Research test method for shaking rule of fuel oil in aircraft fuel tank

Abstract

The invention belongs to the technical field of fuel oil shaking law research in an aircraft fuel tank, and particularly relates to a fuel oil shaking law research test method in an aircraft fuel tank, which is characterized in that a fuel tank scaling model is designed to replace an actual fuel tank to carry out movable test research, and a cover plate above the fuel tank scaling model can be opened; the fuel tank scale model is designed to be made of transparent materials, the fuel tank scale model is designed to be made of transparent materials, the shaking form of fuel oil can be conveniently observed, in addition, the shaking platform is designed, and the shaking platform can be used for conveniently observing the shaking form of the fuel oil tank scale model. The shaking platform is a six-degree-of-freedom shaking platform, so that shaking required by experimental research can be conveniently generated.

Description

Technical Field

[0001] The present application belongs to the technical field of research on fuel sloshing laws in aircraft fuel tanks, and specifically relates to a test method for researching fuel sloshing laws in aircraft fuel tanks. Background Art

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

[0003] Accurately obtaining the fuel sloshing law 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 volume. Directly using it for sloshing test research has a high test cost, and it is not convenient to change the number of holes on the partition, and it is not convenient to observe the fuel sloshing morphology. In this regard, the finite element method is currently mainly used to perform fluid-solid coupling analysis to study the fuel sloshing law. However, when the finite element method is used for fluid-solid coupling calculation, the method selection, particle size, contact type, etc. will have a significant impact on the calculation results, and the correctness cannot be judged.

[0004] This application is proposed in view of the above-mentioned technical defects. Summary of the invention

[0005] The purpose of the present application is to provide a test method for studying the fuel sloshing law in an aircraft fuel tank, so as to overcome or alleviate at least one of the known technical defects.

[0006] The technical solution of this application is:

[0007] A test method for studying the sloshing law of fuel in an aircraft fuel tank, comprising:

[0008] A scaled-down model of a fuel tank is made of a transparent material, the upper cover can be opened, and the edges of both sides of the partition are inserted into the slots on the inner sides of a pair of opposite side walls of the scaled-down model of the fuel tank. Achieve connectivity;

[0009] Arrange pressure measuring points on the side wall of the scaled model of the oil tank, and arrange strain measuring points on the partition;

[0010] Arrange a shaking platform, the shaking platform including a table top;

[0011] Fix the scale model of the fuel tank to the table of the shaking platform, and fill the scale model of the fuel tank with fuel;

[0012] Arrange the camera so that it faces the scaled-down model of the fuel tank;

[0013] Start the shaking platform, drive the scaled-down model of the fuel tank to shake with different amplitudes and frequencies through the platform, measure the pressure on the side wall of the scaled-down model of the fuel tank through the pressure measuring point, and measure the strain of the partition in the scaled-down model of the fuel tank through the strain measuring point, thereby obtaining the load caused by the fuel shaking, and shoot and observe the shaking shape of the fuel in the scaled-down model of the fuel tank through the camera;

[0014] By replacing the partition in the scaled-down model of the fuel tank and changing the number of openings, the load caused by the fuel sloshing in the scaled-down model of the fuel tank with different numbers of openings, various amplitudes and frequencies of shaking is obtained, and the sloshing shape of the fuel in the scaled-down model of the fuel tank is photographed and observed.

[0015] According to at least one embodiment of the present application, in the above-mentioned test method for studying the sloshing law of fuel in an aircraft fuel tank, the sloshing platform further includes a base frame, and an actuator cylinder arranged between the table and the base frame;

[0016] Starting the shaking platform specifically involves starting an actuator in the shaking platform to drive the table top to shake.

[0017] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank, the number of actuators in the sloshing platform is 6.

[0018] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank,

[0019] An angle sensor is set on the table top of the shaking platform, and the shaking amplitude and frequency of the oil tank scale model are analyzed by the angle sensor monitoring data.

[0020] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in the aircraft fuel tank, a monitor is connected to the pressure measuring point and the strain measuring point to monitor the load generated by the fuel sloshing in the scaled model of the fuel tank.

[0021] According to at least one embodiment of the present application, in the above-mentioned test method for studying the sloshing pattern of fuel in an aircraft fuel tank, a monitor is connected to a camera to record and observe the sloshing pattern of the fuel in a scaled model of the fuel tank.

[0022] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in the aircraft fuel tank, a monitor is connected to the six actuators in the sloshing platform, and an angle sensor is connected to constitute a negative feedback control of the sloshing amplitude and frequency of the fuel tank scale model.

[0023] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank, the scaled model of the fuel tank is made of acrylic material.

[0024] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank,

[0025] The lower bottom wall of the scaled model of the oil tank protrudes from the side wall and is fixed to the table top of the shaking platform with screws.

