Airtight test equipment for fuel system of complete aircraft

Abstract

The utility model provides an airtight test device for a fuel system of a whole aircraft, and relates to the technical field of aircraft manufacturing equipment. The air pipeline comprises a main air path, a low-pressure air branch and a micro-pressure air branch, the main air path comprises an air inlet connector, an air inlet valve, a water drop separator, a first barometer and a first electric control pressure reducing valve which are connected in sequence, and the first electric control pressure reducing valve is connected with the low-pressure air branch and the micro-pressure air branch; the nitrogen pipeline comprises a nitrogen inlet connector, a nitrogen inlet valve, a nitrogen filter, a fourth barometer, a third electric control pressure reducing valve, a third electromagnetic valve, a third flow meter and a nitrogen outlet connector which are connected in sequence. The beneficial effects of the utility model are that the device can work under three pressure conditions, is used for solving the problems of airtight test process control and result detection of complex fuel systems of aircrafts such as aircrafts, and can rapidly and accurately carry out airtight inspection of the fuel systems.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft manufacturing equipment, in particular to airtightness testing equipment for a fuel system of a complete aircraft. Background Art

[0002] The fuel system of aircrafts and other aircrafts consists of wing integral fuel tanks, fuel collecting tanks, fuel supply systems, cross-fuel supply systems, measurement and indication systems, ventilation systems, and residual oil discharge systems. The systems are distributed in multiple parts of the fuselage, wings, engine nacelles, etc., and are connected through a variety of fuel pipelines. The structure is complex and the connection forms are diverse. After the fuel system is assembled, it is easy for fuel leakage to occur in various systems, pipelines, and interfaces, affecting the normal operation of the system and easily causing safety hazards. During the assembly of the fuel system and after the overall assembly is completed, the system air tightness measurement needs to be carried out to confirm that the system meets the design requirements.

[0003] The traditional fuel air tightness test is to directly connect the air source through a hose, and supply air to the fuel system pipeline and structure after manual pressure adjustment. The characteristics of this product are simple equipment structure and low cost, but the disadvantage is that the direct manual operation of high-pressure air is easy to cause personal injury. The air pressure filled into the pipeline or system cannot be accurately controlled, which may cause high-pressure damage to the closed structure of the fuel system, and even the wing tank will burst, causing irreparable damage. It has poor safety, requires the cooperation of multiple people, and requires high experience and skills of personnel. Utility Model Content

[0004] In view of this, in order to solve the above-mentioned problems existing in the air tightness detection of the aircraft fuel system, an embodiment of the utility model provides an aircraft fuel system air tightness test device.

[0005] The embodiment of the utility model provides an aircraft fuel system airtightness test device, comprising:

[0006] Movable cabinets;

[0007] An air pipeline, which is arranged in the cabinet, the air pipeline includes an air main circuit, a low-pressure air branch and a micro-pressure air branch, the air main circuit includes an air inlet joint, an air inlet valve, a water drop separator, a first barometer and a first electrically controlled pressure reducing valve connected in sequence, the first electrically controlled pressure reducing valve is respectively connected to the low-pressure air branch and the micro-pressure air branch, the low-pressure air branch includes a first solenoid valve, a second barometer, a flow meter and a low-pressure air outlet joint connected in sequence, the micro-pressure air branch includes a second electrically controlled pressure reducing valve, a second solenoid valve, a third barometer, a second flow meter and a micro-pressure air outlet joint connected in sequence, wherein the air pressure range of the micro-pressure is not higher than 0.009MPa, and the air pressure range of the low pressure is 0.009MPa-0.101325Mpa;

[0008] And a nitrogen pipeline, which is arranged in the cabinet, and the nitrogen pipeline includes a nitrogen inlet joint, a nitrogen inlet valve, a nitrogen filter, a fourth pressure gauge, a third electronically controlled pressure reducing valve, a third solenoid valve, a third flow meter and a nitrogen outlet joint which are connected in sequence.

