CN110763463A - Aviation transmission fault diagnosis system - Google Patents
Aviation transmission fault diagnosis system Download PDFInfo
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- CN110763463A CN110763463A CN201910938943.1A CN201910938943A CN110763463A CN 110763463 A CN110763463 A CN 110763463A CN 201910938943 A CN201910938943 A CN 201910938943A CN 110763463 A CN110763463 A CN 110763463A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/02—Gearings; Transmission mechanisms
- G01M13/028—Acoustic or vibration analysis
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M13/00—Testing of machine parts
- G01M13/04—Bearings
- G01M13/045—Acoustic or vibration analysis
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N23/00—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00
Abstract
The invention discloses an aviation transmission fault diagnosis system, which comprises a base and a top plate, wherein the base is provided with a plurality of through holes; two ends of the base are symmetrically provided with two pillars, and the top ends of the two pillars are connected with the top plate; a first motor is arranged on the left side above the base, an output shaft of the first motor is connected with a coupler, a bearing seat is arranged at the other end of the coupler, an installation bearing is arranged inside the bearing seat, the coupler is connected with the installation bearing, a rotating shaft is connected with the other end of the installation bearing, a rotor is arranged on the rotating shaft and is connected with a transmission shaft to be tested, and the bearing to be tested is installed on the transmission shaft to be tested; according to the invention, after disassembly, the transmission shaft to be detected and the bearing to be detected are installed on the device, the purpose of double detection is achieved through the flaw detection detector and the vibration detection sensor with telescopic structures, and the flaw detection detector is used for detecting the tiny cracks of the transmission shaft to be detected and the bearing to be detected, which can be visually detected through the display instrument, so that faults can be visually diagnosed.
Description
Technical Field
The invention belongs to the field of aviation transmission fault equipment, and particularly relates to an aviation transmission fault diagnosis system.
Background
The supporting transmission system of the aero-engine is an important component of the aero-engine and is the heart of the airplane, and once a fault occurs, serious flight accidents are often caused; the core components of the supporting transmission system are a rolling bearing and a transmission shaft, and the existing fault diagnosis method mainly adopts the mode of simultaneously analyzing the fault types of the bearings under the condition of not disassembling and provides a bearing and a transmission shaft which are suitable for an aeroengine aiming at a vibration signal.
The bearing and the transmission shaft are diagnosed under the condition of not disassembling, the difficulty of diagnosing faults is high, the troubleshooting accuracy of the faults is low, the difficulty of obtaining vibration signals is high, and the accuracy of analyzing the fault information of the bearing through the signals is low.
Chinese patent application 201811053874.8 discloses a portable aeroengine fault diagnosis device, which comprises a data acquisition module, a data preprocessing module 2, a fault diagnosis module, a main control module, a display module, a storage module and a communication module. The vibration data, the Ng rotating speed signals and the Np rotating speed signals of the aircraft engine are collected and processed, the fault mode characteristic information is extracted, the fault mode and the fault position of the aircraft engine are diagnosed from the known conditions and information, the display module, the storage module and the communication module are controlled by the main control module to display, store and communicate the fault diagnosis result and the adjustment and maintenance strategy, time can be effectively saved, and maintenance and guarantee efficiency is improved. The method has the advantages of high acquisition precision, simplicity and convenience in operation, high reliability and the like.
Chinese patent application 201711317696.0 discloses a device and a method for diagnosing vibration test faults of an aircraft engine, relating to the technical field of vibration tests of structural members of aircraft engines; the device comprises a power supply, a power switch, a resistance characteristic fault diagnosis module and a capacitance characteristic fault diagnosis module; the method is characterized in that a resistance characteristic fault diagnosis module is adopted to diagnose the fault of the sensor at the front end of the vibration test system as a magnetoelectric speed sensor, and a capacitance characteristic fault diagnosis module is adopted to diagnose the fault of the sensor at the front end of the vibration test system as a piezoelectric vibration acceleration sensor. According to the aircraft engine vibration test fault diagnosis device, the fault removing process is solidified in the circuit system through the digital logic judgment circuit board, the existing fault removing method with low efficiency and poor accuracy through replacing 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.
