CN-121323877-B - Static test method and system, medium and equipment for aircraft integral drive generator

CN121323877BCN 121323877 BCN121323877 BCN 121323877BCN-121323877-B

Abstract

The application discloses a static test method, a system, a medium and equipment of an aircraft integral driving generator, wherein the method comprises the steps of collecting a cleaning agent liquid level image of a cleaning agent container in real time after immersing the aircraft integral driving generator in the cleaning agent container filled with the cleaning agent, identifying whether bubbles exist in the cleaning agent liquid level image, and determining that a static test result of the aircraft integral driving generator is qualified when no bubbles exist in the cleaning agent liquid level image; when bubbles exist in the cleaning agent liquid level image, the static test result of the aircraft integral driving generator is obtained by combining the interval time of bubble generation and the initial position point of bubble generation, wherein the static test result comprises passing and failing, and when the static test result is failing, the static test result also comprises the portion of the failed aircraft integral driving generator. The high-efficiency and accurate detection of the sealing performance in the static test of the whole driving generator can be realized, and a reliable basis is provided for the quality assurance of equipment.

Inventors

LI CHONG
SONG JICHU
Miao Dapeng
MA YUXUAN
XU YIFENG
Gao Xinshi

Assignees

沈阳北方飞机维修有限公司

Dates

Publication Date: 20260505
Application Date: 20250929

Claims (9)