[0009] Furthermore, the main air path also includes an oil mist separator, and the oil mist separator is arranged between the air intake valve and the water droplet separator.

[0010] Furthermore, the main air path also includes a first one-way valve, which is arranged between the air intake valve and the oil mist separator.

[0011] Furthermore, the first electrically-controlled pressure reducing valve is respectively connected to the low-pressure air branch and the micro-pressure air branch through a three-way joint.

[0012] Furthermore, the low-pressure air branch and the micro-pressure air branch are both provided with a first safety valve.

[0013] Furthermore, the low-pressure air branch and the micro-pressure air branch are both provided with a first exhaust valve and a first muffler connected to the first exhaust valve.

[0014] Furthermore, a second one-way valve is provided on the nitrogen pipeline, and the second one-way valve is arranged between the nitrogen inlet valve and the nitrogen filter.

[0015] Furthermore, the nitrogen pipeline is also provided with a second safety valve, and the second safety valve is arranged between the third solenoid valve and the third flow meter.

[0016] Furthermore, the air inlet connector, the nitrogen inlet connector, the low-pressure air outlet connector, the micro-pressure air outlet connector and the nitrogen outlet connector are all male connectors or female connectors.

[0017] Furthermore, the air inlet connector and the nitrogen inlet connector are disposed on one side of the cabinet, and the low-pressure air outlet connector, the micro-pressure air outlet connector and the nitrogen outlet connector are disposed on the other side of the cabinet.

[0018] The beneficial effects brought about by the technical solution provided by the embodiment of the utility model are:

[0019] The utility model discloses an aircraft fuel system air tightness test equipment, which integrates an air pipeline and a nitrogen pipeline in a cabinet, wherein the air pipeline separates oil and gas and water droplets from the air through an air main line, and then the air is reduced to a first predetermined pressure through a first electrically controlled pressure reducing valve, and is transported to the aircraft fuel system through a low-pressure air branch line for a low-pressure air tightness test, and can be further reduced to a second predetermined pressure through a second electrically controlled pressure reducing valve on a micro-pressure air branch line, and then is transported to the aircraft fuel system through a micro-pressure air branch line for a micro-pressure air tightness test; in addition, the nitrogen pipeline can firstly perform a nitrogen pressure test on the nitrogen, and then the nitrogen can be transported to the aircraft fuel system through a micro-pressure air branch line for a micro-pressure air tightness test; The air is filtered, then compressed to a third predetermined pressure through a third electronically controlled pressure reducing valve, and finally transported to the aircraft's fuel system for a high-pressure air tightness test. In this way, it can operate under three pressure conditions for different tests, and is used to solve the problems of air tightness test process control and result detection for complex fuel systems of aircraft such as aircraft. This type of equipment can quickly and accurately check the air tightness of fuel containers, piping subsystems, and complete fuel systems to ensure the safety of personnel, products, and equipment. At the same time, the integrated piping design is used to reduce the overall size and weight of the equipment, thereby facilitating the improvement of the portability of the equipment. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a schematic diagram of an airtightness test device for a complete aircraft fuel system according to the utility model;

[0021] Figure 2 It is a front side schematic diagram of the air pipeline and nitrogen pipeline;

[0022] Figure 3 It is a rear schematic diagram of the air and nitrogen pipelines;

[0023] Figure 4 It is a schematic diagram of the air line;

[0024] Figure 5 This is the working principle diagram of the air pipeline;

[0025] Figure 6 This is the working principle diagram of the nitrogen pipeline.

