CN112710742A - Nondestructive testing method for glass damage of aircraft canopy framework - Google Patents
Nondestructive testing method for glass damage of aircraft canopy framework Download PDFInfo
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- CN112710742A CN112710742A CN202011529163.0A CN202011529163A CN112710742A CN 112710742 A CN112710742 A CN 112710742A CN 202011529163 A CN202011529163 A CN 202011529163A CN 112710742 A CN112710742 A CN 112710742A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/04—Analysing solids
- G01N29/12—Analysing solids by measuring frequency or resonance of acoustic waves
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N29/00—Investigating or analysing materials by the use of ultrasonic, sonic or infrasonic waves; Visualisation of the interior of objects by transmitting ultrasonic or sonic waves through the object
- G01N29/44—Processing the detected response signal, e.g. electronic circuits specially adapted therefor
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/023—Solids
- G01N2291/0232—Glass, ceramics, concrete or stone
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/023—Solids
- G01N2291/0234—Metals, e.g. steel
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N2291/00—Indexing codes associated with group G01N29/00
- G01N2291/02—Indexing codes associated with the analysed material
- G01N2291/023—Solids
- G01N2291/0235—Plastics; polymers; soft materials, e.g. rubber
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Abstract
The application belongs to the field of airplane structure fatigue tests, and particularly relates to a nondestructive testing method for glass damage of an airplane canopy framework. Step one, constructing a first health frequency response function database of a canopy framework structure under the condition of no damage; step two, acquiring a canopy framework structure to be detected, and testing a detection point of the canopy framework structure to be detected to obtain second health frequency response function data of the canopy framework structure to be detected; and step three, comparing the second health frequency response function data with the frequency response function of the first health frequency response function database, and judging whether the detection point of the canopy framework structure to be detected is damaged or not. This application detects the vibration frequency response function of waiting to examine the structure through the healthy frequency response function database of the canopy skeleton texture that founds under the not damaged condition, judges that the structure of detection point department takes place the damage to avoid destroying the shortcoming that the structure detected, realized carrying out nondestructive test to invisible position, efficient, with low costs.
Description
Technical Field
The application belongs to the field of airplane structure fatigue tests, and particularly relates to a nondestructive testing method for glass damage of an airplane canopy framework.
Background
The determination of the service life of the transparent organic glass of the aircraft canopy is an important link in the design work of the aircraft life, the determination of the service life is mainly realized according to a heating and loading fatigue test of the canopy, and the damage condition of the canopy structure needs to be detected periodically in the fatigue test. The cockpit cover structural damage inspection part mainly comprises a cockpit cover metal framework and organic glass, the metal framework is mainly realized by visual combination with a penetration detection means, the visual part of the organic glass is mainly realized by visual inspection, and the connection part of the organic glass and the cockpit cover metal framework cannot be detected by a conventional means due to the fact that the connection part is invisible.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The application aims to provide a nondestructive testing method for glass damage of an aircraft canopy framework, so as to solve at least one problem existing in the prior art.
The technical scheme of the application is as follows:
a nondestructive testing method for glass damage of an airplane canopy framework comprises the following steps:
step one, constructing a first health frequency response function database of a canopy framework structure under the condition of no damage;
step two, acquiring a canopy framework structure to be detected, and testing a detection point of the canopy framework structure to be detected to obtain second health frequency response function data of the canopy framework structure to be detected;
and step three, comparing the second health frequency response function data with the frequency response function of the first health frequency response function database, and judging whether the detection point of the canopy framework structure to be detected is damaged or not.
Optionally, in the first step, the constructing a first health frequency response function database of the canopy framework structure under the non-damage condition includes:
s101, obtaining a canopy framework structure under the condition of no damage, arranging detection points on the canopy framework structure, and establishing a geometric wire frame model according to the coordinates of the detection points of the canopy framework structure;
s102, mounting a canopy framework structure on a workbench;
s103, installing an acceleration sensor on a detection point of the canopy framework structure;
s104, building a test system, and testing the canopy framework structure after debugging;
s105, first health frequency response function data of the canopy framework structure are obtained, and a first health frequency response function database is constructed.
Optionally, in S103, when the installation position of the acceleration sensor is a curved surface, the installation direction of the acceleration sensor is adjusted to be consistent with the test direction.
