Flexible self-suction air detection device and air detection method for fuselage pressure sensor

Abstract

The invention discloses a flexible self-suction detection device and method for a fuselage pressure sensor, belongs to the technical field of air tightness testing of aircrafts, and solves the problems that an existing air tightness testing mode is tedious in operation and low in detection efficiency. The flexible self-suction detection device for the fuselage pressure sensor comprises a cross beam, wherein at least one hand pump suction cup and a plurality of suction cup assemblies are mounted at the bottom of the cross beam; the multiple suction cup assemblies are communicated through air pipes. And the air pipe is connected with an atmosphere data tester. During use, the hand pump suction cup is adsorbed on the fuselage skin, each suction cup assembly corresponds to the pressure hole in the surface of each skin, the air pressure holes can be subjected to air detection testing at the same time by connecting the air data tester with the air pipe, the testing efficiency is improved, and the working intensity is reduced; a height difference exists between the sucker body and the hand pump sucker assembly, the spring is compressed after the hand pump sucker adsorbs, counter-acting force is applied to the sucker body, the sucker body is pressed on a machine body, and therefore the pressure hole is sealed.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft air tightness testing, and in particular to a flexible self-priming air detection device and an air detection method for a fuselage pressure sensor. Background Art

[0002] When an aircraft is grounded, the fuselage pressure sensors require ground air inspection and maintenance testing. These sensors are mounted on either side of the aircraft fuselage. Pressure holes are provided on the sensor surface for ventilation, and the end faces of the pressure holes are flush with the fuselage skin. The sensor is flush with the fuselage skin, forming a smooth curved surface. Aside from the pressure holes, the rest of the sensor surface is a smooth curved surface with no mounting holes or mounting supports, making ground air inspection testing of the sensors challenging.

[0003] In the existing technology, the main methods of gas detection testing of fuselage pressure sensors include handheld, self-priming suction cup fixed, pressure hole self-priming installation fixed, etc. These gas detection methods can only detect one pressure hole at a time, with low detection efficiency, cumbersome operation, high manual labor consumption, unreliable sealing, poor stability, and easy damage to the sensor pressure hole.

[0004] Therefore, the present invention provides a flexible self-priming gas detection device, which makes the gas detection test operation convenient, the sealing reliable, and the gas detection test stable. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the present invention provides a flexible self-priming air detection device and air detection method for a fuselage pressure sensor, which solves the problems of cumbersome operation and low detection efficiency of the existing air detection test method.

[0006] In the first aspect, in order to achieve the above-mentioned purpose, the technical solution adopted by the present invention is: A flexible self-priming air detection device for a fuselage pressure sensor comprises a crossbeam, at the bottom of which is mounted at least one hand pump suction cup and a plurality of suction cup assemblies; the plurality of suction cup assemblies are connected via an air pipe; and the air pipe is connected to an atmospheric data tester.

[0007] In this solution, when in use, the hand pump suction cup is adsorbed on the fuselage skin, so that each suction cup assembly corresponds to each pressure hole on the skin surface, which can achieve stable fixation of the device and reliable sealing after fixation; several suction cup assemblies are connected by air pipes, and the air pipes are connected using an atmospheric data tester to perform air inspection tests on multiple air pressure holes at the same time, which improves test efficiency and reduces work intensity.

[0008] Furthermore, the suction cup assembly includes a suction cup body, to which a ventilation column is connected; one end of the ventilation column passes through a through hole on the beam and is threadedly connected to a locking nut; a slip ring is also provided in the through hole of the beam, and the ventilation column passes through the slip ring; a spring is provided between the suction cup body and the slip ring.

[0009] In this solution, when the hand pump suction cup is adsorbed on the fuselage skin, the suction cup body and the fuselage squeeze each other, the ventilation column slides in the through hole of the crossbeam, and the spring on the ventilation column is compressed; when the spring is compressed, a reaction force is applied to the suction cup body, making it close to the skin, thereby sealing the pressure hole, achieving reliable sealing of the pressure hole, and providing a guarantee for the results of subsequent gas inspection tests.

[0010] Furthermore, the end of the ventilation column is configured as a pagoda-shaped nozzle, and the ventilation column is connected to the air pipe through the pagoda-shaped nozzle.

[0011] Furthermore, among the several suction cup assemblies, the ventilation columns in the two suction cup assemblies located at both ends of the air pipe are directly connected to the end of the air pipe; the ventilation column in the suction cup assembly located in the middle of the air pipe is connected to the air pipe through a three-way adapter and at least one four-way adapter; the atmospheric data tester is connected to the pagoda-shaped pipe nozzle of the four-way adapter.

