Fuel tank for aircraft fuel shaking test

Abstract

The utility model belongs to the technical field of aircraft fuel shaking test research, and particularly relates to a fuel tank for aircraft fuel shaking test, which comprises a bottom plate made of a transparent material; the four side wall plates are made of transparent materials, the bottoms of the four side wall plates are connected to the bottom plate, a rectangular space is defined by the four side wall plates, and multiple pairs of inserting grooves are formed in the inner sides of a pair of opposite side wall plates; the partition plates are made of transparent materials and provided with open holes, the edges of the two sides of each partition plate are inserted into the corresponding pair of insertion grooves, and the rectangular space is divided into a plurality of small spaces; and the cover plate is made of a transparent material, covers the tops of the four side wall plates and blocks the rectangular space.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft fuel slosh test research, and specifically relates to a fuel tank for aircraft fuel slosh test. Background Art

[0002] When an airplane is flying, the fuel in the tank will shake. The pattern of fuel shaking, including the shape of the shaking and the magnitude of the load it generates, is not only related to the amplitude and frequency of the tank shaking, but also to the size and shape of the partition openings in the tank.

[0003] Accurately obtaining the fuel sloshing pattern in the fuel tank is of great significance for the design and improvement of the fuel tank. The fuel tank on the aircraft is large in size. Directly conducting sloshing tests on it will result in high test costs, and it is not convenient to change the size and form of the holes on the partition, and it is not convenient to observe the fuel sloshing morphology. In view of this, the present application is proposed. Summary of the Invention

[0004] The purpose of the present application is to provide a fuel tank for aircraft fuel sloshing test, so as to overcome or alleviate at least one of the existing technical deficiencies.

[0005] The technical solution of this application is:

[0006] A fuel tank for aircraft fuel sloshing test, comprising:

[0007] a base plate made of transparent material;

[0008] Four side wall panels are made of transparent material, the bottoms of which are connected to the bottom plate and enclose a rectangular space with each other, wherein a pair of opposite side wall panels have multiple pairs of slots on their inner sides;

[0009] A plurality of partitions are made of transparent material and have openings thereon, and the edges on both sides are inserted into the pairs of slots to divide the rectangular space into a plurality of small spaces;

[0010] The cover plate is made of transparent material and covers the top of the four side wall plates to block the rectangular space.

[0011] According to at least one embodiment of the present application, in the above-mentioned fuel tank for aircraft fuel slosh test, the transparent material is acrylic material.

[0012] According to at least one embodiment of the present application, in the above-mentioned fuel tank for aircraft fuel slosh testing, the cover plate and the tops of the four side wall panels are in contact with each other via a step structure.

[0013] According to at least one embodiment of the present application, in the above-mentioned fuel tank for aircraft fuel slosh testing, the cover plate and the tops of the four side wall panels are connected by screws.

[0014] According to at least one embodiment of the present application, the above-mentioned fuel tank for aircraft fuel slosh testing further includes:

[0015] Four groups of angled plates are connected between the bottom plate and the outer sides of the four side wall plates.

[0016] This application has at least the following beneficial technical effects:

[0017] Provided is a fuel tank for aircraft fuel slosh testing, wherein the sidewalls and baffles can be manufactured according to the scaled dimensions of the fuel tank to reduce testing costs. During the fuel slosh test, pressure measuring points can be set on the four sidewalls and strain measuring points can be set on each baffle 3 to measure the load generated by the fuel slosh, and the shape of the fuel slosh can be observed using a camera. In addition, the size and shape of the openings can be conveniently changed by replacing the baffles. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Schematic diagram of the appearance of a fuel tank for an aircraft fuel slosh test provided in an embodiment of the present application;

[0019] Figure 2 This is a schematic structural diagram of a fuel tank for an aircraft fuel slosh test provided in an embodiment of the present application with the cover removed;

[0020] Figure 3 This is a schematic structural diagram of an upper cover plate of a fuel tank for an aircraft fuel slosh test provided in an embodiment of the present application;

[0021] in:

[0022] 1- bottom plate; 2- side wall plate; 3- partition plate; 4- cover plate; 5- angle plate.

[0023] In order to better illustrate this embodiment, some parts of the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative purposes and should not be understood as limiting this application. DETAILED DESCRIPTION

[0024] To make the technical solution and its advantages of this application more clear, the technical solution of this application will be further described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described here are only some of the embodiments of this application and are only used to explain this application, not to limit this application. It should be noted that for ease of description, only the parts relevant to this application are shown in the accompanying drawings, and other relevant parts can refer to the general design.

