A vibration seal test device for the sealing strip of the wing fuel tank cover

Abstract

The present invention relates to a vibration seal test device for a wing fuel tank cover sealing strip, which belongs to the secondary technology of aircraft body design in the field of engineering technology. The device comprises: a box unit for installing the sealing strip to be tested, which is used to hold fuel and apply internal oil pressure; a reciprocating vibration unit, which is arranged on a test bracket and is slidably connected to the box unit, and is used to close the box unit and reciprocate relative to the box unit; a power supply unit, which is fixedly connected to the reciprocating vibration unit, and is used to provide power for the reciprocating vibration of the reciprocating vibration unit. The device of the present invention has a compact structure and is easy to use, and can reduce the risk and R&D cost of the wing fuel tank cover sealing design.

Description

Technical Field

[0001] The invention belongs to the secondary technology of aircraft body design in the field of engineering technology. The invention provides a vibration sealing test device for a civil aircraft wing fuel tank cover sealing strip, which is used for testing the sealing performance of the fuel tank cover sealing strip under a vibration environment. Background Art

[0002] Modern civil aircraft generally adopt the wing design of integral fuel tank, and part of the wing box structure is also the structure of the fuel tank. During the flight of the aircraft, airflow, engine vibration, etc. will cause vibration between the fuel tank cover and the wall panel, so the design of the cover sealing strip is an important consideration.

[0003] At present, there is no special test method and device for testing the sealing performance of civil aircraft wing tank cover sealing strips under vibration conditions. The sealing effect of the tank cover sealing strip is mainly verified in the tank shaking test. This test uses the entire wing tank as the test piece, which has a large structural size and high test cost. It is often carried out in the later stage of wing development. For composite fuel tanks, the design of the sealing strip size will affect the design of the tank wall panel. The later the sealing strip verification is, the greater the impact on the design changes of the composite fuel tank wall panel. Therefore, it is necessary to establish a special test method and device that can use smaller test equipment and test pieces to verify the sealing effect of the tank cover sealing strip under vibration working conditions in the early stage of wing tank design. Summary of the invention

[0004] In order to solve the above problems, the present invention proposes a test device for sealing test of fuel tank cover sealing strip in vibration environment, which is used to verify the design of sealing strip in the wing development stage. The device of the present invention has a compact structure and is easy to use, which can reduce the risk and development cost of wing fuel tank cover sealing design.

[0005] According to the technical solution of the present invention, a vibration seal test device for a wing fuel tank cover seal strip is provided, the device comprising:

[0006] The box unit on which the sealing strip to be tested is installed is used to contain the fuel and apply internal oil pressure;

[0007] A reciprocating vibration unit is arranged on the test bracket, is slidably connected with the box unit, is used to close the box unit, and reciprocates relative to the box unit;

[0008] A power supply unit is fixedly connected to the reciprocating vibration unit and is used to provide power for the reciprocating vibration of the reciprocating vibration unit.

[0009] Furthermore, the box unit includes a box wall, and a threaded blind hole is provided on the upper end surface of the box wall for sliding connection with the reciprocating vibration unit; a groove is designed on the inner side of the threaded blind hole for installing a sealing strip; a first threaded through hole and a second threaded through hole are provided on the side of the box wall for respectively installing a pressure gauge and an oil inlet pipe.

[0010] Furthermore, an oil pipe valve is provided on the oil inlet pipe.

[0011] Furthermore, a flange is provided at the bottom of the box unit and is fixed to the test platform through bolt mounting holes.

[0012] Furthermore, the reciprocating vibration unit includes a cover plate, an exhaust valve, a slide rail, a slider, a positioning nut sleeve and a positioning screw. The cover plate is used to close the box unit and provide a track for reciprocating vibration motion. A slide rail is installed on each side of the track. The slider is fixed to the test bracket by a positioning nut sleeve and a positioning screw.

[0013] Furthermore, the position of the slider can be adjusted by rotating the screw sleeve and the positioning screw; the two pairs of slide rails and the slider ensure that the cover plate reciprocates along the rails.

[0014] Furthermore, the connecting hole between the cover plate and the box unit is designed as a long hole or a clearance-fitting hole to ensure that the slidingly connected cover plate and the box unit can achieve relative movement.

[0015] Furthermore, a threaded through hole is designed on the cover plate for installing an exhaust valve. When fuel is injected into the box unit, the exhaust valve opens to exhaust air; after the fuel is fully filled, the exhaust valve closes.

