RU2592467C1 - Device for control of technical state of engine unit (variants) - Google Patents

Abstract

FIELD: control device.

SUBSTANCE: group of inventions relates to devices for monitoring technical state of an engine unit. Device to control the technical state of a engine unit comprises a module for processing and analysing data, recorder to record parameters and diagnostic data, module to document and display data, module of interfaces, module of controlling and changing software, connected in a certain manner through a network of controllers and made with possibility of connection to aircraft systems and equipment.

EFFECT: to control technical state of an engine unit with capability to foresee the level of reliability of its parts and assemblies, control of development of defects (faults) before they achieve the degree of maximum danger.

13 cl, 6 dwg

Description

FIELD OF THE INVENTION

The invention relates to the field of aircraft instrumentation, and in particular to devices for monitoring the technical condition of an aircraft power plant, collecting and diagnosing the state of an aircraft power plant to ensure operation of a power plant with predetermined functions and characteristics.

State of the art

The power plant of the aircraft is a combination of an aircraft engine, systems and devices of the aircraft and provides the necessary thrust for the flight.

Modern aircraft are equipped with systems that collect, process and analyze information received from aircraft systems and equipment with a wide variety of sensors and signaling devices. Such systems are a complex of computing devices interconnected via a data network.

Known on-board maintenance system (WO 96/41260 A1, IPC G06F 9/45, publ. 12/19/1996) containing an information exchange channel that meets the ARINC-429 specification and provides data exchange between the aircraft’s built-in monitoring systems (VSC) and the computer airborne maintenance system. The known system also comprises a display, a printer, an address reporting system for aviation communications, a data loader and a flight information recorder. A significant drawback of such a system is the use of only one data bus in accordance with the ARINC-429 specification in a switched on-board communications network of an aircraft, which leads to a limitation of controlability and, as a result, to a decrease in flight reliability and safety.

A comprehensive system for diagnosing and presenting information about the state of various aircraft systems is known (US 2012260180 A1, IPC G06F 15/16, published 11.10.2012), containing various data processing and analysis devices connected to a data transmission network, configured to receive information and its subsequent transmission to the network analyzer. The disadvantages of this known system include the difficulty in using it to control aircraft systems directly in flight.

The closest analogue of the invention is a flight information processing system (patent for invention RU 2169394 C1, IPC G09B 9/08, publ. 06/20/2001), comprising an information processing unit, a display, a keyboard, a removable storage device, an information receiving device, analog-digital transducer and generator of acoustic signals. The system provides processing of parametric information accumulated by the on-board recording device using the appropriate software and reflects the processing results on the display screen. The operating mode of the system is set by the operator using the keyboard, and the accumulation and storage of information is carried out on a removable drive.

The disadvantages of the closest analogue include the limited amount of memory, low speed and the impossibility of parallel solving many information and computing problems to determine the status of systems and equipment of the aircraft and control the activities of the crew in flight.

SUMMARY OF THE INVENTION

The problem solved by the invention is the creation of a device for monitoring the technical condition of the power plant, providing the ability to control the technical condition of many aircraft systems and equipment and signaling their wear and tear when parameters go beyond a given range.

Another problem solved by the invention is the creation of a device for monitoring the technical condition of the power plant with increased reliability of the control results.

The tasks are solved by the proposed device for monitoring the technical condition of the power plant, containing a data processing and analysis module, a parameter and diagnostic data recorder, which according to the invention further comprises a data documenting and display module, an interface module, a software control and change module, software, the data processing and analysis module is configured to connect to aircraft systems and equipment, each of these modules and reg the parameters and diagnostic data tracer are connected to the controller network, while the first input and the second output of the data processing and analysis module are connected respectively to the first output and the third input of the software control and change module, the second input of the data processing and analysis module is connected to the second output of the interface module and the first output of the data processing and analysis module is connected to the first input of the parameter and diagnostic data logger, the second input and second output of which are connected to the first output and the four the first input and the third outputs of the parameter and diagnostic data logger are connected respectively to the third output and the second input of the interface module, and the first output of the parameter and diagnostic data logger is connected to the first input of the data documentation and display module, the second input and the second output of which is connected respectively with the third output and the second input of the module for monitoring and changing software, and the first output and third input of the module for documenting and displaying data s are connected respectively with the first input and the fourth output of the interface module, the third input and the first output of which are connected respectively with the second output and the first input of the software control and measurement module.

The technical result of the proposed device for monitoring the technical condition of the power plant is to ensure the operation of engines with a forecast of the level of reliability, namely the operation of parts and assemblies with the control of the development of defects (damage) in operating time until they reach an extremely dangerous degree of development.

Also, another technical result of the invention is to reduce the complexity of the maintenance of the power plant.

Another technical result of the invention is to reduce the maintenance time of the power plant in terms of assessing its technical condition.

In addition, another technical result of the invention is to increase the overhaul life of engines during operation.

In addition, another technical result of the invention is to increase the engine operating time for shutdown in flight.