[0025] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application should have the usual meanings understood by those skilled in the art in the field to which this application belongs. The words indicating orientation used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. The word "include" used in the description of this application means that the elements or objects appearing before the word include the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0026] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "installation", "connection" and similar terms used in the description of this application should be understood in a broad sense. For example, the connection can be a fixed connection or a detachable 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. Technical personnel in the field can understand its specific meaning in this application according to the specific circumstances.

[0027] A fuel tank for aircraft fuel sloshing test, comprising:

[0028] A bottom plate 1 made of a transparent material;

[0029] Four side wall panels 2 are made of transparent material, the bottoms of which are connected to the bottom plate 1 and enclose a rectangular space with each other, wherein a pair of opposite side wall panels 2 have multiple pairs of slots on their inner sides;

[0030] Multiple partitions 3, made of transparent material, with openings on them, with both side edges inserted into the pairs of slots, dividing the rectangular space into multiple small spaces;

[0031] The cover plate 4 is made of a transparent material and covers the top of the four side wall plates 2 to block the rectangular space.

[0032] The aircraft fuel sloshing test tank disclosed in the above embodiment is used for a sloshing test. Fuel can be added into the rectangular space surrounded by the four side wall panels 2, fixed to a vibration table, and shaken at a set amplitude and frequency to simulate the sloshing of the fuel in the tank.

[0033] In the fuel tank for aircraft fuel slosh testing disclosed in the above-mentioned embodiment, the sidewall panels 2 and partitions 3 can be manufactured according to the scaled dimensions of the fuel tank to reduce testing costs. During the slosh test, pressure measuring points can be set on the four sidewall panels 2 and strain measuring points can be set on each partition 3 to measure the load generated by the fuel slosh, and the shape of the fuel slosh can be observed using a camera. In addition, the size and shape of the opening can be conveniently changed by replacing the partition 3.

[0034] In some optional embodiments, in the above-mentioned fuel tank for aircraft fuel slosh test, the transparent material is acrylic material.

[0035] In some optional embodiments, in the above-mentioned fuel tank for aircraft fuel slosh test, the cover plate 4 and the tops of the four side wall panels 2 are in contact with each other via a step structure, so that the cover plate 4 and the four side wall panels 2 are firmly connected.

[0036] In some optional embodiments, in the above-mentioned fuel tank for aircraft fuel slosh testing, the cover plate 4 is connected to the tops of the four side wall panels 2 with screws to facilitate disassembly and assembly, to facilitate replacement of the partition 3, and to change the size and form of the opening.

[0037] In some optional embodiments, the above-mentioned fuel tank for aircraft fuel slosh test further includes:

[0038] Four groups of angled plates 5 are connected between the bottom plate 1 and the outer sides of the four side wall plates 2 to effectively support the four side wall plates 2 and stabilize the structure.

[0039] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referenced to each other. In the absence of conflict, the embodiments in this application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0040] So far, the technical solution of the present application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A fuel tank for aircraft fuel slosh testing, characterized in that: include: a bottom plate (1) made of a transparent material; Four side wall panels (2) are made of transparent material, the bottoms of which are connected to the bottom plate (1) and mutually enclose a rectangular space, wherein a pair of opposite side wall panels (2) have multiple pairs of slots on their inner sides; A plurality of partitions (3) are made of transparent material and have openings thereon, with edges on both sides inserted into the pairs of slots to divide the rectangular space into a plurality of small spaces; The cover plate (4) is made of transparent material and covers the top of the four side wall plates (2) to block the rectangular space.

2. The fuel tank for aircraft fuel slosh testing according to claim 1, characterized in that: The transparent material is acrylic.

3. The fuel tank for aircraft fuel slosh testing according to claim 1, characterized in that: The cover plate (4) and the tops of the four side wall plates (2) are in contact with each other in a step structure.

4. The fuel tank for aircraft fuel slosh testing according to claim 1, characterized in that: The cover plate (4) is connected to the tops of the four side wall plates (2) by screws.

5. The fuel tank for aircraft fuel slosh testing according to claim 1, characterized in that: Also includes: Four groups of angled plates (5) are connected between the bottom plate (1) and the outer sides of the four side wall plates (2).

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