CN112326150B - Air tightness test device and method for aircraft body structure - Google Patents
Air tightness test device and method for aircraft body structure Download PDFInfo
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- CN112326150B CN112326150B CN202011226941.9A CN202011226941A CN112326150B CN 112326150 B CN112326150 B CN 112326150B CN 202011226941 A CN202011226941 A CN 202011226941A CN 112326150 B CN112326150 B CN 112326150B
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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
- G01M3/00—Investigating fluid-tightness of structures
- G01M3/02—Investigating fluid-tightness of structures by using fluid or vacuum
- G01M3/26—Investigating fluid-tightness of structures by using fluid or vacuum by measuring rate of loss or gain of fluid, e.g. by pressure-responsive devices, by flow detectors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Examining Or Testing Airtightness (AREA)
Abstract
The invention discloses an air tightness test device for an aircraft body structure and a test method thereof, wherein the air tightness test device comprises a control system, vacuumizing equipment, a vacuum film, a double-sided sealing adhesive tape, a measuring point vacuum gauge, a cable, a corrugated pipe and two vacuumizing connectors; the outer periphery of the vacuum film is stuck on the outer surface of the aircraft body structure by adopting a double-sided sealing tape, and a closed test area for detecting pressure drop is formed; the measuring point vacuum gauge is arranged on the vacuum film, is electrically connected with the control system through a cable and feeds back the pressure of the measuring point to the control system; the vacuum pumping equipment is used for vacuumizing or inflating the closed cavity of the test area through the communicated corrugated pipe; the control system is used for controlling the running state of the vacuumizing equipment, setting the vacuum degree of the test area and displaying the vacuum degree value detected by the test area measuring point vacuum gauge in real time; the pressure drop detecting device is used for detecting whether the pressure drop of the closed test area on the outer surface of the aircraft body structure meets the requirement or not so as to verify the tightness of the aircraft body structure.
Description
[ field of technology ]
The invention relates to a technology for testing tightness of an aircraft body structure, in particular to an air tightness test device and a test method for the aircraft body structure.
[ background Art ]
At present, for an aircraft adopting an airtight cabin body structural design, an inflation leakage detection method is generally adopted to check the tightness of the aircraft, and if the air tightness is not in accordance with the standard, the cabin is decompressed at high altitude, so that the life safety of a pilot is endangered. Because the volume of the aircraft sealed cabin is large, the air inflation time is long in the airtight test process; part of the machine types have requirements on air pressure gradient in the inflation process, and the internal air pressure needs to be changed stably; if the constant air inflow is used for inflation, the air pressure changes faster in the initial stage of inflation and changes slowly in the later stage.
However, when the air tightness test is required for an aircraft not adopting the airtight cabin structural design, if the inflation leak detection method is adopted, the closed space is difficult to construct for the test area due to the complex shape and connection of the machine body structure. Therefore, only the outer surface of the aircraft body structure can be vacuumized, whether the pressure drop of the test area meets the requirement or not can be checked, so that the tightness of the aircraft body structure can be verified, and a corresponding airtight detection device is urgently needed for the existing aircraft airtight cabin structure so as to perform airtight inspection on the cabin with a complex aircraft body structure.
[ invention ]
The invention provides an air tightness test device and a test method for an aircraft body structure, which are designed for a non-airtight cabin, have irregular shapes and complex connection, and have the advantages of strong universality, simple and ingenious structure and low manufacturing cost, and are easy to popularize and apply in various aircraft manufacturers.
