CN111017238B - Helicopter main rotor dynamic load measuring device and method - Google Patents
Helicopter main rotor dynamic load measuring device and method Download PDFInfo
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- CN111017238B CN111017238B CN201911385222.9A CN201911385222A CN111017238B CN 111017238 B CN111017238 B CN 111017238B CN 201911385222 A CN201911385222 A CN 201911385222A CN 111017238 B CN111017238 B CN 111017238B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
Abstract
The invention discloses a device and a method for measuring the dynamic load of a main rotor of a helicopter, wherein the dynamic load measuring device comprises a dynamic load sensor and a dynamic load signal processor; the dynamic load sensor comprises an elastic body and resistance strain gauges pasted on the elastic body, and the resistance strain gauges form a Wheatstone bridge and are connected with the dynamic load signal processor; and after receiving the signals, the dynamic load signal processor carries out filtering shaping and pre-amplification, then one path of signals is transmitted to an observation end through filtering amplification, and the other path of signals is respectively transmitted to an electromechanical management system and a flight parameter recording system through secondary filtering and AC/DC conversion amplification. The device is high in safety and reliability, the signal processing circuit is an analog circuit, and the device can respond immediately, realizes real-time detection of the change of the dynamic load value borne by the blades in the flight process of the helicopter, feeds the change back to the flight parameter recording system and the electromechanical management system in time, provides reference for the operation of a pilot, and ensures the flight safety.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a device and a method for measuring dynamic load of an active rotor of a helicopter.
Background
The measurement of the dynamic load on the rotor during the flight of a helicopter is of great importance to the flight safety. Because the helicopter has the performance characteristics of hovering, vertical flight, retreating flight, no need of a runway and the like, the applicable range of the aerial three-dimensional operation is wide, and the helicopter is an ideal means for executing special tasks such as earthquake relief and the like. However, the flight of the helicopter has strict limitation on environmental conditions, the power of an engine and the tension of a rotor wing can be reduced due to high air temperature, the requirements on wind direction and wind speed are strict when the helicopter flies in a hovering mode and at a low speed, in addition, the safe flight of the helicopter is influenced by turbulence, cross wind and the like in mountainous areas, and the task site environment such as earthquake relief and the like is often in such complicated weather and terrain. Therefore, it is necessary to acquire some information about the flight of the helicopter to provide the pilot with an operational reference to improve flight safety. The change of the dynamic load value borne by the blade in the flight process of the helicopter is an important index, and in order to obtain the information, a method capable of directly measuring the dynamic load value borne by the blade in the flight process of the helicopter is urgently needed.
Disclosure of Invention
The invention aims to provide a device and a method for measuring the dynamic load of a main rotor of a helicopter, which aim to solve the problem that the dynamic load value borne by a blade in the flying process of the helicopter cannot be directly measured in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme:
a helicopter main rotor dynamic load measuring device comprises a dynamic load sensor and a dynamic load signal processor; the dynamic load sensor comprises an elastic body arranged below the main rotor wing and a plurality of resistance strain gauges pasted on the elastic body, and the resistance strain gauges form a Wheatstone bridge; the fixing frame component is fixed on the elastic body through a countersunk screw, and the socket connector is fixed on the fixing frame component through a bolt; one end of the insulated wire is connected with the Wheatstone bridge through a socket connector, and the other end of the insulated wire is connected with a dynamic load signal processor;
the dynamic load signal processor is arranged in the cabin and comprises a first filter circuit, the input end of the first filter circuit is connected with an onboard power supply, the output end of the first filter circuit is connected with the input end of a voltage stabilizer, the output end of the voltage stabilizer is connected with the input end of a potentiometer, and the output end of the potentiometer is connected with the Wheatstone bridge; the signal input end of the filter shaping circuit is connected with the socket of the connector, the signal output end of the filter shaping circuit is connected with the input end of the pre-amplifying circuit, and the output end of the pre-amplifying circuit is respectively connected with the input end of the filter amplifying circuit and the input end of the second filter circuit; the output end of the filtering amplification circuit is connected with the observation end; the output end of the second filter circuit is connected with the input end of the AC/DC conversion amplifying circuit, the output end of the AC/DC conversion amplifying circuit is respectively connected with the input end of the third filter circuit and the input end of the fourth filter circuit, the output end of the third filter circuit is connected with the flight parameter recording system, and the output end of the fourth filter circuit is connected with the electromechanical management system.
