Air tightness detection device suitable for fuselage pressure sensor

Abstract

The utility model provides an air tightness detection device suitable for a fuselage pressure sensor. The device comprises a large vacuum chuck assembly, a small vacuum chuck, a connecting rod assembly, a support plate, a vacuum tube mouthpiece, a four-way joint and a vacuum tube. Wherein the four large vacuum suction cup assemblies are fixed to the support plate in a threaded connection mode, the small vacuum suction cup assemblies are fixed to the lower ends of the connecting rod assemblies through threads and sealant, the connecting rod assemblies are fixed to kidney-shaped holes of the support plate, and the two vacuum tube connecting nozzles are fixed to the upper ends of the connecting rod assemblies on the two sides in a threaded connection mode. The four-way joint is fixed at the upper end of the middle connecting rod assembly, one end of the vacuum tube is connected with the vacuum tube mouthpiece, and the other end of the vacuum tube is connected with the four-way joint to connect the connecting rod assemblies; according to the invention, performance detection and maintenance can be carried out on the left and right fuselage pressure sensors of the airplane under a single-person operation condition.

Description

Technical Field

[0001] This application belongs to the field of tooling and equipment technology, specifically relating to an airtightness detection device suitable for fuselage pressure sensors. Background Technology

[0002] Aircraft fuselage pressure sensors are an important component of the aircraft air data system. Their sensing part includes pressure measurement areas at seven stations on the left and right sides of the fuselage, and each pressure measurement area (sensing surface) has a pressure-sensing hole.

[0003] When conducting performance tests on fuselage pressure sensors, it is necessary to apply different pressure measurement points to the fuselage pressure sensors through pressure sensing ports on the same side of the fuselage, and to meet the airtightness requirements of the entire system without damaging the sensing surface of the fuselage. At this time, there is an urgent need for a reliable, easy-to-operate, and lightweight airtightness testing device suitable for fuselage pressure sensors to meet the airtightness testing requirements of the left and right fuselage pressure sensors of the aircraft. Utility Model Content

[0004] The purpose of this application is to provide a performance testing device for fuselage pressure sensors to meet the practical needs of airtightness testing of the left and right fuselage pressure sensors of an aircraft without damaging the sensing surface of the aircraft fuselage and under single-person operation conditions.

[0005] This application provides an airtightness detection device for fuselage pressure sensors, the device comprising a large vacuum suction cup assembly, a small vacuum suction cup, a connecting rod assembly, a support plate, a vacuum tube connector, a four-way connector, and a vacuum tube;

[0006] The four large vacuum suction cup assemblies are fixed to the support plate by threaded connection. The small vacuum suction cups are fixed to the lower end of the connecting rod assembly by thread and sealant. The connecting rod assembly is fixed at the waist-shaped hole of the support plate. Two vacuum tube nozzles are fixed to the upper end of the connecting rod assemblies on both sides by threaded connection. The four-way connector is fixed to the upper end of the connecting rod assembly in the middle. One end of the vacuum tube is connected to the vacuum tube nozzle, and the other end of the vacuum tube is connected to the four-way connector, thus connecting the connecting rod assemblies.

[0007] Preferably, the large vacuum suction cup assembly serves to fix the device onto the sensing surface; the small vacuum suction cup covers the pressure-sensing hole, providing a vacuum testing environment; the connecting rod assembly connects the small vacuum suction cup and the vacuum nozzle, providing a certain tension to press the small suction cup onto the pressure-sensing hole; the support plate integrates all components into a whole; the vacuum tube nozzle, four-way connector, and vacuum tube are important components of the vacuum circuit for airtightness testing.

[0008] Preferably, the large vacuum suction cup assembly includes a connecting short rod 8 and a large vacuum suction cup 9;

[0009] The connecting rod 8 and the large vacuum suction cup 9 are connected by threads to fix the device on the sensing surface of the aircraft fuselage. The connecting rod is used to connect the large vacuum suction cup and the bracket plate. The large vacuum suction cup can create an internal and external pressure difference to fix the device on the sensing surface of the aircraft fuselage.