The technical scheme adopted for solving the technical problems is as follows:
the air tightness test device for the aircraft body structure is used for detecting the pressure drop of a closed test area on the outer surface of the aircraft body structure; the airtight test device comprises a control system, vacuumizing equipment, a vacuum film, a double-sided sealing tape, a measuring point vacuum gauge, a cable, a corrugated pipe and two vacuumizing connectors;
the outer periphery of the vacuum film is stuck on the outer surface of the aircraft body structure by adopting the double-sided sealing tape, and a closed test area for detecting pressure drop is formed;
the measuring point vacuum gauge is arranged on the vacuum film through a vacuumizing connector and is communicated with the closed cavity of the test area;
the measuring point vacuum gauge is electrically connected with the control system through the cable and feeds back the pressure of a measuring point corresponding to the measuring point vacuum gauge to the control system;
one end of the corrugated pipe is arranged on the vacuum film through a vacuumizing joint, and the corrugated pipe is communicated with the closed cavity of the test area;
the other end of the corrugated pipe is connected to the vacuumizing equipment, and the vacuumizing equipment vacuumizes or inflates the closed cavity of the test area through the communicated corrugated pipe;
the control system is connected with the vacuumizing equipment and is used for controlling the running state of the vacuumizing equipment, setting the vacuum degree of the test area and displaying the vacuum degree value detected by the test area measuring point vacuum gauge in real time.
Further, the control system is a PLC control system.
Further, the vacuum pumping device and the control system are installed on a mobile vehicle.
Further, the connection part of the vacuumizing connector and the vacuum gauge or the corrugated pipe is also respectively provided with a vacuum clamp for clamping and fixing the connector; the vacuum clamp is made of KF series of national standard GB4982-85, and the vacuum clamp comprises an O-shaped sealing ring with a bracket.
Further, the vacuumizing joint comprises an upper joint piece, a lower pressing piece, a rubber sealing pad and a connecting screw, wherein the upper joint piece is provided with a ventilating joint which is connected with the measuring point vacuum gauge or the corrugated pipe and locked through a vacuum clamp, the upper joint piece and the lower pressing piece clamp a vacuum film through the connecting screw, and sealing grooves for installing the rubber sealing pad are respectively concavely formed in the inner walls of the contact surfaces of the upper joint piece and the lower pressing piece and the vacuum film.
Further, a polyester breathable felt pad for avoiding damaging the outer surface of the machine body structure is also arranged in the test area corresponding to the vacuumizing connector.
Further, the vacuumizing equipment comprises a manual inflation valve, an automatic inflation valve, a large throttle valve, an automatic evacuation valve, a small throttle valve, a maintenance vacuum valve, a manual evacuation valve, a pumping vacuum gauge and a vacuum pump, wherein the pumping vacuum gauge is arranged on an air inlet and outlet pipeline of the vacuum pump;
the manual evacuation valve is respectively connected with the large throttle valve and the automatic evacuation valve which are connected in series, the small throttle valve and the maintenance vacuum valve which are connected in series, and three groups of parallel pipelines are formed and then connected to the air inlet and outlet pipelines of the vacuum pump, and the other ends of the three groups of parallel pipelines are communicated with the closed cavity of the test area through the corrugated pipe and the vacuumizing joint;
the other ends of the three groups of parallel pipelines are also connected in parallel with a manual inflation valve and an automatic inflation valve which are respectively communicated with an external air source;
the vacuum pump and the manual evacuation valve and the manual inflation valve are connected with a pipeline system for manually evacuating and manually inflating the test area, and the vacuum pump and the large throttle valve, the automatic evacuation valve, the small throttle valve, the maintenance vacuum valve and the automatic inflation valve are connected with a pipeline system for automatically evacuating and automatically inflating the test area;
the control system is also used for displaying the pump working pressure value of the pump pressure vacuum gauge detected vacuum pump.
Further, a filter for filtering the air suction source or the air inflation source is further arranged on the pipeline connected with the other ends of the three groups of parallel pipelines.
Further, the area of the test area is 1m multiplied by 1m, the adjustment can be carried out according to the actual condition of the surface of the aircraft body structure, and the division of the test area into the test area is completed for a plurality of times.