Furthermore, a socket protective cover is arranged at the interface of the connector socket.
Further, the electric resistance strain gauge is coated with a sealant.
Further, the insulated wire is fixed on the elastic body through an adhesive tape.
Further, the elastic body is a booster support after grinding and polishing.
Furthermore, a safety circuit is arranged between the pre-amplifying circuit and the second filter circuit.
Furthermore, the dynamic load signal processor has a calibration function, and a potentiometer is arranged at a position, where parameters need to be adjusted, in a circuit, so that the calibration and adjustment of the natural frequency of an output signal, a sensor excitation voltage and an observation signal are realized.
A method for measuring dynamic load based on the device for measuring the dynamic load of the main rotor of the helicopter comprises the following steps: direct current on the helicopter is subjected to filtering, voltage stabilization and conversion sequentially through a first filter circuit, a voltage stabilizer and a potentiometer and then is supplied to a resistance strain gauge as excitation voltage + Vcc(ii) a The elastic body is correspondingly deformed slightly due to stress, so that the resistance value of the resistance strain gauge adhered to the elastic body is changed; a Wheatstone bridge consisting of resistance strain gauges outputs corresponding voltage signals due to resistance value change; voltage signals are transmitted to the dynamic load signal processor through the socket of the connector assembly and the insulated wire;
voltage signals received by the dynamic load signal processor sequentially enter a filter shaping circuit and a prevention large circuit to carry out filter shaping and pre-amplification treatment; then the signal is divided into two paths, one path of signal enters a filtering and amplifying circuit in sequence, forms an alternating current signal after filtering and amplifying and is sent to an observation end, and the other path of signal enters a second filtering circuit in sequence, and an AC/DC conversion amplifying circuit is filtered and amplified; the voltage signal output by the AC/DC conversion amplifying circuit is divided into two paths, one path enters a third filter circuit and is output to the electromechanical management system after being filtered again, and the other path enters a fourth filter circuit and is output to the flight parameter recording system after being filtered again.
Further, the voltage signal received by the dynamic load signal processor is an alternating current-direct current mixed signal.
Further, direct current on the helicopter is transmitted to components of the dynamic load signal processor after being filtered and stabilized by the first filter circuit and the voltage stabilizer in sequence.
Compared with the prior art, the invention has the following beneficial technical effects:
1. the helicopter main rotor dynamic load measuring device provided by the invention is used for carrying out in-situ replacement after the original components of the helicopter are modified, has small influence on the structural performance and strength of the original components to be negligible, and has the advantages of simple structure and high safety and reliability;
2. the helicopter main rotor dynamic load measuring device adopts the principle of a strain sensor, and a signal processing circuit is an analog circuit, so that the real-time response can be realized, and the dynamic load value on the blade can be monitored in real time;
3. the helicopter main rotor dynamic load measuring device has a calibration function, is convenient for adjusting various signals, has a test function and a security function, and can directly test whether the product function operation is normal or not and monitor whether a dynamic load sensor Wheatstone bridge is broken or not on a helicopter; the application range is wide, and the helicopter can be suitable for various helicopters;
4. the method for measuring the dynamic load of the main rotor of the helicopter realizes real-time detection of the change of the dynamic load value borne by the blades in the flight process of the helicopter, and feeds the change back to the flight parameter recording system and the electromechanical management system in time, so that reference is provided for the operation of a pilot, and the flight safety is guaranteed; and the technical blank of directly measuring the dynamic load change born by the blade in the flight process of the helicopter in China is filled.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a schematic diagram of the helicopter main rotor dynamic load measuring device of the present invention;
FIG. 2 is a schematic structural diagram of the helicopter main rotor dynamic load measuring device of the present invention;
FIG. 3 is a schematic diagram of a structural principle of a dynamic load signal processor of the device for measuring the dynamic load of the main rotor of the helicopter;
FIG. 4 is a schematic diagram of a safety circuit of the helicopter main rotor dynamic load measuring device of the present invention;
in the figure: 1-elastic body, 2-fixing frame component, 3-socket protective cover, 4-connector socket, 5-bolt, 6-gasket, 7-nut, 8-resistance strain gauge, 9-countersunk screw, 10-adhesive tape, 11-sealant, 12-insulated wire, 13-first filter circuit, 14-voltage stabilizer, 15-potentiometer, 16-filter shaping circuit, 17-pre-amplification circuit, 18-filter amplification circuit, 19-second filter circuit, 20-AC/DC conversion amplification circuit, 21-third filter circuit and 22-fourth filter circuit.
