CN106033020A - Device and method for detecting air tightness of airplane structure under non-supercharged state - Google Patents
Device and method for detecting air tightness of airplane structure under non-supercharged state Download PDFInfo
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- CN106033020A CN106033020A CN201510111684.7A CN201510111684A CN106033020A CN 106033020 A CN106033020 A CN 106033020A CN 201510111684 A CN201510111684 A CN 201510111684A CN 106033020 A CN106033020 A CN 106033020A
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- sealing device
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- aircaft configuration
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Abstract
The invention discloses a device and a method for detecting air tightness of an airplane structure under a non-supercharged state. The device and the method of the invention can check out air tightness of the airplane structure during an airplane structure component assembling phase, can find a sealing defect in advance and can accurately position the sealing defect, can effectively reduce a maintenance cost, and can save the development time. A vacuum sealing device 2 comprises a vacuum cover or/and a vacuum blanket; if a surface of an object to be tested is smooth, the vacuum blanket is employed, and, if the surface of the object to be tested is bulged, the vacuum cover is employed.
Description
Technical field
The invention belongs to aircaft configuration airtight test technology, particularly to detecting the bubble-tight Apparatus and method for of aircaft configuration under a kind of non pressurized state.
Background technology
At present, according to the manufacturing process of aircraft, the airtight test of aircraft is often after overall aircraft assemble, tests determine the leakage point of housing construction and leakage rate by carrying out pressurising.Determine the leakage rate of airframe structure in factory generally by the measuring machine body structure dwell time, search the method that leakage point small on airframe structure then needs to use stethoscope or use suds to spread upon fuselage surface.There is following inconvenience in such operating process: 1, airtight inspection need to be carried out after totally having assembled, riveting, docking etc. cannot easily occur when parts assemble that the position of leakage check, and the leakage position found in the aircraft manufacturing later stage is often difficult to repair；2, carrying out full machine pressurising test and aircraft is had exclusivity, other work cannot be carried out simultaneously, expends the valuable research and development time；3, the means of leak check point are the most backward, and small leakage point needs testing crew to utilize instrument to go through can to find.
Summary of the invention
The technical problem to be solved in the present invention is, be given a kind of without carrying out pressurising test, the Apparatus and method for that structure air-tightness can be checked at airplane structural parts assembling stage, improve and check efficiency, allow to, to finding that the position that there is airtight defect is repaired ahead of time, improve the air-tightness of structure.
The bubble-tight equipment of aircaft configuration that detects under a kind of non pressurized state is provided for solving the problems referred to above technical solution of the present invention, including vacuum sealing device, flexible pipe, vacuum pump and ultrasonic leak detector, described flexible pipe one end is connected with described vacuum sealing device, the other end is connected with described vacuum pump, vacuum area, the sealing situation of described ultrasonic leak detector detection vacuum area is formed between described vacuum sealing device and Devices to test when described vacuum pump starts.
Preferably, described vacuum sealing device includes vacuum (-tight) housing, and described vacuum (-tight) housing main body uses hard material, and cover mouth uses soft material.
Preferably, described vacuum sealing device includes vacuum blanket.
Technical solution of the present invention also provides for detecting under a kind of non pressurized state the bubble-tight method of aircaft configuration, comprises the following steps:
A, vacuum sealing device is compressed on the test object by the negative pressure produced by vacuum pump absorption, makes to be formed between determinand and vacuum sealing device vacuum area；
B, by using ultrasonic leak detector i.e. to can determine whether leakage and leakage position position at determinand side detection ultrasound wave.
Preferably, said method judges leak sizes by reading the decibels of ultrasound wave.
Technical solution of the present invention detects aircaft configuration air-tightness under non pressurized state, i.e. can check the air-tightness of aircaft configuration at airplane structural parts assembling stage, finds in advance and be accurately positioned seal defect, can effectively drop maintenance cost, saves the research and development time.Favorable expandability of the present invention, no matter determinand surface smoothes out or has boss, all can detect with corresponding device of the present invention and method.
Accompanying drawing explanation
Specific embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings, wherein:
Fig. 1 is detection aircaft configuration bubble-tight equipment schematic diagram under a kind of non pressurized state；
Fig. 2 is to use vacuum blanket large area detection aircaft configuration air-tightness schematic diagram.
Detailed description of the invention
First embodiment of the invention provides the bubble-tight equipment of aircaft configuration that detects under a kind of non pressurized state, including vacuum sealing device 2, flexible pipe 3, vacuum pump 5 and ultrasonic leak detector 1, described flexible pipe 3 one end is connected with described vacuum sealing device 2, the other end is connected with described vacuum pump 5, described vacuum pump 5 forms vacuum area between described vacuum sealing device 2 and Devices to test when starting, described ultrasonic leak detector 1 detects the sealing situation of vacuum area.
Preferably, described vacuum sealing device 2 include vacuum (-tight) housing and or vacuum blanket.Vacuum (-tight) housing is bell-shaped, and top is hard material, and cover mouth is soft material, is used for compensating aircaft configuration profile, it is ensured that sealing.If there is protrusion on aircaft configuration surface, then use vacuum (-tight) housing that this region is checked.Cover protrusion with vacuum (-tight) housing during concrete operations and be adjacent on aircaft configuration surface, using vacuum pump extracting vacuum, then the region that aircraft surfaces is installed such as protrusions such as antennas can be checked, as shown in Figure 1.If aircaft configuration surface is relatively big and without protrusion, vacuum blanket can be used to check.It is adjacent to vacuum blanket during concrete operations, by vacuum blanket peripheral sealing behind aircaft configuration surface, use vacuum pump extracting vacuum, then such as the larger part such as aircraft target ship can be carried out airtight inspection, as shown in Figure 2.