These technical results are achieved by the fact that in the device for monitoring the technical condition of the power plant, which contains a data processing and analysis module, a parameter and diagnostic data recorder, an additional module for documenting and displaying data, an interface module, and a software change and control module are added this data processing and analysis module is configured to connect to aircraft systems and equipment, and each of these modules is connected to the control network er, while the first input and second output of the data processing and analysis module are connected respectively to the first output and third input of the software control and change module, the second input of the data processing and analysis module is connected to the second output of the interface module, and the first output of the data processing and analysis module connected to the first input of the parameter and diagnostic data logger, the second input and second output of which are connected respectively to the first output and fourth input of the software control and change module, and the third input and third outputs the parameter and diagnostic data logger are connected respectively to the third output and the second input of the interface module, the first output of the parameter and diagnostic data recorder is connected to the first input of the documentation and data display module, the second input and second output of which are connected respectively to the third output and the second input of the control module and software changes, and the first output and third input of the documentation and data display module are connected respectively to the first input and fourth output of the module interfaces, the third input and the first output of which are connected respectively with the second output and the first input of the software control and measurement module.

Technical results are achieved through the implementation of neural network algorithms for predicting the occurrence of failures at an early stage of their development, transferring the processing of flight information processing and analysis functions from ground-based control devices to the on-board device, and implementing the upper level of information exchange control between interacting modules in terms of collection, ranking and long-term storage parameters and diagnostic data, the ability to transmit information to ground power station service centers ovki, the open structure of the hardware and software with the ability to adapt to diagnose and base of these algorithms to the specific operating conditions, the possibility of connecting and disconnecting any functional hardware and software included in the service system, from the system without disrupting service system as a whole.

In an embodiment of the invention, the data processing and analysis module comprises a power supply module, an analogue input information module, a discrete interface module, an input information module and a processor module, wherein the power supply module is connected to an airplane power supply system (SES), the analogue input information module, and the discrete interface module and the discrete interface module is connected to signaling devices, as well as to the processor module by means of a data bus, while the input information module is connected It is connected with devices of aircraft systems and equipment via a serial data exchange channel, the input information module is also connected to the analog input information module and the processor module using the data bus, the processor module being configured to connect to the parameter and diagnostic data recorder, to the monitoring module and software and interface module changes using a network of controllers.

Also in another embodiment of the invention, the input analog information module comprises interconnected sensor power supply, a sensor interface device and an analog-to-digital converter, while a sensor power supply device is connected to a power supply module, a sensor interface device is connected to sensors, and an analog-digital the converter is connected to the input information module via a data bus.

In another embodiment of the claimed invention, the parameter and diagnostic data recorder comprises a power supply module, an input information module, a processor module, a data transmission module and a data recording module, wherein the power supply module is connected to the aircraft power supply system and to the processor module, the processor module being connected to the module input information, a data transmission module and a data recording module via a data bus.

In yet another embodiment of the invention, the input information module is configured to connect to a data processing and analysis module, an interface module and a software control and change module through a network of controllers, and the data transmission module is configured to connect to a data documenting and display module, an interface module and software control and measurement module through a network of controllers.

Also, in another embodiment of the invention, the data recording module includes a recorder and a removable recording device.

In another embodiment of the invention, the data documentation and display module comprises a power supply module and a processor module interconnected.

In the particular case of the invention, the processor module comprises a computing device and an input / output interface device interconnected via a data bus, the computing device being connected to a power supply module, and the input / output interface device configured to connect to a printing device, a display device and on-board electronic equipment of the aircraft, as well as with the ability to connect to the registrar of parameters and diagnostic data, interface module and module monitoring and changing software using a network of controllers.

In yet another particular embodiment of the invention, the interface module comprises a power supply module and a calculation module and interfaces interconnected, wherein the power supply module is connected to an aircraft power supply system.

Also, in another embodiment of the invention, the calculation and interface module comprises a calculation device, an input / output interface device and a communication device interconnected via a data bus, the calculation device connected to a power supply module, the communication device connected to a power service center installations via a two-wire data bus, and the input / output interface device is connected to the control device, the on-board electronics of the aircraft, as well as to the processing and analysis module a data recorder parameters and diagnostic data, document data and display module, the control module and change software through a network controllers.

Brief Description of the Drawings

The invention is illustrated by the following drawings:

FIG. 1 is a structural diagram of a device for monitoring the technical condition of a power plant;

FIG. 2 is a structural diagram of a data processing and analysis module of a device for monitoring the technical condition of a power plant;

FIG. 3 is a structural diagram of a recorder of parameters and diagnostic data of a device for monitoring the technical condition of a power plant;

FIG. 4 is a block diagram of a module for documenting and displaying data of a device for monitoring the technical condition of a power plant;

FIG. 5 is a block diagram of an interface module of a power plant technical condition monitoring device;

FIG. 6 is a structural diagram of a module for monitoring and changing software (software) of a device for monitoring the technical condition of a power plant.

In the drawings, the positions indicate the following modules of the proposed device for monitoring the technical condition of the power plant.