Detailed Description
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings. It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict.
The following detailed description is exemplary in nature and is intended to provide further details of the invention. Unless otherwise defined, all technical terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the invention.
As shown in fig. 1, 2 and 3, the device for measuring the dynamic load of the main rotor of the helicopter comprises a dynamic load sensor and a dynamic load signal processor; the dynamic load sensor comprises an elastic body 1 arranged below the main rotor wing and a plurality of resistance strain gauges 8 adhered to the elastic body 1, wherein the resistance strain gauges 8 are used for outputting corresponding electric signals according to micro-strain of the elastic body and responding to dynamic load change sensed by the elastic body, and the resistance strain gauges 8 form a Wheatstone bridge; the dynamic load on the main rotor blade is transferred to a dynamic load sensor through an actuating cylinder, a Wheatstone bridge consisting of resistance strain gauges is pasted on an elastic body of the dynamic load sensor, and a corresponding millivolt-level voltage signal is output to a dynamic load signal processor according to the change of the sensed dynamic load; the fixing frame assembly 2 is fixed on the elastic body 1 through a countersunk screw 9, the socket connector socket 4 is fixed on the fixing frame assembly 2 through a bolt 5, and signals output by the resistance strain gauge on the elastic body 1 are crosslinked to the dynamic load signal processor; one end of an insulated wire 12 is connected with the Wheatstone bridge through a socket connector 4, and the other end is connected with a dynamic load signal processor;
the dynamic load signal processor is arranged in the cabin and comprises a first filter circuit 13, the input end of the first filter circuit 13 is connected with an onboard power supply, the output end of the first filter circuit 13 is connected with the input end of a voltage stabilizer 14, the output end of the voltage stabilizer 14 is connected with the input end of a potentiometer 15, and the output end of the potentiometer 15 is connected with the Wheatstone bridge; the signal input end of the filter shaping circuit 16 is connected with the socket 4 of the connector, the signal output end is connected with the input end of the pre-amplifying circuit 17, and the output end of the pre-amplifying circuit 17 is respectively connected with the input end of the filter amplifying circuit 18 and the input end of the second filter circuit 19; the output end of the filtering amplification circuit 18 is connected with the observation end; the output end of the second filter circuit 19 is connected with the input end of an AC/DC conversion amplifying circuit 20, the output end of the AC/DC conversion amplifying circuit 20 is respectively connected with the input end of a third filter circuit 21 and the input end of a fourth filter circuit 22, the output end of the third filter circuit 21 is connected with a flight parameter recording system, and the output end of the fourth filter circuit 22 is connected with an electromechanical management system.
Further, a socket protective cover 3 is arranged at the interface of the connector socket 4 and plays a role in protecting the socket when the socket is not used.
Furthermore, the electric resistance strain gauge 8 is coated with a sealant 11, so as to play a role in moisture protection, sealing and protection.
Further, the insulated wire 12 is fixed on the elastic body 1 through an adhesive tape 10, and is connected with a wheatstone bridge and a dynamic load signal processor which are formed on the dynamic load sensor body through a socket connector 4, so as to provide excitation voltage for the wheatstone bridge and transmit output signals.
Furthermore, the elastic body 1 is a booster support after polishing, the booster support connected with the helicopter main rotor actuator cylinder is reformed into a sensor and then is installed under the helicopter main rotor in situ, and the sensor is used for sensing the dynamic load change transmitted by the main rotor actuator cylinder and generating corresponding micro-strain.