1. A method for static testing of an aircraft integral drive generator, the method comprising: immersing the whole driving generator of the airplane into a cleaning agent container filled with cleaning agent, and collecting a cleaning agent liquid level image of the cleaning agent container in real time; Based on the cleaning agent liquid level image acquired in a preset time period, identifying whether bubbles exist in the cleaning agent liquid level image, and when no bubbles exist in the cleaning agent liquid level image, determining that the static test result of the whole driving generator of the aircraft is qualified; When bubbles exist in the cleaning agent liquid level image, extracting the interval time of bubble generation and positioning the initial position point of bubble generation, wherein a pressure gauge is arranged in a cleaning agent container, the part of the whole driving generator of the airplane comprises an assembling part and a non-assembling part, and the assembling part comprises an electric plug, a sealing ring part and a part between an input shaft and a sealing part; judging the time law of bubble generation based on the interval time of bubble generation; When the time rule of bubble generation is regular and the initial position point of bubble generation is an assembly part, the static test result of the whole aircraft driving generator is unqualified; when the time rule of bubble generation is regular and the initial position point of bubble generation is a non-assembly part, judging a static test result of the whole driving generator of the aircraft according to the display result of the pressure gauge; When the time rule of bubble generation is irregular, continuously judging whether bubbles are generated in the second half section in a preset time period, and jointly judging a static test result of the whole driving generator of the aircraft according to the continuous judgment result and the display result of the pressure gauge; When the static test result is unqualified, combining initial position points generated by bubbles to obtain a position of the unqualified aircraft integral driving generator, wherein the static test result comprises qualified and unqualified parts, and when the static test result is unqualified, the static test result also comprises the position of the unqualified aircraft integral driving generator.
2. The method of claim 1, wherein the aircraft integral drive generator includes a vent connected to a gas source, and wherein determining a static test result of the aircraft integral drive generator based on the display result of the pressure gauge includes: If the display result of the pressure gauge is stable, the static test result of the whole aircraft driving generator is qualified; And if the display result of the pressure gauge shows instability, continuously collecting the cleaning agent liquid level image of the cleaning agent container in real time after the pressure of the air source is re-stabilized until the static test result of the whole driving generator of the airplane is judged according to the display result of the pressure gauge when the time rule of bubble generation is regular and the initial position point of bubble generation is a non-assembly part.
3. The method of claim 1, wherein the aircraft integral drive generator includes an oil passage hole and a vent hole, and wherein immersing the aircraft integral drive generator in a cleaner container containing a cleaner comprises: after the assembly of the aircraft integral driving generator is completed, the oil through hole of the aircraft integral driving generator is sealed, the air vent is connected with an air source, and the air source pressure is regulated to a preset range.
4. A method according to claim 3, wherein the step of jointly determining the static test result of the aircraft whole driven generator based on the result of the continuous determination and the display result of the pressure gauge comprises: When bubbles are generated in the latter half section within the preset time period and the display result of the pressure gauge shows a descending trend, the static test result of the whole aircraft driving generator is unqualified; And when no bubble is generated in the latter half of the preset time period and the display result of the pressure gauge shows instability, continuously collecting the cleaning agent liquid level image of the cleaning agent container in real time after the pressure of the air source is re-stabilized until the static test result of the whole driving generator of the airplane is qualified when the time rule of bubble generation is irregular and no bubble is generated in the latter half of the preset time period.
5. The method of claim 1, wherein extracting the bubble generation interval time and locating the bubble generation initial position point comprises: carrying out Gaussian filtering treatment on the collected cleaning agent liquid level image, and adopting an improved YOLOv network to position bubbles in the cleaning agent liquid level image after Gaussian filtering treatment; Continuously tracking bubbles in each frame of cleaning agent liquid level image through ByteTrack tracking network, and associating the same bubbles of adjacent frames according to the continuously tracked bubble motion trail to obtain an independent bubble sequence of the bubbles; for a plurality of independent bubble sequences, determining bubbles corresponding to the independent bubble sequences appearing for the first time, and positioning the generation position of the bubbles as an initial position point for bubble generation; And recording bubbles corresponding to the previous independent bubble sequence, and taking the interval time between the bubbles corresponding to the next adjacent independent bubble sequence as the interval time of bubble generation.
6. The method of claim 5, wherein the aircraft-integrally-driven generator includes a vent connected to a gas source, wherein for a plurality of independent bubble sequences, determining a bubble corresponding to the first-occurring independent bubble sequence, and locating a generation position of the bubble as an initial position point of bubble generation includes: Judging whether the bubble motion trail corresponding to the independent bubble sequence accords with the liquid flow rule or not; If the motion trail of the air bubble accords with the flow rule of the liquid, determining the air bubble corresponding to the independent air bubble sequence appearing for the first time aiming at a plurality of independent air bubble sequences, and positioning the generation position of the air bubble as an initial position point of air bubble generation; and if the movement track of the air bubble does not accord with the liquid flow rule, after the pressure of the air source is re-stabilized, the whole aircraft driving generator is immersed into a cleaning agent container filled with cleaning agent again, and the step of collecting the cleaning agent liquid level image of the cleaning agent container again in real time is executed.
7. An aircraft integral drive generator static test system, the system comprising: The image acquisition module is used for acquiring the cleaning agent liquid level image of the cleaning agent container in real time after the whole airplane-driven generator is immersed in the cleaning agent container filled with the cleaning agent; The air bubble judging module is used for identifying whether air bubbles exist in the cleaning agent liquid level image based on the cleaning agent liquid level image acquired in a preset time period, and when no air bubbles exist in the cleaning agent liquid level image, the static test result of the whole aircraft driving generator is qualified; The device comprises a cleaning agent container, a bubble and position joint judging module, a static test result of the aircraft integral drive generator, a static test result and a failure test result, wherein the bubble and position joint judging module is used for extracting the interval time generated by bubbles and positioning the initial position point generated by the bubbles when bubbles are in a cleaning agent liquid level image, a pressure gauge is arranged in the cleaning agent container, the part of the aircraft integral drive generator comprises an assembling part and a non-assembling part, the assembling part comprises an electric plug, a sealing ring part and a part between an input shaft and a sealing position, the time rule generated by the bubbles is judged based on the interval time generated by the bubbles, the static test result of the aircraft integral drive generator is failed when the time rule generated by the bubbles is regular and the initial position point generated by the bubbles is the assembling part, the static test result of the aircraft integral drive generator is judged according to the display result of the pressure gauge when the time rule generated by the bubbles is regular and the initial position point generated by the bubbles is the non-assembling part, the static test result of the aircraft integral drive generator is continuously judged whether the latter half part in a preset time period is generated by the bubbles, and the static test result of the aircraft integral drive generator is jointly judged according to the display result of the continuous judging result and the display result of the pressure gauge in the preset time period is failed when the static test result is failed, and the static test result of the integral drive generator is failed.
8. A medium having stored thereon a computer program, which when executed by a processor implements a method of static testing of an aircraft whole-drive generator according to any one of claims 1 to 6.
9. An apparatus comprising a medium, a processor and a computer program stored on the medium and executable on the processor, wherein the processor, when executing the computer program, implements a method of static testing of an aircraft whole drive generator according to any one of claims 1 to 6.