[0010] Preferably, the connecting rod assembly includes an anti-loosening hexagonal nut 10, a clamping hexagonal nut 11, a sleeve 12, a spring 13, and a connecting rod 14;

[0011] Among them, from top to bottom, spring 13, sleeve 12, clamping hexagonal nut 11, and anti-dislodgement hexagonal nut 10 are installed on the connecting rod 14.

[0012] Preferably, the connecting rod serves as the main body, with a vacuum tube nozzle at the top and a small vacuum suction cup at the bottom; a spring provides tension to press the small vacuum suction cup onto the pressure-sensing hole; a sleeve and a clamping hexagonal nut fix the connecting rod assembly to the support plate, ensuring that the connecting rod can slide up and down; an anti-dislodgement hexagonal nut prevents the clamping hexagonal nut, sleeve, and spring from falling out of the connecting rod assembly under the tension of the spring.

[0013] Preferably, the support plate has four threaded holes and three oblong holes. The threaded holes are used to connect the connecting short rod and fix the large vacuum suction cup assembly; the three oblong holes are used to fix the connecting rod assembly and facilitate the lateral adjustment of the connecting rod assembly so that the small vacuum suction cup can completely cover the pressure-sensing hole.

[0014] This application has the following technical advantages:

[0015] This utility model relates to a performance testing device for fuselage pressure sensors, enabling single-person operation for performance testing and maintenance of the left and right fuselage pressure sensors of an aircraft. The use of high and low temperature resistant vacuum suction cups ensures testing without damaging the aircraft fuselage sensing surface, while also solving the problem of testing in extreme high and low temperature environments. The lightweight structural design allows the device to better fit the fuselage sensing surface and saves manpower. The highly integrated design and simple operation method solve the problem of previously requiring multiple people for testing, which was time-consuming and labor-intensive. This performance testing clamp device significantly improves the pressure accuracy and airtightness testing efficiency of aircraft fuselage pressure sensors, possessing significant practical application value. Attached Figure Description

[0016] Figure 1 This is a schematic diagram of a performance testing device suitable for fuselage pressure sensors;

[0017] Figure 2 This is a schematic diagram of the suction cup assembly structure;

[0018] Figure 3 This is a schematic diagram of the connecting rod assembly structure;

[0019] Figure 4 This is a schematic diagram of the support structure;

[0020] Figure 5 This is a schematic diagram of a performance testing device for fuselage pressure sensors (including the object to be tested already mounted).

[0021] Figure 6 A schematic diagram of the pressure-sensing hole and sensing surface on one side of the device body;

[0022] Figure 7 A schematic diagram of an airtightness detection device for use on one side of the fuselage, suitable for fuselage pressure sensors;

[0023] Figure 8 This is a schematic diagram of a structure for installing an airtightness testing device suitable for fuselage pressure sensors on the surface of the product to be tested on the other side of the fuselage;

[0024] In the diagram: 1-Large vacuum suction cup assembly, 2-Small vacuum suction cup, 3-Connecting rod assembly, 4-Bracket plate, 5-Vacuum tube connector, 6-Four-way connector, 7-Vacuum tube, 8-Connecting short rod, 9-Large vacuum suction cup, 10-Anti-detachment hexagonal nut, 11-Fixed hexagonal nut, 12-Sleeve, 13-Spring, 14-Connecting rod, 15-Threaded hole, 16-Oval hole, 17-Pressure sensing hole, 18-Sensing surface. Detailed Implementation

[0025] Please see Figures 1-8 An airtightness testing device for fuselage pressure sensors is mainly composed of a large vacuum suction cup assembly, a small vacuum suction cup, a connecting rod assembly, a support plate, a vacuum tube connector, a four-way connector, and a vacuum tube. It is used to enable a single person to test the airtightness of the left and right fuselage pressure sensors of an aircraft.

[0026] The large vacuum suction cup assembly consists of three 52mm diameter and one 42mm diameter high and low temperature resistant vacuum suction cups, and aluminum alloy connecting rods 1 and 2. It is used to position and fix the performance testing device on the machine body without damaging the sensing surface. The large vacuum suction cup assembly is fixed to the bracket using threaded connections, and the connection between the vacuum suction cups and the connecting rods is sealed with glue to ensure no air leakage. Considering the shape and size requirements of the sensing surface, using a 52mm diameter vacuum suction cup on one side would cover the seam and fail to provide effective suction and fixation. Therefore, considering the suction and fixation performance requirements, a solution of three 52mm diameter and one 42mm diameter vacuum suction cups is used.

