RU2530700C1 - Aircraft general hardware control system - Google Patents

Abstract

FIELD: aircraft engineering.

SUBSTANCE: proposed system comprises aircraft general equipment (3), control station (2) with control means connected to data exchange system (4) incorporating first and second doubly reserved communication channels (5) and (6), respectively. These are composed by first and second cached channels (7) and (8), and second primary and second secondary data exchange channels (9, 10). First and second computer-concentrator units (11) and (12), first and second units (13) and (15) of DC supply protection and switching units, first and second AC supply protection and switching units (14, 16), first and second signal converters (17) and (18) are connected to the latter.

EFFECT: reliability and perfected control.

4 cl, 1 dwg

Description

FIELD OF THE INVENTION

The invention relates to aircraft and is intended for use in the management of aircraft, including passenger aircraft, and more specifically, to perform the tasks of converting and transmitting information about the parameters of aircraft equipment systems, monitoring the status of systems, issuing information to prepare for displaying their status on indicators , issuing alarm messages about the status of systems and their modes of operation for automatic and manual control of general aircraft equipment and aircraft systems s.

State of the art

In a modern aircraft, the technical capabilities and efficiency of the control system for general aircraft equipment and aircraft systems (SUOSOSS) are crucial to ensure flight safety, improve reliability, and reduce the cost of operating aircraft.

The effectiveness of the use of aviation technology is inextricably linked with the problem of flight safety under the expected operating conditions, and its successful solution largely determines the development prospects of both civil and military aviation.

The intensity of the use of aviation equipment and the expansion of the range of functional tasks it performs determines the role of airborne automated control, diagnostics and control equipment for aircraft, information support for decision-making and crew unloading while ensuring the safety of the functioning of the elements of the on-board ergatic complex “Crew - avionics - aircraft” in the loop of the helm and automatic control of the aircraft.

To ensure flight safety in conditions of possible emergency situations on airplanes, on-board means of instrumental support for the crew are used: critical warning systems, failure monitoring and alarm systems, electronic indication systems, etc.

An increase in the number of functional systems, assemblies and other objects of on-board equipment of modern aviation equipment subjected to control during verification, pre-flight preparation and during the flight, an increase in the number of critical flight parameters that affect the level of safety, necessitates further automation of the monitoring processes of the current state of the aircraft equipment and crew actions, the formation of control actions and operational decisions at all stages from Earth maintenance and pre-flight preparation before take-off, flight, landing and taxiing under the general control of the crew.

The prior art platform for integrated modular avionics (see publication of patent RU 2413280 C1, IPC G06F 9/02, publ. 02/27/2011), made in the form of one or two subracks containing two subsystems with a switch and two pairs installed in each subsystem computing modules. The use of several customizable multifunctional software tools in a well-known platform leads to difficulties in setting the standard mode of operation of such an integrated modular avionics platform.

An aircraft control system is also included in the prior art, including a computing part with redundant processor determination of local control signals depending on the sensor signals of commands entered by the pilot, an extensive network of data lines, matching devices and actuators with individual drives for controlled elements (see Publication of the international application WO 01/93039 A1, IPC G06F 11/16, published on December 6, 2001), however, the functionality of this system is limited, and therefore it is not available Meets a number of requirements for modern passenger aircraft.

Also known from the prior art is an aircraft with a control system for general aircraft equipment (see publication of patent RU 2263044 C1, IPC В64С 13/00, published October 27, 2005) with the possibility of integrated control of general aircraft equipment (OSO) both in automatic and manual mode . A well-known aircraft contains the fuselage, wing, tail, chassis, engines of the main power plant, air intakes, an auxiliary power plant located in the rear of the fuselage, and a control system for general aircraft equipment (SUOSO). This control system for general aircraft equipment has two automatic control loops: the main and backup conversion and computation units connected to executive devices through the control and monitoring unit, as well as a manual control loop with control panels, light-signal board and central light-signal light.

The prior art system for controlling aircraft equipment, which is defined as the closest analogue (prototype) of the invention (see publication of application FR 2858863 A1, IPC G09B 9/03, publ. 02/18/2005).