However, in the prior art, the fault detection device is too complex in structure, is not beneficial to production and use, detects the transmission system under the condition that the fault detection device is not disassembled, and is high in detection difficulty and low in accuracy.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an aviation transmission fault diagnosis system, wherein after disassembly, a transmission shaft to be detected and a bearing to be detected are installed on the device, the purpose of double detection is achieved through a flaw detection detector and a vibration detection sensor which are provided with telescopic structures, and the flaw detection detector is used for detecting tiny cracks of the transmission shaft to be detected and the bearing to be detected, which can be visually detected through a display instrument, so that faults are visually diagnosed; meanwhile, the vibration measurement sensor is adopted to acquire data, and then data analysis is carried out, so that the accuracy of fault analysis is improved.
The invention provides the following technical scheme:
an aviation transmission fault diagnosis system comprises a base and a top plate; two ends of the base are symmetrically provided with two pillars, and the top ends of the two pillars are connected with the top plate; a first motor is arranged on the left side above the base, an output shaft of the first motor is connected with a coupler, a bearing seat is arranged at the other end of the coupler, an installation bearing is arranged inside the bearing seat, the coupler is connected with the installation bearing, a rotating shaft is connected with the other end of the installation bearing, a rotor is arranged on the rotating shaft and is connected with a transmission shaft to be tested, and the bearing to be tested is installed on the transmission shaft to be tested; a plurality of vibration measuring sensors are arranged on the transmission shaft to be measured and the bearing to be measured; be equipped with the detector of detecting a flaw directly over transmission shaft and the bearing that awaits measuring, the detector top of detecting a flaw is connected with extending structure, extending structure includes the telescopic link, the telescopic link with the roof is connected.
Preferably, the telescopic structure further comprises two supporting blocks, the two supporting blocks are symmetrically arranged on the inner sides of the two telescopic rods, and the two connecting blocks are connected with the top plate; a bidirectional screw rod is rotatably connected between the inner walls of the two supporting blocks, two moving blocks are symmetrically arranged on the bidirectional screw rod close to the two ends, and sliding blocks are connected to the side walls above the two moving blocks; a sliding rod is arranged above the bidirectional screw rod, and two ends of the sliding rod are connected with the two supporting blocks; and the two sliding blocks are in sliding connection with the slide way gap.
Preferably, a second motor is arranged below one of the supporting blocks, and a driving gear is fixedly connected to the tail end of an output shaft of the second motor; the driving gear is meshed with a driven gear fixedly connected to the bidirectional screw rod.
Preferably, the side walls below the two moving blocks are rotatably connected with pull rods, one ends of the pull rods, far away from the moving blocks, are rotatably connected with connecting blocks, and the connecting blocks are connected with the flaw detection instrument.
Preferably, flaw detection appearance top symmetry is equipped with two telescopic links, and the top of two telescopic links all is connected with the roof.
Preferably, through holes are formed in the center positions of the two moving blocks, internal threads are formed in the inner walls of the through holes, and the internal threads are meshed with the threads of the bidirectional screw rod in a rotating mode.
Preferably, the flaw detection instrument and the vibration measurement sensor are both connected with a display instrument through data lines.
Preferably, the vibration measurement sensor is a PCB acceleration sensor, and an eddy current displacement sensor is used to measure and obtain displacement pulse signals so as to obtain rotation speed signals, wherein the acceleration sensors are provided with five acceleration sensors, three acceleration sensors are arranged on the outer side wall of the bearing to be measured, and two acceleration sensors are arranged on the outer side wall of the transmission shaft to be measured.
The vibration signals of the outer ring of the bearing to be measured are acquired as much as possible, when periodic itinerant detection is carried out, the positions of the measuring points are kept consistent, the measuring direction is determined according to the bearing condition of the bearing, and the measuring points are arranged at the position with the maximum density, so that the vibration signals of the bearing and the transmission shaft are ensured to be acquired as much as possible.