The method for controlling the air tightness test device of the aircraft body structure is used for the tightness test of the aircraft body structure and comprises the following steps of:
firstly, pushing the mobile vehicle to a position 0.5m near a test area of an aircraft body;
then cutting a vacuum film with the length 50mm greater than each side of the test area, installing two vacuumizing connectors on the vacuum film, preparing vent holes of the vacuum film according to the vent hole sizes of the vacuumizing connectors, adhering the vacuum film on the outer surface of a machine body structure of the test area by using a double-sided sealing adhesive tape, and constructing a closed test area for multiple times in different areas;
secondly, connecting the corrugated pipe with vacuumizing equipment and a vacuumizing joint by using a vacuum clamp, connecting the vacuumizing joint with a measuring point vacuum gauge by using the vacuum clamp, and connecting the measuring point vacuum gauge with a PLC control system by using a cable;
and finally, connecting a power supply of the mobile vehicle, setting the vacuum degree of a test area through a PLC control system, manually or automatically starting a vacuumizing device through the PLC control system, vacuumizing the test area by the vacuumizing device, detecting and feeding back the vacuum degree of the test area to the PLC control system in real time by a measuring point vacuum gauge, after the vacuum degree of the test area reaches a set value, manually or automatically disconnecting the vacuumizing device through the PLC control system, recording the vacuum degree value of the measuring point vacuum gauge in real time, feeding back the test area to the PLC control system in a certain time, calculating the pressure drop of the test area in the certain time, checking the pressure drop after a certain time to verify the tightness of the body structure, and if the tightness of the body structure of the aircraft in the test area is smaller than the test requirement, meeting the requirement.
The beneficial effects of the invention are as follows:
the invention aims at the aircraft body structure which is not designed in an airtight cabin, has irregular shape and is connected with complex, a vacuum film is stuck on the outer surface of the aircraft body structure in a test area by using a double-sided sealing tape, and the test area which is sealed is constructed for a plurality of times in different areas; the measuring point vacuum gauge, the vacuumizing equipment and the control system are effectively matched to vacuumize the outer surface of the aircraft body structure for multiple times in different areas, and whether the pressure drop in the test area within a certain time meets the requirement is checked to verify the tightness of the aircraft body structure.
The device has the advantages of strong universality, simple and ingenious structure, low manufacturing cost and easy popularization and application in various aircraft manufacturers.
[ description of the drawings ]
FIG. 1 is a schematic view of a test apparatus of the present invention;
FIG. 2 is a schematic view of the connection structure of the test area of the present invention;
FIG. 3 is a schematic view of the front view of the vacuum fitting of the present invention;
fig. 4 is a schematic top view of the vacuum fitting of the present invention.
[ detailed description ] of the invention
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
An air tightness test device of an aircraft body structure is shown in fig. 1 and 2 and is used for detecting pressure drop of a closed test area on the outer surface of the aircraft body structure; the device comprises a PLC control system 1, a vacuumizing device 2, a vacuum film 3, a double-sided sealing tape 4, a measuring point vacuum gauge 5, a cable 6, a corrugated pipe 7 and two vacuumizing connectors 8, wherein the vacuumizing device 2 and the PLC control system 1 are arranged on a moving vehicle 9; the outer periphery of the vacuum film 3 is stuck on the outer surface of the aircraft body structure X by adopting a double-sided sealing tape 4, and a closed test area 10 for detecting pressure drop is formed, the area of the test area 10 is 1m multiplied by 1m, the adjustment can be carried out according to the actual condition of the aircraft body structure surface, and the division is completed for a plurality of times. The measuring point vacuum gauge 5 is arranged on the vacuum film 3 through a vacuumizing joint 8, and the measuring point vacuum gauge 5 is communicated with a closed cavity of the test area 10; the measuring point vacuum gauge 5 is electrically connected with the PLC control system 1 through a cable 6, and the pressure of a measuring point corresponding to the measuring point vacuum gauge 5 is fed back to the PLC control system 1.
Continuing to refer to fig. 1 and 2, one end of the bellows 7 is mounted on the vacuum membrane 3 via a vacuum-pumping joint 8, and the bellows 7 is communicated with the closed cavity of the test area 10; the other end of the corrugated pipe 7 is connected to the vacuumizing device 2, and the vacuumizing device 2 vacuumizes or inflates the closed cavity of the test area 10 through the communicated corrugated pipe 7; the connection part of the vacuumizing connector 8 and the vacuum gauge or the corrugated pipe 7 is also respectively provided with a vacuum clamp 11 for clamping and fixing the connector, the vacuum clamp 11 adopts KF series of national standard GB4982-85, and the vacuum clamp 11 comprises an O-shaped sealing ring with a bracket; the polyester ventilation felt pad 12 which can avoid damaging the outer surface of the machine body structure is also arranged in the test area 10 corresponding to the vacuumizing joint 8. The PLC control system 1 is connected with the vacuumizing equipment 2, and the PLC control system 1 is used for controlling the operation state of the vacuumizing equipment 2, setting the vacuum degree of the test area 10 and displaying the vacuum degree value detected by the test area 10 measuring point vacuum gauge 5 in real time.
