Aircraft structure technical condition monitoring system (versions)

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft condition field monitoring systems. The aircraft structure technical state monitoring system contains sensors of technical condition of helicopter blades of an oar or airplane outer wing panels and onboard recorder unit. On each helicopter blade of an oar or airplane outer wing panel there are not less than two fibre-optic Bragg grating strain sensors and not less than two vibroacoustic sensors. The system includes fibre-optic trunk cables, optical connectors, electric control buses, optical switches, fibre-optic measuring lines. Helicopter monitoring system additionally comprises optical rotating connector. The recorder unit contains reference signal unit, fibre-optic switching unit, light source unit, spectrum analysis unit, control and data analysis unit, data storage unit, The recorder unit has electric control signal input/output and electric power supply input, electric power supply unit. Strain sensors and vibroacoustic sensors are imbedded into the mass of composite material in top-loaded parts of helicopter blades of an oar spars and airplane outer wing panels.

EFFECT: possibility to monitor technical condition of blade spars and outer wing panels made of composite materials in manufacturing and in service.

4 cl, 5 dwg

 

The invention relates to aircraft, and in particular to a system for monitoring the technical state of structures of the aircraft (LA). The preemptive scope of the system for monitoring the integrity of the helicopter main rotor and the outer wings of the aircraft, made of composite materials.

Known design alarm system damage the blades of the helicopter, in the inner cavity of the spar which pressurized gas (C. A. Danilov, "the Mi-8 Helicopter, the Device and service, M.: Transport, 1988).

The system includes a valve that is designed for charging compressed air into the internal cavity of the spar, and the indicator of the pressure loss of the spar, which consists of a housing with signal cap made of organic glass and bellows attached to the base and filled with inert gas. Tightness of the spar the elastic forces and the internal pressure of the bellows expands and pushes the signal cap red zone review. The observation of such a detector can only be performed when inspecting the blades before flying on earth. When in flight cracks that could lead to the accident, the pilot does not receive information about an emergency or pre-emergency situation, which is a disadvantage of analogue.

Common signs of an analog of the invention are the presence of the sensor, converts mechanical structural damage of the aircraft in the signal, which occurs when there is damage.

A known system for monitoring the integrity of the blades of the helicopter (utility model EN 10682 U1, B64C 27/46, B64D 45/00, 1999), adopted for the prototype of the invention. It contains a sensor that converts mechanical damage to the blades of the helicopter in the signal, which changes in the presence of damage to the blades. The sensor is designed in the form of an absolute pressure sensor. In addition, it contains a device-charging pump compressed air into the internal cavity of each blade spar, and means of transmitting information about the pressure in the inner cavity of each blade spar with indication of presence of cracks due to the reduction of air pressure.

On each blade set absolute pressure sensor with electrical output signal, and a conversion unit of the sensor signal in a pulsed infrared radiation. On the fuselage of the helicopter, in the line of sight of the IR radiation, set common to the blades of a sensor of infrared radiation, and in the cabin of the helicopter is connected to the output of the photodetector receiving unit for processing and comparing the amplitudes of signals from the blades and display them in cracks.

The disadvantages of this control system is the inability to determine the location of damage, gas leaks and neobhodimosti pump to pump gas to the inside of the side members of the blades, which leads to weight gain. In addition, for structures made of composite materials, the destruction of which is not due to loss of integrity, and with a bundle of material, it is not applicable, because of a gas leak will not, and the material has lost its original strength.

Common features of the prototype and of the invention are:

- presence sensor that converts mechanical structural damage of the aircraft (LA) in the signal that occurs when there is damage.

- block the Registrar, located on Board an aircraft which is used for processing signals from the sensors, alerting to the mechanical damage of the structures of the aircraft.

The technical result of the invention is the provision of control of technical state of structures LA from composite materials, in particular of the side members of the blades and the outer wings of the plane, at the production stage, preflight preparation and during flight of the aircraft.

The technical result of the invention is achieved in two versions of the invention: the first variant of the helicopter, the second aircraft.

In the first embodiment of the invention the technical result is achieved by placing the blades of the helicopter sensors of two types, at least two of each type, the electrical signals to the that characterize the technical condition of the propeller blades, fiber optic strain sensors based on Bragg gratings and fiber-optic vibration sensors, in addition, through the use of fiber-optic rotary connector.

In the second embodiment of the invention, said invention is achieved by placing the consoles of the wing are two types of sensors, at least two of each type, describing the technical condition of the wing: fiber optic strain sensors based on Bragg gratings and fiber-optic vibration sensors.

The invention is illustrated by drawings.

Fig.1. Structural scheme of the system installation check of a technical condition on the plane.

Fig.2. Structural scheme of the system installation check of a technical condition on the helicopter.

Fig.3(a, b). Option of possible structural arrangement of the sensors inside the composite material of the blades of the helicopter: 3A - on the surfaces of the propeller blades; 3b - side of the blade.

Fig.4. Electro-optical functional block circuit-recorder.

Fig.5. Block diagram of the block-recorder.

On the figures entered legend: 1 - the unit Registrar; 2 - fiber optic trunk cable, 3 - electric bus control optical switch, 4 - optical switch; 5 - fiber optic measurement is the turn, 6 - fiber optic strain sensors based on Bragg gratings (load cell), 7 - fiber optic vibration sensors, 8 - fiber-optic cables, 9 - fiber-optic rotary connector, 10 - fiber optic fiber 11 is an optical connector, 12 - spar rotor blades of the helicopter, 13 - power, 14 - broadband light source, 15 - laser source, 16 - single-Board computer, 17 photodetector; 18, 21 - fiber-optic tracts, 19 - supporting fiber optic shoulder, 20 spectrometer, 22 - driver control optical switch 4, 23 - fiber-optic connector, 24 - modulus of stress-strain state (module VAT), 25 - module vibroacoustic, 26 - hard drive, 27 - unit of the light source 28 is a block of storage of information, a 29 - unit management and analysis of information, 30 - unit fiber-optic switching, 31 - unit reference signal, a 32 - unit spectral analysis.

The first variant of the invention (Fig.2, 3, 4, 5)

The technical result of the invention in the first embodiment is achieved due to the fact that the system for monitoring the technical condition of the blades of the helicopter contains: block the Registrar is 1; fiber-optic trunk cable 2, the electrical bus 3 controls the optical switch 4, the optical switch 4; fiber-optical measuring whether the AI 5, at least two strain gages 6, at least two vibration sensors 7, optical fiber cables 8, rotating the connector 9, the light guide 10, the optical connector 11, the power supply unit 13, the light source 14, the laser source 15, a single-Board computer 16, the photodetector 17, the fiber-optic tracts 18, 21, the abutment shoulder 19, the spectrometer 20, the driver 22 controls the optical switch 4, a fiber optic connector 23, the module 24 VAT module 25 vibroacoustic, the hard disk 26, block 27 of the light source unit 28 to store information, unit 29 control and analysis of the information block 30 fiber-optical switching unit 31 of the reference signal unit 32 spectral analysis.

