound signals.

STAUS 26 interacts with MFI 1 and BPS 20 through the information exchange channel 37.

The set of internal lighting and light-signaling equipment STO 27, consisting of a light-signal panel, a light-signal panel with control, a lighting adjustment unit, a brightness mode adjuster, is designed to illuminate the cabin equipment, which allows to improve the light climate of the cabin, thereby reducing crew fatigue, as well as to provide the crew of emergency, warning and notification light signals about the status of systems and assemblies.

The internal lighting and lighting equipment 27 interacts with STAUS 26.

The device for wireless loading of user data 28, consisting of a unit and antennas, makes a stable connection via a wireless communication channel of a certain standard with the pilot's electronic tablet for subsequent loading into the internal memory of the MFI indicator 1 cards, aeronautical databases (ANBD) and user information.

The transponder of the ATC system 29, consisting of a transmitter unit and antennas, works with selective and non-selective secondary radio channels, provides radio surveillance (elementary, advanced and automatic dependent), for receiving, decoding request signals and generating responses to them.

The defendant of the air traffic control system 29 interacts with the IFI 1 through the channel of information exchange 37.

The emergency rescue beacon 30, consisting of an automatic stationary radio beacon and a portable emergency rescue beacon, transmits distress radio signals containing coordinates, as well as providing search tools to the accident site, via artificial earth satellites at the information receiving and processing station of the COSPAS-SARSAT system.

The emergency rescue beacon 30 interacts with MFI 1 through a standard information exchange channel 37.

The compact on-board recorder MBR 31, consisting of a unit and a control panel, collects and registers analog, discrete, digital, parametric and sound information. ICBM 31 provides for the preservation and rewriting of registered information in the ground processing complex, the preservation of recorded flight information in the event of a flight accident.

ICBM 31 interacts with IFI 1, OPP 9, KB 13, ISR 21 through the information exchange channel 37.

The radio altimeter 32 is a radar station with continuous emission of frequency-modulated radio waves. The radio altimeter 32 measures and provides information on the geometric altitude of the aircraft.

The radio altimeter 32 interacts with the MFI 1 and the autopilot 36 via the information exchange channel 37.

The ARC 33 automatic radio compass determines the heading angle of drive and broadcast radio stations.

Automatic radio compass 33 interacts with MFI 1 and OPP 9 through the information exchange channel 37.

The automatic dependent surveillance transponder 34, consisting of a receiving and processing unit, performs:

- receiving and processing on board a helicopter (airplane) ADS-R information based on 1090ES technology;

- reception and processing on board of a helicopter (airplane) of TIS-B ground service information based on 1090ES technology;

- Interaction with on-board analog and digital sensors and systems without additional interface units.

Using the automatic dependent surveillance transponder 34, safe maneuvering is performed based on the obtained coordinate-time information from the surrounding aircraft, ground-based observation data (TIS-B) and on-board coordinate-time sensors (GNSS, etc.). The transponder of automatic dependent surveillance 34, together with the transponder of the air traffic control system 29, fully implements the functions of automatic dependent surveillance.

The introduction of the transponder automatic dependent observation 34 solves the following monitoring tasks:

- improved visual observation (EVAcq);

- conflict detection (CD).

- Improved visual observation during approach (EVApp);

- observation of ground conditions in the area of the aerodrome (ASSA, FAROA).

The automatic dependent surveillance transponder 34 interacts with the MFI 1 via the information exchange channel 37.

A set of short-range navigation and landing equipment VOR / ILS / marker receiver / automatic radio compass 35 provides the determination of the magnetic bearing of a helicopter (airplane) relative to VOR beacons located in all regions of the globe, the approach and landing of aircraft at most airports in the world according to I, II and ICAO III categories, determining the slant range of a helicopter (airplane) to DME beacons located in all regions of the globe. MFI 1 and OPP 9 control and receive data from VOR / ILS / DME equipment.

