Wing fuel tank wall plate falling collision testing device

Abstract

The utility model belongs to the field of aircraft testing components, and particularly relates to a wing fuel tank wall plate falling collision testing device. The testing device mainly comprises a top detachable covering cap, a fuel tank fake piece, a composite material wall plate test piece and a bottom fireproof baffle system. The device is used for measuring the burn-through resistance and the heat-conducting property of the composite material wing fuel tank wall plate of the transportation type airplane under the condition of a falling and collision pool fire disaster.

Description

Technical Field

[0001] The present application belongs to the field of aircraft testing components, and specifically relates to a wing fuel tank wall panel crash testing device. Background Art

[0002] At present, the transport aircraft under development in China plan to widely use composite materials in the wings. Since the main fuel tanks of this type of aircraft are arranged in the wing area, once the aircraft is in danger of crashing and catching fire, the composite fuel tanks and traditional metal fuel tanks may have significant differences in anti-burning and thermal conductivity, which may cause catastrophic consequences such as fuel tank fire and explosion. The relevant units responsible for civil aircraft airworthiness review at home and abroad attach great importance to this issue, but there is a lack of research on this issue in China, and there is also a lack of foreign information related to test equipment.

[0003] In order to fill the gap in domestic testing technology research, it is necessary to design a wing tank composite wall panel burnout resistance test device under the condition of a crash pool fire, which can be used to study the feasible airworthiness requirements and test methods related to combustion and burnout resistance of wing composite wall panels, so as to show that the composite wing tank has the same safety level as the metal structure. Utility Model Content

[0004] The present invention provides a device for testing the burn-through resistance of composite wing tank wall panels of transport aircraft under a crash pool fire, which is used to measure the burn-through resistance and thermal conductivity of composite wing tank wall panels of transport aircraft under crash pool fire conditions.

[0005] The utility model specifically adopts the following technical means:

[0006] The wing fuel tank wall panel crash test device comprises a fuel tank dummy and a cover detachably connected thereto, the cover has a hole in the middle, and the wall panel test piece and a fire baffle are connected to the bottom of the fuel tank dummy; the fuel tank dummy is welded from a number of "L"-shaped steel plates, and the area of ​​the fire baffle is larger than the bottom area of ​​the fuel tank dummy.

[0007] Furthermore, the cover is connected to the fuel tank dummy by means of a twelve-angle spline bolt.

[0008] Furthermore, the fuel tank dummy is connected to the wall panel test piece and the bottom fire damper through the second high locking bolts.

[0009] Furthermore, the fuel tank dummy, the wall panel test piece and the fire baffle together form a sealing structure capable of containing liquid.

[0010] Furthermore, a plurality of first high locking bolts are arranged on one side of the wall panel test piece.

[0011] Furthermore, the high locking bolts are arranged in a 3╳3 manner, the diameter of the high locking bolts is 4.76 mm, and the nail spacing is 50 mm.

[0012] Furthermore, the size of the mouth cover is 500mm╳500mm, the diameter of the middle opening is 50mm, and the thickness is 1mm.

[0013] Furthermore, the long side dimension of the "L"-shaped steel plate is 500mm╳500mm, and the short side dimension is 500mm╳30mm.

[0014] Furthermore, the size of the wall panel test piece is 560 mm ╳ 560 mm, and the thickness is 4.48 mm.

[0015] Furthermore, the fire damper is a square flat plate of 1500mm╳1500mm with a square hole in the middle, with a size of 500mm╳500mm and a thickness of 1.2mm.

[0016] This solution has the following beneficial effects:

[0017] The device adopts a simple and rationally designed structure, including a fuel tank dummy, a cover, a wall panel test piece and a fire baffle. The components are connected by disassembly, which is convenient for assembly and disassembly, and reduces maintenance costs. The fuel tank dummy, the wall panel test piece and the fire baffle form a sealed structure to ensure that the liquid will not leak during the test, thus ensuring the accuracy of the test data.

[0018] The device can test the burn-through resistance of composite wing tank panels under crash pool fire conditions, and evaluate the fire resistance of the panels through visual inspection and instrument test data, providing an important basis for improving aircraft safety.