The system for monitoring the technical state of structures LA contains embedded at the production stage in each blade of the propeller of the helicopter, made of composite materials, distributed fiber-optical measuring line 5 (Fig.3A, b), which shall be not less than two, consisting of fiber-optic strain sensors based on Bragg gratings 6 and fiber optic vibration sensor 7 based on Bragg gratings, or based on Michelson interferometers/Sagnac, depending on the rigidity parameters of the investigated structures made of composite materials. The sensors are located in the most loaded parts of the lo is Geroev thicker material of the blades of the helicopter, for example, in the plane of the blade (Fig.3A) or on the side of the blade (Fig.3b).

Unit-recorder 1 (Fig.5), which is the generation of optical radiation and the subsequent processing of the signals from the load cells 6 and vibro-acoustic sensors 7. Has the input-output signal unit 30 fiber-optic switching, and the output signals from block 29 management and analysis of information. Unit-recorder 1 is placed in the cockpit and part of the system onboard datalogger (SBI), which contains the following blocks.

Unit 13 power output.

The light source unit 27, which has an output optical signal, input-output control signal and power input.

Unit 28 to store information that is input-output electrical control signal and power input.

Block 29 management and analysis of information, which has first, second and third input-output electrical control signal, the third input-output is the output of the block-recorder 1, and the input power.

Block of fiber-optical switching 30, which has first and second inputs-outputs optical signals and the second input-output is the input-output unit-recorder 1, the input and output optical signal.

The block 31 of the reference signal which has the input-output optical signal.

Block 32 spectral analysis, has come the turn of the optical signal, the input power and the input-output signal control.

Modules 24 VAT and 25 vibroacoustic (Fig.4) are input fiber optic trunk cable 2 and the output electric bus 3 control.

Unit 13 power supply is used to convert a standard on-Board electrical voltage in the voltage required for operation of the individual blocks, such as block 29 and control information analysis unit 28 information storage unit 27 of the light source unit 32 spectral analysis, which has a power supply output.

Block 27 of the light source comprises a broadband source 14 light type optical fiber erbium amplifier and laser source 15 type semiconductor fiber laser whose function is to convert electrical energy into optical power transmitted through the optical fiber block 30 fiber-optic switching, consisting of passive optical elements included in a fiber-optic channel 21 and 18 and fiber optic connector 23. The block 27 has an optical output, the electrical input-output control signal and power input.

Block 30 fiber-optic switching in turn serves to distribute the optical signal and channel it in the right fiber optic communication channel with the block 31 of the reference signal is Ala and block 32 spectral analysis, the load cells 6 and vibro-acoustic sensors 7 through fiber-optic trunk cable 2. The block 30 has an input-output reference optical signal, the input-output optical signal, the input optical signal and the optical output signals of the load cells 6 and vibro-acoustic sensors 7.

The block 31 of the reference signal consists of a fiber-optic shoulder 19, which represents a reference fiber-optic element (Bragg grating or a portion of a fiber optic light guide), the signal of which is compared with the signal from the vibration sensor 7 in block 32 spectral analysis. The block 31 has an input-output reference optical signal.

Block 32 spectral analysis consists of a spectrometer 20 and the photodetector 17 and serves to convert the optical signal from the load cells 6 and vibroacoustic sensor 7 into electrical signals that are transmitted in block 29 of management and information analysis. The block 32 has an input power of the input optical signal and the input-output electrical signal control.

Block 29 management and analysis of information consists of a single Board computer 16, performed on the minimized motherboard with CPU, RAM, and analog-to-digital Converter (ADC), and driver control of the optical switch 22. The block 29 has a first input-output the electric signal, the second input-output electrical signal, the third input-output electrical signal, the input power and output electrical bus 3.

The main functions of the unit 29 management and analysis of information are electrical control of the power of the light source 27, a block data storage 28, the block of spectral analysis 32 and the optical switch 4 through an electric control bus 3, as well as the processing of data from the load cells 6 and vibro-acoustic sensors 7.

Unit 28 information storage comprises a hard disk 26, and serves to record and store the processed block 29 management and analysis of information and has a power input and input-output electric signal.

Block the Registrar is 1, the control system maintains a record of current measurements on the hard disk 26, which are statistical data on stress-strain state of the blades during operation, which can then be connected to external devices, protocols, through the external interfaces of the unit Registrar. These data are necessary to determine the balance of resource each blade, as well as allow you to determine the time and place of impact on the design of the blades, which can lead to violation of the integrity of its internal structure, namely delamination of the composite.

Hair is Onno-optic trunk cable 2 (Fig.1) serves to transmit the optical signal from the unit Registrar 1 optical switch 4 through the connector 9 (Fig.2).

Electric bus 3 is used to control the optical switch 4.

The optical switch 4 is an optoelectronic device made in a special protective housing and which serves to combine multiple optical fiber channels into one and giving the ability to skip and get to a certain point in time of the optical signal through a single optical fiber measuring line, for example optical switch type VX500 1XN manufactured by DiCon Fiberoptics, INC.

Fiber-optical measuring line 5 combine connected in series or parallel, fiber-optic strain gages 6 and vibro-acoustic sensors 7 in the chain and are designed to transmit the optical signal from the sensor unit to the Registrar 1.

Fiber optic strain sensors 6 are used to convert strain of the sensing fiber in the modified optical signal passing through it, and made, for example, on the basis of fiber-optic Bragg gratings (RU, patent for useful model №77420, 2008).

Vibro-acoustic sensors 7 are used to convert the acoustic oscillations of the sensing fiber in the modified optical signal passing through it, and can be made on the basis of Bragg gratings or on the basis of the interferometers Maikel what she/Sagnac depending on the parameters of rigidity of composite materials (RU patent No. 2485454, 2013).

Fiber-optic connecting cable 8 on the basis of standard single-mode fiber-optic light guide is used for transmitting the optical signal from the fiber-optical measuring line 5 to the optical switch 4 (Fig.2).