A set of short-range navigation and landing equipment VOR / ILS / marker receiver / automatic radio compass 35 interacts with MFI 1 and OPP 9 and autopilot 36 via information exchange channel 37.

Obviously, the proposed complex has a sufficient set of on-board electronic equipment for connecting a control system - autopilot. The inclusion of an autopilot in the complex allows for the convenience and simplicity of piloting a helicopter (airplane) in all flight modes.

Autopilot 36, consisting of a control computer and drive mechanisms, implements

- automatic stabilization of heading, roll and pitch angles in all flight modes, automatic u-turn coordination, automatic stabilization of instrument flight speed, automatic stabilization of barometric flight altitude, automatic stabilization of geometric altitude (when flying over a plain terrain and above a water surface) in steady-state flight modes , automatic stabilization of vertical flight speed, automatic access to a given course with its subsequent stabilization, automatic reaching a given height with its subsequent stabilization,

- automatic and director control of a helicopter (airplane) during flight en route by route or route method;

- automatic and director stabilization of the helicopter (airplane) on the approach path according to the signals of the radio engineering landing system according to ICAO category 2;

- automatic and director leaving on the second circle;

automatic trimming of the control wiring with simultaneous centering of the steering gear rods in the channels of direction, roll, pitch and total pitch;

- automatic and director stabilization of the helicopter on the approach path to a given navigation point.

- improved controllability and increased stability of the helicopter in all flight modes along the channels of heading, roll and pitch.

Autopilot 36 interacts with MFI 1, a set of short-range navigation and landing equipment VOR / ILS / marker receiver / automatic radio compass 35, radio altimeter 32 via data exchange channel 37.

Information exchange channel 37 is a combination of digital and analog data lines combining the equipment included in the complex.

Thus, the proposed complex of onboard equipment for helicopters and general aviation aircraft provides:

- integration of the display of information (devices, parameters, signals) according to the principles of the "glass cabin";

- integration of the main functions of the complex of on-board equipment due to the optimal number of hardware units - provides the versatility of the use of equipment on any general aviation helicopter (airplane).

Claims (6)

1. A complex of on-board equipment for helicopters and general aviation aircraft, containing a multifunctional indicator, a basic flight instrument, a signal conversion unit, characterized in that the complex contains a combined heading line, an integrated radio communication system, an alarm and notification signaling system, a set of internal lighting and signaling equipment , air pressure receivers, braking temperature receiver, air traffic control system transponder, ava rescue radio beacon, small-sized on-board recorder, device for wireless loading of user data, interacting via an information exchange channel, a multifunctional indicator contains interacting computation and generation units, including n-program modules containing a program indication and signaling module, a program navigation and cartography module , critical warning module, ground proximity early warning module, module a display and a power module, on the front panel of the multifunctional indicator mode controls are located that have built-in illumination, the main flight instrument contains a module for determining spatial position and measuring air data and a module for converting critical signals, the combined vertical cursor contains a main computing module interacting with each other, spatial position module, magnetic heading sensor, as well as measurement and subtraction module Lenia air data GLONASS / GPS receiver and the receivers cooperating with it air receiver pressure and stagnation temperature, the integrated radio communication system comprises a radio unit comprising a voice warning module and negotiating devices and consoles intercom. 2. The complex of onboard equipment for helicopters and general aviation aircraft under item 1, characterized in that it contains a radio altimeter. 3. The complex of onboard equipment for helicopters and general aviation aircraft according to claim 1, characterized in that it contains an automatic radio compass. 4. The complex of on-board equipment of helicopters and general aviation aircraft according to claim 1, characterized in that it contains an automatic dependent surveillance transponder. 5. The complex of onboard equipment for helicopters and general aviation aircraft according to claim 1, characterized in that it contains a set of short-range navigation and landing equipment VOR / ILS / marker receiver / automatic radio compass. 6. The complex of onboard equipment for helicopters and general aviation aircraft according to paragraphs. 1, 2, 5 characterized in that it contains an autopilot.

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