Further, a crowbar circuit is provided between the preamplifier circuit 17 and the second filter circuit 19.
Furthermore, the dynamic load signal processor has a calibration function, and a potentiometer is arranged at a position, where parameters need to be adjusted, in a circuit, so that the calibration and adjustment of the natural frequency of an output signal, a sensor excitation voltage and an observation signal are realized.
A method for measuring dynamic load based on the device for measuring the dynamic load of the main rotor of the helicopter comprises the following steps: the direct current on the helicopter is filtered, stabilized and converted by a first filter circuit 13, a voltage stabilizer 14 and a potentiometer 15 in sequence and then is provided to a resistance strain gauge 8 as excitation voltage + Vcc(ii) a The elastic body 1 is correspondingly deformed slightly due to stress, so that the resistance value of the resistance strain gauge 8 stuck on the elastic body 1 is changed; a Wheatstone bridge consisting of the resistance strain gauges 8 outputs corresponding voltage signals due to resistance value change; the voltage signal is transmitted to the dynamic load signal processor through the socket connector socket 4 and the insulated wire 12;
voltage signals received by the dynamic load signal processor sequentially enter a filter shaping circuit 16 and a prevention large circuit 17 for filter shaping and pre-amplification treatment; then the signal is divided into two paths, one path of the signal sequentially enters a filtering and amplifying circuit 18, is filtered and amplified to form an alternating current signal and is sent to an observation end, and the other path of the signal sequentially enters a second filtering circuit 19 and an AC/DC conversion amplifying circuit 20, is filtered and is amplified by an AC/DC conversion; the voltage signal output by the AC/DC conversion amplifying circuit 20 is divided into two paths, one path enters the third filter circuit 21 and is filtered again to be output to the electromechanical management system, and the other path enters the fourth filter circuit 22 and is filtered again to be output to the flight parameter recording system.
Further, the voltage signal received by the dynamic load signal processor is an alternating current-direct current mixed signal.
Further, direct current on the helicopter is filtered and stabilized by the first filter circuit 13 and the voltage stabilizer 14 in sequence and then is transmitted to components of the dynamic load signal processor.
To further illustrate the technical solutions of the present application, the following embodiments are further described below:
the dynamic load sensor is arranged below the main rotor wing and connected with the main rotor wing through the actuator cylinder, the dynamic load amplitude on the main rotor wing can be transmitted to the elastic body 1 through the actuator cylinder, and the elastic body 1 is a booster support. The booster support (elastic body 1) is correspondingly deformed slightly due to stress, and then the resistance value of a sensitive element (a resistance strain gauge 8) adhered to the inclined wall of the booster support is changed. Under the condition that the dynamic load signal processor provides excitation voltage, a Wheatstone bridge consisting of the resistance strain gauges 8 outputs corresponding voltage signals due to resistance value change to realize measurement of the dynamic load amplitude on the blades of the main rotor, and the main rotor rotates at a natural frequency during normal work, so that the signals are AC/DC mixed signals, the magnitude of the signals is millivolt level, and the signals are transmitted to the dynamic load signal processor through the connector socket 4 and the insulated wire 12. The dynamic load measuring signal processor is arranged in a helicopter cabin, after +28VDC direct current on the helicopter enters the dynamic load measuring signal processor, the stable +12VDC direct current power is output after filtering and voltage stabilization, components of the dynamic load signal processor are supplied with the power voltage, and after the +12VDC voltage is converted into +4.15VDC voltage, the power voltage is supplied to the dynamic load sensor to be used as excitation voltage (+ V)cc). After the composite signal output by the dynamic load sensor is transmitted to the dynamic load signal processor, filtering, shaping and pre-amplifying processing are firstly carried out, one path of the alternating current signal output by pre-amplifying forms a 0 VDC-2 VDC alternating current signal after secondary amplification, and the alternating current signal is sent to an observation end; and the other path outputs a 0 VDC-4 VDC direct-current voltage signal to an electromechanical management system and a flight parameter recording system after filtering, AC/DC conversion and secondary amplification.