Optionally, in S104, the test system includes: a vibration exciter, a data acquisition unit and a computer, wherein,
the force hammer of the vibration exciter is abutted against one side of a canopy framework structure, which is different from one side of the canopy framework structure, the abutting position of the force hammer is corresponding to the mounting position of the acceleration sensor, and the force sensor is arranged on the force hammer;
the output end of the data acquisition unit is connected with the vibration exciter through a power amplifier, and the input end of the data acquisition unit is respectively connected with the acceleration sensor and the force sensor;
and the computer is connected with the data acquisition unit.
Optionally, in S105, first health frequency response function data of the canopy framework structure is obtained by a stochastic method.
Optionally, in S105, first healthy frequency response function data of the canopy framework structure is acquired by using a phase resonance method.
Optionally, in S105, the first health frequency response function data includes frequencies and mode shapes of modes of respective orders.
The invention has at least the following beneficial technical effects:
according to the nondestructive testing method for glass damage of the aircraft canopy framework, the healthy frequency response function database of the canopy framework structure under the nondestructive condition is constructed, the vibration frequency response function of the structure to be tested is detected, and whether the structure at the detection point is damaged or not is judged, so that the defect that the structure is damaged to detect is overcome, the nondestructive testing of invisible parts is realized, and the nondestructive testing is high in efficiency and low in cost.
Drawings
FIG. 1 is a flow chart of a nondestructive testing method for damage to aircraft canopy framework glass according to an embodiment of the present disclosure;
FIG. 2 is a schematic diagram of a test system according to an embodiment of the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The application provides a nondestructive testing method for glass damage of an aircraft canopy framework, which comprises the following steps:
s100, constructing a first health frequency response function database of the canopy framework structure under the condition of no damage;
s200, obtaining a canopy framework structure to be detected, and testing a detection point of the canopy framework structure to be detected to obtain second health frequency response function data of the canopy framework structure to be detected;
s300, comparing the second healthy frequency response function data with the frequency response function of the first healthy frequency response function database, and judging whether the detection point of the canopy framework structure to be detected is damaged or not.
According to the aircraft canopy framework glass damage nondestructive testing method, single-point excitation is carried out on monitored points of a canopy framework structure under the complete and nondestructive condition or a detection point list specified by a detection party, and health frequency response function data of the detection points are collected to form a first health frequency response function database of the canopy framework structure.
In one embodiment of the present application, the constructing a first health frequency response function database of the canopy framework structure under non-damage condition in S100 includes the following steps:
s101, obtaining a canopy framework structure under the condition of no damage, arranging detection points on the canopy framework structure, and establishing a geometric wire frame model according to the coordinates of the detection points of the canopy framework structure;
s102, mounting a canopy framework structure on a workbench;
s103, installing an acceleration sensor on a detection point of the canopy framework structure;
s104, building a test system, and testing the canopy framework structure after debugging;
s105, first health frequency response function data of the canopy framework structure are obtained, and a first health frequency response function database is constructed.
According to the method for nondestructive testing of glass damage of the aircraft canopy framework, after the detection points are arranged on the canopy framework structure under the nondestructive condition, the appropriate workbench is selected for installation of the canopy framework structure, the appropriate detection points are selected according to different testing states for arrangement of the acceleration sensor, and if the installation position of the acceleration sensor is a curved surface, measures are taken to enable the installation direction of the acceleration sensor to be consistent with the testing direction.
In one embodiment of the present application, as shown in fig. 2, in S104, the test system includes: the device comprises a vibration exciter, a data acquisition unit and a computer, wherein a force hammer of the vibration exciter is abutted against one side of a canopy framework structure different from one side on which an acceleration sensor is installed and is used for applying excitation to a detection point of the canopy framework structure, wherein the abutting positions of the force hammer and the canopy framework structure correspond to the installation position of the acceleration sensor, and the force sensor is arranged on the force hammer; the output end of the data acquisition unit is connected with the vibration exciter through a power amplifier, and the input end of the data acquisition unit is respectively connected with the acceleration sensor and the force sensor; and the computer is connected with the data acquisition unit to acquire the modal data acquired by the data acquisition unit and realize data processing and result output.
In one embodiment of the present application, in S105, the first healthy frequency response function data of the canopy framework structure may be acquired by using a stochastic method or a phase resonance method. And the first health frequency response function data comprises the frequency and the mode shape of each order mode.
