Airtight test device and test method for rear pressure frame of civil aircraft

Abstract

The invention provides a civil aircraft rear pressure frame airtightness test device and test method. The civil aircraft rear pressure frame airtightness test device comprises a bottom plate and an inspection cover. The bottom plate is annular and used for being connected with the rear pressure frame in a sealed mode, so that a cavity is formed between the bottom plate and the rear pressure frame, and an inspection opening communicated with the cavity is formed in the bottom plate. The inspection cover is detachably connected to the bottom plate and used for closing or opening the inspection opening. Wherein the bottom plate and / or the inspection cover are / is provided with a loading port communicated with the cavity, and the bottom plate and / or the inspection cover are / is provided with an unloading port communicated with the cavity. The civil aircraft rear pressure frame airtight test device provided by the invention can support independent airtight test under the condition that the rear pressure frame is separated from the aircraft body, the rear pressure frame is independently dispatched without a large instrument, and the required test site is small. According to the civil aircraft rear pressure frame airtight test device, only the inspection cover needs to be disassembled and assembled when a large amount of repeated inspection is carried out on the rear pressure frame, and the inspection difficulty is greatly reduced.

Description

Technical Field

[0001] The present application relates to the technical field of aircraft strength testing, and in particular, to a civil aircraft rear pressure frame airtightness testing device and testing method. Background Art

[0002] The rear pressure frame structure is the process separation surface between the aircraft rear fuselage and the middle and rear fuselage sections. It mainly bears the airtight pressure load inside the cabin. If the rear pressure frame is damaged, it will directly affect the cabin pressure and the safety of the tail system. In order to verify whether the strength of the rear pressure frame structure under airtight load meets the design requirements, it is necessary to carry out positive and negative pressure airtight loading static and fatigue tests on the rear pressure frame structure of civil aircraft.

[0003] At present, the airtightness test of the rear pressure frame structure of civil aircraft is carried out on the whole aircraft or on the section structure composed of the rear pressure frame and the fuselage, and no airtightness loading test is carried out on the separate rear pressure frame. When testing the rear pressure frame, the whole aircraft or the whole fuselage assembly needs to be placed in the test environment. A large and complex test device is required, and a large number of repeated tests are required when conducting airtightness tests on the rear pressure frame. The test device and the rear pressure frame installed on the fuselage are repeatedly installed, which requires a lot of manpower, material resources and time, making the test difficult and costly.

[0004] Furthermore, such experiments require a larger experimental site to accommodate the fuselage, and the scheduling of the fuselage is also very difficult. Summary of the invention

[0005] In order to solve one of the above-mentioned technical defects, an embodiment of the present application provides a civil aircraft rear pressure frame airtightness test device and test method.

[0006] According to a first aspect of an embodiment of the present application, a civil aircraft rear pressure frame airtightness test device is provided, comprising:

[0007] A bottom plate, the bottom plate is annular and is used to be sealed and connected to the rear pressure frame, so that a cavity is formed between the bottom plate and the rear pressure frame, and an inspection port communicating with the cavity is provided on the bottom plate;

[0008] An inspection cover, the inspection cover is detachably connected to the bottom plate, and the inspection cover is used to close or open the inspection port;

[0009] Wherein, a loading port connected to the cavity is provided on the bottom plate and / or the inspection cover, and an unloading port connected to the cavity is provided on the bottom plate and / or the inspection cover.

[0010] Optionally, an edge connector is included, and the rear pressure frame is connected to the base plate via the connector.

[0011] Optionally, the inspection cover is provided with a plurality of through holes around its edge, the bottom plate is provided with a plurality of blind holes around its edge, one end of a plurality of fasteners passes through corresponding through holes and is connected to the blind holes, and a seal is provided between the inspection cover and the bottom plate.

[0012] Optionally, one of the inspection cover and the bottom plate is provided with a convex ring, and the other is provided with an annular groove;

[0013] The sealing member is embedded in the annular groove;

[0014] When the inspection cover and the bottom plate are connected, the convex ring is embedded in the annular groove.

[0015] Optionally, a plurality of pressure sensors are provided on the bottom plate and / or the inspection cover, and the pressure sensors are used to detect the air pressure in the cavity.

[0016] Optionally, a filler is provided in the cavity, the filler is connected to the bottom plate and / or the inspection cover, and there is a gap between the filler and the rear pressure frame.

[0017] Optionally, the civil aircraft rear pressure frame airtightness test device comprises two support bases, and the two support bases are arranged at intervals;

[0018] The bottom plate is located between the two supporting bases, and rotating shafts are respectively arranged on opposite sides of the bottom plate;

[0019] Each rotating shaft is rotatably connected to a corresponding supporting base.

