Method and device for calculating fuel pressure of wing rib angle sheet of fuel tank

Abstract

The invention provides a method for calculating fuel pressure of a wing rib angle piece of a fuel tank, and belongs to the technical field of airplane structural strength calculation. The method comprises the steps that overload of an airplane in all directions in a certain overload state is obtained, and the sum of space vectors of the overload is obtained based on the overload in all the directions; determining a plane perpendicular to the sum of the overload space vectors according to the sum of the overload space vectors; intercepting the fuel projection area based on the plane to obtain the fuel projection area in an overload state, and determining the oil height based on the fuel projection area in the overload state; and constructing a wing rib angle sheet fuel pressure calculation formula based on the oil height, and calculating the fuel pressure of the wing rib angle sheet of the fuel tank in the composite overload state of the aircraft according to the wing rib angle sheet fuel pressure calculation formula.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft structure strength calculation, and particularly relates to a fuel tank wing rib angle piece fuel pressure calculation method and device. BACKGROUND

[0002] When an aircraft is in a large fuel amount and large maneuvering combined overload flight, large combined overload can cause large fuel pressure. Determining the fuel tank wing rib angle piece fuel pressure of the aircraft under the combined overload state is a complex problem, which involves the calculation of the geometric characteristics of the fuel tank, the position of the wing rib angle piece, the initial fuel volume, and the numerical value and direction of the combined overload. The prior art lacks detailed research on such problems, which limits the fine calculation and analysis of the fuel tank wing rib angle piece fuel pressure. SUMMARY

[0003] The purpose of the present application is to provide a fuel tank wing rib angle piece fuel pressure calculation method and device to solve or alleviate at least one problem in the background art.

[0004] The technical solution of the present application is: a fuel tank wing rib angle piece fuel pressure calculation method, comprising:

[0005] Obtaining the overloads of the aircraft in each direction under a certain overload state, obtaining the sum of the spatial vectors of the overloads based on the overloads in each direction, and determining a plane perpendicular to the sum of the spatial vectors of the overloads;

[0006] Intercepting the fuel projection area based on the plane to obtain the fuel projection area under the overload state, and determining the oil height based on the fuel projection area under the overload state;

[0007] Constructing a wing rib angle piece fuel pressure calculation formula based on the oil height, and calculating the fuel pressure of the fuel tank wing rib angle piece under the combined overload state of the aircraft according to the wing rib angle piece fuel pressure calculation formula.

[0008] Preferably, when the fuel projection area is intercepted based on the plane, the fuel projection area under the overload state remains unchanged from the fuel projection area under the non-overload state.

[0009] Preferably, the oil height calculation method is: ,

[0010] In the formula, h is the oil height at the wing rib angle piece;

[0011] h max is the maximum oil height calculated from the fuel projection area under the overload state;

[0012] l a is the position of the intersection of the sum of the spatial vectors of the overloads and the lower wall plate of the fuel tank structure when measuring the highest oil.

[0013] l b The location where the sum of the overload space vectors intersects with the lower wall panel of the oil tank structure when the oil level is 0.

[0014] l c This is the distance between the front beam and the rear beam at the location of the wing rib;

[0015] l represents the distance between the wing rib and the front beam.

[0016] Preferably, the formula for calculating the fuel pressure of the wing rib is: ,

[0017] In the formula: P is the fuel pressure at the wing rib, ρ is the fuel density, g is the gravitational acceleration, n is the aircraft composite overload coefficient, and h is the fuel height at the wing rib.

[0018] On the other hand, the technical solution provided in this application is: a calculation device for fuel pressure on fuel tank ribs, comprising:

[0019] The plane construction module is used to obtain the overload in each direction of the aircraft under a certain overload state, obtain the sum of the spatial vectors of the overload based on the overload in each direction, and determine the plane perpendicular to the sum of the spatial vectors of the overload based on the sum of the spatial vectors of the overload.

[0020] The oil level calculation module extracts the fuel projection area from the plane to obtain the fuel projection area under overload conditions, and determines the oil level based on the fuel projection area under overload conditions.

[0021] The fuel pressure calculation module constructs a fuel pressure calculation formula for the wing rib plate based on the fuel level, and calculates the fuel pressure of the fuel tank wing rib plate under the aircraft's compound overload state according to the wing rib plate fuel pressure calculation formula.

[0022] Preferably, when the fuel projection area is truncated based on a plane, the fuel projection area under overload conditions remains unchanged compared to the fuel projection area under unoverload conditions.

[0023] Preferably, the method for calculating the oil level is as follows: ,

[0024] Where: h is the oil height at the rib corner;

[0025] h max The maximum oil height is calculated based on the projected area of ​​the fuel under overload conditions;

[0026] l a The location where the sum of the overload space vectors intersects with the lower wall panel of the oil tank structure when the oil level is at its highest point;

[0027] l b The location where the sum of the overload space vectors intersects with the lower wall panel of the oil tank structure when the oil level is 0.

