RU2711109C1 - Integrated system for recording data, diagnosing the technical and physical state of the human-machine system - Google Patents

Abstract

FIELD: instrument engineering.SUBSTANCE: invention relates to instrument engineering and can be used on aircraft for processing, storing, displaying and transmitting flight information to ground control stations. Proposed invention consists in the fact that the integrated system for recording data, diagnosing the technical and physical state of the human-machine system comprises an AC data recording subsystem, an information pickup unit, a unit for accumulating and processing diagnostic information of the state of elements and AC units, a unit for diagnosing the physical state of the pilot, a unit for preparing flight information for transmission to ground control stations, device for measuring displacement of rotor blades, device for dynamic balancing of rotor, device for indication of flow stalling on rotor blades, connected in certain manner to each other.EFFECT: technical result of proposed invention consists in improvement of safety and reliability of system operation in aircraft.1 cl, 1 dwg

Description

The invention relates to instrumentation technology and can be used on aircraft for processing, storage, display and transmission of flight information to ground control points.

The integrated system for recording data, diagnosing the technical and physical state of the "man-machine" complex is known, which contains a unit for collecting and converting information, a protected drive, an information retrieval unit, a control unit, a protected drive controller, an accumulation and processing unit for diagnostic information about the status of aircraft components and assemblies , a unit for diagnosing the physical condition of the pilot, a unit for preparing flight information for transmission to ground control points connected in a certain way ( atent RF №2650276, IPC G01D 9/00, G06H17 / 40, G05B 23/02, G06F 11/30, opubl.11.04.2018 g).

The disadvantages of the known system are insufficient safety and reliability due to the lack of diagnosis of the state of the rotor.

Closest to the claimed solution, taken as a prototype, is an integrated system for recording data, diagnosing the technical and physical condition of the human-machine complex (RF patent No. 2687318, IPC G05B 23/02, G06F 11/30, G01D 9/00, G06H 17/40, published May 13, 2019).

This system contains an aircraft data registration subsystem, an information acquisition unit, an accumulation and processing unit for diagnostic information of the state of the aircraft components and assemblies, a unit for diagnosing the physical condition of the pilot, a unit for preparing flight information for transmission to ground control points, and a rotor blade inconsistency measuring device connected to a specific way.

The disadvantage of the system is the lack of safety and reliability in operation.

The technical result of the invention is to increase the safety and reliability of the system as part of the aircraft (especially helicopters).

The technical result is achieved by the fact that the integrated system of data recording, diagnostics of the technical and physical state of the "man-machine" complex, which contains a subsystem for recording data of an aircraft, an information retrieval unit, an accumulation and processing unit for diagnostic information of the state of the elements and units of the aircraft, a diagnostic unit for the physical condition of the pilot , a unit for preparing flight information for transmission to ground control points, a device for measuring the inconsistency of the rotor blades, the first, second the fourth and third inputs of the aircraft data registration subsystem are connected to sensors and digital communication lines of the aircraft system for the registration subsystem, the fourth, fifth and sixth inputs are connected to ground-based information processing equipment, the aircraft on-board control panel and the aircraft on-board audio source, the seventh and eighth inputs connected to the second outputs of the unit for accumulating and processing diagnostic information on the state of the elements and assemblies of the aircraft and the unit for diagnosing the physical state of the pilot, respectively, the second, third and third outputs of the aircraft data registration subsystem are connected to the on-board information display system, to ground-based information processing equipment and the first input of the information acquisition unit, respectively, the fourth output of the aircraft data registration subsystem is connected to the fourth inputs of the storage and diagnostic information processing units of the state of elements and assemblies LA and the unit for diagnosing the physical state of the pilot, respectively, the second and third inputs of the information retrieval unit are connected to the first outputs of the dia Gnostic of the physical state of the pilot and the unit for the accumulation and processing of diagnostic information on the state of the components and assemblies of the aircraft, respectively, the output of the information retrieval unit is connected to the input of the flight information preparation unit for transmission to ground control points, the first and second outputs of which are connected to the HF band transmitter and satellite communication system, respectively, the first, second and third inputs of the accumulation and processing unit of diagnostic information of the state of the elements and units of the aircraft are connected to the sensor for diagnosing the state of the components and assemblies of the aircraft, the first, second and third inputs of the pilot physical condition diagnosis unit are connected to the sensors for diagnosing the physical state of the pilot, the first, second and third inputs of the rotor blade incoherency measuring device are connected to the rotor blade incoherency measuring sensors, the first and the second outputs are connected to the fourth input of the data acquisition unit and to the ninth input of the aircraft data registration subsystem, respectively, the fourth output is the swarm is connected to the fourth input of the rotor blade inconsistency measuring device, is additionally equipped with a device for dynamically balancing the rotor and a device for indicating flow stall on the rotor blades, the first, second and third inputs of which are connected to the flow stall detection sensors on the rotor blades, the first and the second outputs are connected to the fifth input of the information pickup unit and to the tenth input of the aircraft data registration subsystem, respectively, the fourth output of which is connected to the four the first input of the device for indicating flow stall on the rotor blades, the first, second and third inputs of the rotor dynamic balancing device are connected to the rotor dynamic balancing assessment sensors, the first and second outputs are connected to the sixth input of the information pickup unit and to the eleventh input of the registration subsystem aircraft data, respectively, the fourth output of which is connected to the fourth input of the device for dynamic balancing of the rotor.

