CN108021122B - Vibration test fault diagnosis method for aircraft engine - Google Patents

Vibration test fault diagnosis method for aircraft engine Download PDF

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Publication number
CN108021122B
CN108021122B CN201711317696.0A CN201711317696A CN108021122B CN 108021122 B CN108021122 B CN 108021122B CN 201711317696 A CN201711317696 A CN 201711317696A CN 108021122 B CN108021122 B CN 108021122B
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core wire
sensor
circuit board
gear
sub
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CN108021122A (en
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王国鹏
姜凤
杜文川
赵宇
杨天南
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AECC Shenyang Liming Aero Engine Co Ltd
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AECC Shenyang Liming Aero Engine Co Ltd
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    • GPHYSICS
    • G05CONTROLLING; REGULATING
    • G05BCONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00Testing or monitoring of control systems or parts thereof
    • G05B23/02Electric testing or monitoring
    • G05B23/0205Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
    • G05B23/0218Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
    • G05B23/0221Preprocessing measurements, e.g. data collection rate adjustment; Standardization of measurements; Time series or signal analysis, e.g. frequency analysis or wavelets; Trustworthiness of measurements; Indexes therefor; Measurements using easily measured parameters to estimate parameters difficult to measure; Virtual sensor creation; De-noising; Sensor fusion; Unconventional preprocessing inherently present in specific fault detection methods like PCA-based methods

Abstract

The invention provides a vibration test fault diagnosis method for an aircraft engine, and relates to the technical field of vibration tests of aircraft engine structural members. The method adopts a resistance characteristic fault diagnosis module to realize fault diagnosis on the magnetoelectric type speed sensor as the sensor at the front end of the vibration test system, and adopts a capacitance characteristic fault diagnosis module to realize fault diagnosis on the piezoelectric type vibration acceleration sensor as the sensor at the front end of the vibration test system. According to the method for diagnosing the faults of the vibration test of the aircraft engine, the flow of fault elimination is solidified in a circuit system through digital logic judgment of the circuit board, the existing fault elimination method with low efficiency and poor accuracy through replacement of a low-noise cable mode and the like is improved, the occupied time is greatly saved, and the confidence coefficient of fault diagnosis is improved.

Description

Vibration test fault diagnosis method for aircraft engine
Technical Field
The invention relates to the technical field of vibration testing of aircraft engine structural members, in particular to a vibration testing fault diagnosis method for an aircraft engine.
Background
In the operation process of an aircraft engine, a vibration test system is required to monitor the vibration characteristics of the whole aircraft engine so as to ensure the working reliability of the engine, so that the operating state of a vibration sensor, which is a core component in the vibration test system, is a key concern, and the vibration sensors used in the existing engines are divided into two types, namely a resistance type vibration sensor and a capacitance type vibration sensor. At present, the fault of the engine vibration test system is mainly judged by manually checking a vibration sensor, and a voltmeter is used for checking a sensor circuit or an electromagnetic vibration table to excite the sensor to judge whether response output meets requirements. The operation processes are relatively complex, professional technicians are needed to judge results, the efficiency is low, and the consumed time is long.
Disclosure of Invention
Aiming at the defects of the prior art, the invention provides a method for diagnosing vibration test faults of an aero-engine.
On one hand, the invention provides a vibration test fault diagnosis device for an aircraft engine, which comprises a power supply, a power switch, a resistance characteristic fault diagnosis module and a capacitance characteristic fault diagnosis module; the resistance characteristic fault diagnosis module comprises a first indicator lamp group, a first connecting plug, a first gear switch and a first logic judgment circuit board; the capacitance characteristic fault diagnosis module comprises a second indicator lamp group, a second connecting plug, a second gear switch, a second logic judgment circuit board and a gear shifting switch; the input end of the first logic judgment circuit board is connected with a magnetoelectric type speed sensor at the front end of the vibration test system through a first connecting plug, and the input end of the second logic judgment circuit board is connected with a piezoelectric type vibration acceleration sensor at the front end of the vibration test system through a shift switch and a second connecting plug in sequence; the first gear switch is connected with the input end of the first logic judgment circuit board, and the second gear switch is connected with the input end of the second logic judgment circuit board; the output end of the first logic judgment circuit board is connected with the first indicator lamp group, and the output end of the second logic judgment circuit board is connected with the second indicator lamp group.