The detection bubble-tight method of aircaft configuration under second embodiment of the invention a kind of non pressurized state of offer:
Being placed on aircaft configuration by vacuum sealing device 2, open source of the gas, gas flows through suction in puerperal after vacuum pump 5, by the air sucking-off in vacuum sealing device 2, forms negative pressure and is also adjacent on aircaft configuration by vacuum sealing device 2.Now, if there is small leakage point on determinand, then under the effect of negative pressure, gas is only capable of being flowed into vacuum sealing device 2 by leakage point from aircaft configuration opposite side, and the flow at high speed process of this gas will produce ultrasound wave.By using ultrasonic leak detector 1 i.e. to can determine that leakage position in the method for aircaft configuration opposite side detection ultrasound wave, judge leak sizes by reading the decibels of ultrasound wave.
Finding in a particular application, the leakage point that the leak position using ultrasonic leak detector 1 to detect finds in testing with pressurising substantially conforms to, and has identical variation tendency through analyzing actual leakage rate during ultrasonic leak detector 1 reading is tested with pressurising.
Claims (5)
1. detect the bubble-tight equipment of aircaft configuration under a non pressurized state, it is characterised in that include vacuum sealing device (2), flexible pipe (3), true
Empty pump (5) and ultrasonic leak detector (1), described flexible pipe (3) one end is connected with described vacuum sealing device (2), the other end and described vacuum pump
(5) being connected, form vacuum area when described vacuum pump (5) starts between described vacuum sealing device (2) and Devices to test, described ultrasonic spy is leaked
The sealing situation of instrument (1) detection vacuum area.
Equipment the most according to claim 1, it is characterised in that described vacuum sealing device (2) includes vacuum (-tight) housing, described vacuum (-tight) housing main body uses
Hard material, cover mouth uses soft material.
Equipment the most according to claim 1, it is characterised in that described vacuum sealing device (2) includes vacuum blanket.
4. detect the bubble-tight method of aircaft configuration under a non pressurized state, it is characterised in that comprise the following steps:
A, vacuum sealing device (2) is compressed on the test object by the negative pressure produced by vacuum pump (5) absorption, makes determinand seal dress with vacuum
Put formation vacuum area between (2)；
B, by using ultrasonic leak detector (1) i.e. to can determine whether leakage and leakage position position at determinand side detection ultrasound wave.
Method the most according to claim 4, it is characterised in that judge leak sizes by reading the decibels of ultrasound wave.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510111684.7A CN106033020A (en) | 2015-03-13 | 2015-03-13 | Device and method for detecting air tightness of airplane structure under non-supercharged state |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510111684.7A CN106033020A (en) | 2015-03-13 | 2015-03-13 | Device and method for detecting air tightness of airplane structure under non-supercharged state |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106033020A true CN106033020A (en) | 2016-10-19 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201510111684.7A Pending CN106033020A (en) | 2015-03-13 | 2015-03-13 | Device and method for detecting air tightness of airplane structure under non-supercharged state |
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| CN (1) | CN106033020A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105928667A (en) * | 2016-05-06 | 2016-09-07 | 南京航空航天大学 | Non-enclosed body leakage detection method and apparatus |
| CN107515082A (en) * | 2017-07-04 | 2017-12-26 | 西安飞机工业（集团）有限责任公司 | The airtight inspection method that a kind of aircraft skin is repaired |
| CN109323822A (en) * | 2018-11-23 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Sealant experiments of sealing performance method |
| PL424167A1 (en) * | 2018-01-03 | 2019-07-15 | Instytut Techniczny Wojsk Lotniczych | Analog system for detection and monitoring of development of the structure elements damages, preferably of an aircraft structure |
| CN110723311A (en) * | 2019-10-12 | 2020-01-24 | 哈尔滨哈飞航空工业有限责任公司 | Method for checking tightness of detachable cover of airplane |
| CN114112227A (en) * | 2021-11-08 | 2022-03-01 | 陕西飞机工业有限责任公司 | Air tightness inspection method and device |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105928667A (en) * | 2016-05-06 | 2016-09-07 | 南京航空航天大学 | Non-enclosed body leakage detection method and apparatus |
| CN107515082A (en) * | 2017-07-04 | 2017-12-26 | 西安飞机工业（集团）有限责任公司 | The airtight inspection method that a kind of aircraft skin is repaired |
| PL424167A1 (en) * | 2018-01-03 | 2019-07-15 | Instytut Techniczny Wojsk Lotniczych | Analog system for detection and monitoring of development of the structure elements damages, preferably of an aircraft structure |
| CN109323822A (en) * | 2018-11-23 | 2019-02-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Sealant experiments of sealing performance method |
| CN110723311A (en) * | 2019-10-12 | 2020-01-24 | 哈尔滨哈飞航空工业有限责任公司 | Method for checking tightness of detachable cover of airplane |
| CN114112227A (en) * | 2021-11-08 | 2022-03-01 | 陕西飞机工业有限责任公司 | Air tightness inspection method and device |
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