The device for monitoring the technical condition of the power plant (see Fig. 1) contains a module (1) for processing and analyzing data; data logger (2) of parameters and diagnostic data; module (3) for documenting and displaying data; module (4) interfaces; module (5) for monitoring and changing software.

The data processing and analysis module (1) (see FIG. 2) comprises a power supply module (11); module (12) input analog information; module (13) of discrete interfaces; input information module (14); processor module (15); device (16) power sensors; device (17) sensor interfaces; analog-to-digital converter (18).

The registrar (2) of parameters and diagnostic data (see Fig. 3) contains a power supply module (21); input information module (22); processor module (23); data transmission module (24); a data recording module (25); registrar (26); interchangeable recording device (27).

The module (3) for documenting and displaying data (see Fig. 4) comprises a power supply module (31); processor module (32); computing device (33); input / output interface device (34).

An interface module (4) (see FIG. 5) comprises a power supply module (41); module (42) computing and interfaces; a calculation device (43); input / output interface device (44); communication device (45).

The software control and change module (5) (FIG. 6) comprises a power supply module (51) and a calculation, control and interface module (52); computing device (53); a reader (54); device (55) for reading and processing data; an input / output interface device (56).

Disclosure of invention

The proposed device for monitoring the technical condition of the power plant includes (see Fig. 1) a module (1) for processing and analyzing data, a recorder (2) for parameters and diagnostic data, a module (3) for documenting and displaying data, an module (4) for interfaces, software control and change module (5) connected via a network of controllers as follows: the first input and second output of the data processing and analysis module (1) are connected respectively to the first output and third input of software control and change module (5), the second input of the module ( 1) ki and data analysis is connected to the second output of the interface module (4), the first output of the data processing and analysis module (1) is connected to the first input of the registrar (2) of parameters and diagnostic data, the second input and second output of the registrar (2) of parameters and diagnostic data connected respectively to the first output and fourth input of the module (5) for monitoring and changing software, the third input and third outputs of the recorder (2) of parameters and diagnostic data are connected respectively to the third output and second input of the module (4) interfaces, the first the course of the recorder (2) of parameters and diagnostic data is connected to the first input of the module (3) for documenting and displaying data, the second input and second output of the module (3) for documenting and displaying data are connected respectively with the third output and second input of the module (5) for monitoring and changing The software, the first output and the third input of the data documentation and display module (3) are connected respectively to the first input and the fourth output of the interface module (4), the third input and the first output of the interface module (4) are connected to the second Exit and the first input of the module (5) monitoring and measurement software.

The data processing and analysis module (1) (see Fig. 2) is intended, in particular, for receiving signals from sensors, signaling devices and devices of the following aircraft systems and equipment (not shown in the drawing):

- from the electronic-digital engine control system (FADEC) of the propulsion system;

- from the power distributor marching power plant;

- from the electronic-digital engine control system (FADEC) of the auxiliary power unit;

- from the computer control system and fuel measurement;

- from the computer fire protection system;

- from the computer calculator control system of aircraft equipment (SUOSO);

- from a computer calculator on-board electronic equipment.

These aircraft systems and equipment are connected to the data processing and analysis module (1) through a serial data exchange channel. In an embodiment of the invention, said serial communication channel conforms to the ARINC-429 specification.

In addition, the data processing and analysis module (1) is also connected to sensors and signaling devices of the power plant and the aircraft (not shown in FIG.), From which signals about the measured parameters and condition of the product are sent to the data processing and analysis module (1).

The data processing and analysis module (1) contains (see FIG. 2) a power supply module (11), analog input information module (12), discrete interface module (13), input information module (14) and a processor module (15). The power supply module (11) is connected to the aircraft power supply system (SES), the analog input information module (12) and the discrete interface module (13), which, in turn, is connected to the said signaling devices. The discrete interface module (13) is connected to the processor module (15) via a data bus. The input information module (14) is connected to devices of aircraft systems and equipment via a serial information exchange channel (not shown in the drawing). The input information module (14) is connected to the analog input information module (12) and the processor module (15) using a data bus. The signal from the processor module (15) through a network of controllers is fed to the parameter and diagnostic data logger (2), to the software control and change module (5), and to the interface module (4).

The power supply module (11) is connected to the aircraft power supply system and protects the analog input module (12), discrete interface module (13), and the processor module (15) from overvoltage received from the aircraft power supply system (SES). The power supply module (11) can be implemented on the basis of a device generating a reference voltage and current level for the operation of the analog input information module (12), discrete interface module (13) and the processor module (15).

The analogue input information module (12) comprises interconnected sensor power supply device (16), sensor interface device (17) and an analog-to-digital converter (18). The sensor power supply device (16) is connected to the power supply module (11). The device (17) of the sensor interfaces is connected to the sensors, and the analog-to-digital converter (18) is connected to the input information module using the data bus.

The input analog information module (12) provides an interface with all sensors and converts the physical signals from the sensors into a voltage value, which is read by the processor. The sensor power supply device (16) can be implemented on the basis of standard reference voltage and current sources, etc.