Preferably, the first logic judgment circuit board comprises three sub-circuits, the first indicator light group comprises four indicator lights, the first indicator light and the second indicator light are both connected with the output end of the first sub-circuit in the first logic judgment circuit board, the third indicator light is connected with the output end of the second sub-circuit in the first logic judgment circuit board, and the fourth indicator light is connected with the output end of the third sub-circuit in the first logic judgment circuit board; the second logic judgment circuit board comprises five sub-circuits, the second indicator light group comprises five indicator lights, and the five indicator lights are respectively connected with the output ends of the five sub-circuits in the second logic judgment circuit board.
Preferably, the first gear switch includes four gears respectively connected to the input terminals of the three sub-circuits in the first logic judgment circuit board, wherein the first gear and the second gear are connected to the first sub-circuit in the first logic judgment circuit board, the third gear is connected to the second sub-circuit in the first logic judgment circuit board, and the fourth gear is connected to the third sub-circuit in the first logic judgment circuit board; the second gear switch comprises five gears which are respectively connected with the input ends of the five sub-circuits in the second logic judgment circuit board.
Preferably, the gear shifting switch comprises three gears; the input end of the first gear is connected with a core wire I and a core wire II of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug, and the output end of the first gear is connected with a first sub-circuit of the second logic judgment circuit board; the input end of a second gear of the gear shifting switch is connected with a core wire II and a ground wire of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug, and the output end of the second gear is connected with a second sub circuit of the second logic judgment circuit board; the third gear of the gear shifting switch is neutral.
Preferably, the aircraft engine vibration test fault diagnosis device further comprises a chassis; the power supply, the first logic judgment circuit board and the second logic judgment circuit board are all arranged in the case; the first indicator lamp group, the second indicator lamp group, the first connecting plug, the second connecting plug, the first gear switch and the second gear switch are all arranged on the front side face of the case.
On the other hand, the invention also provides a method for diagnosing the vibration test fault of the aero-engine by adopting the vibration test fault diagnosis device of the aero-engine, which comprises the following steps:
step 1: selecting a resistance characteristic fault diagnosis module or a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to carry out fault diagnosis according to the type of a front-end sensor of the vibration test system; if the front end sensor of the vibration test system is a magnetoelectric speed sensor, executing the step 2, and using a resistance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to diagnose faults; if the front end sensor of the vibration test system is a piezoelectric vibration acceleration sensor, executing the step 3, and using a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to perform fault diagnosis;
step 2: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the resistance characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a first connecting plug position of the vibration testing fault diagnosis device of the aero-engine, and turning on a power switch of the vibration testing fault diagnosis device of the aero-engine;
rotating the first gear switch, sequentially rotating to four gears, triggering a first logic judgment circuit board to test the resistance of an output end core wire I, a core wire II and a ground wire of a sensor at the front end of the vibration test system, and judging whether the core wire I, the core wire II and the ground wire of the output end of the sensor are connected or not according to the indication condition of a first indication lamp group;
and step 3: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the capacitive characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a second connecting plug of the vibration testing fault diagnosis device of the aircraft engine, and turning on a power switch of the vibration testing fault diagnosis device of the aircraft engine;
and rotating the second gear switch to five gear positions in sequence, and matching with the rotating gear shifting switch to touch the second logic judgment circuit board to test the capacitance of the output end core wire I, the core wire II and the ground wire of the front end sensor of the vibration test system, and judging whether the output end core wire I, the core wire II and the ground wire of the sensor are connected or not according to the indication condition of the second indicator lamp set.