[0027] The connecting rod assembly, consisting of a connecting rod, a sleeve, an anti-loosening hexagonal nut, a fastening hexagonal nut, and a spring, is used to connect and fix the small vacuum suction cup, the bracket, and the vacuum nozzle, ensuring that the small vacuum suction cup has a Z-axis degree of freedom, so that the small vacuum suction cup can tightly fit the sensing surface when the device is fixed to the machine body. The bottom of the connecting rod assembly is connected to the small vacuum suction cup via an external thread, and the connection is sealed with glue; the top of the connecting rod is connected to the vacuum nozzle via an internal thread, and the connection is sealed with glue; the connecting rod assembly is fixed to the bracket by the sleeve and the fastening hexagonal nut.

[0028] The support plate is made of aluminum alloy and features a weight-reduction design that ensures structural strength, significantly reducing the weight of the device. The support plate uses a waist-shaped hole design at the mounting point of the connecting rod assembly to ensure that the small vacuum suction cup below the connecting rod assembly can be adjusted in real time according to the position of the pressure-sensing hole on the sensing surface of the device body. Since the sensing surface of the device body has a certain curvature, the support plate, which is made of an integrated aluminum alloy sheet, can accommodate the slight deformation when the small vacuum suction cup is attached to the sensing surface of the device body.

[0029] The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0030] A performance testing device for fuselage pressure sensors (see Figure 1 The device mainly consists of a large vacuum suction cup assembly, a small vacuum suction cup, a connecting rod assembly, a support plate, a vacuum tube connector, a four-way connector, and a vacuum tube. It is used for single-person performance testing and maintenance of the left and right fuselage pressure sensors of an aircraft. The large vacuum suction cup assembly 1 is attached to the mounting surface of the fuselage pressure sensor. The small vacuum suction cup 2 is aligned with the pressure sensing hole. The tension of the spring 13 in the connecting rod assembly 3 and the suction force of the large suction cup assembly press the small vacuum suction cup onto the pressure sensing hole on the fuselage sensing surface, thus fixing the testing device in place. The vacuum channel is formed by the vacuum connector 5, the four-way connector 6, the vacuum tube 7, the connecting rod assembly, and the small vacuum suction cup. An external pressure controller is connected to the four-way connector to bring the pressure of the fuselage pressure sensor chamber to the pressure value at the detection point, thereby testing the airtightness of the pressure sensor and performing routine testing and maintenance.

[0031] The price of the large vacuum suction cup assembly (see...) Figure 2 The device mainly consists of a connecting rod 8 and a large vacuum suction cup 9, used to fix the testing device to the surface of the aircraft fuselage. Using a vacuum suction cup for fixation meets the requirements of not damaging the fuselage surface during use, and is convenient, quick, and operable by a single person. The connecting rod is made of aluminum alloy with a hollow internal structure, and the connection point of the large vacuum suction cup is also made of aluminum alloy, greatly reducing the weight of the testing device and meeting the requirements for portability.

[0032] The connecting rod assembly (see) Figure 3The main components include an anti-detachment hexagonal nut 10, a clamping hexagonal nut 11, a sleeve 12, a spring 13, and a connecting rod 14. These components are used to connect and fix the small vacuum suction cup to the support plate, and together with the small vacuum suction cup, vacuum nozzle, and vacuum tube, form a vacuum channel. The spring is made of high-strength spring steel wire, providing appropriate tension. When the testing device is fixed to the machine body by the suction force of the large vacuum suction cup, the spring tension causes the small suction cup to press against the pressure sensing hole 17, preventing the entire testing device from detaching from the machine body. Except for the spring, all parts are made of aluminum alloy, which greatly reduces the weight of the testing device while meeting structural strength requirements, allowing the testing device to be firmly fixed to the sensing surface 18 of the machine body by the suction force of the large vacuum suction cup.