[0026] According to at least one embodiment of the present application, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank, a plurality of angular support plates are provided between the lower bottom wall and the outer side of the side wall in the scaled model of the fuel tank for support.

[0027] This application has at least the following beneficial technical effects:

[0028] Provided is a test method for studying the sloshing law of fuel in an aircraft fuel tank. A fuel tank scale model is designed to replace an actual fuel tank for sloshing test research. The cover plate on the fuel tank scale model is designed to be open, and the edges on both sides of the partition are inserted into the slots on the inner sides of a pair of opposite side walls of the fuel tank scale model, so that the partition can be conveniently replaced, and the number of openings can be easily changed. The fuel tank scale model is designed to be made of transparent material, so that the fuel sloshing form can be conveniently observed. In addition, a sloshing platform is designed to be a six-degree-of-freedom sloshing platform, so that the sloshing required for the test research can be conveniently generated. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 is a schematic diagram of a scaled model of a fuel tank provided in an embodiment of the present application;

[0030] Figure 2 is a schematic diagram of a shaking platform provided in an embodiment of the present application;

[0031] in:

[0032] 1- scale model of the oil tank; 2- partition; 3- shaking platform; 4- base frame; 5- table top; 6- actuator; 7- angle sensor; 8- angular support plate.

[0033] In order to better illustrate the present 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 construed as limitations on the present application. DETAILED DESCRIPTION

[0034] In order to make the technical solution and advantages of the present application clearer, the technical solution of the present application will be described in further detail in detail and in detail with reference to the accompanying drawings. It can be understood that the specific embodiments described here are only partial embodiments of the present application, which are only used to explain the present application, not to limit the present application. It should be noted that, for the convenience of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design.

[0035] In addition, unless otherwise defined, the technical terms or scientific terms used in the description of this application shall have the usual meanings understood by those of ordinary skill in the art to which this application belongs. The words used in the description of this application to indicate orientation 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 indicates 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.

[0036] In addition, it should be noted that, unless otherwise clearly specified 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.

[0037] A test method for studying the sloshing law of fuel in an aircraft fuel tank, comprising:

[0038] A fuel tank scale model 1 is made of a transparent material, the upper cover can be opened, and the edges of the partition 2 are inserted into the grooves on the inner sides of a pair of opposite side walls of the fuel tank scale model 1 to achieve connection. Figure 1 As shown;

[0039] Arrange pressure measuring points on the side wall of the oil tank scale model 1, and arrange strain measuring points on the partition 2;

[0040] The shaking platform 3 is arranged, and the shaking platform 3 includes a base frame 4, a table 5, and six actuators 6 connected between the base frame 4 and the table 5. Figure 2 As shown;

[0041] The scaled-down model 1 of the fuel tank is fixed to the table 5 of the shaking platform 3, and fuel is added into the scaled-down model 1 of the fuel tank;

[0042] Arrange a camera so that the camera faces the scaled-down model 1 of the fuel tank;

[0043] The six actuators 6 in the shaking platform 3 are started, and the oil tank scale model 1 is driven to shake with different amplitudes and frequencies through the table 5. The pressure on the side wall of the oil tank scale model 1 is measured by the pressure measuring point, and the strain of the partition 2 in the oil tank scale model 1 is measured by the strain measuring point, thereby obtaining the load generated by the oil shaking, and the shaking form of the oil in the oil tank scale model 1 is observed by shooting with a camera;

[0044] The partition 2 in the fuel tank scale model 1 is replaced, and the number of openings is changed to obtain the load caused by the fuel sloshing in the fuel tank scale model 1 under different numbers of openings, various amplitudes and frequencies of shaking, and the sloshing shape of the fuel in the fuel tank scale model 1 is photographed and observed.

[0045] The experimental method for studying the fuel sloshing law in an aircraft fuel tank disclosed in the above-mentioned embodiment is designed to use a fuel tank scale model 1 to replace the actual fuel tank for sloshing test research, and the cover plate on the fuel tank scale model 1 is designed to be open, and the edges on both sides of the partition 2 are inserted into the grooves on the inner sides of a pair of opposite side walls of the fuel tank scale model 1, so that the partition 2 can be conveniently replaced, and the number of openings can be easily changed. The fuel tank scale model 1 is designed to be made of transparent material, so that the fuel sloshing shape can be conveniently observed. In addition, the sloshing platform 3 is designed to be a six-degree-of-freedom sloshing platform, so that the sloshing required for the experimental research can be conveniently generated.

[0046] In some optional embodiments, in the above-mentioned test method for studying the fuel sloshing law in the aircraft fuel tank, an angle sensor 7 is set on the table 5 of the sloshing platform 3, and the sloshing amplitude and frequency of the fuel tank scale model 1 are analyzed by monitoring data of the angle sensor 7.