[0020] According to a second aspect of an embodiment of the present application, a test method for the airtightness test device for the rear pressure frame of a civil aircraft as described above is provided, comprising:

[0021] Step S1: sealingly connecting the rear pressure frame to the bottom plate, and sealingly connecting the inspection cover to the bottom plate;

[0022] Step S2: vacuuming the loading port to perform negative pressure loading or inflation pressurization to detect the pressure change data in the cavity;

[0023] Step S3: unload or release air through the unloading port, remove the inspection cover, open the inspection port, and detect the state of the recessed surface of the rear pressure frame through the inspection port.

[0024] Optionally, the base plate is rotatably connected to the support base;

[0025] In step S2, the step of rotating the bottom plate to be perpendicular to the horizontal plane is included;

[0026] In step S3, a step of rotating the bottom plate to be parallel to the horizontal plane is included.

[0027] By adopting the above technical solution, the present application has the following beneficial effects:

[0028] The airtightness test device for the rear pressure frame of a civil aircraft of the present application can perform airtightness test independently when the rear pressure frame is separated from the fuselage. The rear pressure frame does not require large equipment for independent dispatching, and the required test site is small. The rear pressure frame and the airtightness test device need to be sealed and connected, and a large number of connectors are required to ensure airtightness during connection, so disassembly and assembly are relatively complicated. The airtightness test device for the rear pressure frame of a civil aircraft is provided with an inspection port that can be closed or opened by an inspection cover on the bottom plate that is sealed and connected to the rear pressure frame. When performing a large number of repeated inspections on the rear pressure frame, only the inspection cover needs to be disassembled and assembled, which greatly reduces the difficulty of inspection. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0030] Figure 1 A schematic structural diagram showing a first direction of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application;

[0031] Figure 2 A schematic structural diagram showing a second direction of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application;

[0032] Figure 3 A schematic diagram of the front view of the airtightness test device for the rear pressure frame of a civil aircraft provided in an embodiment of the present application is shown;

[0033] Figure 4 Show Figure 3 Schematic diagram of the cross-sectional structure in the AA direction;

[0034] Figure 5 Show Figure 4 A partial enlarged view of the middle A;

[0035] Figure 6 A schematic diagram showing the filling arrangement structure of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application is shown;

[0036] Figure 7 A schematic structural diagram of a bottom plate of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application is shown;

[0037] Figure 8 A schematic diagram showing the structure of an inspection cover of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application;

[0038] Fig. 9A schematic diagram showing the arrangement of a loading port, an unloading port and a pressure sensor of a civil aircraft rear pressure frame airtightness test device provided in an embodiment of the present application is shown.

[0039] Figure numerals: base plate 1, inspection port 11, screw hole 12, blind hole 13, rotating shaft 14, convex ring 15, inspection cover 2, reinforcing rib 21, through hole 22, annular groove 23, cavity 3, loading port 41, unloading port 42, pressure sensor 5, edge connector 6, connecting hole 61, filler 8, support base 9, rear pressure frame 100. DETAILED DESCRIPTION

[0040] In order to make the technical solutions and advantages in the embodiments of the present application more clearly understood, the exemplary embodiments of the present application are further described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present application, rather than an exhaustive list of all the embodiments. It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0041] In the description of the present application and its embodiments, it should be understood that the orientation or positional relationship indicated by the terms "top", "bottom", "height", etc. is based on the orientation or positional relationship shown in the accompanying drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0042] In the present application and its embodiments, unless otherwise clearly specified and limited, the terms "set", "install", "connect", "connect", "fix" and the like 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, an electrical connection, or a communication; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present application can be understood according to the specific circumstances.

[0043] In the present application and its embodiments, unless otherwise clearly specified and limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features not being in direct contact but being in contact through another feature between them. Moreover, a first feature being "above", "above" and "above" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is higher in level than the second feature. A first feature being "below", "below" and "below" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicates that the first feature is lower in level than the second feature.

[0044] Embodiment 1

[0045] like Figures 1 to 9 As shown, a civil aircraft rear pressure frame 100 airtightness test device comprises a base plate 1 and an inspection cover 2. The base plate 1 is annular and is used to be sealed and connected to the rear pressure frame 100, so that a cavity 3 is formed between the base plate 1 and the rear pressure frame 100, and an inspection port 11 connected to the cavity 3 is provided on the base plate 1. The inspection cover 2 is detachably connected to the base plate 1, and the inspection cover 2 is used to close or open the inspection port 11. The base plate 1 and / or the inspection cover 2 are provided with a loading port 41 connected to the cavity 3, and the base plate 1 and / or the inspection cover 2 are provided with an unloading port 42 connected to the cavity 3.