[0028] l c This is the distance between the front beam and the rear beam at the location of the wing rib;

[0029] l represents the distance between the wing rib and the front beam.

[0030] Preferably, the formula for calculating the fuel pressure of the wing rib is: ,

[0031] In the formula: P is the fuel pressure at the wing rib, ρ is the fuel density, g is the gravitational acceleration, n is the aircraft composite overload coefficient, and h is the fuel height at the wing rib.

[0032] Thirdly, this application provides an electronic device, comprising:

[0033] One or more processors;

[0034] Memory;

[0035] One or more applications, which are stored in the memory and configured to be executed by the one or more processors, are configured to implement the method for calculating fuel pressure on the fuel tank fin angle plate as described in any one of the above.

[0036] Finally, this application provides a computer-readable storage medium storing at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, the at least one program, the code set, or the instruction set is loaded and executed by a processor to implement the method for calculating the fuel pressure of the fuel tank wing ribs as described above.

[0037] The method and apparatus of this application fully consider the geometric characteristics of the fuel tank, the position of the ribs, the initial fuel volume and the value and direction of the combined overload, etc., and can accurately calculate the fuel pressure of the fuel tank ribs under the combined overload state, avoiding problems such as the failure and damage of part of the fuel tank structure due to inaccurate or unrealistic fuel pressure of the ribs. Attached Figure Description

[0038] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0039] Figure 1 A schematic diagram illustrating the method for calculating fuel pressure on the fuel tank ribs for this application.

[0040] Figure 2 This is a schematic diagram of the sum of spatial vectors of overload in various directions of the aircraft in this application and plane P.

[0041] Figure 3 This is a schematic diagram of the fuel projection shape at a certain rib of the fuel tank in this application under the condition of not being overloaded.

[0042] Figure 4 This is a schematic diagram of the fuel projection shape at a certain rib of the fuel tank under combined overload conditions.

[0043] Figure 5 This is a schematic diagram of the fuel tank projection shape at a certain rib of the fuel tank under combined overload conditions in this embodiment of the application.

[0044] Figure 6 A schematic diagram of a device for calculating fuel pressure on the fuel tank ribs for this application. Detailed Implementation

[0045] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0046] This application proposes a method and apparatus with certain versatility for calculating fuel pressure on the wing ribs of a fuel tank under combined overload conditions in aircraft. This method and apparatus are used to calculate the fuel pressure on the wing ribs of a fuel tank under combined overload conditions in aircraft, providing support for the optimized design of aircraft fuel tanks.

[0047] like Figure 1 As shown, the method for calculating fuel pressure on the fuel tank rib corner plates proposed in this application includes:

[0048] Step S1: Obtain the overload in each direction of the aircraft under a certain overload state, obtain the sum of the spatial vectors of the overload based on the overload in each direction, and determine the plane perpendicular to the sum of the spatial vectors of the overload based on the sum of the spatial vectors of the overload.

[0049] Under a certain overload condition of the aircraft, the fuel level will be perpendicular to the sum of the spatial vectors of the overload in all directions of the aircraft. For example... Figure 2 As shown, when an aircraft is subjected to overloads in various directions during flight or landing, the overloads in each direction can be expressed as follows: the overload in the x-direction is... The overload in the y-direction is The overload in the z-direction is At this moment, the sum of the spatial vectors of the aircraft's overload in all directions is: The plane perpendicular to the sum of the spatial vectors is called P.

[0050] Step S2: Based on the plane obtained in step S1, the fuel projection area is cut off to obtain the fuel projection area under overload conditions, and the fuel level is determined based on the fuel projection area under overload conditions.

[0051] When the sum of spatial vectors is projected onto the plane of the rib station, it can be considered that it is mainly projected in the XOZ plane. Therefore, the oil level at each rib is mainly related to the overload of the aircraft in the x and z directions.

[0052] like Figure 3 The diagram shows the projected area of ​​fuel at a certain rib of the fuel tank under no-overload conditions. The figure is shown in Figure 3. When the aircraft is subjected to an x-axis overload... y-direction overload Z-axis overload Composition of composite overload A plane P is established perpendicular to the sum of the composite overload vectors under this working condition. Based on plane P, the fuel projection area A of a certain rib is intercepted to obtain the fuel projection area under the composite overload state. Based on this fuel projection area, the oil height h can be obtained. In this application, when the fuel projection area A under the unloaded state is intercepted by plane P, the fuel projection area A remains unchanged.