[0047] In some optional embodiments, in the above-mentioned test method for studying the fuel sloshing law in the aircraft fuel tank, a monitor is connected to the pressure measuring point and the strain measuring point to monitor the load generated by the fuel sloshing in the fuel tank scale model 1;

[0048] Connect the camera to the monitor to record and observe the sloshing pattern of the fuel in the scaled model 1 of the fuel tank;

[0049] The monitor is connected to the six actuators 6 in the shaking platform 3 and the angle sensor 7 to form a negative feedback control of the shaking amplitude and frequency of the oil tank scale model 1.

[0050] In some optional embodiments, in the above-mentioned test method for studying the fuel sloshing law in the aircraft fuel tank, the fuel tank scale model 1 is made of acrylic material, and can also be made of other transparent plastics with stable properties.

[0051] In some optional embodiments, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank, the lower bottom wall of the fuel tank scale model 1 protrudes from the side wall and is fixed to the table top 5 of the sloshing platform 3 by screws.

[0052] In some optional embodiments, in the above-mentioned test method for studying the fuel sloshing law in an aircraft fuel tank, a plurality of angular support plates 8 are provided between the lower bottom wall and the outer side of the side wall of the fuel tank scale model 1 for support.

[0053] In the same specific implementation, four test scenarios were designed. The shaking amplitude was characterized by the shaking angle. The test results are shown in the following table:

[0054] Under the conditions of the same number of openings and sloshing frequency, the peak values ​​of the wall pressure and the partition strain increase with the increase of the sloshing amplitude. The partition has a significant effect on the sloshing characteristics of the oil tank under the partial filling rate state, and the test data will increase with the increase of the sloshing amplitude.

[0055] 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.

[0056] 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 substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will fall within the scope of protection of the present application.

Claims

1. A test method for studying the sloshing law of fuel in an aircraft fuel tank, characterized in that: include: A scaled-down model of a fuel tank (1) is made of a transparent material, the upper cover plate can be opened, and the edges of both sides of the partition plate (2) are inserted into the slots on the inner sides of a pair of opposite side walls of the scaled-down model of the fuel tank (1) to achieve connection; Arranging pressure measuring points on the side wall of the scaled model (1) of the oil tank, and arranging strain measuring points on the partition (2); Arranging a shaking platform (3), wherein the shaking platform (3) comprises a table top (5); The scaled-down model of the fuel tank (1) is fixed to the tabletop (5) of the shaking platform (3), and fuel is added to the scaled-down model of the fuel tank (1); Arrange a camera so that the camera faces the scaled model of the fuel tank (1); The shaking platform (3) is started, and the oil tank scale model (1) is driven to shake at different amplitudes and frequencies through the table (5), and the pressure on the side wall of the oil tank scale model (1) is measured through the pressure measuring point, and the strain of the partition (2) in the oil tank scale model (1) is measured through the strain measuring point, thereby obtaining the load caused by the oil shaking, and the shaking shape of the oil in the oil tank scale model (1) is photographed and observed through a camera; The partition plate (2) in the scaled-down model of the fuel tank (1) is replaced, and the number of openings is changed to obtain the load caused by the sloshing of the fuel in the scaled-down model of the fuel tank (1) under different numbers of openings, various amplitudes, and frequencies of sloshing, and the sloshing form of the fuel in the scaled-down model of the fuel tank (1) is photographed and observed.

2. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 1, characterized in that: The shaking platform (3) also includes a base frame (4) and an actuating cylinder (6) arranged between the table top (5) and the base frame (4); Starting the shaking platform (3) specifically involves starting the actuator (6) in the shaking platform (3) to drive the table top (4) to shake.

3. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 2, characterized in that: The number of the actuators (6) in the shaking platform (3) is 6.

4. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 3 is characterized in that: An angle sensor (7) is arranged on a table top (5) of the shaking platform (3), and the shaking amplitude and frequency of the oil tank scale model (1) are analyzed using monitoring data from the angle sensor (7).

5. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 4, characterized in that: The pressure measuring points and strain measuring points are connected with a monitor to monitor the load caused by fuel sloshing in the scaled model (1) of the fuel tank.

6. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 5, characterized in that: The monitor is connected to a camera to record and observe the sloshing pattern of the fuel in the scaled model of the fuel tank (1).

7. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 6, characterized in that: The monitor is connected to six actuators (6) in the shaking platform (3) and an angle sensor (7) to form negative feedback control of the shaking amplitude and frequency of the oil tank scale model (1).

8. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 1, characterized in that: The scaled model of the fuel tank (1) is made of acrylic material.

9. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 8, characterized in that: The lower bottom wall of the oil tank scale model (1) protrudes from the side wall and is fixed to the table top (5) of the shaking platform (3) by screws.

10. The test method for studying the fuel sloshing law in an aircraft fuel tank according to claim 9, characterized in that: A plurality of angular support plates (8) are arranged between the lower bottom wall and the outer side of the side wall of the oil tank scale model (1) for support.

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