Rotary connector 9 (Fig.2) designed for transmission of optical and electrical signal through the current collector on the rotating blade of the screw in the opposite direction and consists of a stator and a rotor hub mounted on the axis of rotation of the output shaft of the main gearbox has an input - output optical signal and performed in a protective housing (RU patent No. 2402794, 2010). The connector 9 allows you to connect a fiber-optic rotary output coupling with fiber-optic input optical switch 4, powered and controlled by an electric signal by means of an electric bus 6 through a rotating current collector connector 9.

The light guide 10 is made of fiber and is designed to transmit optical signal sensors fiber optic cables 8.

The optical connector 11 is designed for interfacing fiber optic connecting cable 8 and the optical fiber 10 is fixed to the end of the butt portion of the spar of the blade and is made in the protective case.

The power supply unit 13 system control voltage, such as 12 In the post is permanent power 100 watts.

A broadband light source 14 with a capacity of, for example, 1 mW is used to generate optical radiation in a wide range of the infrared spectrum, of the order of 100 nm, and is made, for example, as a module broadband erbium-doped fiber light source LTD. FE "ofsc-Photonics".

The laser source 15 is designed to generate laser radiation in the infrared region and is made, for example, as superluminescent diode.

Single-Board computer 16 is designed to process signals received from block 32 spectral analysis and control unit 27 of the light source unit 28 information storage unit 32 of the spectral analysis and the driver 22 controls the optical switch 4.

The photodetector 17 is designed to convert optical signal vibroacoustic sensor 7 into an electrical signal and is made, for example, as fiber-optic InGaAs PIN photodiode.

Fiber optic tract 18 is designed to distribute optical signals between the fiber optic shoulder 19 and the photodetector 17.

Fiber-optic shoulder 19 is intended for comparison of the optical signal with the signal from the vibration sensor and is made, for example, in the form of a coil of fiber-optic light guide (RU patent No. 2485454, 2013)

The spectrometer 20 is DL the conversion of the optical signal from the load cell 6 into an electrical signal and performed, for example as a spectrometer I-Mon, firms Ibsen Photonics, Denmark.

Fiber optic tract 21 is designed to transfer the optical signal from the broadband light source 14 to the load cells 6 and in the opposite direction from the load cells 6 to the spectrometer 20.

The driver 22 is designed to control the optical switch 4 and is made in the form of electric charge.

Fiber optic connector 23 is designed to combine fiber optic line fiber optic tract 18 and fiber-optic lines from the fiber optic tract 21 in one optical cable and made in the form of optical cable.

Sensors 6 and 7, at the production stage, inside of a composite material of the side members 12 of all of the blades of the helicopter (Fig.3). The sensors 6 indicate the destruction of the material of the side members, and the sensors 7 are used to determine the moment of impact and location of impact on the spar of the blade of the screw.

Perform system with integrated load cells 6 and vibro-acoustic sensors 7 in the design of the propeller blades made of composite materials allows you to control the strength parameters of the blade at the stage of its manufacture and operation of the helicopter.

Connect the blocks of the control system in the first embodiment (Fig.2, 5)

Group of load cells 6 and the vibration is cysticerci sensors 7 are connected inside the material of construction integrated fiber-optic light guide 10 (Fig.3), okantovany at the end of the butt portion of the spar blades 12 of the rotor helicopter special optical connector 11, with the ability to connect via fiber-optic line to block the Registrar, for example, type unified registration module FIU-44-1.55-40Er production company "ofsc-Photonics", Russia.

The first input-output optical signal of the block 31 of the reference signal is connected to the input-output unit 30 of the fiber-optical switching, the second input-output unit 30 is input-output unit Registrar 1.

The output of block 30 is connected to the first input unit 32 spectral analysis and its input is connected to a block 27 of the light source.

The input-output unit 27 of the light source is connected to the input-output unit 29 management and analysis of information, and the input unit 27 is connected to the output unit 13 of the power supply.

The second input unit 32 spectral analysis is connected to the output unit 13 of the power supply. The input-output unit 32 connected to the first input-output unit 29 management and analysis of information, the second input-output of which is connected to the input / output unit information storage 28, and the input unit 29 with the output of block 13 of the power supply. The input unit 28 is connected to the output unit 13 of the power supply.

The input-output unit-recorder 1 is connected to the input fiber optic trunk cable 2, and its output to the electrical bus 3 from the manage ment of the optical switch 4 (Fig.5).

The outputs of the cable 2 and bus 3 through the rotary connector 9 is connected to the inputs of the optical switch 4, the outputs of which are connected with fiber-optic connecting cables 8 and fiber-optical measuring lines 5.

The second variant of the invention (Fig.1, 4, 5)

The technical result of the invention according to the second embodiment is achieved due to the fact that the system for monitoring the technical condition of the aircraft structure contains: block the Registrar is 1; fiber-optic trunk cable 2, the electrical control bus optical switch 3, the optical switch 4; fiber-optical measuring line 5, fiber optic strain gages 6, fiber optic vibration sensors 7, optical fiber cables 8, the optical fiber 10, the optical connector 11, the power supply unit 13, the light source 14, the laser source 15, a single-Board computer 16, the photodetector 17, fiber optic tracts 18, 21, the abutment shoulder 19, the spectrometer 20, the driver controls the optical switch 22, a fiber optic connector 23, the module VAT 24, the module vibroacoustic 25, a hard disk 26, the light source unit 27, the block information storage 28, a control unit and data analysis 29, block of fiber-optical switching 30, the block reference signal 31, the block of spectral analysis 32.

In the second variant the execution of the invention, the block-recorder 1 (Fig.4 and 5), blocks: waveguide-optical backbone cable 2, electric control bus switch 4, the optical switch 4, a fiber optic measuring line 5, the load cell 6, vibro-acoustic sensors 7, optical fiber cables 8, an optical fiber 10, the optical connector 11, is made the same way as in the first embodiment.

Group of fiber-optic strain gages 6 and vibro-acoustic sensors 7 are connected inside the composite material structure consoles wing aircraft integrated fiber-optic light guide 10 (Fig.1), special optical connector, can connect via fiber-optic line to block the Registrar, for example, type unified registration module FIU-44-1.55-40Er production company "ofsc-Photonics", Russia.

The input-output unit-recorder 1 is connected to the input fiber optic trunk cable 2, and its output to the electrical bus and 3 control optical switch (Fig.5).

The outputs of the cable 2 and bus 3 is connected to the inputs of the optical switch 4, the outputs of which are connected with fiber-optic connecting cables 8 and fiber-optical measuring lines 5.