As shown in FIG. 4, the device for measuring the dynamic load of the main rotor of the helicopter has a safety function, a safety circuit is designed by adopting the principle of a comparator, and when any one bridge arm in a dynamic load sensor is disconnected, two paths of direct current signals are output to be less than or equal to 0V. A threshold voltage is set at the positive end (pin 3 of IC 3) of an operational amplifier through resistance voltage division, when a sensor works normally, the pin 3 voltage of the operational amplifier IC3 is larger than the pin 2 voltage, a diode D3 is cut off, when one or more arbitrary places in a sensor bridge are broken, the pin 3 voltage of the operational amplifier IC3 is larger than the pin 2 voltage, a voltage comparator outputs a low level, and D3 is conducted, because the resistance value of the input end (pin 5 of IC 3) of the operational amplifier of a rear end circuit is infinite and the output end is close to 0, the direct current voltage output by a peak detection circuit built by IC2 and peripheral devices is counteracted by the low level, the current does not flow to the rear end any more and flows to the voltage comparator, so that the rear end outputs a signal not larger than 0V, and an alarm effect is achieved.
The dynamic load measuring device is further designed with a calibration function, the output signals, the test signals, the sensor excitation voltage, the observation signals, the inherent frequency of the test function and the like of the product can be adjusted, the device can be applied to a wider range, and powerful help is provided for flight safety guarantee of more models.
When the method is used for testing, the vibration frequency of the main rotor wing is simulated by setting the oscillator, an alternating current voltage signal output by the sensor is simulated by taking 21Hz of a certain helicopter as an example, the signal is added to the output end of the dynamic load sensor after being filtered and shaped, and a direct current voltage signal with the voltage of 2VDC is output to the flight parameter recording system and the electromechanical management system after being amplified, filtered and AC/DC converted, so that whether the dynamic load measuring device has normal function or not can be judged according to the voltage value.
It will be appreciated by those skilled in the art that the invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The embodiments disclosed above are therefore to be considered in all respects as illustrative and not restrictive. All changes which come within the scope of or equivalence to the invention are intended to be embraced therein.
Claims (6)
1. A method for measuring dynamic load of a device for measuring dynamic load of a main rotor of a helicopter is characterized by comprising the following steps: direct current on the helicopter is filtered, stabilized and converted by a first filter circuit (13), a voltage stabilizer (14) and a potentiometer (15) in sequence and then is provided to a resistance strain gauge (8) to serve as excitation voltage + Vcc(ii) a The elastic body (1) is stressed to deform slightly, so that the resistance value of the resistance strain gauge (8) adhered to the elastic body (1) changes; a Wheatstone bridge consisting of the resistance strain gauges (8) outputs corresponding voltage signals due to resistance value change; voltage signals are transmitted to the dynamic load signal processor through the socket connector socket (4) and the insulated lead (12);
voltage signals received by the dynamic load signal processor sequentially enter a filter shaping circuit (16) and a prevention large circuit (17) for filter shaping and pre-amplification treatment; then the signal is divided into two paths, one path of the signal sequentially enters a filtering and amplifying circuit (18) to form an alternating current signal after filtering and amplifying and then is sent to an observation end, and the other path of the signal sequentially enters a second filtering circuit (19) and an AC/DC conversion amplifying circuit (20) to be filtered and AC/DC conversion amplified; the voltage signal output by the AC/DC conversion amplifying circuit (20) is divided into two paths, one path enters a third filter circuit (21) and is filtered again to be output to the electromechanical management system, and the other path enters a fourth filter circuit (22) and is filtered again to be output to the flight parameter recording system;
the voltage signal received by the dynamic load signal processor is an alternating current-direct current mixed signal;
direct current on the helicopter is filtered and stabilized by a first filter circuit (13) and a voltage stabilizer (14) in sequence and then is transmitted to components of a dynamic load signal processor;