As shown in fig. 3 and 4, the vacuumizing joint 8 comprises an upper joint piece 80, a lower pressing piece 81, a rubber sealing gasket 82 and a connecting screw 83, wherein a ventilating joint 800 which is connected with the measuring point vacuum gauge 5 or the corrugated pipe 7 and is locked by the vacuum clamp 11 is arranged on the upper joint piece 80, the upper joint piece 80 and the lower pressing piece 81 clamp the vacuum film 3 through the connecting screw 83, and sealing grooves 84 for installing the rubber sealing gasket 82 are respectively concavely arranged on the inner walls of the contact surfaces of the upper joint piece 80 and the lower pressing piece 81 and the vacuum film 3.
As shown in fig. 1 and 2, the vacuum pumping apparatus 2 includes a manual air charging valve 20, an automatic air charging valve 21, a large throttle valve 22, an automatic air evacuation valve 23, a small throttle valve 24, a maintenance vacuum valve 25, a manual air evacuation valve 26, a pumping vacuum gauge 27 and a vacuum pump 28, wherein the pumping vacuum gauge 27 is installed on an air inlet and outlet pipeline of the vacuum pump 28; the manual evacuation valve 26 is respectively connected with the large throttle valve 22 and the automatic evacuation valve 23 which are connected in series, the small throttle valve 24 and the maintenance vacuum valve 25 which are connected in series, and three groups of parallel pipelines are formed and then are connected to the air inlet and outlet pipelines of the vacuum pump 28, and the other ends of the three groups of parallel pipelines are communicated with the closed cavity of the test area 10 through the corrugated pipe 7 and the vacuumizing joint 8; the other ends of the three groups of parallel pipelines are also connected in parallel with a manual inflation valve 20 and an automatic inflation valve 21 which are respectively communicated with an external air source; a filter 29 for filtering the pumping air source or the inflating air source is also arranged on the pipeline of the corrugated pipe 7 connected with the other ends of the three groups of parallel pipelines. The PLC control system 1 is also used to display the pump operating pressure value of the pump pressure gauge 27 detecting the vacuum pump 28.
In use, as further shown in fig. 1 and 2, the vacuum pump 28 and the manual evacuation valve 26 and the manual inflation valve 20 form a pipeline system for manually evacuating and manually inflating the test area 10, and the vacuum pump 28 and the large throttle valve 22, the automatic evacuation valve 23, the small throttle valve 24, the maintenance vacuum valve 25 and the automatic inflation valve 21 form a pipeline system for automatically evacuating and automatically inflating the test area 10.
The test method of the air tightness test device of the aircraft body structure is used for the tightness test of the aircraft body structure and comprises the following steps:
first, the mobile carriage 9 is pushed to about 0.5m near the test area 10 of the aircraft body;
then cutting a vacuum film 3 with the length approximately 50mm greater than each side of the test area 10, installing two vacuumizing connectors 8 on the vacuum film 3, preparing vent holes of the vacuum film 3 according to the vent hole size of the vacuumizing connectors 8, adhering the vacuum film 3 on the outer surface of the machine body structure of the test area 10 by using a double-sided sealing adhesive tape 4, and constructing a closed test area 10 for multiple times in different areas;
secondly, connecting the corrugated pipe 7 with the vacuumizing equipment 2 and the vacuumizing connector 8 by using a vacuum clamp 11, connecting the vacuumizing connector 8 with the measuring point vacuum gauge 5 by using the vacuum clamp 11, and connecting the measuring point vacuum gauge 5 with the PLC control system 1 by using a cable 6;
finally, connecting a power supply of the mobile vehicle 9, setting the vacuum degree of the test area 10 through the PLC control system 1, manually or automatically starting the vacuumizing equipment 2 through the PLC control system 1, vacuumizing the test area 10 by the vacuumizing equipment 2, detecting and feeding back the vacuum degree of the test area 10 to the PLC control system 1 in real time by the measuring point vacuum gauge 5, after the vacuum degree of the test area 10 reaches a set value, manually or automatically disconnecting the vacuumizing equipment 2 through the PLC control system 1, recording the vacuum degree value of the measuring point vacuum gauge 5 in real time, feeding back the test area 10 to the PLC control system 1 in a certain time, calculating the pressure drop of the test area 10 in the certain time, checking the pressure drop after a certain time (such as 5 min) to verify the tightness of the airframe structure, and if the tightness of the airframe structure of the test area 10 is smaller than the test requirement (such as less than 5 KPa), meeting the requirement.