In addition, the technical result of the invention the second option is due to the fact that the system of control of technical condition of constructiivity contains: embedded in the console wing caisson made of composite materials at least two fiber-optic strain gages 6 on the basis of Bragg gratings and at least two fiber optic vibroacoustic sensors 7, the signals from which are supplied to the block register 1 via the optical fiber cables 8, connected to the optical switch 4, which in turn is powered and controlled through an electric bus 3, and fiber-optic trunk cable 2.

To achieve a technical result, at least two fiber-optical measuring line should be placed in the thickness of the composite material wing in the most loaded areas (Fig.1), for example, near the points of attachment of caisson wing to the fuselage, near the mounting position of the steering parts to the torsion box and the bow of the torsion box, the number of load cells 6 on the basis of Bragg gratings must be at least two, which are located in different directions of the cross-section of the torsion box, depending on the form of the measured voltage and the number of vibro-acoustic sensors 7 should be at least two to determine the location of impact on the torsion box of an aircraft.

Perform system with integrated load cells 6 and vibro-acoustic sensors 7 in the wing design of composite materials, which allows you to monitor the strength parameters at the stage of manufacture and operation.

The system maintains a record of current measurements on the hard disk 26, which are the Xia statistical data on stress-strain state of the wing during operation, necessary to determine the balance of resource wing, and data regarding the presence of internal defects in the material design of the wing, namely delamination of the composite material resulting impact on the design. These data subsequently can be transferred to external devices according to the protocols of the interface block-Registrar 1.

The system for monitoring the technical state of structures LA contains embedded at the production stage in the wing of the aircraft from composite materials distributed fiber-optical measuring line 5 (Fig.1), which must be not less than two, consisting of fiber-optic strain gages 6 and vibroacoustic sensor 7 based on Bragg gratings, or based on Michelson interferometers/Sagnac, depending on the stiffness parameters of the studied structures made of composite materials.

Group of fiber-optic strain gages 6 and vibro-acoustic sensors 7 are combined within the material of construction of fiber-optic light guide and connected with the block by the Registrar 1 type unified registration module FIU-44-1.55-40Er production company "ofsc-Photonics" using fiber-optic communication lines, consisting of fiber optic cables 8, fiber optic Magistralnaya 2 and the optical switch 4 (Fig.1) with the ability to connect via fiber-optic line to block the Registrar, for example, type unified registration module FIU-44-1.55-40Er production company "ofsc-Photonics", Russia.

Fiber-optic connecting cable 8 on the basis of standard single-mode fiber-optic light guide is used for transmitting the optical signal from the fiber-optical measuring line 5 to the optical switch 4 (Fig.1).

The optical switch 4 is an optoelectronic device, which serves to combine multiple optical fiber channels into one and giving the ability to skip and get to a certain point in time of the optical signal through a single optical fiber measuring line, for example, the type of the optical switch VX500 1XN manufactured by DiCon Fiberoptics, INC.

Block the Registrar is 1, which is the generation of optical radiation and the subsequent processing of the signals from fiber-optic strain gages 6 and vibro-acoustic sensors 7, is placed in the cockpit and is part of the onboard measuring system (SBI). The unit Registrar module includes measurement and analysis of stress-strain state 24 (module VAT) and the module 25 vibroacoustic for measurement and analysis of vibroacoustic signals.

Fiber optic trunk cable 2 (Fig.1) serves to transmit the optical signal from block-recorder 1 on the optical SW is 4 PM.

The system according to the invention in two versions of the invention operates as follows.

When you enable the software block-recorder 1 is an electric power to the control driver broadband light source 14 (Fig.4) module VAT 24 and the driver laser source 15 module vibroacoustic.

Under the action of external loads on the structure of the composite material varies the optical signal passing through the fiber-optic strain gages 6, can reflect the signal. Impact on the structure, in turn, causes the propagation of acoustic waves inside the structure, which are perceived vibro-acoustic sensors 7. Optical signals from the load cells 6 and vibro-acoustic sensors 7 with all of the investigated structures are transmitted through fiber optic cables 8 to the optical switch 4. Depending on the command in the form of an electrical signal sent through an electric bus 3 driver control optical switch 22, the optical switch 4 connects the block-recorder 1 with one of the fiber-optical measuring line 5 through the trunk optical fiber cable 2 in the second embodiment of the invention, as in the first embodiment through the trunk optical fiber cable 2 and the rotary optical fiber is obedinitel 9.

The optical signal from the fiber-optic strain gages 6 and vibro-acoustic sensors 7 through the power of fiber-optical switching 31 enters the spectrometer 20 and the photodetector 19, the pre-mixed with the reflected optical signal of the block reference signal 32, thereby creating an interference pattern, which is in direct dependence on external influences on the acoustic vibration sensor 7.

Single-Board computer 16 after processing the electrical signals from the spectrometer 20 and the photodetector 17 using the software generates the values on the current stress-strain state of structures LA and the parameters of the acoustic portrait design, giving a sense of presence and place of impact.

The system for monitoring the technical state of structures LA allows to estimate the residual life of structures, through the analysis of the stress-strain state, as well as to pay attention to the possible occurrence of internal damage to the structure due to impact.

Distinguishing features according to the first embodiment of the invention.

In each blade screw additional introduced N-1 sensors technical condition, where N is at least two, and all N sensors technical condition made in the form of fiber-optic thansadet is of IKI 6, in addition, there is N vibroacoustic sensor 7, and in the system of the optical switch 4 and fiber optic rotary connector 9 with the optical input-output and electrical input and output fiber optic cables 8 and the optical connector 11, the number of blades of the helicopter, at least one fiber optic trunk cable 2 and the same electrical bus 3 control, at least two fiber-optical measuring lines 5, in which are included interconnected in series or in parallel to at least one of the optical fiber 10 at least two of the load cells 6 and vibro-acoustic sensors 7.

Moreover, the block-recorder 1 has the optical and electrical inputs and outputs, which are respectively connected with fiber-optic input / output trunk cable 2 to the input-output electric bus 3 control, a second input the output of which is connected to the electrical input-output optical switch 4 and the second end of the trunk cable 2 through the corresponding input-output fiber-optic rotary connector 9 is connected with the first optical inputs-outputs of the switch 4, the second input-output through which the optical input-output fiber optic cables 8, which are connected with inputs of the fiber optic Izmeritel the data lines 5, and consist of fiber optic strain sensors (6) and vibro-acoustic sensors 7.

All of the sensors 6 and 7 are mounted in the most loaded parts of the side members of the blades of the helicopter into the thickness of the composite material and is connected inside the structure of the embedded optical fiber 10, okantovany at the end of the butt portion of the spar blades 12 of the rotor helicopter optical connector 11.