The device (17) of the sensor interfaces provides an interface with the sensors of frequency, resistance, etc. and verifies the characteristics of the interfaces with these sensors. The device (17) of the sensor interfaces can be implemented on the basis of standard devices that provide an interface with sensors of frequency, resistance, etc.

An analog-to-digital converter (18) provides signal processing and data collection from device (17) in various frequency ranges. An analog-to-digital converter (18) can be implemented on the basis of standard electronic devices, the characteristics of which provide signal processing and data collection.

The module (13) of discrete interfaces can be implemented on the basis of standard devices, including electronic ones, which by means of hardware provide switching of various types of input signals, for example, the presence of voltage / open, etc., which are read and controlled by the processor module (15) .

The input information module (14) provides reception and validation of the received information from aircraft systems and equipment, as well as the interface with the processor module (15). The input information module (14) can be implemented on the basis of standard ARINC receivers (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.).

The processor module (15) provides computational functions and the function of checking devices included in the data processing and analysis module (1), as well as interacting with the discrete interface module (13), the interface module (4), and the program control and change module (5) providing. The processor module (15) can be implemented on the basis of a standard multifunctional processor using external and internal memory.

The registrar (2) of parameters and diagnostic data contains (see Fig. 3) a power supply module (21), an input information module (22), a processor module (23), a data transmission module (24) and a data recording module (25). The power supply module (21) is connected to the aircraft power supply system and to the processor module (23). The processor module (23) is connected to the input information module (22), the data transmission module (24) and the data recording module (25) via the data bus. The input information module (22) is connected to the data processing and analysis module (1), the interface module (4) and the software control and change module (5) through a network of controllers. The data transmission module (24) is connected to the data recording and display module (3), the interface module (4) and the software control and measurement module (5) via the controller network.

The registrar (2) of parameters and diagnostic data can be implemented on the basis of a single-board computer with a memory capacity of at least 10 GB, a recording speed of at least 30 frames per second for 1024 parameters and signals.

The power supply module (21) provides protection for the processor module (23) from surges of voltage received from the SES of the aircraft. The power supply module (21) can be implemented on the basis of a standard device that generates a reference level of voltage and current for the operation of the processor module (23).

Input information module (22) includes an interface with data processing and analysis module (1), interfaces module (4) and software change and control module (5) and provides reception and verification of received information from data processing and analysis module (1), module (4) interfaces and module (5) for monitoring and changing software. The input information module (22) can be implemented on the basis of standard ARINC or CAN receivers (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.).

The processor module (23) provides the functions of calculating and verifying the devices included in the parameters and diagnostic data logger (2), and also interacts with the data transmission module (24) and the data recording module (25). The processor module (23) can be implemented on the basis of a standard multifunction processor, which can use external and internal memory, including non-volatile memory.

The data transmission module (24) is equipped with an interface with a data documentation and display module (3), interfaces module (4) and software change and control module (5) and provides reception and transmission of signals from the registrar (2) of parameters and diagnostic data to the module ( 3) documentation and display of data, interface module (4) and software control and change module (5). The data transmission module (24) can be implemented on the basis of standard ARINC or CAN transmitters (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.).

The data recording module (25) includes a recorder (26) and a removable recording device (27). The recorded information is a standard frame, the registration frequency of a standard frame is 2-4 Hz. The frame contains parametric, signaling information and information about failures and malfunctions, accompanied by service information.

The beginning and end of recording information in the module (25) for recording data and non-volatile memory of the processor module (23) is determined automatically based on the analysis of several input parameters (discrete signals). The totality of such signals can include engine operation signals, separation signal, etc.

Registrar (26) can be implemented on the basis of a standard solid-state device with a capacity of at least 10 GB.

Replaceable recording device (27) can be implemented, for example, in the form of a flash card in the PCMCIA standard with a capacity of at least 12 GB.

The module (3) for documenting and displaying data (see Fig. 4) contains interconnected power module (31) and processor module (32).

The module (3) for documenting and displaying data provides functions for documenting and displaying data. The module (3) for documenting and displaying data can be implemented on the basis of a single-board computer.

The processor module (32) comprises a calculation device (33) and an input / output interface device (34) interconnected via a data bus. The calculation device (33) is also connected to the power supply module (31). The input / output interface device (34) is configured to connect and exchange signals with a printing device, a display device and on-board electronic equipment of the aircraft, as well as with the ability to exchange signals with a registrar (2) of parameters and diagnostic data, an interface module (4) and a module (5) monitoring and changing software using a network of controllers.

The processor module (32) provides the necessary calculations, information storage, and an interface with a registrar (2) of parameters and diagnostic data, an interface module (4), a software control and change module (5), a printing device, a display device, and aircraft electronic equipment.

The computing device (33) provides the functions of computing, checking devices included in the module (3) for documenting and displaying data, creating and storing an electronic data library, and interacting with the input / output interface device (34). The computing device (33) can be implemented on the basis of a standard processor, which can use external and internal memory, including non-volatile.