Preferably, the specific method for testing the resistances of the core wire I, the core wire II and the ground wire of the output end of the sensor at the front end of the vibration testing system in the step 2 is as follows:
rotating the first gear switch to a gear I, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the lower limit of the resistance characteristic of a first sub-circuit test front-end sensor of the circuit board is less than 10 ohms or not through a first logic; if the signal is smaller than the preset value, the core wire I and the core wire II are connected, the first logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator lamp of a first indicator lamp group is lightened, otherwise, the first indicator lamp of the first indicator lamp group is not lightened, and the signal wire I and the signal wire II of the sensor corresponding to the core wire I and the core wire II have faults and need to be subjected to fault removal processing;
rotating the first gear switch to a gear II, checking the resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the upper limit of the resistance characteristic of the interior of the front-end sensor is greater than 50M ohm or not by a first logic when a first sub-circuit of the circuit board tests; if the signal is greater than the preset value, the first logic judges that a first sub circuit of the circuit board outputs a signal, a second indicator light of the first indicator light group is lightened, otherwise, the second indicator light of the first indicator light group is not lightened, and the signal line I and the signal line II of the sensor corresponding to the core wire I and the core wire II are in fault, and fault removal processing is required;
rotating the first gear switch to a III gear, checking the resistance values of an output end core wire II and a ground wire of a front end sensor of the vibration test system, judging whether the upper limit of the resistance characteristics of the output end core wire II and the ground wire of the front end sensor is larger than 50M ohm or not through a second sub circuit of the first logic, if so, indicating that the core wire II is insulated from the ground wire, judging that a second sub circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a third indicator lamp of the first indicator lamp group is lightened, otherwise, indicating that the signal wire II and the ground wire of the sensor corresponding to the core wire II and the ground wire have faults, and needing to carry out fault removal treatment;
rotating the first gear switch to an IV gear, checking the resistance values of an output end core wire I and a ground wire of a front end sensor of the vibration testing system, judging whether the resistance characteristics of the output end core wire I and the ground wire of the front end sensor are larger than 50M ohm or not through a third sub-circuit of the first logic judgment circuit board, if so, indicating that the core wire I is insulated from the ground wire, judging that a third sub-circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a fourth indicator lamp of the first indicator lamp group is turned on, otherwise, indicating that the signal wire I and the ground wire of the sensor corresponding to the core wire I and the ground wire have faults, and needing to carry out fault removal processing.
Preferably, the specific method for testing the capacitances of the core line I, the core line II and the ground line at the output end of the sensor at the front end of the vibration testing system in step 3 is as follows:
rotating a second gear switch to a position of a first gear, shifting the gear switch to a first gear, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration testing system, and judging the on-off of the output end core wire I and the core wire II of the front-end sensor of the vibration testing system through a first sub-circuit of a second logic judgment circuit board; if the resistance values of the core wire I and the core wire II are less than 10 ohms, the core wire I and the core wire II are in a path, the second logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator light of the second indicator light group is lightened, otherwise, the first indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating a second gear switch to a gear II, shifting the gear switch to a second gear, checking the resistance values of a core wire II and a ground wire of the output end of the front-end sensor of the vibration test system, and judging the on-off of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system through a second sub-circuit of a second logic judgment circuit board; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that a second sub circuit of the circuit board outputs signals, a second indicator lamp of a second indicator lamp group is lightened, otherwise, the second indicator lamp of the second indicator lamp group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire;
rotating the second gear switch to a gear III, shifting the gear switch to a neutral position, checking the resistance values of a core wire I and a core wire II of the output end of the front-end sensor of the vibration testing system, and judging the insulation condition between the core wire I and the core wire II of the output end of the front-end sensor of the vibration testing system by a third sub-circuit of the circuit board through a second logic; if the resistance values of the core wire I and the core wire II are more than 50M ohms, the core wire I and the core wire II are insulated, the second logic judges that a third sub-circuit of the circuit board outputs signals, and a third indicator light of the second indicator light group is lightened, otherwise, the third indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating the second gear switch to the IV gear, shifting the gear switch to the neutral position, checking the resistance values of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system by a fourth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire I and the ground wire is larger than 50M ohm, the core wire I and the ground wire are insulated, the second logic judges that a fourth sub circuit of the circuit board outputs a signal, a fourth indicator light of the second indicator light group is lightened, otherwise, the fourth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the ground wire;
rotating the second gear switch to a V gear, shifting the gear switch to a neutral position, checking the resistance values of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system by a fifth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that the fifth sub-circuit of the circuit board outputs signals, the fifth indicator light of the second indicator light group is lightened, otherwise, the fifth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire.