[0026] In the figure: 1, cabinet; 2, air pipeline; 3, main air line; 4, low-pressure air branch; 5, micro-pressure air branch; 6, nitrogen pipeline; 7, air inlet connector; 8, air inlet valve; 9, first non-return valve; 10, water drop separator; 11, first pressure gauge; 12, first electronically controlled pressure reducing valve; 13, three-way connector; 14, first solenoid valve; 15, second pressure gauge; 16, first safety valve; 17, first flow meter; 18, low-pressure air outlet connector; 19, oil mist separator; 20, second electronically controlled pressure reducing valve; 21, second solenoid valve; 22, third pressure gauge; 23, second flow meter; 24, micro-pressure air outlet connector; 25. Nitrogen inlet connector; 26. Nitrogen inlet valve; 27. Second one-way valve; 28. Nitrogen filter; 29. ​​Fourth pressure gauge; 30. Third electronically controlled pressure reducing valve; 31. Third solenoid valve; 32. Second safety valve; 33. Third flow meter; 34. Nitrogen outlet connector; 35. Second exhaust valve; 36. Second silencer; 37. Fifth pressure gauge; 38. Roller; 39. Air source; 40. Nitrogen source; 41. Air inlet pipeline; 42. First gate valve; 43. Nitrogen inlet pipeline; 44. Nitrogen bottle pressure reducing valve; 45. Second gate valve; 46. Gas input pipeline; 47. First exhaust valve; 48. First silencer. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the utility model clearer, the following will further describe the implementation of the utility model in conjunction with the accompanying drawings. The following is a preferred embodiment of the utility model among multiple possible embodiments, which is intended to provide a basic understanding of the utility model, but is not intended to confirm the key or decisive elements of the utility model or limit the scope of protection.

[0028] In all examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limiting. Therefore, other examples of the exemplary embodiments may have different values.

[0029] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered as part of the specification.

[0030] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further discussed in the subsequent drawings. At the same time, it should be understood that for ease of description, the sizes of the various parts shown in the drawings are not drawn according to the actual proportional relationship.

[0031] It should be noted that, unless otherwise clearly specified and limited, the terms "installation" and "connection" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this utility model can be understood according to specific circumstances.

[0032] Please refer to Figure 1 and Figure 5 An embodiment of the utility model provides an aircraft fuel system airtightness test device, which is applied to the airtightness test of the fuel system of aircraft such as aircraft, and mainly includes a movable cabinet 1, an air pipeline 2 and a nitrogen pipeline 6.

[0033] The cabinet 1 can be moved freely, so that the air tightness test equipment of the fuel system of the whole aircraft can be moved to any position around the aircraft to be tested, which is convenient for the pipeline connection between the air pipeline 2 and the nitrogen pipeline 6 and the air source and the aircraft. As in the present embodiment, the cabinet 1 is a rectangular parallelepiped, and a plurality of rollers 38 are provided at the bottom of the cabinet 1, and the rollers 38 are universal wheels, so that the cabinet 1 can be moved freely. It should be noted that the shape of the cabinet 1 can be flexibly set according to the actual application scenario and the layout of the air pipeline 2 and the nitrogen pipeline 6, and is not limited to a rectangular parallelepiped.

[0034] The air pipeline 2 and the nitrogen pipeline 6 are both arranged in the cabinet 1, extending from one side of the cabinet 1 to the other opposite side. Both ends of the air pipeline 2 and the nitrogen pipeline 6 respectively pass through the opposite sides of the cabinet 1 for air intake and air outlet.

[0035] Specifically, Figure 2 and Figure 4 As shown, the air pipeline 2 includes an air main circuit 3, a low-pressure air branch 4 and a micro-pressure air branch 5. The air main circuit 3 mainly includes an air intake connector 7, an air intake valve 8, a water droplet separator 10, a first barometer 11 and a first electrically controlled pressure reducing valve 12 which are connected in sequence. The first electrically controlled pressure reducing valve 12 is respectively connected to the low-pressure air branch 4 and the micro-pressure air branch 5. Generally, the first electrically controlled pressure reducing valve 12 is respectively connected to the low-pressure air branch 4 and the micro-pressure air branch 5 through a three-way connector 13.

[0036] The low-pressure air branch 4 mainly includes a first solenoid valve 14, a second pressure gauge 15, a flow meter and a low-pressure air outlet connector 18 connected in sequence, and the micro-pressure air branch 5 mainly includes a second electrically-controlled pressure reducing valve 20, a second solenoid valve 21, a third pressure gauge 22, a second flow meter 23 and a micro-pressure air outlet connector 24 connected in sequence.