[0046] The present application discloses a device for testing the air tightness of a rear pressure frame 100 of a civil aircraft. When in use, the rear pressure frame 100 is sealed and connected to the bottom plate 1, and the inspection cover 2 seals and closes the inspection port 11. The loading port 41 is used to draw air from the outside of the cavity 3 to perform negative pressure loading or inflation and pressurization, and the pressure in the cavity 3 is increased to a preset value. After a preset time, air is introduced into the cavity 3 from the unloading port 42 to perform unloading or pressure relief. After repeating the above-mentioned pressurization and unloading process for a certain number of times, the inspection cover 2 is opened to detect whether the rear pressure frame 100 is deformed or damaged after being pressurized through the inspection port 11. If there is no damage, the inspection cover 2 is used to seal and close the inspection port 11, and the above-mentioned pressurization and unloading process is repeated, and then the inspection cover 2 is opened to inspect the rear pressure frame 100. Repeat the above-mentioned process of pressurizing and inspecting the rear pressure cover until the number of times required is reached. If the rear pressure frame is deformed or damaged, the above-mentioned process of pressurizing and inspecting the rear pressure frame can also be repeated after the damage is treated accordingly until the number of times required is reached or the rear pressure frame is deformed or damaged to an irreparable state.

[0047] The present application discloses a civil aircraft rear pressure frame 100 airtightness test device, which can perform airtightness test on the rear pressure frame 100 when it is separated from the fuselage. The rear pressure frame 100 can be independently dispatched without large equipment, and the required test site is small. The rear pressure frame 100 and the airtightness test device need to be sealed and connected, and a large number of connectors are required to ensure airtightness during connection, so disassembly and assembly are relatively complicated. The civil aircraft rear pressure frame 100 airtightness test device is provided with an inspection port 11 that can be closed or opened by an inspection cover 2 on the bottom plate 1 that is sealed and connected to the rear pressure frame 100. When a large number of repeated inspections are performed on the rear pressure frame 100, only the inspection cover 2 needs to be disassembled and assembled, which greatly reduces the difficulty of inspection.

[0048] The loading port 41 and the unloading port 42 are arranged at a distance from each other to ensure that the air pressure load is evenly applied to the rear pressure frame 100 .

[0049] In one possible embodiment, Figure 2As shown, the airtightness test device of the rear pressure frame 100 of a civil aircraft includes an edge connector 6, and the rear pressure frame 100 is connected to the bottom plate 1 through the connector. The bottom plate 1 also needs to be connected to the supporting structure, the inspection cover 2 and other structures. The direct connection between the bottom plate 1 and the rear pressure frame 100 is not convenient for sealing. The rear pressure frame 100 and the bottom plate 1 are connected through the edge connector 6, which makes the connection more convenient and also more convenient to improve the sealing effect.

[0050] Furthermore, the edge connector 6 and the rear pressure frame 100 may be connected by welding, riveting, bonding, etc., which does not affect the integrity of the rear pressure frame 100 and ensures a stable connection.

[0051] In a possible implementation, the inspection cover 2 is provided with a plurality of through holes 22 around its edge, and the bottom plate 1 is provided with a plurality of blind holes 13 around its inspection port 11, the blind holes 13 are provided corresponding to the through holes 22, and one end of a plurality of fasteners passes through the corresponding through holes 22 and is connected to the blind holes 13. The blind holes 13 may be bolt holes, and the fasteners may be bolts, which pass through the through holes 22 and are threadedly connected to the blind holes 13. The connecting holes provided on the bottom plate 1 are blind holes 13, which are non-through holes and do not have the risk of air leakage. A seal is provided between the inspection cover 2 and the bottom plate 1. The provision of the seal can ensure the sealing when the inspection cover 2 closes the inspection port 11. The seal is made of a sealing material such as rubber or PVC.

[0052] In one possible embodiment, Figure 5 , Figure 7 , Figure 8 One of the inspection cover 2 and the bottom plate 1 is provided with a convex ring 15, and the other is provided with an annular groove 23. The seal is embedded in the annular groove 23, and when the inspection cover 2 and the bottom plate 1 are connected, the convex ring 15 is embedded in the annular groove 23. The convex ring 15 and the annular groove 23 cooperate to position the inspection cover 2 and the bottom plate 1, ensuring that the position of the inspection cover 2 is accurate when connected. The seal is arranged in the annular groove 23, which can ensure that the position is stable and not easily offset by force, and the sealing performance is better when it is arranged here.