According to the technical scheme, the invention has the beneficial effects that: according to the method for diagnosing the faults of the vibration test of the aircraft engine, the digital circuit logic judgment circuit board is adopted to solidify the troubleshooting process in the circuit system, and the judgment conclusion of the faults is displayed in real time through the indicator lamp, so that the existing troubleshooting method with low efficiency and poor accuracy in a low-noise cable replacement mode is improved, the occupied time is greatly saved, and the confidence coefficient of fault diagnosis is improved.
Drawings
Fig. 1 is a schematic structural diagram of a chassis of an aircraft engine vibration test fault diagnosis device provided in an embodiment of the present invention;
fig. 2 is a schematic diagram of a connection structure between a resistance characteristic fault diagnosis module and an output end of a magnetoelectric speed sensor at a front end of a vibration test system according to an embodiment of the present invention;
fig. 3 is a schematic diagram of a connection structure between a capacitive characteristic fault diagnosis module and an output end of a piezoelectric velocity sensor at a front end of a vibration testing system according to an embodiment of the present invention;
fig. 4 is a schematic view of a connection structure between a position switch and a piezoelectric speed sensor according to an embodiment of the present invention.
In the figure: 1. a power switch; 2. a first connection plug; 3. a first gear switch; 4. a first indicator light set; 5. a second connection plug; 6. a second gear switch; 7. a second indicator light set; and 8, a chassis.
Detailed Description
The following detailed description of embodiments of the present invention is provided in connection with the accompanying drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.
In this embodiment, all the engine vibration test systems of the 12# test run rack and the 5# test run rack of a certain aircraft engine factory are taken as an example, and the vibration test system is subjected to fault diagnosis by using the aircraft engine vibration test fault diagnosis device and the diagnosis method of the present invention.
The invention provides a vibration test fault diagnosis device for an aircraft engine, which comprises a case 8, a power supply, a power switch 1, a resistance characteristic fault diagnosis module and a capacitance characteristic fault diagnosis module. The resistance characteristic fault diagnosis module comprises a first indicator lamp group 4, a first connecting plug 2, a first gear switch 3 and a first logic judgment circuit board. The capacitance characteristic fault diagnosis module comprises a second indicator lamp group 7, a second connecting plug 5, a second gear switch 6, a second logic judgment circuit board and a second gear shifting switch. The power supply, the first logic judgment circuit board and the second logic judgment circuit board are all arranged in the case 8; the first indicator light group 4, the second indicator light group 7, the first connecting plug 2, the second connecting plug 5, the first gear switch 3 and the second gear switch 6 are all arranged on the front side surface of the case 8, as shown in fig. 1. The first logic judgment circuit board comprises three sub-circuits, the first indicator lamp group 4 comprises four indicator lamps, the first gear switch 3 comprises four gears, the second logic judgment circuit board comprises five sub-circuits, the second indicator lamp group 7 comprises five indicator lamps, and the second gear switch 6 comprises five gears.
The connection between the resistance characteristic fault diagnosis module and the output end of the magnetoelectric speed sensor at the front end of the vibration test system is shown in fig. 2, and the input end of the first logic judgment circuit board is connected with the magnetoelectric speed sensor at the front end of the vibration test system through a first connection plug 2; four gears of the first gear switch are respectively connected with input ends of three sub-circuits in the first logic judgment circuit board, wherein the first gear and the second gear are connected with a first sub-circuit in the first logic judgment circuit board, the third gear is connected with a second sub-circuit in the first logic judgment circuit board, the fourth gear is connected with a third sub-circuit in the first logic judgment circuit board, and an output end of the first logic judgment circuit board is connected with the first indicator lamp group 4. The first indicator light and the second indicator light are connected with the output end of a first sub-circuit in the first logic judgment circuit board, the third indicator light is connected with the output end of a second sub-circuit in the first logic judgment circuit board, and the fourth indicator light is connected with the output end of a third sub-circuit in the first logic judgment circuit board.