[0053] like Figure 4 As shown, determining the fuel level h requires calculation based on the fuel tank's geometry, the wing rib location, the initial fuel volume, the combined overload value, and the direction. In this application, the fuel level h at the wing rib is calculated using the following formula:

[0054]

[0055] Where: h is the oil height at the rib corner;

[0056] h max The calculated maximum oil height;

[0057] l a The location where the sum of the overload space vectors intersects with the lower wall panel of the oil tank structure when the oil level is at its highest point;

[0058] l b The location where the sum of the overload space vectors intersects with the lower wall panel of the oil tank structure when the oil level is 0.

[0059] l c This is the distance between the front beam 1 and the rear beam 2 at the location where the wing rib is located;

[0060] l is the distance between the wing rib and the front beam 1.

[0061] Step S3: Construct a fuel pressure calculation formula for the wing rib plate based on the oil level, and calculate the fuel pressure of the fuel tank wing rib plate under the combined overload state of the aircraft according to the fuel pressure calculation formula.

[0062] In this application, the fuel pressure calculation formula for the wing rib corner plate is:

[0063] In the formula: P is the fuel pressure at the wing rib, ρ is the fuel density (taken as 775 kg / m3), g is the gravitational acceleration (taken as 9.8 N / kg), n is the aircraft composite overload coefficient, which is determined by the spatial vector sum of overloads in various directions of the aircraft, and h is the fuel height at the wing rib.

[0064] This application uses the fuel tank's projected area at a certain rib under no-overload conditions as 3.445m². 2 Taking this example, in this embodiment, the aircraft is subjected to a combined overload of 1.11g in the x-direction, -0.49g in the y-direction, and 1.66g in the z-direction. A plane P is established perpendicular to the sum of the spatial vectors of this combined overload. The projected cross-sectional area of ​​the fuel in a certain rib is intercepted through plane P. Based on the principle that the intercepted fuel projected area remains unchanged, the fuel projected area under this combined overload is obtained. The maximum fuel height can be obtained by measuring the fuel projected area under this combined overload—that is, the fuel height h = 1453.66mm. a =901.331mm, l b =3998.815、l c =4900.146 and other data. Based on this altitude and fuel pressure, the maximum fuel pressure of this wing rib corner piece is calculated.

[0065] Table 1 shows the fuel pressure gauges for each corner plate of the wing rib in this embodiment of the application (overload conditions: x-direction overload 1.11g, y-direction overload -0.49g, z-direction overload 1.66g).

[0066] Table 1

[0067] Corner piece station Corner piece to front beam distance (mm) Oil level (mm) Maximum pressure (KPa) 1 0 1453.66 22.64 2 184 1453.66 22.64 3 368 1453.66 22.64 4 552 1453.66 22.64 5 736 1453.66 22.64 6 920 1453.66 22.64 7 1104 1351.62 21.05 8 1288 1259.13 19.61 9 1472 1166.65 18.17 10 1656 1074.16 16.73 11 1840 981.67 15.29 12 2024 889.19 13.85 13 2208 796.70 12.41 14 2392 704.21 10.97 15 2576 611.72 9.53 16 2760 519.24 8.09 17 2944 426.75 6.65 18 3128 334.26 5.21 19 3312 241.77 3.77 20 3496 149.29 2.33 21 3680 56.80 0.88 22 3864 0.0 0.0 23 4048 0.0 0.0 24 4232 0.0 0.0 25 4416 0.0 0.0 26 4600 0.0 0.0 27 4784 0.0 0.0

[0068] The method in this application fully considers the geometric characteristics of the fuel tank, the position of the ribs, the initial fuel volume and the value and direction of the combined overload, etc. It can accurately calculate the fuel pressure of the fuel tank ribs under the combined overload state, avoiding problems such as the failure and damage of part of the fuel tank structure due to inaccurate or unrealistic fuel pressure of the ribs.

[0069] Based on the above method, this application also provides a device for calculating the fuel pressure of the fuel tank ribs, the device 100 comprising:

[0070] The plane construction module 101 is used to obtain the overload in each direction of the aircraft under a certain overload state, obtain the sum of the spatial vectors of the overload based on the overload in each direction, and determine the plane perpendicular to the sum of the spatial vectors of the overload based on the sum of the spatial vectors of the overload.

[0071] The oil level calculation module 102 is used to extract the fuel projection area based on the plane, obtain the fuel projection area under overload conditions, and determine the oil level based on the fuel projection area under overload conditions.

[0072] The fuel pressure calculation module 103 is used to construct a fuel pressure calculation formula for the wing rib plate based on the fuel level, and to calculate the fuel pressure of the fuel tank wing rib plate under the combined overload state of the aircraft according to the fuel pressure calculation formula.

[0073] The processing procedure for each module of the device 100 can be referred to the above-mentioned calculation method for fuel pressure of fuel tank wing ribs, and will not be repeated here.