The input / output interface device (34) has an interface with a registrar (2) of parameters and diagnostic data, an interface module (4) and a software control and change module (5), as well as on-board electronic equipment of the aircraft, a printing device, and a display device (on not shown). The input / output interface device (34) provides reception and validation of the received information, transmission of generalized diagnostic information, including in the form of special frames formed by commands from the interface module (4). The input / output interface device (34) can be implemented on the basis of standard ARINC or CAN receivers / transmitters (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.).

The interface module (4) (see FIG. 5) contains a power supply module (41), a calculation module (42) and interfaces interconnected. The power supply module (41) is connected to the aircraft power supply system.

Interface module (4) can be implemented on the basis of a standard multi-function single-board computer.

The power supply module (41) protects the calculation module (42) and interfaces against over-voltage received from the SES of the aircraft. The power supply module (41) can be implemented on the basis of a standard device generating a reference voltage and current level for operation.

The calculation and interface module (42) comprises a calculation device (43), an input / output interface device (44) and a communication device (45) interconnected via a data bus. The calculation device (43) is connected to the power supply module (41). The communication device (45) is connected to the power plant service center via a two-wire data bus. The input / output interface device (44) is connected to the control device, as well as to the data processing and analysis module (1), the parameter and diagnostic data recorder (2), the data recording and display module (3), the control and change module (5) Software using a network of controllers.

The calculation device (43) provides the functions of computing, checking devices included in the interface module (4), and also generates commands according to predetermined algorithms and interacts with the input / output interface device (44) and the communication device (45). The computing device (43) can be implemented on the basis of a standard processor, which can use external and internal memory, including non-volatile memory.

The input / output interface device (44) provides reception and validation of the received information, information transfer, including in the form of special frames formed by the registrar (2) of parameters and diagnostic data and the module (3) for documenting and displaying data, and also provides an interface with a module (1) for processing and analyzing data, a registrar (2) for parameters and diagnostic data, a module (3) for documenting and displaying data, a module (5) for monitoring and changing software, and also with on-board electronic equipment flight and module control device (4). The input / output interface device (44) can be implemented on the basis of standard ARINC or CAN receivers / transmitters (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.) with RS type ports .

The communication device (45) provides the reception and transmission of information in flight to the ground, including in the form of special frames formed upon request from the power plant service center, or on command from the aircraft’s on-board electronic equipment, or manually by the crew. Also, the communication device (45) provides an interface with the power plant service center. The communication device (45) can be implemented on the basis of standard network receivers / transmitters.

The software control and change module (5) contains (see FIG. 6) a power supply module (51) and a calculation, control and interface module (52) interconnected. The power supply module (51) is connected to the aircraft power supply system (SES).

The power supply module (51) provides protection for the calculation, control and interface module (52) against over-voltage received from the SES of the aircraft. The power supply module (51) can be implemented on the basis of a standard device that generates a reference level of voltage and current for operation.

The calculation, control and interface module (52) comprises a calculation device (53), a reader (54), a data reader and processor (55), and an input / output interface device (56) interconnected by a data bus. The calculation device (53) is connected to the power supply module (51). The reader (54) is connected to a software loader. A device (55) for reading and processing data is connected to emergency reading and a data loader. The input / output interface device (56) is connected to the data processing and analysis module (1), parameters and diagnostic data recorder (2), data documentation and display module (3) and interfaces module (4) using a network of controllers.

The calculation, control and interface module (52) provides the necessary calculations, information storage, algorithmic operations and an interface with a data processing and analysis module (1), a parameter and diagnostic data recorder (2), data recording and display module (3) and a module ( 4) interfaces, a software loader, a data loader and an emergency reading device, made, for example, on the basis of standard ARINK receivers (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circu its and others).

The calculation device (53) provides functions for calculating, checking devices included in the software control and change module (5) and monitoring the status (failure / serviceability / limited use) of the data processing and analysis module (1), the data logger (2), and diagnostic data, module (3) for documenting and displaying data and module (4) for interfaces. The calculation device (53) also provides the formation of control commands and decision-making about the settings and changes of the control device of the technical condition of the power plant. Also, the calculation device (53) automatically detects failures and malfunctions according to specified algorithms, system and neural network programs, as well as interacts with a reader (54), a device for reading and processing data, and an input / output interface device (56). The calculation device (53) can be implemented on the basis of a standard processor, which can use external and internal memory, including non-volatile memory.

The reader (54) provides reception and validation of the received information, and information transfer to the calculation device (53), as well as the network interface with the calculation device (53). The reader (54) can be implemented on the basis of standard ARINC or CAN receivers (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.) having an RS-type port.

The device (55) for reading and processing data provides reception and verification of the reliability of the information received and information transfer to the calculation device (53), as well as the network interface with the calculation device (53). The device (55) for reading and processing data can be implemented on the basis of standard ARINC or CAN receivers (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.) having an RS-type port.