The connection of the capacitance characteristic fault diagnosis module and the output end of the piezoelectric type speed sensor at the front end of the vibration test system is shown in fig. 3, the input end of the second logic judgment circuit board is connected with the piezoelectric type vibration acceleration sensor at the front end of the vibration test system sequentially through the shift switch and the second connecting plug 5, five gears of the second shift switch 6 are respectively connected with the input ends of five sub-circuits of the second logic judgment circuit board, and the output end of the second logic judgment circuit board is connected with the second indicator lamp group 7. And the five indicator lights of the second indicator light group are respectively connected with the output ends of the five sub-circuits in the second logic judgment circuit board.
The shift switch comprises three gears, as shown in fig. 4, an input end of a first gear is connected with a core wire I and a core wire II of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug 5, and an output end of the first gear is connected with a first sub-circuit of the second logic judgment circuit board. The input end of the second gear is connected with a core wire II and a ground wire of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug 5, and the output end of the second gear is connected with a second sub-circuit of the second logic judgment circuit board; the third gear is neutral.
The diagnosis method for the vibration test fault of the aero-engine by adopting the vibration test fault diagnosis device of the aero-engine comprises the following steps:
step 1: selecting a resistance characteristic fault diagnosis module or a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to carry out fault diagnosis according to the type of a front-end sensor of the vibration test system; if the front end sensor of the vibration test system is a magnetoelectric speed sensor, executing the step 2, and using a resistance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to diagnose faults; if the front end sensor of the vibration test system is a piezoelectric vibration acceleration sensor, executing the step 3, and using a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to perform fault diagnosis;
step 2: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the resistance characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a first connecting plug position of the vibration testing fault diagnosis device of the aero-engine, and turning on a power switch of the vibration testing fault diagnosis device of the aero-engine;
rotating the first gear switch to a gear I, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the lower limit of the resistance characteristic of a first sub-circuit test front-end sensor of the circuit board is less than 10 ohms or not through a first logic; if the signal is smaller than the preset value, the core wire I and the core wire II are connected, the first logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator lamp of a first indicator lamp group is lightened, otherwise, the first indicator lamp of the first indicator lamp group is not lightened, and the signal wire I and the signal wire II of the sensor corresponding to the core wire I and the core wire II have faults and need to be subjected to fault removal processing;
rotating the first gear switch to a gear II, checking the resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the upper limit of the resistance characteristic of the interior of the front-end sensor is greater than 50M ohm or not by a first logic when a first sub-circuit of the circuit board tests; if the signal is greater than the preset value, the first logic judges that a first sub circuit of the circuit board outputs a signal, a second indicator light of the first indicator light group is lightened, otherwise, the second indicator light of the first indicator light group is not lightened, and the signal line I and the signal line II of the sensor corresponding to the core wire I and the core wire II are in fault, and fault removal processing is required;
rotating the first gear switch to a III gear, checking the resistance values of an output end core wire II and a ground wire of a front end sensor of the vibration test system, judging whether the upper limit of the resistance characteristics of the output end core wire II and the ground wire of the front end sensor is larger than 50M ohm or not through a second sub circuit of the first logic, if so, indicating that the core wire II is insulated from the ground wire, judging that a second sub circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a third indicator lamp of the first indicator lamp group is lightened, otherwise, indicating that the signal wire II and the ground wire of the sensor corresponding to the core wire II and the ground wire have faults, and needing to carry out fault removal treatment;
rotating the first gear switch to an IV gear, checking the resistance values of an output end core wire I and a ground wire of a front end sensor of the vibration testing system, judging whether the resistance characteristics of the output end core wire I and the ground wire of the front end sensor are larger than 50M ohm or not through a third sub-circuit of the first logic judgment circuit board, if so, indicating that the core wire I is insulated from the ground wire, judging that a third sub-circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a fourth indicator lamp of the first indicator lamp group is turned on, otherwise, indicating that the signal wire I and the ground wire of the sensor corresponding to the core wire I and the ground wire have faults, and needing to carry out fault removal processing.