The invention is illustrated in the drawing, which shows a structural diagram of an integrated system for recording data, diagnosing the technical and physical condition of the complex "man-machine".

The system consists of a subsystem 1 for recording aircraft data, made on the basis of switch microcircuits, analog-to-digital converters (ADCs), microprocessors and non-volatile memory microchips, an information retrieval unit 2, which includes a microprocessor and an adapter for recording information on a removable cartridge with non-volatile memory, unit 3 accumulation and processing of diagnostic information on the state of the elements and units of the aircraft, which can be performed on the basis of ADC chips, programmable logic (FPGA), microprocessors, block 4 dia nosti the physical condition of the pilot, which can be performed on the basis of ADC, FPGA, light sources and receivers, flight information preparation unit 5 for transmission to ground control points, which can be performed on the basis of microprocessor and code adapters for HF band and satellite communication lines. The principle of operation of the rotor blade inconsistency measuring device 6 consists in the formation of video frames of coordinates of the tips of the rotor blades of the helicopter in flight conditions with the determination and fixing of the amplitudes of the signals from the tips of all rotor blades. Based on the measurement results, recommendations are made on the need for corrections to the process of mechanical adjustment of the blades. The device 6 can be made on the basis of an optical emitter, a photodetector, a video signal processing unit containing an ADC, a microcontroller, threshold devices (comparators), serial code generators for transmitting current information for registration in block 2 and an on-board information display system (see, for example , RF patent No. 2180122, publ. 02/27/2002, RF patent No. 2415053, publ. March 27, 2011).

The rotor dynamic balancing device 7 can be performed using opto-electronic measuring instruments to achieve such a weight distribution of the blades that will ensure normal operation in all modes. It may contain an optical head, a photodetector, an ADC, a comparator, a video processing unit, voice filters, a Fourier transducer, and an imbalance analysis unit (see, for example, RF patent No. 2441807, publ. 02.10.2012)

A device 8 for indicating flow stall on the rotor blades provides measurement of sensor signals that vary depending on the appearance of stall air flow.

The device can be implemented using fiber-optic sensors, optical connectors and cables, a light source, a fiber optic switching unit, an information analysis unit, a spectral analysis unit and a digital-to-analog converter with sensors placed on a swashplate (see, for example, RF patent No. 2555258 published on 07/10/2015)

The system operates as follows. Information from sensors and digital lines of aircraft systems to the inputs 1, 2, 3 of subsystem 1 is converted to a digital code. A message is formed and stored in the form of an information subframe from information on a program specific to a particular application. Identification data (block numbers, date, time, etc.) is input to input 5 of subsystem 1 from the on-board console, which are also recorded in information subframes and stored in a protected drive, which is part of subsystem 1. At the same time, audio information is recorded by input 6. Each subframe is digitized by time with digital marks, which from the output of 4 subsystem 1 go to the inputs of 4 blocks 3, 4 and devices 6, 7 and 8. Information in the form of subframes is digitized by time and transmitted from the output of 3 subsystem 1 to the input 1 b eye 2.

In block 2, frame-by-frame recording and storage of information is performed, which is recorded in a specially allocated area of a removable memory cassette.

In other areas of the removable memory cassette, frame-by-frame recording of information digitized by time stamps is performed at input 2 of block 2 from output 1 of block 4, at input 3 from output 1 of block 3, at input 4 from output 1 of device 6, and input 6 from output 1 of the device 7 and input 5 from output 1 of device 8.

In block 3 and 4 and devices 6, 7 and 8, information from the sensors at inputs 1, 2, 3 is converted into a digital code with the formation of subframes, their digitization in time and transmission to block 2 for recording in a removable memory cassette.

During ground-based processing of diagnostic information, sensor readings recorded on a removable memory cartridge of unit 2 during the last flight are processed using special algorithms using statistical data accumulated during previous flights of this aircraft. Based on the processing results, a forecast is made of the possible time of the onset of aircraft failures with the specification of specific nodes (units, systems) that are in precautionary state.

In subsystem 1, blocks 3, 4 and devices 6, 7 and 8 during operation, a periodic test control of operation is provided, which from the outputs of 2 devices 6, 7 and 8 is fed to the inputs 9, 11 and 10 of subsystem 1, respectively, from the output of block 2 4 to input 8 of subsystem 1 and from output 2 of block 3 to input 7 of subsystem 1.

The results of the test control in subsystem 1 are recorded in a subframe and transmitted from output 3 to input 1 of block 2 and output from output 1 to the on-board information display system.