In addition, a single chip microcomputer is integrated in the display instrument, a data acquisition system is integrated in the single chip microcomputer, the data acquisition system can acquire the working conditions of the bearing to be detected and the transmission shaft to be detected, and the working conditions are analyzed to obtain a fault diagnosis result; the faults of the bearing and the transmission shaft are various, when the bearing is damaged and has nonlinear faults, the characteristic frequency of the bearing is different to a certain degree, and the damage degree and the damage position are accurately determined according to the difference of the frequency.
The flaw detection instrument adopts a seamless flaw detection instrument (X-ray flaw detector), detection data and pictures are transmitted to a display instrument through a data line, and fault data and pictures are displayed after being processed by a single chip microcomputer.
Preferably, the first motor is a servo motor, the maximum rotating speed n of the motor is 6000, and in order to improve the accuracy of fault detection, the relation n/a between the acceleration a of the bearing to be detected and the rotating speed n of the first motor is greater than or equal to 1.27 and less than or equal to 5.38.
Preferably, the bearing to be detected has angular phase position deviation when running at high speed, the offset is delta, the accuracy of fault detection is influenced, and the bearing to be detected has higher strain and stability; the offset delta, a, n and the radius of the bearing to be measured satisfy the following relations:
δ＝k·(n/a)1/2·2r；
wherein a is a constant with the value range of 0.1-1.25; the above relation is only numerical.
Compared with the prior art, the invention has the following beneficial effects:
(1) according to the aviation transmission fault diagnosis system, the different heights of the flaw detection detector are adjusted by arranging the telescopic machine, so that the bearing to be detected is convenient to mount, the different heights and angles are adjusted at the same time, a more appropriate angle is found for seamless flaw detection, and the fault detection accuracy of the bearing microcracks is improved.
(2) According to the aviation transmission fault diagnosis system, the vibration measurement sensor and the flaw detection detector are connected with the display through the data line, and the single chip microcomputer system is integrated, so that the convenience of integrated intelligent control of the device is improved; and fault data can be displayed more intuitively.
(3) According to the aviation transmission fault diagnosis system, the aviation bearing and the transmission shaft are disassembled, the aviation bearing and the transmission shaft are mounted on the fault detection device for fault detection, the operation is convenient, the purpose of double fault detection is achieved through the flaw detection instrument with the telescopic structure and the vibration detection sensor, and the fault detection accuracy is further improved.
(4) The invention relates to an aviation transmission fault diagnosis system, which aims to increase the strain and stability of a bearing to be tested and reduce the angular phase offset; the offset delta, the offset a, the offset n and the radius of the bearing to be measured meet a series of relations, and the running stability of the device is guaranteed; the device has simple structure and low manufacturing cost, and is convenient to use in production.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
Fig. 1 is a schematic view of the overall structure of the present invention.
Fig. 2 is a partially enlarged schematic view of the present invention.
Figure 3 is a schematic view of the moving mass of the present invention.
In the figure: 1. a base; 2. a top plate; 3. a first motor; 4. a coupling; 5. a bearing seat; 6. a rotating shaft; 7. a rotor; 8. a transmission shaft to be tested; 9. a vibration measuring sensor; 10. a bearing to be tested; 11. a flaw detection instrument; 12. a telescopic rod; 13. connecting blocks; 14. a display instrument; 15. a data line; 16. a pillar; 17. a pull rod; 18. a bidirectional screw rod; 19. a slide bar; 20. a support block; 21. a second motor; 22. a driving gear; 23. a driven gear; 24. a moving block; 25. a slider; 26. an internal thread.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be described in detail and completely with reference to the accompanying drawings. It is to be understood that the described embodiments are only a few embodiments of the present invention, and not all embodiments. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The first embodiment is as follows:
referring to fig. 1-3, an aviation transmission fault diagnosis system includes a base 1 and a top plate 2; two struts 16 are symmetrically arranged at two ends of the base 1, and the top ends of the two struts 16 are connected with the top plate 2; a first motor 3 is arranged on the left side above the base 1, an output shaft of the first motor 3 is connected with a coupler 4, a bearing seat 5 is arranged at the other end of the coupler 4, an installation bearing is arranged inside the bearing seat 5, the coupler 4 is connected with the installation bearing, the other end of the installation bearing is connected with a rotating shaft 6, a rotor 7 is arranged on the rotating shaft 6, the rotor 7 is connected with a transmission shaft 8 to be tested, and a bearing 10 to be tested is arranged on the transmission shaft 8 to be tested; a plurality of vibration measuring sensors 9 are arranged on the transmission shaft to be measured 8 and the bearing to be measured 10; be equipped with flaw detection appearance 11 directly over transmission shaft 8 and the bearing 10 that awaits measuring, flaw detection appearance 11 top is connected with extending structure, extending structure includes telescopic link 12, telescopic link 12 with roof 2 is connected.