In the description of the present invention, it should be noted that, the azimuth or positional relationship indicated by the terms "inner", "outer", etc. are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship in which the inventive product is conventionally put in use, are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore, should not be construed as limiting the present invention.
The above embodiments are merely preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, but all equivalent changes according to the shape, construction and principle of the present invention are intended to be included in the scope of the present invention.
Claims (9)
1. The air tightness test device for the aircraft body structure is used for detecting the pressure drop of a closed test area on the outer surface of the aircraft body structure; the method is characterized in that:
the airtight test device comprises a control system, vacuumizing equipment, a vacuum film, a double-sided sealing tape, a measuring point vacuum gauge, a cable, a corrugated pipe and two vacuumizing connectors;
the outer periphery of the vacuum film is stuck on the outer surface of the aircraft body structure by adopting the double-sided sealing tape, and a closed test area for detecting pressure drop is formed;
the measuring point vacuum gauge is arranged on the vacuum film through a vacuumizing connector and is communicated with the closed cavity of the test area;
the measuring point vacuum gauge is electrically connected with the control system through the cable and feeds back the pressure of a measuring point corresponding to the measuring point vacuum gauge to the control system;
one end of the corrugated pipe is arranged on the vacuum film through a vacuumizing joint, and the corrugated pipe is communicated with the closed cavity of the test area;
the other end of the corrugated pipe is connected to the vacuumizing equipment, and the vacuumizing equipment vacuumizes or inflates the closed cavity of the test area through the communicated corrugated pipe;
the control system is connected with the vacuumizing equipment and is used for controlling the running state of the vacuumizing equipment, setting the vacuum degree of the test area and displaying the vacuum degree value detected by the test area measuring point vacuum gauge in real time;
the vacuumizing equipment comprises a manual inflation valve, an automatic inflation valve, a large throttle valve, an automatic evacuation valve, a small throttle valve, a maintenance vacuum valve, a manual evacuation valve, a pumping pressure vacuum gauge and a vacuum pump, wherein the pumping pressure vacuum gauge is arranged on an air inlet and outlet pipeline of the vacuum pump;
the manual evacuation valve is respectively connected with the large throttle valve and the automatic evacuation valve which are connected in series, the small throttle valve and the maintenance vacuum valve which are connected in series, and three groups of parallel pipelines are formed and then connected to the air inlet and outlet pipelines of the vacuum pump, and the other ends of the three groups of parallel pipelines are communicated with the closed cavity of the test area through the corrugated pipe and the vacuumizing joint;
the other ends of the three groups of parallel pipelines are also connected in parallel with a manual inflation valve and an automatic inflation valve which are respectively communicated with an external air source;
the vacuum pump and the manual evacuation valve and the manual inflation valve are connected with a pipeline system for manually evacuating and manually inflating the test area, and the vacuum pump and the large throttle valve, the automatic evacuation valve, the small throttle valve, the maintenance vacuum valve and the automatic inflation valve are connected with a pipeline system for automatically evacuating and automatically inflating the test area;
the control system is also used for displaying the pump working pressure value of the pump pressure vacuum gauge detected vacuum pump.
2. An aircraft body structure tightness test device according to claim 1, wherein: the control system is a PLC control system.
3. An aircraft body structure tightness test device according to claim 1 or 2, wherein: the vacuumizing equipment and the control system are arranged on the mobile vehicle.