The input / output interface device (56) provides reception and verification of the received information, information transfer to the data processing and analysis module (1), data and diagnostic data recorder (2), data documentation and display module (3) and module (4) interfaces, as well as a network interface with a module (1) for processing and analyzing data, a registrar (2) of parameters and diagnostic data, a module (3) for documenting and displaying data, and a module (4) for interfaces. The input / output interface device (56) can be implemented on the basis of standard CAN receivers / transmitters (for example, devices from Device Engineering Inc.), Everspin, MICROCHIP TECHNOLOGY, POWERSMART, Holt Integrated Circuits, etc.).

The device for monitoring the technical condition of the power plant operates as follows.

Service information (for example, passport data of units, attributes of repair and periodic maintenance, etc.) is transferred to the interface module (4) from the power plant service center.

The module (5) for monitoring and changing software from the software loader receives information about the settings and changes in the software and the mathematical model of the main engine and auxiliary engine.

The interface module (4) and the software change and control module (5) evaluate the reliability of the information received, analyze the need to transmit updated data, and after receiving a “yes” receipt, transfer data to the data processing and analysis module (1).

The software control and change module (5), in parallel with the functions described above, carries out self-monitoring and status monitoring (failure / serviceability / limited use) of the data processing and analysis module (1), data logger (2) of parameters and diagnostic data, documentation and (3) documentation and data mapping, interface module (4), automatically locates failures and malfunctions of the power plant, as well as its systems, units and nodes, and transfers this information to the data documentation and display module (3). These actions are provided by system programs that provide self-monitoring of operability and diagnostics of the device for monitoring the technical condition of the power plant, as well as neural network programs for training and recognition of defects and malfunctions at an early stage of their development.

The data processing and analysis module (1) receives information from the following aircraft systems and equipment:

- an electronic-digital engine control system (FADEC) of the marching power plant, from which information on the state, control and monitoring of the marching power plant, necessary for assessing the technical condition of the marching power plant, is received to the data processing and analysis module (1), as well as information about dangerous deviations of parameters from normative levels and fixed failures;

- the monitoring and diagnostic unit (MDU) of the propulsion system (N), from which the information necessary for assessing the technical condition of the engine, finding the place of failure, diagnostic information about the propulsion system as a whole and about its individual products;

- an electronic-digital engine control system (FADEC) of the auxiliary power unit, from which current information on the state, control and monitoring of the auxiliary engine, as well as information necessary for assessing its technical condition and finding a place, is supplied to the data processing and analysis module (1) failure, information about dangerous deviations of parameters from standard levels and recorded failures, diagnostic information about the auxiliary engine as a whole and individual engine products;

- a calculator of the fuel control and measurement system, from which current information about the state of the fuel system and the fuel control and measurement system, as well as information necessary for assessing the technical condition of the fuel system and the fuel control and measurement system, is supplied to the data processing and analysis module (1) , the search for the place of failure, as well as information about dangerous deviations of parameters from standard levels and recorded failures, diagnostic information about the fuel system as a whole and individual fuel products th system;

- a fire protection system calculator, from which current information about the state of the fire protection system, as well as information necessary to assess its technical condition, search for the place of failure, information about dangerous deviations of parameters from standard levels, and into the data processing and analysis module (1) are received fixed failures, diagnostic information about the fire protection system as a whole and individual products of the fire protection system;

- a calculator for the control system for general aircraft equipment, from which information on the state of the fuel system, fire protection system, propulsion system, auxiliary power unit and neutral gas system (LPG), information on recorded failures, diagnostic is received in the data processing and analysis module (1) information about the fuel system, fire protection system, marching power plant, auxiliary power plant and the CIS, information from aircraft systems (for example, air signal systems, and in pilot, landing gear, etc.), necessary for the implementation of the control and monitoring functions of the fuel system, fire protection system, main propulsion system, auxiliary power unit;

- an on-board electronic equipment calculator, from which current information about flight parameters and operation of the on-board electronic equipment (for example, power supply systems, consoles, etc.) is received by the data processing and analysis module (1), which is necessary for the control, monitoring and diagnosing the state of the fuel system, fire protection system, marching power plant, auxiliary power plant.

The data processing and analysis module (1) receives received information and monitors the reliability of this information.

According to neural network algorithms, using the analysis of the tendency to change generalized diagnostic features, the module (1) for processing and analyzing data performs:

- a generalized analysis of the current technical condition of the power plant and the possibility of its further operation;

- prediction of the pre-failure condition of engine parts and assemblies, power plant products, including those caused by accidental defects;

- evaluates the production and predicts the residual resources of the main engine parts, taking into account low-cycle and multi-cycle damage in real operating conditions;

- the forecast of deterioration of the traction and flow characteristics of engines in the process of long running hours;

- development of recommendations for unscheduled flushing of the gas-air tract of engines;

- automatic localization of failures and malfunctions of the power plant, as well as its systems, units and components;

- development of recommendations and instructions for further actions in case of detected malfunctions and / or deviations of the characteristics of the power plant (for example, additional diagnostics of the technical condition on the ground using non-destructive testing methods and means or the need for repair work) according to the algorithms specified by the developers of the aircraft and products.