In subsystem 1, blocks 3, 4, and devices 6,7 and 8, pre-emergency signal modes are recorded, above and below the acceptable levels of which pre-emergency signals are generated, these signals are transmitted to subsystem 1 via the test control channels described above and are also recorded in a subframe, formed by subsystem 1 and are output to the on-board information display system through output 1.

The subframes from subsystem 1 of blocks 3, 4 and devices 6, 7 and 8 are received in block 2, where single recording frames of all system information are formed, which are recorded in a removable memory cassette of block 2.

Information from the removable memory cassette of unit 2 is used for processing by ground-based complexes with determining the state of on-board equipment by generating diagnostic information for aircraft components and assemblies, determining the physical state of the pilot, measuring the incoherence of the rotor blades, assessing the dynamic balancing of the rotor and determining the stall of the flow on the rotor blades. At the same time, from the subsystem 1, the navigation navigation parameters necessary for registration in the event of flight accidents are recorded on a removable memory cassette.

The most important information affecting flight safety during the execution of the latter is transferred from the output of block 2 to the input of block 5, which is converted according to special algorithms for wireless transmission to ground points and using code adapters the amount of information necessary for decision-making by flight managers is formed and broadcasts from outputs 1 and 2.

The system provides for work with a ground processing complex not only with a removable memory cassette of unit 2, but also by electrically connecting it to output 2 and input 4 of subsystem 1 to read the necessary information for ground processing.

The introduction of devices 7 and 8 into the system makes it possible to increase the operational safety of the aircraft and to determine all main rotor operation parameters with the aim of displaying emergency situations by this parameter on the on-board information display system and transmitting this information in real time to the flight manager for taking emergency measures by both the pilot and and ground support services.

It should be noted that depending on the requirements for operation, each aircraft can be equipped with the necessary set of sensors and blocks, in several versions, i.e. the required part of the described integrated system can be installed at the facility, as blocks 3, 4, 5 and devices 6, 7, 8 can operate independently of each other in any combination.

The introduction of devices 7 and 8 into the system makes it possible to diagnose the condition of not only the transmission, engines, airframe, but also all the elements of the rotor.

Claims (1)

An integrated system for recording data, diagnosing the technical and physical state of the man-machine complex, containing a subsystem for recording data from an aircraft, an information retrieval unit, a unit for accumulating and processing diagnostic information about the state of aircraft components and assemblies, a unit for diagnosing the physical condition of the pilot, and a unit for preparing flight information for transmission to ground control points, a device for measuring the inconsistency of the rotor blades, the first, second and third inputs of the registration subsystem These aircraft are connected to the sensors and digital communication lines of the aircraft system for the registration subsystem, the fourth, fifth and sixth inputs are connected to ground-based information processing equipment, the aircraft on-board control panel and the aircraft on-board audio information sources, respectively, the seventh and eighth inputs are connected to the second outputs of the storage unit and processing diagnostic information about the state of the elements and assemblies of the aircraft and the unit for diagnosing the physical condition of the pilot, respectively, the first, second and third outputs of the subsystem register radios of aircraft data are connected to the on-board information display system, to ground-based information processing equipment and to the first input of the information acquisition unit, respectively, the fourth output of the aircraft data registration subsystem is connected to the fourth inputs of the accumulation and processing unit for diagnostic information of the state of the elements and units of the aircraft, and the unit for diagnosing the physical condition of the pilot and devices for measuring the inconsistency of the rotor blades, the second and third inputs of the information pickup unit are connected to the first outputs of the di agnosticizing the physical state of the pilot and the unit for accumulating and processing diagnostic information on the state of the components and assemblies of the aircraft, respectively, the output of the information retrieval unit is connected to the input of the flight information preparation unit for transmission to ground control points, the first and second outputs of which are connected to the HF-band transmitter and satellite communication system, respectively, the first, second and third inputs of the accumulation and processing unit of diagnostic information of the state of the elements and units of the aircraft are connected to the sensor for diagnosing the state of the components and assemblies of the aircraft, the first, second and third inputs of the pilot physical condition diagnosis unit are connected to the sensors for diagnosing the physical state of the pilot, the first, second and third inputs of the rotor blade incoherency measuring device are connected to the rotor blade incoherency measuring sensors, the first and the second outputs are connected to the fourth input of the information retrieval unit and to the ninth input of the aircraft data registration subsystem, respectively, characterized in that o equipped with a device for dynamic balancing of the main rotor and a device for indicating stall flow on the rotor blades, the first, second and third inputs of which are connected to sensors for detecting stall flow on the rotor blades, the first and second outputs of the device for indicating stall flow on the rotor blades connected to the fifth input of the information pickup unit and the tenth input of the aircraft data registration subsystem, respectively, the first, second and third inputs of the rotor dynamically balancing device and are connected to sensors for evaluating the dynamic balancing of the main rotor, the first and second outputs of the device for dynamic balancing of the main rotor are connected to the sixth input of the information pickup unit and the eleventh input of the aircraft data recording subsystem, respectively, the fourth inputs of the device for indicating flow stall on the rotor blades and the device for rotor dynamic balancing connected to the fourth output of the aircraft data registration subsystem.

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