And step 3: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the capacitive characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a second connecting plug of the vibration testing fault diagnosis device of the aircraft engine, and turning on a power switch of the vibration testing fault diagnosis device of the aircraft engine;
the specific method for testing the capacitance of the core wire I and the core wire II of the output end of the sensor at the front end of the vibration testing system and the capacitance of the ground wire comprises the following steps:
rotating a second gear switch to a position of a first gear, shifting the gear switch to a first gear, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration testing system, and judging the on-off of the output end core wire I and the core wire II of the front-end sensor of the vibration testing system through a first sub-circuit of a second logic judgment circuit board; if the resistance values of the core wire I and the core wire II are less than 10 ohms, the core wire I and the core wire II are in a path, the second logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator light of the second indicator light group is lightened, otherwise, the first indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating a second gear switch to a gear II, shifting the gear switch to a second gear, checking the resistance values of a core wire II and a ground wire of the output end of the front-end sensor of the vibration test system, and judging the on-off of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system through a second sub-circuit of a second logic judgment circuit board; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that a second sub circuit of the circuit board outputs signals, a second indicator lamp of a second indicator lamp group is lightened, otherwise, the second indicator lamp of the second indicator lamp group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire;
rotating the second gear switch to a gear III, shifting the gear switch to a neutral position, checking the resistance values of a core wire I and a core wire II of the output end of the front-end sensor of the vibration testing system, and judging the insulation condition between the core wire I and the core wire II of the output end of the front-end sensor of the vibration testing system by a third sub-circuit of the circuit board through a second logic; if the resistance values of the core wire I and the core wire II are more than 50M ohms, the core wire I and the core wire II are insulated, the second logic judges that a third sub-circuit of the circuit board outputs signals, and a third indicator light of the second indicator light group is lightened, otherwise, the third indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating the second gear switch to the IV gear, shifting the gear switch to the neutral position, checking the resistance values of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system by a fourth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire I and the ground wire is larger than 50M ohm, the core wire I and the ground wire are insulated, the second logic judges that a fourth sub circuit of the circuit board outputs a signal, a fourth indicator light of the second indicator light group is lightened, otherwise, the fourth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the ground wire;
rotating the second gear switch to a V gear, shifting the gear switch to a neutral position, checking the resistance values of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system by a fifth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that the fifth sub-circuit of the circuit board outputs signals, the fifth indicator light of the second indicator light group is lightened, otherwise, the fifth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit of the corresponding technical solutions and scope of the present invention as defined in the appended claims.

Claims (3)

1. A vibration test fault diagnosis method for an aircraft engine is realized based on a vibration test fault diagnosis device for the aircraft engine, wherein the device comprises a power supply, a power switch, a resistance characteristic fault diagnosis module and a capacitance characteristic fault diagnosis module; the resistance characteristic fault diagnosis module comprises a first indicator lamp group, a first connecting plug, a first gear switch and a first logic judgment circuit board; the capacitance characteristic fault diagnosis module comprises a second indicator lamp group, a second connecting plug, a second gear switch, a second logic judgment circuit board and a gear shifting switch; the input end of the first logic judgment circuit board is connected with a magnetoelectric type speed sensor at the front end of the vibration test system through a first connecting plug, and the input end of the second logic judgment circuit board is connected with a piezoelectric type vibration acceleration sensor at the front end of the vibration test system through a shift switch and a second connecting plug in sequence; the first logic judgment circuit board comprises three sub-circuits, the first indicator lamp group comprises four indicator lamps, the first indicator lamp and the second indicator lamp are both connected with the output end of the first sub-circuit in the first logic judgment circuit board, the third indicator lamp is connected with the output end of the second sub-circuit in the first logic judgment circuit board, and the fourth indicator lamp is connected with the output end of the third sub-circuit in the first logic judgment circuit board; the second logic judgment circuit board comprises five sub-circuits, the second indicator lamp group comprises five indicator lamps, and the five indicator lamps are respectively connected with the output ends of the five sub-circuits in the second logic judgment circuit board; the first gear switch is connected with the input end of the first logic judgment circuit board, and the second gear switch is connected with the input end of the second logic judgment circuit board; the output end of the first logic judgment circuit board is connected with the first indicator lamp group, and the output end of the second logic judgment circuit board is connected with the second indicator lamp group; the first gear switch comprises four gears which are respectively connected with the input ends of three sub-circuits in the first logic judgment circuit board, wherein the first gear and the second gear are connected with the first sub-circuit in the first logic judgment circuit board, the third gear is connected with the second sub-circuit in the first logic judgment circuit board, and the fourth gear is connected with the third sub-circuit in the first logic judgment circuit board; the second gear switch comprises five gears which are respectively connected with the input ends of the five sub-circuits in the second logic judgment circuit board; the gear shifting switch comprises three gears; the input end of the first gear is connected with a core wire I and a core wire II of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug, and the output end of the first gear is connected with a first sub-circuit of the second logic judgment circuit board; the input end of a second gear of the gear shifting switch is connected with a core wire II and a ground wire of a piezoelectric vibration acceleration sensor at the front end of the vibration test system through a second connecting plug, and the output end of the second gear is connected with a second sub circuit of the second logic judgment circuit board; the third gear of the gear shifting switch is a neutral gear;