Description

Static test method and system, medium and equipment for aircraft integral drive generator Technical Field The application relates to the technical field of civil aviation, in particular to a static test method, a static test system, a static test medium and static test equipment for an aircraft integral drive generator. Background The integral driving generator (IntegratedDriveGenerator, IDG for short) is used as aviation core power guarantee equipment, and the sealing performance directly determines the reliability, safety and service life of the equipment. In the maintenance and assembly process of the IDG, static test is a key link for verifying the sealing performance of the IDG before delivery, the core purpose of the test is to simulate the static working condition (namely, the closed environment in a non-running state) of the IDG after installation, and the effectiveness of key sealing parts is judged by detecting the isolation effect of the inside and the outside environment of the IDG, wherein the key sealing parts specifically comprise 1, dynamic sealing between an input shaft and a shell (realized by a sealing assembly, and the sealing performance in a moving state is ensured due to the relative movement of the input shaft and the shell), 2, the sealing ring assembly quality of static sealing points such as an electric plug and a pipeline interface (the static sealing is realized by fixing the sealing ring, whether the sealing ring is perfect or not and whether the sealing ring is assembled in place or not is required to be verified), and 3, the integrity of a shell body and a welding/connecting part (detecting whether the defect of medium leakage is caused by cracks, sand holes or the like) is detected, and the traditional integral driving generator sealing detection is mostly carried out by manual naked eyes, and the precision is low. Disclosure of Invention In view of the above, the application provides a static test method and system, medium and equipment for an aircraft integral driving generator, which can realize high-efficiency and accurate detection of sealing performance in static test of the integral driving generator and provide reliable basis for quality assurance of the equipment. According to one aspect of the application, there is provided a method of static testing of an aircraft whole drive generator, the method comprising: immersing the whole driving generator of the airplane into a cleaning agent container filled with cleaning agent, and collecting a cleaning agent liquid level image of the cleaning agent container in real time; Based on the cleaning agent liquid level image acquired in a preset time period, identifying whether bubbles exist in the cleaning agent liquid level image, and when no bubbles exist in the cleaning agent liquid level image, determining that the static test result of the whole driving generator of the aircraft is qualified; When bubbles exist in the liquid level image of the cleaning agent, extracting the interval time of bubble generation, positioning the initial position point of bubble generation, and combining the interval time of bubble generation and the initial position point of bubble generation to obtain the static test result of the aircraft integral driving generator, wherein the static test result comprises passing and failing and comprises the portion of the failed aircraft integral driving generator when the static test result is failing. According to another aspect of the present application there is provided an aircraft integral drive generator static test system, the system comprising: The image acquisition module is used for acquiring the cleaning agent liquid level image of the cleaning agent container in real time after the whole airplane-driven generator is immersed in the cleaning agent container filled with the cleaning agent; The air bubble judging module is used for identifying whether air bubbles exist in the cleaning agent liquid level image based on the cleaning agent liquid level image acquired in a preset time period, and when no air bubbles exist in the cleaning agent liquid level image, the static test result of the whole aircraft driving generator is qualified; And the bubble and position combined judging module is used for extracting the interval time generated by bubbles and positioning the initial position point generated by the bubbles when the bubbles exist in the liquid level image of the cleaning agent, and combining the interval time generated by the bubbles and the initial position point generated by the bubbles to obtain the static test result of the aircraft integral drive generator, wherein the static test result comprises qualified and unqualified parts, and when the static test result is unqualified, the static test result also comprises the unqualified parts of the aircraft integral drive generator. According to a further aspect of the application there is provided a medium having stored thereon a compute