The control system for general aircraft equipment, defined as a prototype, includes control panels with control tools configured to control the flight crew, general aircraft equipment and a communication system connecting it to control means, containing the first and second communication channels, separated from each other and laid different routes in an airplane, each of which contains two channels of information exchange, a set of the first computers connected to general aircraft equipment backhoes, and to control panels via the first communications channel and the second set of computers connected to obschesamoletnomu equipment directly and to control panels via a second communication channel.

The prototype of the present invention does not provide the required level of reliability, and also does not achieve high controllability, as functionality for performing the necessary operations of monitoring and diagnosing the technical condition.

SUMMARY OF THE INVENTION

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

This goal is achieved due to the fact that the control system for general aircraft equipment contains a control panel with controls for the flight crew, general aircraft equipment, an information exchange system that provides data exchange between general aircraft equipment and the control panel via the first and second communication channels, each of which contains the main and backup channel of information exchange, the first and second blocks of calculators, hubs, the first and second blocks of signal conversion the information inputs and outputs of which are connected respectively to the first and second information input and output of general aircraft equipment, the first and second protection and switching units of DC power lines, the outputs of which are connected respectively to the first and second DC power input of general aircraft equipment, the first and second blocks of protection and switching of AC power lines, the outputs of which are connected respectively to the first and second input of AC power general aircraft equipment, each of the listed blocks containing the main and backup modules, while the interface of the main and backup modules of the first block of calculators, hubs, the first signal conversion unit, the first protection and switching unit of DC power lines, the first protection and switching unit of AC power lines current are connected respectively to the first primary and first backup channel of information exchange, and the interface of the primary and backup modules of the second eye calculators hubs, the second signal converting unit, the second unit protection switching and power lines DC, and the second unit protection switching AC power lines - to the second base and the second backup channel of information exchange respectively.

In one embodiment of the control system for general aircraft equipment, said control panels with controls are made in the form of an integrated ceiling control panel.

In another embodiment of the proposed system, the primary and backup communication channels of the first and second communication channels of the information exchange system are made in the form of a bi-directional multiplex information exchange channel that meets the ARINC-825 specification.

The technical result of the invention is to increase the reliability and improve the suitability of the control system for general aircraft equipment.

The specified technical result is achieved in the proposed control system for aircraft equipment containing

control panel (2) with controls for flight personnel,

general aircraft equipment (3),

information exchange system (4), providing data exchange between general aircraft equipment (3) and the control panel (2) via the first (5) and second (6) communication channels,

moreover, the first communication channel (5) contains the first main (7) and the first backup (8) communication channels, and the second (6) communication channel - the second main (9) and backup (10) communication channels, and the system also contains

the first (11) and second (12) blocks of computers-concentrators (BVK1-O (11) and BVK1-R (12), respectively),

the first (17) and second (18) signal conversion blocks (BPS1-O (11) and BPS2-R (12), respectively), the information inputs and outputs of which are connected respectively to the first and second information input and output of general aircraft equipment (3) ,

the first (13) and second (15) blocks of protection and switching of direct current power lines (БЗК1-О (13) and БЗК1-Р (15), respectively), the outputs of which are connected respectively to the first and second DC power supply inputs of general aircraft equipment (3 ),

the first (14) and second (16) blocks of protection and switching of AC power lines (BZK2-O (14) and BZK2-R (16), respectively), the outputs of which are connected respectively to the first and second AC power inputs of general aircraft equipment (3 ),

moreover, the first (11) and second (12) blocks of calculators, hubs, the first (13) and second (15) blocks of protection and switching of DC power supply lines, the first (14) and second (16) blocks of protection and switching of AC power lines , as well as the first (17) and second and (18) signal conversion blocks contain the main (channel O) and backup (channel P) modules,

the interfaces of the main and backup modules of the first block (11) of the calculating hubs, the first block (17) of signal conversion, the first block (13) of protection and switching of the DC power supply lines, the first block (14) of protection and switching of the AC power lines are connected respectively, to the first main (7) and first backup (8) channel of information exchange, and the interfaces of the main and backup modules of the second block (12) of calculators-hubs, the second block (18) of signal conversion, the second and (15) and protection switching power lines DC, the second block (16) and protection switching AC power lines - to the second base (9) and to the second reserve (10) the traffic channel, respectively.