[0016] Furthermore, the cover plate is designed with ears for connecting with the power supply unit to provide power for the reciprocating vibration motion.

[0017] Furthermore, the test bracket includes a column, a cross plate and a base, the base is fixed to the test platform by bolts, and the column has a threaded through hole for installing a positioning screw.

[0018] Beneficial effects of the present invention:

[0019] By using the sealing strip vibration sealing test device of the present invention, the sealing performance of the sealing strip under vibration conditions can be tested in the early stage of wing design with a smaller test device and test cost, the sealing strip design parameters can be determined, and the progress and cost risks caused by changes in the sealing strip design in the later stage of wing tank design can be reduced. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0021] Figure 1 It is a structural diagram of a vibration seal test device for a wing fuel tank cover seal strip according to the present invention;

[0022] Figure 2 It is a box structure diagram of the vibration sealing test device of the wing oil tank cover sealing strip according to the present invention;

[0023] Figure 3 A structural diagram of a cover plate of a wing fuel tank cover sealing strip vibration sealing test device according to the present invention;

[0024] Figure 4 It is a structural diagram of a test bracket of a vibration seal test device for a wing fuel tank cover seal strip according to the present invention;

[0025] Figure 5 is a schematic diagram of a vibration seal test device for a wing fuel tank cover seal strip according to the present invention;

[0026] Figure 6 It is a schematic diagram of the exploded structure of the vibration sealing test device of the wing fuel tank cover sealing strip according to the present invention.

[0027] The realization of the purpose, functional features and advantages of the present invention will be further explained in conjunction with embodiments and with reference to the accompanying drawings. DETAILED DESCRIPTION

[0028] Exemplary embodiments will be described in detail herein, examples of which are shown in the accompanying drawings. When the following description refers to the drawings, the same numbers in different drawings represent the same or similar elements unless otherwise indicated. The embodiments described in the following exemplary embodiments do not represent all embodiments consistent with the present disclosure. Instead, they are merely examples of devices and methods consistent with some aspects of the present disclosure as detailed in the appended claims.

[0029] The terms "first", "second", etc. in the specification and claims of the present disclosure are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that the terms used in this way can be interchanged where appropriate, so that the embodiments of the present disclosure described herein can be implemented in an order other than those illustrated or described herein, for example.

[0030] In addition, the terms "comprises," "comprising," and "having," and any variations thereof, are intended to cover non-exclusive inclusions. For example, a process, method, system, product, or apparatus that includes a series of steps or elements is not necessarily limited to those steps or elements explicitly listed, but may include other steps or elements not explicitly listed or inherent to such process, method, product, or apparatus.

[0031] Multiple includes two or more.

[0032] It should be understood that the term "and / or" used in this disclosure is only a description of the association relationship of associated objects, indicating that three relationships may exist. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone.

[0033] Modern civil aircraft generally adopt a wing design with an integral fuel tank, and a part of the wing box structure is also the structure of the fuel tank. During the flight of the aircraft, airflow, engine vibration, etc. will cause vibration between the fuel tank cover and the wall panel, and the design of the cover sealing strip is an important consideration. The present invention proposes a test device for testing the sealing of the fuel tank cover sealing strip in a vibration environment, which is used to verify the design of the sealing strip during the wing research and development stage. The device of the present invention has a compact structure and is easy to use, and can reduce the risk and research and development cost of the wing fuel tank cover sealing design.

[0034] The present invention provides a sealing test device for a wing oil tank cover sealing strip under vibration conditions, the device comprising a box body 1, a cover plate 2, an exhaust valve 3, a pressure gauge 4, an oil inlet pipe 5, an oil pipe valve 6, a test bracket 7, a slide rail 8, a slide block 9, a positioning screw sleeve 10 and a positioning screw 11. Figure 1 shown.

[0035] The box 1 is used to hold fuel and place sealing strips. Figure 2 As shown. The upper end surface of the box wall 101 is designed with a threaded blind hole 102 for connecting with the cover plate 2; a groove 103 is designed inside the threaded hole 102 for installing the sealing strip; a threaded through hole 104 is reserved on the side of the box wall 101 for installing the pressure gauge 4; a threaded through hole 105 is reserved on the side of the box wall 101 for installing the oil inlet pipe 5. A flange 106 is designed at the bottom of the box 1, which is fixed to the test platform through bolt mounting holes 107.