[0012] In this solution, the air pipes are connected using a four-way adapter and a three-way adapter, so that each suction cup body is connected to a whole air path. The pagoda-shaped nozzle of the four-way adapter is connected to the atmospheric data tester for ventilation, so that negative pressure can be drawn on all suction cup bodies.

[0013] Furthermore, when the spring is in a naturally extended state, the distance between the suction cup body and the crossbeam is greater than the distance between the hand pump suction cup and the crossbeam.

[0014] In this solution, there is a height difference between the suction cup body and the hand pump suction cup after assembly. The suction cup body is lower than the hand pump suction cup, so that after the hand pump suction cup is adsorbed on the fuselage, the suction cup body and the fuselage are squeezed, the spring is compressed, and the suction cup body is pressed tightly against the fuselage through the elastic force, which provides a guarantee for air tightness.

[0015] Furthermore, the suction cup body is made of silicone.

[0016] Further, the hand pump suction cup is connected to the crossbeam by bolts.

[0017] In a second aspect, the present invention provides a flexible self-priming air detection method for a fuselage pressure sensor based on the flexible self-priming air detection device provided in the first aspect, comprising the following steps: Step S1: Installing the flexible self-priming air detection device of the fuselage pressure sensor on the fuselage skin surface, with the suction cup body aligned with the pressure hole on the skin surface during installation; Step S2: using a hand pump suction cup to provide negative pressure so that the hand pump suction cup is adsorbed on the surface of the skin; Step S3: Connect the atmospheric data tester and perform a ground atmospheric test of the fuselage pressure sensor.

[0018] In this plan, Furthermore, step S2 specifically includes: Step S201: negative pressure is applied by pressing the pump of the hand pump suction cup, and after the negative pressure is applied, the hand pump suction cup is adsorbed on the surface of the fuselage skin; Step S202: Due to the height difference between the suction cup body and the hand pump suction cup assembly, the suction cup body and the vent column move relative to the through hole on the beam, the spring on the vent column is compressed, and under the reaction force of the spring, the suction cup body abuts against the skin surface to seal the pressure hole.

[0019] Furthermore, step S3 specifically includes: Step S301: Connecting the air data tester to the pagoda-shaped nozzle of the four-way adapter; Step S302: activating the air extraction valve to gradually reduce the pressure at the test port to a target negative pressure value; Step S303: Detecting the air leakage rate or air leakage amount of the fuselage pressure sensor.

[0020] The beneficial effects of the present invention are: In the flexible self-priming air detection device for the fuselage pressure sensor provided by the present invention, a hand pump suction cup is installed on the crossbeam. By pressing the hand pump to draw negative pressure, the hand pump suction cup can be flexibly adsorbed on the skin surface. It can adapt to the skin shape, is reliably installed and does not fall off, and is easy to operate. The suction cup body made of silicone material flexibly adheres to the skin surface of the fuselage and aligns with the pressure hole, which can effectively seal the pressure hole. At the same time, there is a height difference between the suction cup body and the hand pump suction cup assembly. After the hand pump suction cup is adsorbed, the spring is compressed, exerting a reaction force on the suction cup body, pressing the suction cup body tightly against the fuselage, thereby sealing the pressure hole. A locking nut is provided on the ventilation column. By adjusting the locking nut, the height of the ventilation column relative to the crossbeam through hole can be changed, thereby adjusting the installation height of the suction cup body, so that the height difference between the hand pump suction cup and the suction cup body can be adjusted according to the usage. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 This is a structural schematic diagram of a flexible self-priming air detection device for a fuselage pressure sensor according to the present invention; Figure 2 It is a schematic diagram of the cross-sectional structure of the suction cup assembly in the present invention.

[0022] Reference numerals: 1. Crossbeam; 11. Tee adapter; 12. Air pipe; 2. Hand pump suction cup; 3. Suction cup body; 4. Ventilation column; 5. Slip ring; 6. Spring; 7. Lock nut; 8. Bolt; 9. Four-way adapter; DETAILED DESCRIPTION The present invention will be further described below with reference to the accompanying drawings and specific embodiments. Specific embodiments of the present invention are described below to facilitate understanding of the present invention by those skilled in the art. However, it should be understood that the present invention is not limited to the scope of the specific embodiments. For those skilled in the art, as long as various changes are within the spirit and scope of the present invention as defined and determined by the appended claims, these changes are obvious, and all inventions and creations utilizing the concepts of the present invention are protected.