The telescopic structure further comprises two supporting blocks 20, the two supporting blocks 20 are symmetrically arranged on the inner sides of the two telescopic rods 12, and the two connecting blocks 13 are connected with the top plate 2; a bidirectional screw rod 18 is rotatably connected between the inner walls of the two supporting blocks 20, two moving blocks 24 are symmetrically arranged on the bidirectional screw rod 18 close to the two ends, and sliding blocks 25 are connected to the upper side walls of the two moving blocks 24; a slide rod 19 is arranged above the bidirectional screw rod 18, and two ends of the slide rod 19 are connected with the two supporting blocks 20; the two sliding blocks 25 are in sliding connection with the slide way gaps; through setting up the telescopic machine enough, adjust the not co-altitude of detecting a flaw detector 11, the bearing 10 installation of awaiting measuring of being convenient for adjusts different height and angle simultaneously, finds more suitable angle and carries out seamless flaw detection, improves the fault detection accuracy of bearing crazing.
A second motor 21 is arranged below one of the supporting blocks 20, and a driving gear 22 is fixedly connected to the tail end of an output shaft of the second motor 21; the driving gear 22 is meshed with a driven gear 23 fixedly connected to the bidirectional screw rod 18.
The side walls below the two moving blocks 24 are rotatably connected with pull rods 17, one ends, far away from the moving blocks 24, of the pull rods 17 are rotatably connected with connecting blocks 13, and the connecting blocks 13 are connected with the flaw detection instrument 11.
Two telescopic rods 12 are symmetrically arranged above the flaw detection instrument 11, and the top ends of the two telescopic rods 12 are connected with the top plate 2; the telescopic rod 12 is a hydraulic telescopic rod 12.
The center positions of the two moving blocks 24 are both provided with through holes, inner threads 26 are arranged on the inner walls of the through holes, and the inner threads 26 are meshed with the threads of the bidirectional screw rod 18 in a rotating mode.
The flaw detection instrument 11 and the vibration measurement sensor 9 are both connected with a display instrument 14 through a data line 15.
Example two:
referring to fig. 1-3, an aviation transmission fault diagnosis system includes a base 1 and a top plate 2; two struts 16 are symmetrically arranged at two ends of the base 1, and the top ends of the two struts 16 are connected with the top plate 2; a first motor 3 is arranged on the left side above the base 1, an output shaft of the first motor 3 is connected with a coupler 4, a bearing seat 5 is arranged at the other end of the coupler 4, an installation bearing is arranged inside the bearing seat 5, the coupler 4 is connected with the installation bearing, the other end of the installation bearing is connected with a rotating shaft 6, a rotor 7 is arranged on the rotating shaft 6, the rotor 7 is connected with a transmission shaft 8 to be tested, and a bearing 10 to be tested is arranged on the transmission shaft 8 to be tested; a plurality of vibration measuring sensors 9 are arranged on the transmission shaft to be measured 8 and the bearing to be measured 10; be equipped with flaw detection appearance 11 directly over transmission shaft 8 and the bearing 10 that awaits measuring, flaw detection appearance 11 top is connected with extending structure, extending structure includes telescopic link 12, telescopic link 12 with roof 2 is connected.