[0037] like Figure 3 As shown, the nitrogen pipeline 6 mainly includes a nitrogen inlet connector 25, a nitrogen inlet valve 26, a nitrogen filter 28, a fourth pressure gauge 29, a third electronically controlled pressure reducing valve 30, a third solenoid valve 31, a third flow meter 33 and a nitrogen outlet connector 34 which are connected in sequence.

[0038] Before conducting an air tightness test on an aircraft fuel system, the air inlet connector 7 on the main air path 3 is connected to an air source 39 , and the nitrogen inlet connector 25 on the nitrogen pipeline 6 is connected to a nitrogen source 40 .

[0039] When conducting a low-pressure air-tightness test on an aircraft fuel system, the high-pressure air in the air source 39 is filtered through the water droplet separator 10 to remove water vapor, then reduced to a first predetermined pressure through the first electrically-controlled pressure reducing valve 12, and then transported to the aircraft fuel system through the low-pressure air branch 4 for a low-pressure air-tightness test; and when conducting a micro-pressure air-tightness test on an aircraft fuel system, the air reduced to a first predetermined pressure through the first electrically-controlled pressure reducing valve 12 is input into the micro-pressure air branch 5, then further reduced to a second predetermined pressure through the second electrically-controlled pressure reducing valve 20, and finally transported to the aircraft fuel system for a micro-pressure air-tightness test.

[0040] When performing a high-pressure air-tightness test on an aircraft fuel system, the high-pressure nitrogen in the nitrogen source 40 is filtered by the nitrogen filter 28 and then reduced to a third predetermined pressure by the third electrically controlled pressure reducing valve 30 , and then input into the aircraft fuel system for the high-pressure air-tightness test.

[0041] It should be noted that in the present invention, micro pressure, low pressure and high pressure are relative probabilities of air pressure, wherein the air pressure of high pressure is greater than that of low pressure, and the air pressure of low pressure is greater than micro pressure. For example, in this embodiment, the air pressure range of the micro pressure is not higher than 0.009 MPa, the air pressure range of the low pressure is 0.009 MPa-0.101325 MPa, and the air pressure range of the high pressure is higher than 0.101325 MPa.

[0042] Taking into account that oil and gas may be mixed in the air pipeline 2 after the previous test of the aircraft fuel system airtightness test equipment, the main air path 3 also includes an oil mist separator 19, and the oil mist separator 19 is arranged between the air intake valve 8 and the water droplet separator 10. The oil and gas mixed in the air pipeline 2 are filtered by the oil mist separator 19 to improve the accuracy of the airtightness test.

[0043] In some embodiments, the main air path 3 further includes a first one-way valve 9, which is disposed between the air intake valve 8 and the oil mist separator 19. The first one-way valve 9 prevents oil and gas in the aircraft fuel system from overflowing. Similarly, the nitrogen pipeline 6 is provided with a second one-way valve 27, which is disposed between the nitrogen intake valve 26 and the nitrogen filter 28.

[0044] In some embodiments, the low-pressure air branch 4 and the micro-pressure air branch 5 are both further provided with a first safety valve 16. In the low-pressure air branch 4, the first safety valve 16 is arranged between the first solenoid valve 14 and the first flowmeter 17. In the micro-pressure air branch 5, the first safety valve 16 is arranged between the second solenoid valve 21 and the second flowmeter 23. The first installation valve can automatically release pressure to provide overpressure protection for the low-pressure air branch 4 and the micro-pressure air branch 5. Similarly, a second safety valve 32 is further provided on the nitrogen pipeline 6, and the second safety valve 32 is arranged between the third solenoid valve 31 and the third flowmeter 33.