[0023] like Figure 1 As shown, this embodiment provides a flexible self-priming air detection device for a fuselage pressure sensor. The flexible self-priming air detection device for a fuselage pressure sensor is simple to operate, can quickly perform air detection tests on multiple pressure holes, and has high detection efficiency. The device specifically includes: Crossbeam 1, air pipe 12, hand pump suction cup 2 and several suction cup assemblies; The bottom of the crossbeam 1 is equipped with at least one hand pump suction cup 2 and several suction cup assemblies. These assemblies are connected via an air pipe 12, which is connected to an atmospheric data tester. During use, the hand pump suction cup 2 is attached to the fuselage skin, with each suction cup assembly corresponding to a pressure hole on the skin surface. Using the atmospheric data tester connected to the air pipe 12, multiple pressure holes can be tested simultaneously, improving testing efficiency.

[0024] The suction cup assembly includes a suction cup body 3, a vent column 4, a locking nut 7, a slip ring 5, and a spring 6. The vent column 4 is connected to the suction cup body 3. One end of the vent column 4 extends through a through-hole in the crossbeam 1 and is threadedly connected to the locking nut 7. A slip ring 5 is also provided in the through-hole of the crossbeam 1, through which the vent column 4 is inserted. A spring 6 is provided between the suction cup body 3 and the slip ring 5. When the hand pump suction cup 2 is attached to the fuselage skin, the suction cup body 3 and the fuselage are squeezed against each other, the vent column 4 slides within the through-hole of the crossbeam 1, and the spring 6 on the vent column 4 is compressed. When the spring 6 is compressed, it exerts a reaction force on the suction cup body 3, causing the suction cup body 3 to adhere tightly to the fuselage skin, thereby sealing the pressure hole.

[0025] When the spring 6 is in a naturally extended state, the distance between the suction cup body 3 and the crossbeam 1 is greater than the distance between the hand pump suction cup 2 and the crossbeam 1; in this design, there is a height difference between the suction cup body 3 and the hand pump suction cup 2 after assembly, and the suction cup body 3 is lower than the hand pump suction cup 2, so that after the hand pump suction cup 2 is adsorbed on the fuselage, the suction cup body 3 and the fuselage are squeezed, the spring 6 is compressed, and the suction cup body 3 is pressed against the fuselage through the elastic force, which ensures air tightness.

[0026] The end of the ventilation column 4 is set as a pagoda-shaped nozzle, and the ventilation column 4 is connected to the air pipe 12 through the pagoda-shaped nozzle.

[0027] Among several suction cup assemblies, the ventilation columns 4 in the two suction cup assemblies located at both ends of the air pipe 12 are directly connected to the end portions of the air pipe 12; the ventilation column 4 in the suction cup assembly located in the middle of the air pipe 12 is connected to the air pipe 12 through a three-way adapter 11 and at least one four-way adapter 9; the atmospheric data tester is connected to the pagoda-shaped pipe nozzle of the four-way adapter 9; this design utilizes the four-way adapter 9 and the three-way adapter 11 to connect the air pipe 12, so that each suction cup body 3 is connected to a whole air path, and the pagoda-shaped pipe nozzle of the four-way adapter 9 is connected to the atmospheric data tester for ventilation, so that negative pressure can be drawn on all suction cup bodies 3.

[0028] As a preferred embodiment of this invention, four groups of suction cup assemblies are provided, and two hand pump suction cups 2 are provided. The four groups of suction cup assemblies are equidistantly spaced along the length of the beam 1; the two hand pump suction cups 2 are connected to the beam 1 between the first and second groups of suction cup assemblies, and between the third and fourth groups of suction cup assemblies, respectively.

[0029] The material of the suction cup body 3 is silicone.

[0030] The hand pump suction cup 2 is connected to the crossbeam 1 by bolts 8.

[0031] Example 2: Based on the flexible self-priming air detection device for a fuselage pressure sensor provided in Example 1, this example provides a flexible self-priming air detection method for a fuselage pressure sensor, including the following steps: Step S1: Install the flexible self-priming air detection device of the fuselage pressure sensor on the surface of the fuselage skin. During installation, visually observe the suction cup body 3 and align it with the pressure hole on the skin surface.

[0032] Step S2: using the hand pump suction cup 2 to provide negative pressure so that the hand pump suction cup 2 is adsorbed on the surface of the skin; specifically comprising: Step S201: negative pressure is applied by pressing the pump of the hand pump suction cup 2. After the negative pressure is applied, the hand pump suction cup 2 is adsorbed on the surface of the fuselage skin; Step S202: Due to the height difference between the suction cup body 3 and the hand pump suction cup 2, the suction cup body 3 and the vent column 4 move relative to the through hole on the beam 1, and the spring 6 on the vent column 4 is compressed. Under the reaction force of the spring 6, the suction cup body 3 abuts against the skin surface to seal the pressure hole.