The telescopic structure further comprises two supporting blocks 20, the two supporting blocks 20 are symmetrically arranged on the inner sides of the two telescopic rods 12, and the two connecting blocks 13 are connected with the top plate 2; a bidirectional screw rod 18 is rotatably connected between the inner walls of the two supporting blocks 20, two moving blocks 24 are symmetrically arranged on the bidirectional screw rod 18 close to the two ends, and sliding blocks 25 are connected to the upper side walls of the two moving blocks 24; a slide rod 19 is arranged above the bidirectional screw rod 18, and two ends of the slide rod 19 are connected with the two supporting blocks 20; the two sliding blocks 25 are in sliding connection with the slide way gaps; through setting up the telescopic machine enough, adjust the not co-altitude of detecting a flaw detector 11, the bearing 10 installation of awaiting measuring of being convenient for adjusts different height and angle simultaneously, finds more suitable angle and carries out seamless flaw detection, improves the fault detection accuracy of bearing crazing.
A second motor 21 is arranged below one of the supporting blocks 20, and a driving gear 22 is fixedly connected to the tail end of an output shaft of the second motor 21; the driving gear 22 is meshed with a driven gear 23 fixedly connected to the bidirectional screw rod 18.
The side walls below the two moving blocks 24 are rotatably connected with pull rods 17, one ends, far away from the moving blocks 24, of the pull rods 17 are rotatably connected with connecting blocks 13, and the connecting blocks 13 are connected with the flaw detection instrument 11.
Two telescopic rods 12 are symmetrically arranged above the flaw detection instrument 11, and the top ends of the two telescopic rods 12 are connected with the top plate 2; the telescopic rod 12 is a hydraulic telescopic rod 12.
The vibration measurement sensor 9 is a PCB acceleration sensor, an eddy current displacement sensor is adopted to measure displacement pulse signals so as to obtain rotating speed signals, the acceleration sensor is provided with five acceleration sensors, three acceleration sensors are arranged on the outer side wall of the bearing 10 to be measured, and two acceleration sensors are arranged on the outer side wall of the transmission shaft 8 to be measured.
The vibration signals of the outer ring of the bearing 10 to be measured are acquired as many as possible, when periodic itinerant detection is carried out, the positions of the measuring points are kept consistent, the measuring direction is determined according to the bearing condition of the bearing, and the measuring points are arranged at the position with the maximum density, so that the vibration signals of the bearing and the transmission shaft are ensured to be acquired as much as possible.
In addition, a single chip microcomputer is integrated in the display instrument 14, a data acquisition system (LMSSCADAIII) is integrated in the single chip microcomputer, the data acquisition system can acquire the working conditions of the bearing 10 to be detected and the transmission shaft 8 to be detected, and the working conditions are analyzed to obtain a fault diagnosis result; the faults of the bearing and the transmission shaft are various, when the bearing is damaged and has nonlinear faults, the characteristic frequency of the bearing is different to a certain degree, and the damage degree and the damage position are accurately determined according to the difference of the frequency.
The flaw detector 11 adopts a seamless flaw detector 11 (X-ray flaw detector), detection data and pictures are transmitted to a display through a data line 15, and fault data and pictures are displayed after being processed by a single chip microcomputer.
EXAMPLE III
The difference between the first and second embodiments is that the first motor 3 is a servo motor, the maximum rotation speed n of the motor is 6000, and in order to improve the accuracy of fault detection, the relation n/a between the acceleration a of the bearing 10 to be detected and the rotation speed n of the first motor 3 satisfies 1.27 or more and 5.38 or less.
When the bearing to be detected 10 runs at a high speed, the angular phase shifts, the offset is delta, the accuracy of fault detection is influenced, and the bearing to be detected has the strain property and the stability; the offset delta, a, n and the radius of the bearing 10 to be measured satisfy the following relations:
δ＝k·(n/a)1/2·2r；
wherein a is a constant with the value range of 0.1-1.25; the above relation is only numerical.