4. An aircraft body structure tightness test device according to claim 1, wherein: and the connection part of the vacuumizing joint and the vacuum gauge or the corrugated pipe is also respectively provided with a vacuum clamp for joint clamping and fixing.
5. An aircraft body structure tightness test device according to claim 1 or 4, wherein: the vacuumizing joint comprises an upper joint piece, a lower pressing piece, a rubber sealing gasket and a connecting screw, wherein the upper joint piece is provided with a ventilating joint which is connected with the measuring point vacuum gauge or the corrugated pipe and locked through a vacuum clamp, the upper joint piece and the lower pressing piece clamp a vacuum film through the connecting screw, and sealing grooves for installing the rubber sealing gasket are respectively concavely formed in the inner walls of the contact surfaces of the upper joint piece and the lower pressing piece and the vacuum film.
6. An aircraft body structure tightness test device according to claim 1 or 4, wherein: and a polyester breathable felt pad for avoiding damaging the outer surface of the machine body structure is also arranged in the test area corresponding to the vacuumizing joint.
7. An aircraft body structure tightness test device according to claim 1, wherein: the corrugated pipe is also provided with a filter for filtering an air suction source or an air inflation source on a pipeline connected with the other ends of the three groups of parallel pipelines.
8. An aircraft body structure tightness test device according to claim 1, wherein: the area of the test area was 1m×1m.
9. Method for operating an aircraft body structure air tightness test device according to any of claims 1-8 for the tightness test of an aircraft body structure, characterized in that it comprises the following steps:
firstly, pushing the mobile vehicle to a position 0.5m near a test area of an aircraft body;
then cutting a vacuum film with the length 50mm greater than each side of the test area, respectively installing two vacuumizing connectors on the vacuum film, preparing vent holes of the vacuum film according to the vent hole sizes of the vacuumizing connectors, adhering the vacuum film on the outer surface of a machine body structure of the test area by using a double-sided sealing adhesive tape, and constructing a closed test area for multiple times in different areas;
secondly, connecting the corrugated pipe with vacuumizing equipment and a vacuumizing joint by using a vacuum clamp, connecting the vacuumizing joint with a measuring point vacuum gauge by using the vacuum clamp, and connecting the measuring point vacuum gauge with a PLC control system by using a cable;
and finally, connecting a power supply of the mobile vehicle, setting the vacuum degree of a test area through a PLC control system, manually or automatically starting a vacuumizing device through the PLC control system, vacuumizing the test area by the vacuumizing device, detecting and feeding back the vacuum degree of the test area to the PLC control system in real time by a measuring point vacuum gauge, after the vacuum degree of the test area reaches a set value, manually or automatically disconnecting the vacuumizing device through the PLC control system, recording the vacuum degree value of the measuring point vacuum gauge in real time, feeding back the test area to the PLC control system in a certain time, calculating the pressure drop of the test area in the certain time, checking the pressure drop after a certain time to verify the tightness of the body structure, and if the tightness of the body structure of the aircraft in the test area is smaller than the test requirement, meeting the requirement.
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| CN202011226941.9A CN112326150B (en) | 2020-11-05 | 2020-11-05 | Air tightness test device and method for aircraft body structure |
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| CN114001873A (en) * | 2021-10-18 | 2022-02-01 | 中航通飞华南飞机工业有限公司 | Air tightness inspection integrated equipment and detection method for aircraft anti-icing and rain-removing system |
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| US10259597B1 (en) * | 2012-08-08 | 2019-04-16 | Tronair, Inc. | Aircraft fuel system test unit |
| CN105547608A (en) * | 2014-11-03 | 2016-05-04 | 中国飞行试验研究院 | Apparatus for air tightness testing of airplane |
| CN106768726B (en) * | 2016-11-30 | 2019-03-29 | 江西洪都航空工业集团有限责任公司 | A method of for technique for aircraft composite fuel tank sealing propertytest |
| CN109189113A (en) * | 2018-08-13 | 2019-01-11 | 北京卫星环境工程研究所 | The control pressurer system and control method of small pressure difference spacecraft product in vacuum test |
| CN110954271A (en) * | 2018-09-27 | 2020-04-03 | 中国商用飞机有限责任公司 | Plugging device and method for air tightness test of machine body |
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