[0019] The device is suitable for testing different volumes and different types of liquids (such as water, inert fuel), and the core composite wall panel test piece can be adjusted according to the design characteristics of the specific model of aircraft, with strong adaptability.

[0020] During the design process, the test measurement requirements are fully considered, and heat flow measurement equipment and temperature measurement equipment can be arranged inside the box to improve the comprehensiveness and accuracy of the test. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is an overall view of a specific embodiment of the utility model;

[0022] Figure 2 It is a partial view of a specific embodiment of the utility model;

[0023] Figure 3 It is a layout diagram of connecting fasteners of a specific embodiment of the utility model.

[0024] Numbers in the figure:

[0025] 1. Cover; 2. Fuel tank dummy; 3. Wall panel test piece; 4. Fire baffle; 5. Twelve-angle spline bolt; 6. First high locking bolt; 7. Second high locking bolt; 8. Inside of the box; 9. Outside of the box. DETAILED DESCRIPTION

[0026] The following describes the implementation of the present invention through specific examples. Those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific implementations, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that the illustrations provided in the following embodiments only illustrate the basic concept of the present invention in a schematic manner. The following embodiments and the features in the embodiments can be combined with each other without conflict.

[0027] See also Figure 1-3 A device for testing the burn-through resistance of composite wing fuel tank wall panels of transport aircraft under a crash pool fire mainly comprises a cover 1, a fuel tank dummy 2, a wall panel test piece 3 and a fire baffle 4. The fuel tank dummy 2, the wall panel test piece 3 and the fire baffle 4 together form a sealing structure that can contain liquid. The cover 1 and the fuel tank dummy 2 are detachably connected.

[0028] In this embodiment, the main function of the top removable cover 1 is to close the top of the fuel tank body dummy and reserve an opening for the temperature collection device to pass through. The top removable cover 1 has no requirements for sealing, but needs to be easy to disassemble. The cover 1 is connected to the fuel tank body dummy through ordinary bolts. The size of the cover 1 is 500mm╳500mm, the diameter of the middle opening is 50mm, the material is ordinary steel, and the thickness is 1mm. The top removable cover 1 is connected to the fuel tank dummy 2 through 16 steel twelve-angle spline bolts 5 with a diameter of 9.5mm.

[0029] In this embodiment, the fuel tank dummy 2 is mainly used to simulate the box structure of the wing fuel tank. After being assembled with the composite wall panel test piece 3 and the bottom fire baffle 4, it has good sealing performance and can hold a certain volume of liquid (water, inert fuel, etc.), and the liquid temperature will not leak within the range of 0 to 100° C. The fuel tank dummy 2 is connected to the top cover 1 through a steel twelve-angle spline bolt 5, and is connected to the composite wall panel test piece 3 and the bottom fire baffle 4 through a second high locking bolt 7.

[0030] In this embodiment, the main function of the composite wall panel test piece 3 is to simulate the lower wall panel structure of the wing, and its material, layering, thickness, and molding method need to be consistent with the actual configuration of the aircraft to be verified. The raw material of this test piece is medium-mode high-strength carbon fiber reinforced M21C epoxy resin unidirectional tape prepreg, which is cured in an autoclave and has a thickness of 4.48mm. The size of the composite wall panel test piece 3 is 560mm╳560mm. The composite wall panel test piece 3 is connected to the bottom fire baffle 4 and the fuel tank body dummy by countersunk high-locking bolts. The diameter of the high-locking bolts is 4.76mm, and the nail spacing is 29.375mm.

[0031] Furthermore, in order to simulate the burn-through resistance of the fastener connection area, 3×3 first high locking bolts 6 were arranged on one side of the composite wall panel. The diameter of the high locking bolts was 4.76 mm and the nail spacing was 50 mm.

[0032] In this embodiment, the main function of the bottom fire baffle 4 is to prevent the flame from bypassing the composite wall panel test piece 3 from the side during the combustion test, heating the side wall of the fuel tank body and causing the test failure. The bottom fire baffle 4 is a square flat plate of 1500mm×1500mm with a square hole in the middle and a size of 500mm×500mm. The bottom fire baffle 4 is made of ordinary steel with a thickness of 1.2mm. The bottom fire baffle 4, the composite wall panel test piece 3 and the fuel tank dummy 2 are connected by high-locking bolts.