Brief Description of the Drawings

The invention is further illustrated by specific examples of its implementation with reference to the accompanying drawing materials (see figure 1), which shows a structural diagram of the proposed control system for aircraft equipment.

The implementation of the invention

The control system for general aircraft equipment, the structural diagram of which is shown in Fig. 1, contains control panels (2) with controls made with the ability to control the flight crew, general aircraft (3) equipment and the information exchange system (4) connecting it to the controls containing the first primary (7), first backup (8), second primary (9) and second backup (10) communication channels that are laid in different ways in the aircraft, and the control system for general aircraft equipment also holds the first (11) and second (12) blocks of computers-concentrators, the first (13) and second (15) blocks of protection and switching of DC power supply lines, the first (14) and second (16) blocks of protection and switching of AC power lines connected directly to general aircraft equipment (3), and to the first block (11) of the hub calculator - using the first communication channel (5), the second block (15) of protection and switching of DC power supply lines (БЗК1-Р) and the second block ( 16) protection and switching of AC power lines (B ЗК2-Р), connected directly to general aircraft equipment (3), and to the second block (12) of computer-hubs - using the second communication channel (6), as well as the first signal conversion unit (17) (БПС1-0), connected to general aircraft equipment (3) directly, and to the first block (11) of computer-hubs using the first communication channel (5), the second signal conversion unit (18) (BPS2-R) connected directly to general aircraft equipment (3), and to the second block (12) of calculators-hubs - using the second to anal (6) connection.

The structure of general aircraft equipment (3) includes (not shown in Fig.):

- control system for cleaning and releasing the chassis;

- hydraulic system;

- oxygen system;

- neutral gas system;

- integrated air conditioning system;

- monitoring system of temperature and pressure of wheels;

- emergency rescue equipment system;

- system of water supply and utilization of waste products;

- a system for monitoring the position of doors and hatches;

- system of household and kitchen equipment;

- Aircraft glazing heating system;

- anti-icing system.

The proposed control system for general aircraft equipment allows the control, monitoring and diagnostics of the state of general aircraft equipment (3) during ground monitoring, verification and preparation for flight with a high degree of completeness, reliability and reliability.

The claimed control system for aircraft equipment provides the following functions:

- automatic control of interfaced systems of the aircraft at all stages of flight; collecting information from interfaced systems, sensors and actuators;

- processing streams of collected data to ensure the operation of interfaced systems; remote direct control of aircraft systems from the controls on the integrated ceiling pilot control panel;

- flight and ground control of the technical condition of general aircraft systems;

- visualization of the state of interfaced systems and equipment on multifunctional indicators and annunciators of control panels;

- organization of the alarm loop.

The first (11) and second (12) blocks of computers-hubs, which are part of the proposed control system for general aircraft equipment, perform the following functions:

- information exchange in accordance with the requirements of current standards and technical regulations;

- reception from the interfaced equipment of input one-time commands of the first and second levels;

- self-control;

- logical processing of information;

- control of supply voltage of the unit;

- current control unit health;

- formation of the current state of the block.

The first (17) and second (18) signal conversion blocks provide:

- reception of all analog and discrete signals;

- primary processing of these signals and the issuance of the first primary (7), first backup (8), second primary (9) and second backup (10) communication channels of the corresponding communication channels (5), (6) information exchange network (4) ;

- power sensors avionics systems of the aircraft;

- control of supply voltage of the unit;

- current control unit health;

- formation of the current state of the block.

The first (13) and second (15) blocks of protection and switching of DC power lines in the version with a voltage of 27 volts carry out the following functions:

- receiving information on the first (5) and second (6) communication channels, as well as five discrete direct control signals coming from the control panel (2) with control means, which in the embodiment of the claimed system can be made in the form of an integrated ceiling panel ( Gearbox);

- self-control;

- the formation of management teams executive mechanisms of aircraft systems,

- "echo control" of control commands and protection of the output power circuits of the unit from overloads,

- control of supply voltage of the unit,

- current control unit health,

- formation of the current state of the block.