Diagnostic information from the module (1) for processing and analyzing data is transmitted to the registrar (2) of parameters and diagnostic data, where, in accordance with the information received from the module (4) of the interfaces, the generalized diagnostic information is generated, structured, ranked and stored in the diagnostic database data using algorithms with advanced functions of intelligent archiving and search for output data.

Information from the registrar (2) of parameters and diagnostic data is fed to the module (3) for documenting and displaying data, in which electronic documentation of generalized diagnostic information is carried out and information is prepared for visualization of data on the emergency state of the power plant, as well as data on the self-monitoring of the power condition monitoring device installation.

Generalized diagnostic data and / or temporary “slices” with packed information about the technical condition of the power plant are transmitted from the interface module (4) to the power plant service center and to the aircraft electronic equipment. For this, the interface module (4) transmits a signal to the registrar (2) of parameters and diagnostic data, through which all the necessary information from the registrar (2) of parameters and diagnostic data is transmitted to the interface module (4). The structure and amount of information transmitted depends on the mode that defines the module (4) of the interfaces.

The interface module (4), on command from the service center and / or on-board electronic equipment of the aircraft, in addition to information packed into a standard file, transmits a file that contains a “slice” of information important for diagnostics, the list and contents of which are predetermined by the product developers.

The interface module (4), upon a command from the service center and / or on-board electronic equipment of the aircraft, can access information stored in the registrar (2) of parameters and diagnostic data, including for searching data in the diagnostic database.

From the module (3) for documenting and displaying data, information about the technical condition of the power plant, for example, about dangerous failures of the power plant products, and / or messages about the possibility of further operation of the power plant, with recommendations and instructions on further actions, for example, about additional diagnostics of the technical condition on the ground by methods and means of non-destructive testing or the need for repair work, is transmitted to the aircraft electronic equipment and / or to the printing stroystva and visualization tools. Information from the module (3) for documenting and displaying data is transmitted by commands to the module (4) interfaces. The interface module (4) generates these commands either by internal algorithms or by commands from the power plant service center and / or aircraft electronic equipment for printing and visualization.

On command from a ground-based device, which can be implemented on the basis of a standard multifunction processor, which will provide interaction with the software control and change module (5), emergency reading of stored diagnostic information is provided. For this, a command is sent from the module (5) for monitoring and changing software to the interface module (4) and the data processing and analysis module (1), by which the process of transmitting special diagnostic information from the data processing and analysis module (1) is started. Information is packed into a file.

The module (5) for monitoring and changing the software according to the information received from the software loader, adapts the software of the device for monitoring the technical condition of the power plant based on the operating experience of the power plant.

In modules (1), (2), (3), (4) and (5), which are part of the proposed device for monitoring the technical condition of the power plant, applied programs that implement all the functions in all operating modes, such as:

- system software that implements the exchange of data between the interacting modules that are part of the proposed device, providing, for example, a network interface CAN 2.0B or ARINC 604;

- system software that implements the physical exchange of information between the device (device modules) with interfaced systems and provides, for example, the exchange in accordance with GOST 18977-79 and RTM 1495 as amended. 3, with recommendations of ARINC 604, over CAN 2.0B network interface, with recommendations of ARINC 739, ARINC 717;

- system software that implements interaction with ground-based devices in accordance with ARINC-724 and the output of parametric and fault information to interfaced systems (Cellular, Wi-Fi, WiMAX, Satcom, ACARs);

- system software that implements interaction with ground-based devices, for example, via RS-422 and RS-485 and adapted with the MS Windows XP operating system;

- system programs that provide self-monitoring of health and diagnostics of the device modules and the device as a whole;

- programs for creating a database with advanced functions of intelligent archiving and searching for output data, as well as storing data in the device’s drive;

- programs that implement mathematical models of diagnosed engines to form generalized diagnostic features;

- neural network programs for recognition of defects and malfunctions at an early stage of their development;

- a program for evaluating and predicting the life of the main engine parts taking into account low-cycle and multi-cycle damage;

- Trend analysis programs for controlled parameters;

- diagnostic decision-making programs for a set of diagnostic features.

Application programs are developed for a specific object and are designed to solve various functional problems, taking into account the application conditions and characteristics of the object.

The work of application programs is based on the processing of interrupts for five IRQs (vectors, including timer interrupts). Interrupts from different devices can have different priorities, and priority can change dynamically. The number of priorities can be easily changed to almost any number depending on the tasks.

Programming can be built on the principles of object-oriented programming.

Utilities or system utilities that are used to perform auxiliary data processing or servicing device devices (diagnostics, hardware and software testing, optimizing disk space usage, restoring information destroyed on a magnetic disk, etc.), for example, Norton Utilities - company Symantec Checkit PRO Deliuxe 2.0 - Touch Stone; Reg Organizer; SpeedFan, utilities from Motorola et al.

The real-time operating system, under the control of which the operation of application and service programs is ensured, can be, for example, On Time RTOS-32 (RTTarget-32 and RTFiles-32 packages) of On Time Informatik (Germany). This operating system allows you to develop and debug software in high-level languages, for example, ADA95, C ++, etc.