Distinguishing features according to the second embodiment of the invention. In each wing further introduced N-1 sensors technical condition, where N is at least two, and all N sensors technical condition made in the form of fiber-optic strain gages 6, in addition, entered N of vibro-acoustic sensors 7, at least one fiber-optic connecting cable 8, at least one fiber optic trunk cable 2, at least two optical connectors 11, electric bus 3 control, at least one optical switch 4, at least two fiber-optical measuring lines 5, in which are included interconnected in series or in parallel to at least one of the optical fiber 10 at least two of the load cells 6 and 7 vibration.

Moreover, the block-recorder 1 has the optical and electrical inputs and outputs, which are respectively connected with a fiber-optic input-vyhoda the trunk cable 2, with the entrance-exit electric bus 3 control, a second input the output of which is connected to the electrical input-output optical switch 4 and the second end of the main cable 2 is connected with the first optical inputs-outputs of the switch 4, the second input-output through which the optical input-output fiber optic cables 8 are connected to the inputs of an optical fiber measuring lines, which consist of fiber-optic strain gages 6 and vibro-acoustic sensors 7.

All of the sensors 6 and 7 are mounted in the most loaded part of the outer wings in thickness of a composite material and is connected inside the structure embedded optical fibers (10), okontsevanie in the end face of the outer wings of the optical connectors (11).

Distinctive features of dependent claim.

Unit-Registrar 1 contains:

the block 31 of the reference signal which has the input-output optical signals,

block of fiber-optical switching 30, which has first and second inputs-outputs optical signals and the second input-output is an optical input-output unit-recorder 1,

the light source unit 27, which has an output optical signal, the electrical input-output control signal and the input power,

block 32 spectral analysis has an input Opti the definition of the signal, the input power and electrical input-output control signal,

block 29 management and analysis of information, which has first, second and third inputs and outputs electrical control signals, the output electrical signal which is the output of the block-recorder 1, and the input power,

block 28 storing information is input-output electrical control signal and the input power,

block 13 of the power supply from the power supply output.

Moreover, the input-output optical signal of the block 31 reference signal connected to the first input-output unit 30 of the fiber-optical switching, the second input-output of which is connected to the input / output fiber optic trunk cable 2, the optical input unit 30 of the fiber-optical switching is connected to the input unit 32 spectral analysis.

In addition, the optical output unit 27 of the light source is connected with the optical input unit 30 of the fiber-optical switching, and the electrical input-output unit 27 of the light source connected to the first electrical input-output unit 29 management and analysis of information, and the electrical input-output unit 32 spectral analysis is connected with the second electrical input-output unit 29 management and analysis of information, his third electrical input-output is connected to the block 28 storing information, the electrical output is the electrical output of the registration unit 1, which is connected to the electrical bus and 3 control optical switch.

In addition, the inputs of power supply units: a light source 27, information storage 28, management and analysis of information 29 and spectral analysis 32 is connected to the output unit 13 of the power supply.

Distinctive features of the unit Registrar 1

Unit-recorder 1 includes: a block 31 of the reference signal which has the input-output optical signals, the unit fiber-optic switching 30, which has first and second inputs-outputs optical signals and the second input-output is an optical input-output unit-recorder 1, the light source unit 27, which has an output optical signal, the electrical input-output control signal and the input power-supply unit 32 spectral analysis has an input optical signal, the input power and electrical input-output control signal, block 29 management and analysis of information has first, second and third inputs and outputs electrical control signals, the output of the electric control signal, which is the output of the block-recorder 1, and the input power, the unit 28 of the storage information is input-output electrical control signal and the input power supply unit 13 of the power supply from the power supply output.

Moreover, the input-output optical signal of the block 31 and the reference signal is connected to the first input-output unit 30 of the fiber-optical switching, the second input-output of which is connected to the input / output fiber optic trunk cable 2, the optical input unit 30 of the fiber-optical switching is connected to the input unit 32 spectral analysis.

Optical output unit 27 of the light source is connected with the optical input unit 30 of the fiber-optical switching, and the electrical input-output unit 27 of the light source connected to the first electrical input-output unit 29 management and analysis of information, and the electrical input-output unit 32 spectral analysis is connected with the second electrical input-output unit 29 management and analysis of information, his third electrical input-output is connected to the block 28 storage of information, and its electrical output is the electrical output of the control block register 1, which is connected to the electrical bus and 3 control optical switch, in addition, the inputs of power supply units: a light source 27, information storage 28, management and analysis of information 29 and spectral analysis 32 is connected to the output unit 13 of the power supply.

1. The system for monitoring the technical state of structures of the aircraft, containing sensors technical design installed on each blade of the propeller of the aircraft, which converts mechanical damage to the propeller blades in the signal is, which changes in the presence in it of mechanical damage, and block the Registrar (1), placed on Board the aircraft, which is used for processing sensor signals, characterized in that each blade entered at least two fiber-optic strain sensors (6) and at least two fiber optic vibration sensors (7), and the system optical switch (4) and fiber-optic rotary connector (9) with an optical input-output and electrical input and output, fiber-optic cables (8) and optical connectors (11), the number of blades of the aircraft, at least one fiber optic trunk cable (2) and one electric bus (3) control, at least two fiber-optical measuring lines (5) in which interconnected in series or in parallel to at least one of the light guide (10) at least two load cells (6) and vibration (7), and block the registrant (1) has optical and electrical inputs and outputs, which are respectively connected with fiber-optic input / output trunk cable (2) with input-output electric bus (3) control, the second input-output of which is connected to the electrical input-output optical switch (4) and the second end of the trunk cable (2) across the corresponding input-output fiber-optic rotary connector (9) is connected with the first optical inputs-outputs of the switch (4), the second set of inputs and outputs through which the optical input-output fiber-optic cables (8), which are connected with inputs of a fiber-optical measuring lines 5, and consist of fiber optic strain sensors (6) and vibro-acoustic sensors (7), all of the sensors (6, 7) mounted in the most loaded parts of the side members of the propeller blades of aircraft in thickness of a composite material and is connected inside the structure built fiber-optic light guide (10), okantovany at the end of the butt portion of the spar of the blade (12) jet aircraft optical connector (11).