[0053] Furthermore, the bottom plate 1 is provided with two circles of blind holes 13 along the inspection opening 11, and the inspection cover 2 is also provided with two circles of through holes 22, wherein the two circles of blind holes 13 and the through holes 22 are evenly arranged on the inner and outer sides of the convex ring 15 or the annular groove 23. With such a configuration, the seal can be squeezed from both sides of the convex ring 15 and the annular groove 23, which can ensure balanced squeezing of both sides of the seal ring, ensure the sealing effect of the seal ring, and also ensure that the service life of both sides of the seal ring is the same.

[0054] Furthermore, the inspection cover 2 is provided with a plurality of reinforcing ribs 21, which extend along the radial direction of the inspection cover 2, and the plurality of reinforcing ribs 21 are arranged to diverge outward from the middle of the inspection cover 2. The reinforcing ribs 21 can be connected to the inspection cover 2 by bolts, welding, riveting, etc. If connected by bolts, the bolt holes do not penetrate the inspection cover.

[0055] In a possible implementation, a plurality of pressure sensors 5 are provided on the bottom plate 1 and / or the inspection cover 2, and the pressure sensors 5 are used to detect the air pressure of the cavity 3. A plurality of pressure sensors 5 are evenly arranged on the bottom plate 1 and the inspection port 11 cover, wherein one pressure sensor 5 is used as control feedback, or an average value of a plurality of pressure sensors 5 is taken as control feedback, and the remaining pressure sensors 5 monitor whether the internal pressure of the test piece is uniform. In this way, accurate airtight loading is achieved.

[0056] In one possible embodiment, Figure 6 As shown, a filler 8 is arranged in the cavity 3, and the filler 8 is connected to the bottom plate 1 and / or the inspection cover 2, and there is a gap between the filler 8 and the rear pressure frame 100. The special-shaped filler 8 is arranged inside the cavity 3 of the test device, which reduces the pressurized volume, improves the test rate, and reduces the test cost. Among them, the compressive strength of the filler 8 should be higher than the maximum load of the test to prevent the filler 8 from being deformed and damaged during the test. At the same time, the filler 8 is fixed to the bottom plate 1 and / or the inspection cover 2 by bolts and does not contact the rear pressure frame 100.

[0057] In a possible implementation, the airtightness test device of the rear pressure frame 100 of a civil aircraft includes two support bases 9, and the two support bases 9 are arranged at intervals. The bottom plate 1 is located between the two support bases 9, and the two opposite sides of the bottom plate 1 are respectively provided with rotating shafts 14, and each rotating shaft 14 is rotatably connected to the corresponding support base 9. During the test, the rear pressure frame 100 is placed vertically, and the posture is consistent with the actual use state, so as to avoid the influence of its own weight on the test results. When performing maintenance, the rear pressure frame 100 is placed horizontally in a maintenance posture for easy maintenance. The free switching between the test state and the maintenance state is realized by connecting the rotating shaft 14, which ensures that the rear pressure frame 100 is reachable and inspectable while ensuring that the test state is consistent with the actual use state.

[0058] Embodiment 2

[0059] like Figures 1 to 9 As shown, the test method of the airtightness test device of the rear pressure frame 100 of the civil aircraft described in the first embodiment includes:

[0060] Step S1: sealingly connecting the rear pressure frame 100 to the bottom plate 1, and sealingly connecting the inspection cover 2 to the bottom plate 1;

[0061] Step S2: vacuuming or inflating through the loading port 41 to perform negative pressure loading or pressurization, and detecting the pressure change data in the cavity 3;

[0062] Step S3: unload or release air through the unloading port 42, remove the inspection cover 2, open the inspection port 11, and detect the state of the concave surface of the rear pressure frame 100 through the inspection port 11.

[0063] This embodiment uses the airtightness test device of the rear pressure frame 100 of the civil aircraft in the first embodiment, and can perform airtightness test on the rear pressure frame 100 separately from the fuselage. An inspection port 11 that can be closed or opened by an inspection cover 2 is provided on the bottom plate 1 to which the rear pressure frame 100 is sealed. When performing a large number of repeated inspections on the rear pressure frame 100, only the inspection cover 2 needs to be disassembled, which greatly reduces the inspection difficulty. The rear pressure frame 100 does not require large equipment for independent dispatch, and the required test site is small.