According to the nondestructive testing method for glass damage of the canopy framework of the airplane, in S200, a detection point of the canopy framework structure to be tested is tested, the same testing method in S100 is adopted, the detection point is arranged on the canopy framework structure to be tested, a vibration exciter is arranged on one side of the canopy framework structure to be tested, an acceleration sensor is arranged on the other side of the canopy framework structure to be tested, after excitation is carried out through a force hammer, vibration signal data of the detection point are collected, and the vibration signal data are processed to obtain second healthy frequency response function data of the canopy framework structure to be tested.
According to the nondestructive testing method for glass damage of the aircraft canopy framework, the initial state of the structure to be tested and the vibration frequency response function after the test state are detected through a modal testing identification technology, and whether the structure at the detection point is damaged or not is judged. According to the method, the metal framework of the canopy to be detected is not damaged through in-situ vibration analysis, so that the defect that the structure is damaged for detection is overcome, and the non-destructive detection on the invisible part is realized; secondly, the detection cost of the instrument and the equipment used in the application is low; thirdly, the modal detection method is not easily interfered by environmental conditions, and is favorable for the outfield use of the damage detection of the canopy framework glass.
The nondestructive testing method for the glass damage of the aircraft canopy framework provides an effective solution for nondestructive testing of an organic glass structure in the metal framework of the aircraft canopy, has important application value in the aspects of experimental research and verification of the service life of the organic glass structure of the aircraft canopy, and can provide guarantee for monitoring the faults of the organic glass structure of the existing aircraft canopy.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A nondestructive testing method for glass damage of an aircraft canopy framework is characterized by comprising the following steps:
step one, constructing a first health frequency response function database of a canopy framework structure under the condition of no damage;
step two, acquiring a canopy framework structure to be detected, and testing a detection point of the canopy framework structure to be detected to obtain second health frequency response function data of the canopy framework structure to be detected;
and step three, comparing the second health frequency response function data with the frequency response function of the first health frequency response function database, and judging whether the detection point of the canopy framework structure to be detected is damaged or not.
2. The method for nondestructive testing of glass damage of an aircraft canopy framework of claim 1 wherein in step one, said constructing a first healthy frequency response function database of a canopy framework structure under non-damage conditions comprises:
s101, obtaining a canopy framework structure under the condition of no damage, arranging detection points on the canopy framework structure, and establishing a geometric wire frame model according to the coordinates of the detection points of the canopy framework structure;
s102, mounting a canopy framework structure on a workbench;
s103, installing an acceleration sensor on a detection point of the canopy framework structure;
s104, building a test system, and testing the canopy framework structure after debugging;
s105, first health frequency response function data of the canopy framework structure are obtained, and a first health frequency response function database is constructed.
3. The method for nondestructive testing of glass damage of aircraft canopy framework of claim 2 wherein in S103, when the mounting position of the acceleration sensor is curved, the mounting direction of the acceleration sensor is adjusted to be consistent with the testing direction.
4. The method for nondestructive testing of glass damage of aircraft canopy framework of claim 3 wherein in S104 the testing system comprises: a vibration exciter, a data acquisition unit and a computer, wherein,
the force hammer of the vibration exciter is abutted against one side of a canopy framework structure, which is different from one side of the canopy framework structure, the abutting position of the force hammer is corresponding to the mounting position of the acceleration sensor, and the force sensor is arranged on the force hammer;
the output end of the data acquisition unit is connected with the vibration exciter through a power amplifier, and the input end of the data acquisition unit is respectively connected with the acceleration sensor and the force sensor;
and the computer is connected with the data acquisition unit.
5. The nondestructive testing method for glass damage of an aircraft canopy framework according to claim 4, wherein in S105, the first health frequency response function data of the canopy framework structure is obtained by a stochastic method.
6. The nondestructive testing method for glass damage of an aircraft canopy framework according to claim 4, wherein in S105, the first healthy frequency response function data of the canopy framework structure is obtained by a phase resonance method.
7. The method for nondestructive testing of glass damage of aircraft canopy framework according to claim 5 or 6 wherein in S105, the first health frequency response function data includes frequency and mode shape of each order mode.
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| CN202011529163.0A CN112710742A (en) | 2020-12-22 | 2020-12-22 | Nondestructive testing method for glass damage of aircraft canopy framework |
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| CN202011529163.0A CN112710742A (en) | 2020-12-22 | 2020-12-22 | Nondestructive testing method for glass damage of aircraft canopy framework |
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Cited By (1)
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| CN117864414A (en) * | 2023-11-07 | 2024-04-12 | 广州民航职业技术学院 | Method, system, equipment and storage medium for detecting damage of airplane windshield |
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