[0045] Further, the low-pressure air branch 4 and the micro-pressure air branch 5 are both provided with a first exhaust valve 47 and a first muffler 48 connected to the first exhaust valve 47. In the low-pressure air branch 4, the first exhaust valve 47 is arranged between the first solenoid valve 14 and the first flowmeter 17. In the micro-pressure air branch 5, the first exhaust valve 47 is arranged between the second solenoid valve 21 and the second flowmeter 23. The first exhaust valve 47 can be manually depressurized to provide overpressure protection for the low-pressure air branch 4 and the micro-pressure air branch 5. Similarly, a second exhaust valve 35 and a second muffler 36 connected thereto can also be arranged on the nitrogen pipeline 6, and the nitrogen pipeline 6 can be manually depressurized through the second exhaust valve 35. In addition, a fifth barometer 37 can be arranged on the nitrogen pipeline 6 between the third solenoid valve 31 and the second safety valve 32 to monitor the nitrogen pressure after the third electrically controlled pressure reducing valve 30 is depressurized.

[0046] In addition, in order to facilitate the pipeline connection between the air pipeline 2, the nitrogen pipeline 6, the air source 39, the nitrogen source 40 and the aircraft fuel system, the air inlet connector 7 and the nitrogen inlet connector 25 are arranged on one side of the cabinet 1, and the low-pressure air outlet connector 18, the micro-pressure air outlet connector 24 and the nitrogen outlet connector 34 are arranged on the other side of the cabinet 1.

[0047] Furthermore, the air inlet connector 7, the nitrogen inlet connector 25, the low-pressure air outlet connector 18, the micro-pressure air outlet connector 24 and the nitrogen outlet connector 34 can all adopt male connectors or female connectors. In this way, it is only necessary to configure matching male connectors or female connectors for the pipelines connected to the air source 39, the nitrogen source 40 and the aircraft fuel system to complete quick connection and disassembly.

[0048] Please refer to Figure 5 The aircraft fuel system air tightness test equipment in this embodiment can perform a 0.1MPa low-pressure test air tightness test, a 0.009MPa micro-pressure air tightness test, and a 1MPa high-pressure nitrogen tightness test on the aircraft according to the "Technical Conditions for Installation Inspection of Fuel Systems of Unmanned Transport Aircraft", as follows:

[0049] The air source 39 is a factory air source of 0.6-08MPa. The air source 39 is connected to an air intake pipeline 41. The air intake pipeline 41 is a hose and is provided with a first gate valve 42. The air source 39 is connected to the air intake connector 7 via the air intake pipeline 41.

[0050] The nitrogen gas source 40 is a 13 MPa nitrogen bottle, and the nitrogen gas source 40 is connected to a nitrogen gas intake pipeline 43 . The nitrogen gas intake pipeline 43 is a hose and is provided with a nitrogen gas bottle pressure reducing valve 44 and a second gate valve 45 . The nitrogen gas intake pipeline 43 is connected to the nitrogen gas intake connector 25 .

[0051] Low-pressure air-tightness test: The low-pressure air outlet connector 18 on the low-pressure air branch 4 is connected to the aircraft fuel system through the gas input pipeline 46. The high-pressure air in the air source 39 is filtered through the water droplet separator 10 to remove water vapor, and then reduced to a first predetermined pressure of 0.1 MPa through the first electrically controlled pressure reducing valve 12. Then, the high-pressure air is transported to the gas input pipeline 46 of the aircraft fuel system through the low-pressure air branch 4 for a low-pressure air-tightness test.

[0052] Micro-pressure air-tightness test: The micro-pressure air outlet connector 24 on the micro-pressure air branch 5 is connected to the aircraft fuel system through the gas input pipeline 46. The high-pressure air in the air source 39 is filtered through the water droplet separator 10 to remove water vapor, and then reduced to a first predetermined pressure of 0.1 MPa through the first electrically-controlled pressure reducing valve 12. The first predetermined pressure is 0.1 MPa, and then further reduced to a second predetermined pressure of 0.009 MPa through the second electrically-controlled pressure reducing valve 20. Finally, it is transported to the gas input pipeline 46 of the aircraft fuel system for a micro-pressure air-tightness test.