[0036] Cover 2 Figure 3 As shown, it is used to close the box 1 and provide a track 203 for vibration movement. A slide rail 8 is installed on both sides of the track 203. The slider 9 is fixed to the test bracket 7 by a positioning screw sleeve 10 and a positioning screw 11. The position of the slider 9 can be adjusted by rotating the screw sleeve 10 and the positioning screw 11. The four pairs of slide rails 8 and sliders 9 ensure that the cover plate 2 reciprocates along the track 203.

[0037] The connecting hole 201 between the cover plate 2 and the box body 1 is designed as a long hole or a clearance-fitting hole to ensure that the cover plate 2 and the box body 1 can move relative to each other.

[0038] The cover plate 2 is provided with a threaded hole 202 for installing the exhaust valve 3. When the fuel is injected into the tank 1, the exhaust valve 3 is opened to exhaust air; after the fuel is fully injected, the exhaust valve 3 is closed.

[0039] The cover plate 2 is designed with an ear piece 204 connected to the testing machine to provide power for the vibration movement.

[0040] like Figure 4 As shown, the test support 7 includes a column 701, a horizontal plate 702 and a base 703. The base 703 is fixed to the test bench by bolts. The column 701 has a threaded hole 704 for installing the positioning screw 11.

[0041] like Figure 5 As shown, the vibration sealing test device for the wing fuel tank cover sealing strip proposed by the present invention applies internal pressure to the sealing strip to be tested through the oil in the box body, and applies a vibration environment to the sealing strip to be tested through the relative movement of the cover plate and the box body. It can be used to verify the sealing performance of the wing fuel tank sealing strip under the combined action of vibration and internal oil pressure during the flight of the aircraft, eliminating the need to use the entire or part of the wing fuel tank structure to verify the sealing condition of the sealing strip under dynamic load conditions, thereby reducing the research and development and verification costs of the wing fuel tank cover sealing strip.

[0042] Example

[0043] According to an embodiment of the present invention, a vibration seal test device for a wing fuel tank cover seal strip is provided. The structure is decomposed as follows: Figure 6 As shown, it includes a box body 1, a cover plate 2, an exhaust valve 3, a pressure gauge 4, an oil inlet pipe 5, an oil pipe valve 6, a test bracket 7, a slide rail 8, a slide block 9, a positioning screw sleeve 10 and a positioning screw 11

[0044] The bottom of the box body 1 is fixed to the test bench by bolts, and a sealing strip is installed in the groove 103 on the upper part of the box body 1 and is combined with the cover plate 2 by bolts.

[0045] A pressure gauge 4 is installed on the side wall of the box body 1 to display the internal oil pressure value in real time.

[0046] An oil inlet pipe 5 is installed on the side wall of the box body 1, and an oil pipe valve 6 is installed on the oil inlet pipe 5. Fuel of a predetermined pressure is injected into the box body according to the test requirements.

[0047] An exhaust valve 3 is installed on the cover plate 2. The valve is opened when fuel is injected and closed after the fuel is fully injected.

[0048] Slide rails 8 are installed on the tracks 203 on both sides of the cover plate 2 .

[0049] The test bracket 7 is fixed on the test bench by bolts. A positioning screw 11 is installed on the test bracket 7.

[0050] The positioning screw 11 and the positioning nut sleeve 10 are combined together through threads.

[0051] The positioning screw sleeve 10 is combined with the slider 9 through threads.

[0052] By rotating the positioning screw 11 and the positioning screw sleeve 10 , the position of the sliding block 9 is adjusted so as to make it contact with the sliding rail 8 .

[0053] The cover plate 2 is connected to the vibration testing machine through the ear piece on the right side. Driven by the testing machine, the cover plate 2 reciprocates relative to the box body 1 along the direction of the slide rail 8.

[0054] The key points of the present invention proposal are:

[0055] 1. The upper end surface of the housing 1 of the device is designed with a groove 103 for installing and fixing the sealing strip;

[0056] 2. A pressure gauge 4 is installed on the side wall of the box 1 of the present invention to observe the pressure of the oil in the box 1 in real time;

[0057] 3. The oil inlet pipe 5 is installed on the side wall of the box 1 of the present invention, which is used to inject oil into the box 1 during the test and discharge the oil from the box 1 after the test;

[0058] 4. The cover plate 2 of the present invention is provided with an exhaust valve 3 for exhausting the internal air when injecting oil into the box body 1;