the method is characterized in that: the method comprises the following steps:
step 1: selecting a resistance characteristic fault diagnosis module or a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to carry out fault diagnosis according to the type of a front-end sensor of the vibration test system; if the front end sensor of the vibration test system is a magnetoelectric speed sensor, executing the step 2, and using a resistance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to diagnose faults; if the front end sensor of the vibration test system is a piezoelectric vibration acceleration sensor, executing the step 3, and using a capacitance characteristic fault diagnosis module of the aeroengine vibration test fault diagnosis device to perform fault diagnosis;
step 2: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the resistance characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a first connecting plug position of the vibration testing fault diagnosis device of the aero-engine, and turning on a power switch of the vibration testing fault diagnosis device of the aero-engine;
rotating the first gear switch, sequentially rotating to four gears, triggering a first logic judgment circuit board to test the resistance of an output end core wire I, a core wire II and a ground wire of a sensor at the front end of the vibration test system, and judging whether the core wire I, the core wire II and the ground wire of the output end of the sensor are connected or not according to the indication condition of a first indication lamp group;
and step 3: the method for diagnosing the faults of the front-end sensor of the vibration testing system by using the capacitive characteristic fault diagnosis module of the vibration testing fault diagnosis device of the aircraft engine comprises the following steps:
connecting a plug of a sensor at the front end of the vibration testing system to a second connecting plug of the vibration testing fault diagnosis device of the aircraft engine, and turning on a power switch of the vibration testing fault diagnosis device of the aircraft engine;
and rotating the second gear switch to five gear positions in sequence, and matching with the rotating gear shifting switch to touch the second logic judgment circuit board to test the capacitance of the output end core wire I, the core wire II and the ground wire of the front end sensor of the vibration test system, and judging whether the output end core wire I, the core wire II and the ground wire of the sensor are connected or not according to the indication condition of the second indicator lamp set.
2. The method for diagnosing the vibration test fault of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: the specific method for testing the resistances of the core wire I and the core wire II of the output end of the sensor at the front end of the vibration testing system and the ground wire in the step 2 is as follows:
rotating the first gear switch to a gear I, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the lower limit of the resistance characteristic of a first sub-circuit test front-end sensor of the circuit board is less than 10 ohms or not through a first logic; if the signal is smaller than the preset value, the core wire I and the core wire II are connected, the first logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator lamp of a first indicator lamp group is lightened, otherwise, the first indicator lamp of the first indicator lamp group is not lightened, and the signal wire I and the signal wire II of the sensor corresponding to the core wire I and the core wire II have faults and need to be subjected to fault removal processing;
rotating the first gear switch to a gear II, checking the resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration test system, and judging whether the upper limit of the resistance characteristic of the interior of the front-end sensor is greater than 50M ohm or not by a first logic when a first sub-circuit of the circuit board tests; if the signal is greater than the preset value, the first logic judges that a first sub circuit of the circuit board outputs a signal, a second indicator light of the first indicator light group is lightened, otherwise, the second indicator light of the first indicator light group is not lightened, and the signal line I and the signal line II of the sensor corresponding to the core wire I and the core wire II are in fault, and fault removal processing is required;
rotating the first gear switch to a III gear, checking the resistance values of an output end core wire II and a ground wire of a front end sensor of the vibration test system, judging whether the upper limit of the resistance characteristics of the output end core wire II and the ground wire of the front end sensor is larger than 50M ohm or not through a second sub circuit of the first logic, if so, indicating that the core wire II is insulated from the ground wire, judging that a second sub circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a third indicator lamp of the first indicator lamp group is lightened, otherwise, indicating that the signal wire II and the ground wire of the sensor corresponding to the core wire II and the ground wire have faults, and needing to carry out fault removal treatment;
rotating the first gear switch to an IV gear, checking the resistance values of an output end core wire I and a ground wire of a front end sensor of the vibration testing system, judging whether the resistance characteristics of the output end core wire I and the ground wire of the front end sensor are larger than 50M ohm or not through a third sub-circuit of the first logic judgment circuit board, if so, indicating that the core wire I is insulated from the ground wire, judging that a third sub-circuit of the circuit board outputs a signal through the first logic, and if not, indicating that a fourth indicator lamp of the first indicator lamp group is turned on, otherwise, indicating that the signal wire I and the ground wire of the sensor corresponding to the core wire I and the ground wire have faults, and needing to carry out fault removal processing.