The invention allows to reduce the complexity of maintenance of the power plant by 20-30%, reduce the time of maintenance of the power plant in terms of assessing its technical condition by 1.5-2 times, increase the overhaul life of engines during operation by 20-25% and increase the engine operating time by shutdown in flight by 50-70%.

Industrial applicability

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

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

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

Claims (13)

1. A device for monitoring the technical condition of the power plant, containing a data processing and analysis module, a parameter and diagnostic data recorder, characterized in that it further comprises a data documenting and display module, an interface module, a control and software change (software) module, the module data processing and analysis is made with the ability to connect to aircraft systems and equipment, with each of these modules and a registrar of parameters and diagnostic data connected nets to the controller network, in this case, the first input and second output of the data processing and analysis module are connected respectively to the first output and third input of the software control and change module, the second input of the data processing and analysis module is connected to the second output of the interface module, and the first output of the module data processing and analysis is connected to the first input of the parameter and diagnostic data logger, the second input and second output of which are connected respectively to the first output and fourth input of the software control and change module, and the third the input and the third output of the parameter and diagnostic data logger are connected respectively to the third output and the second input of the interface module, and the first output of the parameter and diagnostic data logger is connected to the first input of the data documentation and display module, the second input and second output of which are connected respectively to the third output and the second input of the software control and change module, and the first output and the third input of the data documentation and display module are connected respectively to the first input and the fourth fifth output interface module, the third input and a first output of which is connected respectively to the second output and the first input module control and measurement software. 2. The device according to p. 1, characterized in that the data processing and analysis module comprises a power supply module, an analogue input information module, discrete interface module, an input information module and a processor module, wherein the power supply module is connected to the aircraft power supply system (SES), the input analog information module and the discrete interface module, and the discrete interface module is connected to the signaling devices, as well as to the processor module via the data bus, while the input information module connected to devices of aircraft systems and equipment via a serial information exchange channel, the input information module is also connected to the analog input information module and the processor module using the data bus, the processor module being configured to connect to the parameter and diagnostic data recorder, to the monitoring module and software and interface module changes using a network of controllers. 3. The device according to p. 2, characterized in that the input analog information module contains a sensor power supply device, a sensor interface device and an analog-to-digital converter connected to each other, while the sensor power supply device is connected to the power supply module, the sensor interface device is connected to the sensors and the analog-to-digital converter is connected to the input information module using a data bus. 4. The device according to claim 1, characterized in that the parameter and diagnostic data recorder comprises a power supply module, an input information module, a processor module, a data transmission module and a data recording module, wherein the power supply module is connected to the aircraft power supply system and to the processor module, moreover, the processor module is connected to the input information module, the data transmission module and the data recording module via the data bus. 5. The device according to claim 4, characterized in that the input information module is configured to connect to a data processing and analysis module, an interface module and a software control and change module via a network of controllers, and the data transmission module is configured to connect to a documentation module and data display, interface module, and software monitoring and measurement module through a network of controllers. 6. The device according to claim 4, characterized in that the data recording module includes a registrar and a removable recording device. 7. The device according to claim 1, characterized in that the documenting and data display module comprises a power supply module and a processor module interconnected. 8. The device according to claim 7, characterized in that the processor module comprises a calculation device and an input / output interface device interconnected via a data bus, the calculation device is connected to a power supply module, and the input / output interface device is configured to connections with a printing device, a display device and avionics of the aircraft, as well as with the ability to connect with the registrar of parameters and diagnostic data, an interface module and a module for monitoring and changing software and through a network of controllers. 9. The device according to claim 1, characterized in that the interface module comprises a power supply module and a calculation module and interfaces interconnected, wherein the power supply module is connected to the aircraft power supply system. 10. The device according to claim 9, characterized in that the calculation and interface module comprises a calculation device, an input / output interface device and a communication device interconnected by a data bus, the calculation device being connected to a power supply module, the communication device being connected with the power plant service center via a two-wire data bus, and the input / output interface device is connected to the control device, aircraft avionics, as well as to the data processing and analysis module, the recorder ohms of parameters and diagnostic data, a module for documenting and displaying data, a module for monitoring and changing software using a network of controllers. 11. The device according to p. 1, characterized in that the module for monitoring and changing software contains a power module and a calculation, control and interface module interconnected, while the power module is connected to the aircraft power supply system. 12. The device according to p. 12, characterized in that the calculation, control and interface module comprises a calculation device, a reader, a data reading and processing device and an input / output interface device connected to each other by a data bus, the calculation device being connected to power supply module, the reader is connected to the software loader, the data reader and processor is connected to the emergency read and data loader, and the input / output interface device is connected to the data processing and analysis module, the registrar parameter and diagnostic data, document data module and display module and interface using network controllers. 13. A device for monitoring the technical condition of the power plant, containing a data processing and analysis module, a parameter and diagnostic data recorder, characterized in that it further comprises a data documenting and display module, an interface module, a control and software change (software) module, the module data processing and analysis is made with the ability to connect to aircraft systems and equipment, and each of these modules is connected to a network of controllers.

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