[0033] Design of composite panel test specimen 3: The lower wing panel is usually a reinforced panel structure with a certain curvature. In order to simplify the manufacture of the test specimen and reduce the manufacturing cost, the inner reinforcement structure is ignored when designing the test specimen, and the influence of curvature is not considered. The final test specimen is a flat plate containing the panel skin layer information. This simplification has little impact on the test.

[0034] Sealing requirements: To prevent leakage of the liquid contained in the fuel tank dummy 2, the connection interface between the tank dummy and the composite wall panel test piece 3 needs to be filled and sealed. The sealant needs to be able to work normally at a high temperature of 100°C.

[0035] Clamping requirements for the test device: The maximum weight of the test device when filled with water is 177.3Kg. If the safety factor is 2.0, the clamping device should be able to guarantee a load-bearing requirement of 354.6Kg. At the same time, due to the large size of the test device, some deformation will occur during the test, so the clamping of the test device is required to use a mechanical connection with no less than double-row fasteners. In addition, there are certain requirements for the rigidity of the clamping tool itself, and the maximum deformation of the final test device should not exceed 10mm.

[0036] Distance control between the fire source and the composite material wall panel test piece 3: The distance between the fire source and the composite material wall panel test piece 3 should be controlled according to the center position of the wall panel, and needs to be adjusted according to the deformation of the test piece.

[0037] During the test of the utility model, a prescribed volume of liquid simulating fuel is first injected into the fuel tank dummy 2, and sensors such as thermocouples are arranged inside the wall panel test piece 3. The wires of the sensors are led out from the opening in the middle of the cover 1 and connected to the collection equipment. Then, a fire source of a specified specification is used at the center of the bottom of the test piece to simulate an oil pool fire for burning.

Claims

1. Wing tank wall panel crash test device, characterized in that: The invention comprises a fuel tank dummy (2) and a cover (1) detachably connected thereto, the cover (1) has a hole in the middle, and a wall panel test piece (3) and a fire baffle (4) are connected below the fuel tank dummy (2); the fuel tank dummy (2) is welded from a plurality of "L"-shaped steel plates, and the area of ​​the fire baffle (4) is larger than the bottom area of ​​the fuel tank dummy (2).

2. The wing tank wall panel crash test device according to claim 1, characterized in that: The opening cover (1) is connected to the fuel tank dummy (2) via a twelve-angle spline bolt (5).

3. The wing tank wall panel crash test device according to claim 1, characterized in that: The fuel tank dummy (2) is connected to the wall panel test piece (3) and the bottom fire baffle (4) via the second high locking bolt (7).

4. The wing tank wall panel crash test device according to claim 1, characterized in that: The fuel tank dummy (2), the wall panel test piece (3) and the fireproof baffle (4) together form a sealed structure capable of containing liquid.

5. The wing tank wall panel crash test device according to claim 1, characterized in that: A plurality of first high locking bolts (6) are arranged on one side of the wall panel test piece (3).

6. The wing tank wall panel crash test device according to claim 1, characterized in that: The high locking bolts are arranged in a 3╳3 pattern, the diameter of the high locking bolts is 4.76mm, and the nail spacing is 50mm.

7. The wing tank wall panel crash test device according to claim 1, characterized in that: The size of the mouth cover (1) is 500mm×500mm, the diameter of the middle opening is 50mm, and the thickness is 1mm.

8. The wing tank wall panel crash test device according to claim 1, characterized in that: The long side dimension of the "L"-shaped steel plate is 500mm╳500mm, and the short side dimension is 500mm╳30mm.

9. The wing tank wall panel crash test device according to claim 1, characterized in that: The dimensions of the wall panel test piece (3) are 560 mm x 560 mm and the thickness is 4.48 mm.

10. The wing tank wall panel crash test device according to claim 1, characterized in that: The fireproof baffle (4) is a square flat plate of 1500mm×1500mm with a square hole in the middle, a size of 500mm×500mm and a thickness of 1.2mm.

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