2. The system of technical inspection of aircraft structures under item 1, characterized in that the block-Registrar (1) contains: block (31) of the reference signal which has the input-output optical signals, the unit fiber-optical switching (30), which has first and second inputs-outputs optical signals and the second input-output is an optical input-output unit Registrar (1), the unit of the light source (27), which has an output optical signal, the electrical input-output control signal and the input power, block (32) spectral analysis has an input optical signal, the input power and electrical input-output signal control unit (29) management and analysis of information, the which has the first, the second and third inputs and outputs electrical control signals, the output of the electric control signal, which is the output of the block-Registrar (1), and the input power supply unit (28) storage information is input-output electrical control signal and the input power supply unit (13) of the power supply from the power supply output, and input-output optical signal of the block (31) reference signal connected to the first input-output unit (30) fiber-optical switching, the second input-output of which is connected to the input / output fiber optic trunk cable (2), optical input unit (30) fiber-optical switching is connected to the input unit (32) spectral analysis, in addition, the optical output unit (27) of the light source is connected with the optical input unit (30) fiber-optical switching, and the electrical input-output unit (27) a light source connected to the first electrical input / output block (29) management and analysis of information, and the electrical input-output unit (32) spectral analysis is connected with the second electrical input / output block (29) management and analysis of information his third electrical input-output is connected to the block (28) storage of information, and its electrical output is the electrical output of the control block register (1), which is connected with Elektricheskiye (3) control the optical switch, in addition, the inputs of power supply units: a light source (27), information storage (28), management and information analysis (29) and spectral analysis (32) connected to the output unit (13) power supply.

3. The system for monitoring the technical state of structures of the aircraft, containing sensors technical state of structures installed on consoles wing flying machine that converts mechanical damage in the signal, which changes in the presence of mechanical damage of the wing, and the block-Registrar (1) placed on Board the aircraft and used for processing sensor signals, characterized in that each wing is entered at least two fiber-optic strain sensors (6) and at least two fiber optic vibration sensors (7), at least one fiber-optic connecting cable (8), at least one fiber optic trunk cable (2), at least two optical connectors (11), electric bus (3) control, at least one optical switch (4), at least two fiber-optical measuring lines (5) in which interconnected in series or in parallel to at least one of the light guide (10) at least two load cells (6) and vibration (7), and block the registrant (1) has an optical and electrical inputs in the passages, which are respectively connected with fiber-optic input / output trunk cable (2) with input-output electric bus (3) control, the second input-output of which is connected to the electrical input-output optical switch (4) and the second end of the trunk cable (2) connected with the first optical inputs-outputs of the switch (4), second inputs and outputs through which the optical input-output fiber-optic cables (8) connected to inputs of a fiber-optical measuring lines, which consist of fiber optic strain sensors (6) and vibro-acoustic sensors (7), all of the sensors (6, 7) mounted in the most loaded part of the outer wings in thickness of a composite material and is connected inside the structure embedded optical fibers (10), okontsevanie at the ends of the outer wings of the optical connectors (11).

4. The system of technical inspection of aircraft structures under item 3, characterized in that the block-Registrar (1) contains: block (31) of the reference signal which has the input-output optical signals, the unit fiber-optical switching (30), which has first and second inputs-outputs optical signals and the second input-output is an optical input-output unit Registrar (1), the unit of the light source (27), which has an exit directly violates the definition of the signal, electrical input-output control signal and the input power supply unit (32) spectral analysis has an input optical signal, the input power and electrical input-output signal control unit (29) management and analysis of information, which has first, second and third inputs and outputs electrical control signals, the output of the electric control signal, which is the output of the block-Registrar (1), and the input power supply unit (28) storage information is input-output electrical control signal and the input power supply unit (13) of the power supply from the power supply output, moreover, the input-output optical signal of the block (31) reference signal connected to the first input-output unit (30) fiber-optical switching, the second input-output of which is connected to the input / output fiber optic trunk cable (2), the optical input unit (30) fiber-optical switching is connected to the input unit (32) spectral analysis, in addition, the optical output unit (27) of the light source is connected with the optical input unit (30) fiber-optical switching, and the electrical input-output unit (27) a light source connected to the first electrical input / output block (29) management and analysis of information, and the electrical input-output unit (32) spectral analysis is connected with the second electrically the input-output unit (29) management and analysis of information his third electrical input-output is connected to the block (28) storage of information, and its electrical output is the electrical output of the control block register (1), which is connected to the electrical bus (3) control optical switch, in addition, the inputs of power supply units: a light source (27), information storage (28), management and information analysis (29) and spectral analysis (32) connected to the output unit (13) power supply.



 

Same patents:

FIELD: test engineering.

SUBSTANCE: device comprises pipelines of supply and discharge of air with valves located on them, as well as the means of automatic program control of these valves. The structure of the means of automatic control comprises a pressure regulator, a pressure sensor, a program setting unit, two blocks of comparison, two blocks of setting the pressure levels and the logic element and connections to arrange interaction of these functional elements.

EFFECT: improved accuracy of development of loading programs, and reduction of technical means necessary to create plants of such type.

2 dwg

FIELD: machine building.

SUBSTANCE: test bench comprises three independent follower electrohydraulic drives including three hydraulic cylinders, three servovalves, three dynamometers, three regulators and three mechanical systems while one of the latter comprises a lever system, all drives are energized from an oil pump station and are controlled by the same computer. One of the follower electrohydraulic drives is fixed stationary and the other two together with cross bars can move freely. One support of a sleeper opposite the fixed drive is in fixed position and the other support of the sleeper can change its position depending on the loading diagram.

EFFECT: possibility to test any sleeper with rail gauge from 1067 to 1520 mm.

4 dwg

FIELD: aviation.

SUBSTANCE: during method implementation during the fuselage loading the compressed air pressure supplied from the external source is stabilised upstream the input valve with large flow rate. The valve with large flow rate is opened to the specified degree ensuring the program rate of the pressure increasing in the fuselage. At the horizontal area the valve with large flow rate is opened to specified degree ensuring compensation of some gas losses from the fuselage due to leaks. Accurate compensation of losses is ensured due to operation of the control valve with low flow rate of the controlled gas pressure in fuselage.

EFFECT: increased accuracy of loading program test run, extension of scope of use, simplified design.

2 dwg

FIELD: testing equipment.

SUBSTANCE: invention relates to the field of testing equipment, in particular, to plants for strength testing of aircraft hulls for endurance by cyclic loading by inner pressure of compressed air. The plant uses one input control valve with an equal percentage characteristic, which, depending on the section of the program of pneumatic loading, ascending or horizontal, is opened to a larger or smaller extent, for this purpose the plant comprises two blocks of valve opening settings, two comparison units, two units of pressure level setting in the hull, a correction unit, a summator, a timer, key elements and communication lines for organisation of interaction of listed functional elements.

EFFECT: increased accuracy of loading programs adjustment, reduced technical means for its development, and also expanded area of application.

3 dwg

FIELD: aviation.