3. The method for diagnosing the vibration test fault of the aircraft engine as claimed in claim 1, wherein the method comprises the following steps: the specific method for testing the capacitance of the core wire I and the core wire II of the output end of the sensor at the front end of the vibration testing system and the capacitance of the ground wire in the step 3 is as follows:
rotating a second gear switch to a position of a first gear, shifting the gear switch to a first gear, checking resistance values of an output end core wire I and a core wire II of a front-end sensor of the vibration testing system, and judging the on-off of the output end core wire I and the core wire II of the front-end sensor of the vibration testing system through a first sub-circuit of a second logic judgment circuit board; if the resistance values of the core wire I and the core wire II are less than 10 ohms, the core wire I and the core wire II are in a path, the second logic judges that a first sub circuit of the circuit board outputs a signal, a first indicator light of the second indicator light group is lightened, otherwise, the first indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating a second gear switch to a gear II, shifting the gear switch to a second gear, checking the resistance values of a core wire II and a ground wire of the output end of the front-end sensor of the vibration test system, and judging the on-off of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system through a second sub-circuit of a second logic judgment circuit board; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that a second sub circuit of the circuit board outputs signals, a second indicator lamp of a second indicator lamp group is lightened, otherwise, the second indicator lamp of the second indicator lamp group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire;
rotating the second gear switch to a gear III, shifting the gear switch to a neutral position, checking the resistance values of a core wire I and a core wire II of the output end of the front-end sensor of the vibration testing system, and judging the insulation condition between the core wire I and the core wire II of the output end of the front-end sensor of the vibration testing system by a third sub-circuit of the circuit board through a second logic; if the resistance values of the core wire I and the core wire II are more than 50M ohms, the core wire I and the core wire II are insulated, the second logic judges that a third sub-circuit of the circuit board outputs signals, and a third indicator light of the second indicator light group is lightened, otherwise, the third indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the core wire II;
rotating the second gear switch to the IV gear, shifting the gear switch to the neutral position, checking the resistance values of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire I and the ground wire of the output end of the front-end sensor of the vibration test system by a fourth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire I and the ground wire is larger than 50M ohm, the core wire I and the ground wire are insulated, the second logic judges that a fourth sub circuit of the circuit board outputs a signal, a fourth indicator light of the second indicator light group is lightened, otherwise, the fourth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire I and the ground wire;
rotating the second gear switch to a V gear, shifting the gear switch to a neutral position, checking the resistance values of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system, and judging the insulation condition of the core wire II and the ground wire of the output end of the front-end sensor of the vibration test system by a fifth sub-circuit of the circuit board through a second logic; if the resistance value of the core wire II and the ground wire is larger than 50M ohm, the core wire II and the ground wire are insulated, the second logic judges that the fifth sub-circuit of the circuit board outputs signals, the fifth indicator light of the second indicator light group is lightened, otherwise, the fifth indicator light of the second indicator light group is not lightened, and fault removal processing needs to be carried out on the core wire II and the ground wire.
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