[0064] In a possible embodiment, the base plate 1 is rotatably connected to the support base 9;

[0065] In step S2, the bottom plate 1 is rotated to be perpendicular to the horizontal plane;

[0066] In step S3, the step of rotating the base plate 1 to be parallel to the horizontal plane is included.

[0067] During the test, the rear pressure frame 100 is placed vertically, and its posture is consistent with the actual use state, so as to avoid the influence of its own weight on the test results. During the inspection, the rear pressure frame 100 is placed horizontally in the inspection posture for easy inspection. The free switching between the test state and the inspection state is realized through the connection of the rotating shaft 14, which ensures that the rear pressure frame 100 is accessible and inspectable while ensuring that the test state is consistent with the actual use state.

[0068] The disclosure above provides many different embodiments or examples to realize the different structures of the present application. In order to simplify the disclosure of the present application, the parts and settings of specific examples are described above. Of course, they are only examples, and the purpose is not to limit the present application. In addition, the present application can repeat reference numbers and / or reference letters in different examples, and this repetition is for the purpose of simplification and clarity, which itself does not indicate the relationship between the various embodiments and / or settings discussed. In addition, the various specific processes and material examples provided by the present application, but those of ordinary skill in the art can be aware of the application of other processes and / or the use of other materials.

[0069] Although the preferred embodiments of the present application have been described, those skilled in the art may make other changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications falling within the scope of the present application.

[0070] Obviously, those skilled in the art can make various changes and modifications to the present application without departing from the spirit and scope of the present application. Thus, if these modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is also intended to include these modifications and variations.

Claims

1. A civil aircraft rear pressure frame airtightness test device, characterized in that: include: A bottom plate, the bottom plate is annular and is used to be sealed and connected to the rear pressure frame, so that a cavity is formed between the bottom plate and the rear pressure frame, and an inspection port communicating with the cavity is provided on the bottom plate; An inspection cover, the inspection cover is detachably connected to the bottom plate, and the inspection cover is used to close or open the inspection port; Wherein, a loading port connected to the cavity is provided on the bottom plate and / or the inspection cover, and an unloading port connected to the cavity is provided on the bottom plate and / or the inspection cover.

2. The civil aircraft rear pressure frame airtightness test device according to claim 1, characterized in that: It comprises an edge connecting piece, and the rear pressure frame is connected to the bottom plate through the connecting piece.

3. The civil aircraft rear pressure frame airtightness test device according to claim 1, characterized in that: The inspection cover is provided with a plurality of through holes around its edge, the bottom plate is provided with a plurality of blind holes around its edge, one end of a plurality of fasteners passes through corresponding through holes and is connected to the blind holes, and a sealing member is provided between the inspection cover and the bottom plate.

4. The civil aircraft rear pressure frame airtightness test device according to claim 3, characterized in that: One of the inspection cover and the bottom plate is provided with a convex ring, and the other is provided with an annular groove; The sealing member is embedded in the annular groove; When the inspection cover and the bottom plate are connected, the convex ring is embedded in the annular groove.

5. The civil aircraft rear pressure frame airtightness test device according to claim 1, characterized in that: A plurality of pressure sensors are arranged on the bottom plate and / or the inspection cover, and the pressure sensors are used to detect the air pressure in the cavity.

6. The civil aircraft rear pressure frame airtightness test device according to claim 1, characterized in that: A filler is arranged in the cavity, the filler is connected to the bottom plate and / or the inspection cover, and there is a gap between the filler and the rear pressure frame.

7. The civil aircraft rear pressure frame airtightness test device according to claim 1, characterized in that: It comprises two supporting bases, and the two supporting bases are arranged at intervals; The bottom plate is located between the two supporting bases, and rotating shafts are respectively arranged on opposite sides of the bottom plate; Each rotating shaft is rotatably connected to a corresponding supporting base.

8. The test method of the civil aircraft rear pressure frame airtightness test device according to any one of claims 1 to 7, characterized in that: include: Step S1: sealingly connecting the rear pressure frame to the bottom plate, and sealingly connecting the inspection cover to the bottom plate; Step S2: vacuuming the loading port to perform negative pressure loading or inflation pressurization to detect the pressure change data in the cavity; Step S3: unload or release air through the unloading port, remove the inspection cover, open the inspection port, and detect the state of the recessed surface of the rear pressure frame through the inspection port.

9. The test method according to claim 8, characterized in that The bottom plate is rotatably connected to the support base; In step S2, the step of rotating the bottom plate to be perpendicular to the horizontal plane is included; In step S3, a step of rotating the bottom plate to be parallel to the horizontal plane is included.

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