SUBSTANCE: during implementation of the suggested method the air pressure increasing in the fuselage and its stabilisation at horizontal areas of the program are ensured by the same input control valve having equal percentage flow characteristic. At that at the program unplug the input control valve is opened to the specified value ensuring the program rate of pressure increasing in the fuselage, pressure is measured upstream the input valve, and degree of the valve opening is regulated based on the pressure value. At the horizontal are of the program the input valve is closed to specified degree and control is performed as per pressure in fuselage.

EFFECT: increased accuracy of loading program test run, decreasing of hardware number required to create the such type units, extension of scope of their use.

3 dwg

FIELD: test equipment.

SUBSTANCE: object is secured in cantilever at bearing column to use mechanical curvature gage for measurement of object curvature at its separate sections at objected bending under preset load applied to its free end. Curvature of separate parts in different cross-sections over the object length is measured by sequential transfer of curvature gage from cross-section to another one along reference washers, first, at initial flexed state under initial load and, then, at flexure after application of preset extra load curvature of every section corresponding to appropriate bending moment is defined as the difference between curvatures measured at two said strained states of the object. Bending stiffness at design cross-section is defined as the quotient of division of bending moment at section mid cross-section by measured curvature multiplied by correction factor. The latter is predetermined by calculations of known functions of nominal bending stiffness distribution set at tests as the relationship between nominal mean curvature to that at object mid section.

EFFECT: higher accuracy, lower labour input.

2 cl, 4 dwg

FIELD: measuring instrumentation.

SUBSTANCE: invention refers to modelling and can be applied for behaviour modelling for aviation structures and products with uncertain input parameters. Method involves behaviour modelling for aviation structures and products with uncertain input parameters at two levels: at macro level by method of end element modelling, and at micro level by quantum and molecular mechanics methods; first, microscopic samples of the model similar geometrically to standard samples used in mechanical tests are examined and tested by molecular dynamics methods, and obtained mechanical parameters of microscopic samples are used as missing macroscopic parameters in material models for end element modelling; transition from micro to macro level and back is made with the use of scale invariance of mechanical parameters and laws.

EFFECT: increased accuracy of mechanical and operation property tests of developed and reconstructed units and components.

4 dwg

Strength test bench // 2529733

FIELD: aircraft engineering.

SUBSTANCE: test bench comprises device to apply distributed loads to object under test composed by outer limiting shell with lengthwise and crosswise ribs. The latter makes cells to accommodate inflatable resilient bags connected with pressure gages and gas variable pressure feed system, resilient edges being arranged along edges of said cells. Resilient edges have bearing part attached to said ribs, and lug part pressed to tested object by inflatable bags. Said cells have transducer of displacements at ribs, manhole in limiting shell and are equipped with extra gas variable pressure transducer. Said gas variable pressure feed system relieves pressure in bag at pressure drop rate in opposite cell. Height of bearing part and width of lug part of the edge and its thickness are defined experimentally.

EFFECT: higher reliability and accuracy of flight conditions simulation.

1 dwg

FIELD: electricity.

SUBSTANCE: bench for thermal and strength tests contains radiation heaters, auxiliary heaters in the area of the most heat-stressed and heat-consuming areas of a tested object and these heaters are equipped with individual adjustable voltage sources and power load system. The auxiliary heaters are made as contact heaters with resistive elements pressed by electric contacts directly to the electroconductive surface of the most heat-stressed and heat-consuming areas of tested object and one pole of the electric contacts is jointed by the common bus. The resistive elements are made as a double-layer pack of electroconductive particles of high-temperature materials and transient resistance values between them define the total resistance of the resistive element. The pack layer adjoining tested object has larger resistance value, and size of the pack, particles and degree of their compression are defined experimentally.

EFFECT: provision of required temperature for the most heat-stressed and heat-consuming areas of tested object thus ensuring the closest approximation of the test conditions to the actual ones.

1 dwg

FIELD: testing equipment.

SUBSTANCE: bench comprises an oil pump station, electric hydraulic amplifiers, hydraulic cylinders. In the oil pump station of the bench there is an additional high-pressure pump of permanent efficiency of low capacity, connected to a common discharge header, providing for commissioning works separately for each channel of a multi-channel system of loading, regardless of the common loading system with main pumps of high pressure of high capacity.

EFFECT: reduced energy costs and increased manufacturability of tests during commissioning works.

1 dwg

FIELD: measurement technology.

SUBSTANCE: invention refers to measurement equipment and is applied to determine mechanical stress in surface layer of an object. Method involves direction of unfocused visible range radiation flow of any intensity onto the test surface and registration of reflected flow by photodetector, comparison of the result with reference value obtained with known mechanical stress, temperature and surface layer roughness values for this radiation source. Stress gauge includes laser, defocusing devices for beam directed onto the test surface and focusing devices for flow reflected by the surface; photodetector of reflected signal; photodetector signal amplifier; comparator comparing voltage supplied by the amplifier with variable voltage of generator and generating voltage pulse; AND circuit encoding comparator pulse to short pulse string of reference frequency generator; temperature measurement unit; test surface roughness measurement unit; reference code storage device; digital comparator comparing signal obtained from the test surface with reference signals obtained with definite temperature and roughness; indicator displaying stress value for the test surface.

EFFECT: voltage determination in surface layer of examination object.

2 cl, 2 dwg

Strain-gauge sensor // 2530467

FIELD: measuring instrumentation.

SUBSTANCE: strain-gauge sensor includes loading element in the form of a hollow cylinder attached to the monitored object, pieso-optic converter converting tension value in stress-optical element attached in preloaded state into electrical signal, and signal processing unit. Optic axis of pieso-optic converter coincides with the cylinder axis and is perpendicular to measured deformation plane, loading element is a continuous hollow cylinder out of tensile material with wall thickness ensuring required elasticity of loading element in direction of deformations measured and determining sensitivity of strain-gauge sensor sealed at the ends and featuring hard lugs on the outside for attachment of the sensor to a monitored object and transmission of object deformation to stress-optical element.

EFFECT: enhanced functional capabilities of device.

9 cl, 14 dwg

FIELD: measuring instrumentation.

SUBSTANCE: strain-gauge converter includes loading element attached to the monitored object, pieso-optic converter converting tension value in stress-optical element attached in preloaded state into electrical signal, and signal processing unit. Loading element is a plate with cylindrical hole where stress-optical element of cylindrical form is clamped adjustably in direction of measured deformations by two rods made of material with thermal expansion factor larger than respective factor of the plate. Rod length is designed so as to ensure independence of preloading compression from temperature.