[0033] The support plate ( Figure 4 The bracket plate integrates the large suction cup assembly and the connecting rod assembly into a single unit through four threaded holes 15 and three oblong holes 16. The oblong holes on the bracket plate provide space for adjusting the position of the connecting rod assembly, allowing the three small vacuum suction cups to simultaneously and completely cover the pressure sensor's sensing hole on the machine body. The laser-engraved arrow markings on the bracket plate allow users to quickly identify the installation direction of the detection device, improving work efficiency. The bracket plate as a whole has undergone structural optimization design while meeting structural strength requirements, significantly reducing weight and accommodating slight deformation when fully conforming to the curved sensing surface of the machine body without affecting pressure detection.

[0034] Figure 5 This is a schematic diagram of a performance testing device for a machine body pressure sensor installed on the surface of the product to be tested. The testing personnel connect the testing device and the pressure controller, grasp the support plate with both hands, align the three small vacuum suction cups with the pressure-sensing holes on the technical surface, and press the testing device vertically onto the sensing surface, allowing the large vacuum suction cups to adhere and fix it to the sensing surface. Then, the testing personnel can operate the pressure controller to begin the testing.

Claims

1. A device for detecting the airtightness of a fuselage pressure sensor, characterized in that, The device includes a large vacuum suction cup assembly, a small vacuum suction cup, a connecting rod assembly, a support plate, a vacuum tube connector, a four-way connector, and a vacuum tube; The four large vacuum suction cup assemblies are fixed to the support plate by threaded connection. The small vacuum suction cups are fixed to the lower end of the connecting rod assembly by thread and sealant. The connecting rod assembly is fixed at the waist-shaped hole of the support plate. Two vacuum tube nozzles are fixed to the upper end of the connecting rod assemblies on both sides by threaded connection. The four-way connector is fixed to the upper end of the connecting rod assembly in the middle. One end of the vacuum tube is connected to the vacuum tube nozzle, and the other end of the vacuum tube is connected to the four-way connector, thus connecting the connecting rod assemblies.

2. The apparatus according to claim 1, characterized in that, The large vacuum suction cup assembly serves to fix the device onto the sensing surface; the small vacuum suction cup covers the pressure sensing hole, providing a vacuum testing environment; the connecting rod assembly connects the small vacuum suction cup and the vacuum nozzle, providing a certain tension to press the small suction cup onto the pressure sensing hole; the bracket plate integrates all components into a whole; the vacuum tube nozzle, four-way connector, and vacuum tube are important components of the vacuum circuit for airtightness testing.

3. The apparatus according to claim 2, characterized in that, The large vacuum suction cup assembly includes a connecting rod (8) and a large vacuum suction cup (9); The connecting rod (8) and the large vacuum suction cup (9) are connected by threads to fix the device on the sensing surface of the aircraft fuselage. The connecting rod is used to connect the large vacuum suction cup and the bracket plate. The large vacuum suction cup can form an internal and external pressure difference to fix the device on the sensing surface of the aircraft fuselage.

4. The apparatus according to claim 3, characterized in that, The connecting rod assembly includes an anti-loosening hexagonal nut (10), a clamping hexagonal nut (11), a sleeve (12), a spring (13), and a connecting rod (14); Among them, from top to bottom, the spring (13), sleeve (12), clamping hexagonal nut (11), and anti-dislodgement hexagonal nut (10) are installed on the connecting rod (14).

5. The apparatus according to claim 4, characterized in that, The connecting rod serves as the main body, with a vacuum tube nozzle at the top and a small vacuum suction cup at the bottom. A spring provides tension to press the small vacuum suction cup onto the pressure-sensing hole. A sleeve and a clamping hexagonal nut fix the connecting rod assembly to the bracket plate, ensuring that the connecting rod can slide up and down. An anti-dislodgement hexagonal nut prevents the clamping hexagonal nut, sleeve, and spring from falling out of the connecting rod assembly under the tension of the spring.

6. The apparatus according to claim 5, characterized in that, The support plate has four threaded holes and three oblong holes. The threaded holes are used to connect the connecting short rod and fix the large vacuum suction cup assembly. The three oblong holes are used to fix the connecting rod assembly and facilitate the lateral adjustment of the connecting rod assembly so that the small vacuum suction cup can completely cover the pressure-sensing hole.

Images