[0053] High-pressure air-tightness test: The nitrogen outlet connector 34 on the nitrogen pipeline 6 is connected to the aircraft fuel system through the gas input pipeline 46. The high-pressure nitrogen in the nitrogen source 40 is filtered by the nitrogen filter 28 and then reduced to a third predetermined pressure by the third electrically-controlled pressure reducing valve 30. The third predetermined pressure is 1 MPa, and then transported to the gas input pipeline 46 of the aircraft fuel system for a high-pressure air-tightness test.

[0054] In this article, the directional words such as front, back, top, and bottom involved are defined by the positions of the parts in the drawings and the positions of the parts relative to each other, just for the sake of clarity and convenience in expressing the technical solution. It should be understood that they are relative concepts and can change accordingly according to different ways of use and placement, and the use of the directional words should not limit the scope of protection claimed in this application.

[0055] In the absence of conflict, the above embodiments and features in the embodiments can be combined with each other. The above description is only a preferred embodiment of the utility model and is not intended to limit the utility model. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. An aircraft fuel system airtightness test equipment, characterized in that: include: Movable cabinets; An air pipeline, which is arranged in the cabinet, the air pipeline includes an air main circuit, a low-pressure air branch and a micro-pressure air branch, the air main circuit includes an air inlet joint, an air inlet valve, a water drop separator, a first barometer and a first electrically controlled pressure reducing valve connected in sequence, the first electrically controlled pressure reducing valve is respectively connected to the low-pressure air branch and the micro-pressure air branch, the low-pressure air branch includes a first solenoid valve, a second barometer, a flow meter and a low-pressure air outlet joint connected in sequence, the micro-pressure air branch includes a second electrically controlled pressure reducing valve, a second solenoid valve, a third barometer, a second flow meter and a micro-pressure air outlet joint connected in sequence, wherein the air pressure range of the micro-pressure is not higher than 0.009MPa, and the air pressure range of the low pressure is 0.009MPa-0.101325Mpa; And a nitrogen pipeline, which is arranged in the cabinet, and the nitrogen pipeline includes a nitrogen inlet joint, a nitrogen inlet valve, a nitrogen filter, a fourth pressure gauge, a third electronically controlled pressure reducing valve, a third solenoid valve, a third flow meter and a nitrogen outlet joint which are connected in sequence.

2. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The main air path further comprises an oil mist separator, and the oil mist separator is arranged between the air intake valve and the water droplet separator.

3. The aircraft fuel system airtightness test equipment according to claim 2, characterized in that: The main air path further includes a first one-way valve, which is arranged between the air intake valve and the oil mist separator.

4. An aircraft fuel system airtightness test equipment as claimed in any one of claims 1 to 3, characterized in that: The first electrically controlled pressure reducing valve is respectively connected to the low-pressure air branch and the micro-pressure air branch through a three-way joint.

5. An aircraft fuel system airtightness test equipment as claimed in any one of claims 1 to 3, characterized in that: The low-pressure air branch and the micro-pressure air branch are both provided with a first safety valve.

6. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The low-pressure air branch and the micro-pressure air branch are both provided with a first exhaust valve and a first muffler connected to the first exhaust valve.

7. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The nitrogen pipeline is provided with a second one-way valve, and the second one-way valve is arranged between the nitrogen inlet valve and the nitrogen filter.

8. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The nitrogen pipeline is also provided with a second safety valve, and the second safety valve is arranged between the third solenoid valve and the third flow meter.

9. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The air inlet connector, the nitrogen inlet connector, the low-pressure air outlet connector, the micro-pressure air outlet connector and the nitrogen outlet connector are all male connectors or female connectors.

10. The aircraft fuel system airtightness test equipment according to claim 1, characterized in that: The air inlet joint and the nitrogen inlet joint are arranged on one side of the cabinet, and the low-pressure air outlet joint, the micro-pressure air outlet joint and the nitrogen outlet joint are arranged on the other side of the cabinet.

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