EFFECT: enhanced measurement accuracy, simpler device design.

7 cl, 3 dwg

FIELD: construction.

SUBSTANCE: invention relates to the system of "smart" cable for bridge with the use of built-in sensors based on fibre Bragg gratings (FBG) and can be used in cable load-bearing structures of cable, suspension, arched and other types of bridges. System comprises anchor glass, plate for separating wires, connecting clutches, sensor based on fibre diffraction grating and cable itself. Sensor based on fibre diffraction grating comprises strain gauge 9 with fibre diffraction grating and temperature sensor with fibre diffraction grating. The ends of optical fibres of strain gauge 9 and temperature sensor are led outwards. Assembled strain gauge 9 is rigidly connected with the steel wire in the connection coupling. Assembled temperature sensor is suspended on the steel wire in the connection coupling. Openings are punched in the plate to separate wires. Protective steel tube is dipped in advance in the front part into the connecting sleeve and anchor glass.

EFFECT: system improves survival of sensors and optic fibre during manufacture and operation of cable, provides reliable sealing of sensors and permits to transmit signals effectively and accurately from fibre diffraction gratings outward from cable.

11 dwg

FIELD: physics.

SUBSTANCE: problem is solved by designing a fibre-optic pressure sensor, having a housing with two tubular elements, having at least one plugged end, mounted in the housing such that the second end of the first tubular element is connected to the housing and is linked with a channel for feeding working medium, and the second end of the second tubular element is open and linked with the inside of the housing through which is passed an optical fibre with two Bragg gratings, attached by areas with the Bragg gratings directly to the outer cylindrical surface of the tubular elements such that one of the gratings is located on the first tubular element and the second grating is located on the second tubular element. The problem is also solved by mounting the second tubular element to the inner wall of the housing and by mounting the second tubular element to the inner wall of the housing coaxially to the first tubular element. The tubular elements are made of the same material and have identical geometrical dimensions. The problem is also solved directing portions of the optical fibres equipped with Bragg gratings along the edge of the cylindrical surface of the tubular elements. The disclosed design of the fibre-optic pressure sensor enables to solve the problem of quality and reliable measurement of pressure of working medium of remote objects with transmission of information over a fibre-optic link for long-term operation, up to several years, without intermediate maintenance and adjustment procedures.

EFFECT: simple design of a fibre-optic pressure sensor, assembly thereof and avoiding the need to adjust sensor elements thereof during assembly, smaller size of the sensor and high reliability and accuracy of measuring pressure.

6 cl, 3 dwg

FIELD: engines and pumps.

SUBSTANCE: proposed system comprises light source to transmit light onto shaft surface via multiple optic fibres made at multiple points nearby said surface in, in fact, axial direction between the ends of at least one shaft, high-temperature reflection probe built around fibre bundle to detect light reflected from shaft surface and mechanism to measure torque or oscillation at the shaft. The latter comprise coding mechanism composed of changed texture shaped to wedge-like groove on shaft surface of variable depth. Said depth generates the front and rear working point signals so that appropriate time delay can be detected from whatever two positions of said groove for determination of shaft twist angle by differentiation of reflection pattern characteristics during every rotation cycle.

EFFECT: higher precision of measurements.

23 cl, 24 dwg

FIELD: measuring equipment.

SUBSTANCE: invention belongs to fibre-optical sensors and can be used for check and measurement of parameters of voltage. The fibre-optical sensor of spiral structure is the multi-turn spiral element created by a spring wire. The set of a teeth of deformation is continuously distributed on the top surface and the bottom surface of a spring wire in the longitudinal direction along a spring wire; in two adjacent turns of the spring wire the deformation teeth on the bottom surface of the top turn of the spring wire and deformation teeth on the top surface of the bottom turn of the spring wire are arranged in staggered order to each other. An alarm optical fibre is clamped between deformation teeth on the bottom surface of the top wire of the spring wire and deformation teeth on the top surface of the bottom turn of the spring wire and is connected to the test facility by the optical fibre of transfer.

EFFECT: increase of accuracy of measurement.

10 cl, 10 dwg

FIELD: measuring equipment.

SUBSTANCE: invention belongs to area of instrumentation and can be used for creation of distributive systems of measurement of temperature and deformation. The Brillouin system for tracking of temperature and deformation contains one - or bilateral fibre with a set of fibre Bragg gratings (FBG) on different lengths of waves and a laser system with the setting excitation, adjusted in a range essentially bigger, than Brillouin shift. FBG are distributed along the length of the placed fibre and serve as chosen reflectors of length of the wave, allowing to support operation of the device even in case of a rupture of fibre.

EFFECT: increase of accuracy and reliability of these measurements.

7 cl, 4 dwg

FIELD: electricity.

SUBSTANCE: invention is referred to electric cable with in-built strain-gage fit specifically to measure static and dynamic deformations, in particular, bending strain. Method of bending strain control for electric cable includes stages of the cable equipment with peripheral and mechanically unsymmetrical bearing element having higher resistance to tensile loads than to compression ones and with fibre-optical sensor.

EFFECT: invention provides for high duty cables, in particular, in mobile units, controllability and traceability of bending strain area.

9 cl, 15 dwg

FIELD: electricity.

SUBSTANCE: electric cable with strain-gage located longitudinally along the cable and containing strain-gage optical fibre installed in flexible neutral area that surrounds and includes flexible neutral longitudinal axis of the electric cable, and at least two longitudinal structural elements where at least one of at least two longitudinal structural elements represent a core containing electric conductor with strain-gage in-built into filler resistant to strain; it connects at least one of at least two longitudinal structural elements with strain-gage. By means of open cable structure strain endured by at least one of at least two longitudinal structural elements can be transmitted to strain-gage at least in stretched state. In preferred variants of implementation the electric cable represents high-duty cable. Invention is also related to control method of strain and, preferably, temperature of electric cable.

EFFECT: invention is oriented to creation of deformation control system to measure at least stretching strain for several electrical cables and, in particular, several high-duty cables.

30 cl, 12 dwg

FIELD: chemistry.

SUBSTANCE: method includes forming a sensor on an area of probable occurrence of a defect on a structure. The sensor used is a diagnostic coating which consists of a mica pigment and a protective layer of polymer material, which is deposited on the area of probable occurrence of a defect. The layer of mica pigment has thickness of 0.1-0.12 mm and the protective layer of polymer material has thickness of not more than 2 mm. Presence and development of a defect is determined visually from the change in optical properties of the diagnostic coating.

EFFECT: simple method, enabling detection of defects at the onset thereof.

2 cl, 6 dwg

Up!