The device obtained by the technical scheme is an aviation transmission fault diagnosis system, the transmission shaft 8 to be detected and the bearing 10 to be detected are installed on the device after being disassembled, the purpose of double detection is achieved through the flaw detection detector 11 with a telescopic structure and the vibration measurement sensor 9, the flaw detection detector 11 is used for detecting tiny cracks which can visually detect the transmission shaft 8 to be detected and the bearing 10 to be detected through the display 14, and faults are visually diagnosed; meanwhile, the vibration measurement sensor 9 is adopted to acquire data for data analysis, and the accuracy of fault analysis is improved.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the present invention, and it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention; any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. An aviation transmission fault diagnosis system comprises a base (1) and a top plate (2); the novel support is characterized in that two ends of the base (1) are symmetrically provided with two struts (16), and the top ends of the two struts (16) are connected with the top plate (2); a first motor (3) is arranged on the left side above the base (1), an output shaft of the first motor (3) is connected with a coupler (4), a bearing seat (5) is arranged at the other end of the coupler (4), an installation bearing is arranged inside the bearing seat (5), the coupler (4) is connected with the installation bearing, the other end of the installation bearing is connected with a rotating shaft (6), a rotor (7) is arranged on the rotating shaft (6), the rotor (7) is connected with a transmission shaft (8) to be tested, and a bearing (10) to be tested is arranged on the transmission shaft (8) to be tested; a plurality of vibration measuring sensors (9) are respectively arranged on the transmission shaft (8) to be measured and the bearing (10) to be measured; be equipped with flaw detection appearance (11) directly over transmission shaft (8) and the bearing (10) that awaits measuring, flaw detection appearance (11) top is connected with extending structure, extending structure includes telescopic link (12), telescopic link (12) with roof (2) are connected.
2. The airborne transmission fault diagnosis system according to claim 1, characterized in that the telescopic structure further comprises two support blocks (20), the two support blocks (20) are symmetrically arranged at the inner sides of the two telescopic rods (12), and the two connecting blocks (13) are connected with the top plate (2); a bidirectional screw rod (18) is rotatably connected between the inner walls of the two supporting blocks (20), two moving blocks (24) are symmetrically arranged on the bidirectional screw rod (18) close to the two ends, and sliding blocks (25) are connected to the upper side walls of the two moving blocks (24); a sliding rod (19) is arranged above the bidirectional screw rod (18), and two ends of the sliding rod (19) are connected with the two supporting blocks (20); the two sliding blocks (25) are in sliding connection with the sliding way gaps.
3. The aircraft transmission fault diagnosis system according to any one of claims 1-2, wherein a second motor (21) is arranged below one of the support blocks (20), and a driving gear (22) is fixedly connected to the tail end of an output shaft of the second motor (21); the driving gear (22) is meshed with a driven gear (23) fixedly connected to the bidirectional screw rod (18).
4. The aviation transmission fault diagnosis system according to claim 1 or 3, characterized in that a pull rod (17) is rotatably connected to the lower side wall of each of the two moving blocks (24), a connecting block (13) is rotatably connected to one end of each pull rod (17) far away from the corresponding moving block (24), and the connecting block (13) is connected with the flaw detector (11).
5. The airborne transmission fault diagnosis system according to any one of claims 1-4, characterized in that two telescopic rods (12) are symmetrically arranged above the flaw detection detector (11), and the top ends of the two telescopic rods (12) are connected with the top plate (2).
6. The aviation transmission fault diagnosis system according to any one of claims 1 to 4, wherein a through hole is formed in the center of each of the two moving blocks (24), internal threads (26) are formed in the inner wall of the through hole, and the internal threads (26) are meshed with and rotatably connected with the threads of the bidirectional screw rod (18).
7. The airborne transmission fault diagnosis system according to any one of claims 1-4, characterized in that the flaw detector (11) and the vibration sensor (9) are both connected with a display (14) through a data line (15).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910938943.1A CN110763463B (en) | 2019-09-30 | 2019-09-30 | Aviation transmission fault diagnosis system |
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|---|---|---|---|
| CN201910938943.1A CN110763463B (en) | 2019-09-30 | 2019-09-30 | Aviation transmission fault diagnosis system |
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| CN110763463B CN110763463B (en) | 2021-09-03 |
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