[0033] Step S3: Connecting the atmospheric data tester and performing a ground atmospheric test of the fuselage pressure sensor; specifically including: Step S301: Connecting the air data tester to the pagoda-shaped nozzle of the four-way adapter 9; Step S302: activating the air extraction valve to gradually reduce the pressure at the test port to a target negative pressure value; Step S303: Detecting the air leakage rate or air leakage amount of the fuselage pressure sensor.

[0034] Those skilled in the art will appreciate that the embodiments herein are intended to help readers understand the principles of the present invention, and it should be understood that the scope of protection of the present invention is not limited to such specific descriptions and embodiments. Those skilled in the art can make various other specific variations and combinations based on the technical teachings disclosed in the present invention without departing from the essence of the present invention, and such variations and combinations are still within the scope of protection of the invention.

Claims

1. A flexible self-priming air detection device for a fuselage pressure sensor, characterized in that: The invention comprises a crossbeam (1), wherein at least one hand pump suction cup (2) and a plurality of suction cup assemblies are installed at the bottom of the crossbeam (1); the plurality of suction cup assemblies are connected via an air pipe (12); and the air pipe (12) is connected to an atmospheric data tester.

2. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 1, characterized in that: The suction cup assembly comprises a suction cup body (3), and a vent column (4) is connected to the suction cup body (3); one end of the vent column (4) passes through the through hole on the crossbeam (1) and is threadedly connected to the locking nut (7); a slip ring (5) is also provided in the through hole of the crossbeam (1), and the vent column (4) passes through the slip ring (5); a spring (6) is provided between the suction cup body (3) and the slip ring (5).

3. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 2, characterized in that: The end of the ventilation column (4) is provided as a pagoda-shaped nozzle, and the ventilation column (4) is connected to the air pipe (12) via the pagoda-shaped nozzle.

4. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 2, characterized in that: Among the plurality of suction cup assemblies, the ventilation columns (4) in the two suction cup assemblies located at both ends of the air pipe (12) are directly connected to the ends of the air pipe (12); the ventilation column (4) in the suction cup assembly located in the middle of the air pipe (12) is connected to the air pipe (12) through a three-way adapter (11) and at least one four-way adapter (9); and the atmospheric data tester is connected to the pagoda-shaped nozzle of the four-way adapter (9).

5. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 2, characterized in that: When the spring (6) is in a naturally extended state, the distance between the suction cup body (3) and the crossbeam (1) is greater than the distance between the hand pump suction cup (2) and the crossbeam (1).

6. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 2, characterized in that: The material of the suction cup body (3) is silicone.

7. The flexible self-priming air detection device for a fuselage pressure sensor according to claim 1, characterized in that: The hand pump suction cup (2) is connected to the crossbeam (1) via bolts (8).

8. A gas detection method according to any one of claims 1 to 7, characterized in that: The following steps are involved: Step S1: Install the flexible self-priming air detection device of the fuselage pressure sensor on the surface of the fuselage skin, and align the suction cup body (3) with the pressure hole on the skin surface during installation; Step S2: using the hand pump suction cup (2) to provide negative pressure so that the hand pump suction cup (2) is adsorbed on the surface of the skin; Step S3: Connect the atmospheric data tester and perform a ground atmospheric test of the fuselage pressure sensor.

9. The air inspection method of the flexible self-priming air inspection device of the fuselage pressure sensor according to claim 8, characterized in that: The step S2 specifically includes: Step S201: negative pressure is generated by pressing the pump of the hand pump suction cup (2), and after the negative pressure is generated, the hand pump suction cup (2) is adsorbed on the surface of the fuselage skin; Step S202: Due to the height difference between the suction cup body (3) and the hand pump suction cup (2), the suction cup body (3) and the vent column (4) move relative to the through hole on the beam (1), the spring (6) on the vent column (4) is compressed, and under the reaction force of the spring (6), the suction cup body (3) abuts against the skin surface to form a seal for the pressure hole.

10. The air inspection method of the flexible self-priming air inspection device of the fuselage pressure sensor according to claim 9, characterized in that: The step S3 specifically includes: Step S301: Connect the atmospheric data tester to the pagoda-shaped nozzle of the four-way adapter (9); Step S302: activating the air extraction valve to gradually reduce the pressure at the test port to a target negative pressure value; Step S303: Detecting the air leakage rate or air leakage amount of the fuselage pressure sensor.

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