[0074] In addition, this application also provides an electronic device comprising: one or more processors, a memory, and one or more application programs, wherein the one or more application programs are stored in the memory and configured to be executed by the one or more processors, and the one or more application programs are configured to implement a method for calculating fuel pressure on fuel tank wing ribs as described above.

[0075] Finally, this application also provides a computer-readable storage medium storing at least one instruction, at least one program, code set, or instruction set, wherein the at least one instruction, the at least one program, the code set, or the instruction set is loaded and executed by a processor to implement the method for calculating fuel pressure on fuel tank wing ribs as described above.

[0076] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A method of calculating fuel tank stringer corner piece fuel pressure, comprising: The method comprises the following steps: obtaining the overloads of the aircraft in each direction under a certain overload state, obtaining the sum of the spatial vectors of the overloads based on the overloads in each direction, and determining a plane perpendicular to the sum of the spatial vectors of the overloads; intercepting the fuel projection area based on the plane to obtain the fuel projection area under the overload state, and determining the oil level based on the fuel projection area under the overload state; constructing a wing rib angle piece fuel pressure calculation formula based on the oil level, and calculating the fuel pressure of the wing rib angle piece of the fuel tank of the aircraft under a combined overload state according to the wing rib angle piece fuel pressure calculation formula.

2. The method of claim 1, wherein, When the fuel projection area is intercepted based on the plane, the fuel projection area under the overload state remains unchanged from the fuel projection area under the non-overload state.

3. The method for calculating fuel pressure on the fuel tank ribs as described in claim 2, characterized in that, The oil liquid level calculation method is: , In the formula, h is the oil level at the wing rib angle piece; h max Maximum oil level calculated for fuel projection area in overload condition; l a For measuring the highest point of the oil, the sum of the overload space vectors intersects the position of the lower wall plate of the oil tank structure; l b For measuring oil level is 0, overload space vector sum and the position of the intersection with the lower wall of the tank structure; l c D is the distance between the front spar and the rear spar at the station where the wing rib is located; l is the distance of the wing rib angle piece from the front beam.

4. The method of claim 1, wherein: The wing rib angle piece fuel pressure calculation formula is: , In the formula, P is the fuel pressure of the wing rib angle piece, p is the fuel density, g is the gravitational acceleration, n is the combined overload coefficient of the aircraft, and h is the oil level at the wing rib angle piece.

5. A device for calculating fuel tank wing rib corner piece fuel pressure, characterized by, The method comprises the following steps: a plane construction module is configured to obtain the overloads of the aircraft in each direction under a certain overload state, obtain the sum of the spatial vectors of the overloads based on the overloads in each direction, and determine a plane perpendicular to the sum of the spatial vectors of the overloads; an oil level calculation module is configured to intercept the fuel projection area based on the plane to obtain the fuel projection area under the overload state, and determine the oil level based on the fuel projection area under the overload state; a fuel pressure calculation module is configured to construct a wing rib angle piece fuel pressure calculation formula based on the oil level, and calculate the fuel pressure of the wing rib angle piece of the fuel tank of the aircraft under a combined overload state according to the wing rib angle piece fuel pressure calculation formula.

6. The fuel tank stringer corbel fuel pressure calculation device of claim 5, wherein, When the fuel projection area is intercepted based on the plane, the fuel projection area under the overload state remains unchanged from the fuel projection area under the non-overload state.

7. The fuel tank sponson corner piece fuel pressure calculation device of claim 6, wherein, The oil liquid level calculation method is: , In the formula, h is the oil level at the wing rib angle piece; h max Maximum oil level calculated for fuel projection area in overload condition; l a For measuring the highest point of the oil, the sum of the overload space vectors intersects the position of the lower wall plate of the oil tank structure; l b For measuring oil level is 0, overload space vector sum and the position of the intersection with the lower wall of the tank structure; l c D is the distance between the front spar and the rear spar at the station where the wing rib is located; l is the distance of the wing rib angle piece from the front beam.

8. The fuel tank stringer corbel fuel pressure calculation device of claim 5, wherein, The wing rib angle piece fuel pressure calculation formula is: , In the formula, P is the fuel pressure of the wing rib angle piece, p is the fuel density, g is the gravitational acceleration, n is the combined overload coefficient of the aircraft, and h is the oil level at the wing rib angle piece.

9. An electronic device, comprising: The method comprises the following steps: one or more processors; a memory; one or more application programs stored in the memory and configured to be executed by the one or more processors, the one or more application programs being configured to implement the calculation method of the fuel pressure of the wing rib angle piece of the fuel tank as claimed in any one of claims 1-4.

10. A computer-readable storage medium, characterized in that, The computer readable storage medium stores at least one instruction, at least one program, a code set or an instruction set, which is loaded and executed by the processor to implement the calculation method of the fuel pressure of the wing rib angle piece of the fuel tank as claimed in any one of claims 1-4.

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