[0059] 5. The bolt hole 201 of the cover plate 2 of the present invention is designed as a long hole or a gap assembly hole, and a sufficient gap is left between the screw rod and the bolt hole, so that the screw rod will not collide with the bolt hole 201 when the cover plate 2 reciprocates relative to the box body 1;

[0060] 6. The cover plate 2 of the present invention is designed with rails 203 on both sides for installing the slide rails 8 for controlling the movement direction of the cover plate;

[0061] 7. A connecting ear piece 204 is designed on one side of the cover plate 2 of the present invention, which is used to connect the cover plate 2 to the actuator of the testing machine;

[0062] 8. Slide rails 8 are installed on both sides of the track 203 of the cover plate 2 of the present invention, which are used to support the cover plate 2 to move along the track 203;

[0063] 9. The present invention is designed with a positioning screw sleeve 10 and a positioning screw 11. The position of the slider 9 relative to the test bracket 7 is adjusted by rotating the positioning screw sleeve 10 and the positioning screw 11 to ensure that the slider 9 fits the slide rail 8, thereby reducing the positioning requirements for the test bracket 11;

[0064] 10. The present invention is designed with a test bracket 7 for installing a positioning screw 11 to provide support for the positioning screw sleeve 10 and the positioning screw 11.

[0065] In the research of key technologies of CR929 wing fuel tank, a static pressure sealing test of fuel tank cover sealing strip has been carried out, and the test results are good, achieving the purpose of verifying the static pressure sealing performance of the sealing strip. The present invention is an improved design based on the static pressure sealing test method, and has strong feasibility.

[0066] The embodiments of the present invention are described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementation modes, which are merely illustrative rather than restrictive. Under the guidance of the present invention, ordinary technicians in this field can also make many forms without departing from the scope of protection of the present invention and the claims, all of which are within the protection of the present invention.

Claims

1. A vibration seal test device for a wing fuel tank cover seal strip, characterized in that: The device is used to verify the sealing performance of the wing oil tank seal under the combined effects of vibration and internal oil pressure during aircraft flight, including: The box unit with the seal strip to be tested is used to hold the fuel and apply internal oil pressure. The box unit comprises a box wall, and a threaded blind hole is arranged on the upper end surface of the box wall for sliding connection with the cover plate of the reciprocating vibration unit; a groove is designed inside the threaded blind hole for installing a sealing strip; a first threaded through hole and a second threaded through hole are arranged on the side surface of the box wall for installing a pressure gauge and an oil inlet pipe respectively; The reciprocating vibration unit is arranged on the test bracket and is slidably connected with the box unit, and is used to close the box unit and reciprocate relative to the box unit. The reciprocating vibration unit comprises a cover plate, an exhaust valve, a slide rail, a slider, a positioning nut sleeve and a positioning screw. The cover plate is used to close the box unit and provide a track for the reciprocating vibration movement. A slide rail is installed on each side of the track. The slider is fixed to the test bracket through the positioning nut sleeve and the positioning screw. The position of the slider can be adjusted by rotating the positioning nut sleeve and the positioning screw. The two pairs of slide rails and sliders ensure that the cover plate reciprocates along the track. The connection hole between the cover plate and the box unit is designed as a long hole or a clearance fit hole to ensure that the slidingly connected cover plate and the box unit can achieve relative movement. A power supply unit is fixedly connected to the reciprocating vibration unit and is used to provide power for the reciprocating vibration of the reciprocating vibration unit.

2. The wing fuel tank cover sealing strip vibration seal test device according to claim 1, characterized in that: The oil inlet pipe is provided with an oil pipe valve.

3. The wing fuel tank cover sealing strip vibration seal test device according to claim 1, characterized in that: A flange is provided at the bottom of the box unit and is fixed to the test platform through bolt mounting holes.

4. The wing fuel tank cover sealing strip vibration seal test device according to claim 1, characterized in that: The cover plate is designed with a threaded through hole for installing an exhaust valve. When fuel is injected into the box unit, the exhaust valve opens to exhaust air; after the fuel is fully injected, the exhaust valve closes.

5. The wing fuel tank cover sealing strip vibration seal test device according to claim 1, characterized in that: The cover plate is designed with ears for connecting with the power supply unit to provide power for reciprocating vibration motion.

6. The wing fuel tank cover sealing strip vibration seal test device according to claim 1, characterized in that: The test bracket comprises a column, a cross plate and a base. The base is fixed to the test platform by bolts. The column is provided with a threaded through hole for installing a positioning screw.

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