the helicopter main rotor dynamic load measuring device comprises a dynamic load sensor and a dynamic load signal processor; the dynamic load sensor comprises an elastic body (1) arranged below the main rotor wing and a plurality of resistance strain gauges (8) adhered to the elastic body (1), wherein the resistance strain gauges (8) form a Wheatstone bridge; the fixing frame component (2) is fixed on the elastic body (1) through a sunk screw (9), and the socket connector socket (4) is fixed on the fixing frame component (2) through a bolt (5); one end of an insulated wire (12) is connected with the Wheatstone bridge through a socket connector (4), and the other end of the insulated wire is connected with a dynamic load signal processor;
the dynamic load signal processor is arranged in the cabin and comprises a first filter circuit (13), the input end of the first filter circuit (13) is connected with an onboard power supply, the output end of the first filter circuit is connected with the input end of a voltage stabilizer (14), the output end of the voltage stabilizer (14) is connected with the input end of a potentiometer (15), and the output end of the potentiometer (15) is connected with the Wheatstone bridge; the signal input end of the filter shaping circuit (16) is connected with the socket connector (4), the signal output end is connected with the input end of the pre-amplifying circuit (17), and the output end of the pre-amplifying circuit (17) is respectively connected with the input end of the filter amplifying circuit (18) and the input end of the second filter circuit (19); the output end of the filtering amplification circuit (18) is connected with the observation end; the output end of the second filter circuit (19) is connected with the input end of an AC/DC conversion amplifying circuit (20), the output end of the AC/DC conversion amplifying circuit (20) is respectively connected with the input end of a third filter circuit (21) and the input end of a fourth filter circuit (22), the output end of the third filter circuit (21) is connected with a flight parameter recording system, and the output end of the fourth filter circuit (22) is connected with an electromechanical management system;
the elastic body (1) is a booster support which is polished.
2. Method according to claim 1, characterized in that a socket protection cover (3) is provided at the interface of the connector socket (4).
3. Method according to claim 1, characterized in that the resistive strain gauge (8) is coated with a sealant (11).
4. Method according to claim 1, characterized in that the insulated conductor (12) is fixed to the elastomer body (1) by means of a tape (10).
5. A method according to claim 1, characterized in that a crowbar circuit is provided between the pre-amplifying circuit (17) and the second filter circuit (19).
6. The method according to claim 1, wherein the dynamic load signal processor has a calibration function, and the calibration and adjustment of the natural frequency of the output signal, the sensor excitation voltage and the observation signal are realized by arranging a potentiometer at a position in the circuit where a parameter needs to be adjusted.
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| CN201911385222.9A CN111017238B (en) | 2019-12-28 | 2019-12-28 | Helicopter main rotor dynamic load measuring device and method |
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| CN201911385222.9A CN111017238B (en) | 2019-12-28 | 2019-12-28 | Helicopter main rotor dynamic load measuring device and method |
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| CN103693211A (en) * | 2013-12-25 | 2014-04-02 | 北京航天测控技术有限公司 | Test method for helicopter rotating part signal and wireless collecting device therefor |
| GB201512607D0 (en) * | 2015-07-17 | 2015-08-26 | Airbus Operations Ltd | Calibration of transducers |
| RU2599108C1 (en) * | 2015-07-07 | 2016-10-10 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Method of monitoring loads and accumulated fatigue damage in operating conditions of aircraft |
| CN107933957A (en) * | 2017-12-21 | 2018-04-20 | 中国人民解放军总参谋部第六十研究所 | A kind of unmanned helicopter blade aerodynamic load flight actual measurement system and its measurement method |
| CN110371320A (en) * | 2019-08-07 | 2019-10-25 | 山东交通学院 | A kind of device, method and application for testing revolution speed of propeller, lift and noise |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103693211A (en) * | 2013-12-25 | 2014-04-02 | 北京航天测控技术有限公司 | Test method for helicopter rotating part signal and wireless collecting device therefor |
| RU2599108C1 (en) * | 2015-07-07 | 2016-10-10 | Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") | Method of monitoring loads and accumulated fatigue damage in operating conditions of aircraft |
| GB201512607D0 (en) * | 2015-07-17 | 2015-08-26 | Airbus Operations Ltd | Calibration of transducers |
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| CN110371320A (en) * | 2019-08-07 | 2019-10-25 | 山东交通学院 | A kind of device, method and application for testing revolution speed of propeller, lift and noise |
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