The first (14) and second (16) blocks of protection and switching of AC power lines in an embodiment with a voltage of 115 Volts carry out:

- receiving information on the first primary (7), first backup (8), second primary (9) and second backup (10) communication channels;

- reception of discrete direct control signals from the upper control panel of pilots;

- self-control;

- the formation of management teams executive mechanisms of aircraft systems;

- “echo control” of control commands and protection of the output power circuits of the unit from overloads;

- control of supply voltage of the unit;

- current control unit health;

- formation of the current state of the block.

All units included in the declared control system for general aircraft equipment are developed using multiprocessor tools that provide high performance and functional division of tasks: digital signal processing, execution of control algorithms for parametric information, execution of reconfiguration algorithms for the control system to minimize the consequences of failure, formation management teams, assessment of their own performance without the use of ground control full-time equipment.

Each unit included in the declared control system for general aircraft equipment consists of two functionally independent modules - the main and backup.

Improving the suitability of the aircraft with this control system for general aircraft equipment compared to the prototype is achieved by introducing the first (17) and second (18) signal conversion units.

Blocks BPS1-O (17) and BPS2-R (18) make it possible to determine in real time the compliance of general aircraft equipment (3) with the requirements of operational monitoring of operability and regular functioning at all stages of flight, as well as the fulfillment of requirements for processing and accumulating flight diagnostic information for its subsequent use on the ground and forecasting.

Improving the reliability of an aircraft with such a control system for general aircraft equipment is achieved through the implementation of a fourfold redundancy scheme for all units of the system.

The quadruple redundancy scheme is implemented by double redundancy at the level of the first and second blocks of calculators, hubs, the first and second blocks of protection and switching of DC power lines, the first and second blocks of protection and switching of AC power lines, the first and second signal conversion blocks, in which in turn, there is the first - the main unit and the second - the backup unit.

Thus, the first (11) and second (12) blocks of calculators, hubs, the first (13) and second (15) blocks of protection and switching of DC power lines, the first (14) and second (16) blocks of protection and switching of power lines alternating current, as well as the first (17) and second (18) signal conversion units are respectively the main and backup units of the claimed control system for general aircraft equipment.

In addition, in order to ensure the required level of reliability, double reservation was made in each of the indicated blocks at the level of modules (channels) due to the introduction of two integrated functionally and technically identical pairs of modules (main channels and redundant channels).

Industrial applicability

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

All hardware and software that support their work, the use of which is provided for by the invention, are developed and produced by both domestic industrial enterprises and leading companies of 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 for general aircraft equipment and aircraft systems, standard, standard industrial equipment, known materials and components can be used.

Claims (4)

1. The control system of aircraft equipment, containing
control panel with controls for the flight crew,
general aircraft equipment, and
the first and second blocks of calculators, hubs,
information exchange system that provides data exchange between general aircraft equipment and the control panel via the first and second communication channels,
characterized in that
the first communication channel contains a first primary and first backup communication channels, and the second communication channel contains a second primary and backup communication channels, the system also comprising
the first and second signal conversion blocks, the information inputs-outputs of which are connected respectively to the first and second information input-output of general aircraft equipment,
the first and second blocks of protection and switching of DC power supply lines, the outputs of which are connected respectively to the first and second DC power supply input of general aircraft equipment,
the first and second protection and switching units of AC power lines, the outputs of which are connected respectively to the first and second AC power input of general aircraft equipment,
each of these blocks contains the main and backup modules,
the interface of the main and backup modules of the first block of calculators, hubs, the first signal conversion unit, the first protection and switching unit of the DC power lines, the first protection and switching unit of the AC power lines are connected respectively to the first main and first backup data exchange channel, and the interface of the main and backup modules of the second block of calculators-hubs, the second block of signal conversion, the second block of protection and switching iny DC power, and the second unit protection switching AC power lines - to the second base and the second backup channel of information exchange respectively. 2. The system according to claim 1, in which the main and backup modules of the first and second blocks of calculators, hubs, the first and second blocks of protection and switching of DC power supply lines, the first and second blocks of protection and switching of AC power lines, and the first and second signal conversion units are respectively identical. 3. The system according to claim 1, in which the control panel with controls is made in the form of an integrated ceiling control panel. 4. The system according to claim 1, in which the primary and secondary first and primary and secondary second communication channels of the information exchange system are bidirectional multiplex channels that comply with the ARINC-825 specification.