Aircraft strength test fuselage compensation loading method

Abstract

The invention belongs to the field of airplane structure strength tests, and particularly relates to a fuselage compensation loading method for an airplane strength test. The method comprises the following steps: acquiring fuselage deformation and lateral loading point mounting dimensions under different load values; the deflection angle of a lateral loading force line is calculated according to the fuselage deformation and the installation size of the lateral loading point; calculating a new lateral load instruction according to an original lateral load instruction and the deflection angle; calculating a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle; and according to the new lateral load instruction and the new vertical load instruction, applying the airplane strength test fuselage load. According to the method, the vertical and lateral load values are adjusted according to the fuselage deformation data and the geometric installation size of the loading point, and the problem that the loading precision is reduced due to lateral loading force line deflection can be solved.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure strength testing, and in particular relates to a fuselage compensation loading method for aircraft strength testing. Background Art

[0002] In the aircraft structure strength test, vertical loads and lateral loads need to be applied to the fuselage structure at the same time under multiple load conditions. When the fuselage stiffness is relatively small, a large vertical deformation will usually occur. At this time, since the front end of the lateral loading point is connected to the aircraft and the rear end is fixed to the load-bearing structure, the loading force line will deflect with the deformation of the fuselage, and then the lateral load will produce a vertical component, affecting the vertical and lateral loading accuracy.

[0003] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0004] The purpose of the present application is to provide a fuselage compensation loading method for aircraft strength testing to solve at least one problem existing in the prior art.

[0005] The technical solution of this application is:

[0006] A fuselage compensation loading method for aircraft strength test, comprising:

[0007] Obtain the fuselage deformation and the installation dimensions of the lateral loading points under different load values;

[0008] Calculating the deflection angle of the lateral load force line according to the fuselage deformation and the installation size of the lateral loading point;

[0009] Calculating a new lateral load instruction according to the original lateral load instruction and the deflection angle;

[0010] Calculating a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle;

[0011] The fuselage load of the aircraft strength test is applied according to the new lateral load instruction and the new vertical load instruction.

[0012] In at least one embodiment of the present application, the deflection angle of the side load force line is calculated according to the deformation of the fuselage and the installation size of the side load point, including:

[0013] The deflection angle of the lateral load force line is:

[0014] α=arctan(h / L)

[0015] Among them, α is the deflection angle, h is the deformation of the fuselage, and L is the installation size of the lateral loading point.

[0016] In at least one embodiment of the present application, calculating a new lateral load instruction according to the original lateral load instruction and the deflection angle includes:

[0017] The new side load instructions are:

[0018] F0'=F0 / cosα

[0019] Among them, F0' is the new lateral load instruction, and F0 is the original lateral load instruction.

[0020] In at least one embodiment of the present application, calculating a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle includes:

[0021] Calculating a new vertical load component according to the new lateral load instruction and the deflection angle;

[0022] The new vertical load component is superimposed on the original vertical load instruction to obtain a new vertical load instruction.

[0023] In at least one embodiment of the present application, calculating a new vertical load component according to the new lateral load instruction and the deflection angle includes:

[0024] The new vertical load components are:

[0025] F 1分 '=F0'×sinα

[0026] Among them, F 1分 ' is the new vertical load component.

[0027] In at least one embodiment of the present application, the new vertical load component is superimposed on the original vertical load instruction to obtain a new vertical load instruction, including:

[0028] The new vertical load instructions are:

[0029] F1'=F1+F 1分 '

[0030] Right now:

[0031] F1'=F1+F0'×sinα

[0032] Among them, F1' is the new vertical load instruction.

[0033] The invention has at least the following beneficial technical effects:

[0034] The aircraft strength test fuselage compensation loading method of the present application can be used to apply fuselage loads in aircraft strength tests. The vertical and lateral load values ​​are adjusted according to the fuselage deformation data and the geometric installation dimensions of the loading point, which can eliminate the problem of reduced loading accuracy caused by the deflection of the lateral loading force line. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] Figure 1 It is a schematic diagram of fuselage compensation loading for an aircraft strength test according to one embodiment of the present application. DETAILED DESCRIPTION

[0036] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0037] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0038] The following is combined with Figure 1 This application is described in further detail.

[0039] The present application provides a fuselage compensation loading method for aircraft strength test, comprising the following steps:

[0040] Obtain the fuselage deformation and the installation dimensions of the lateral loading points under different load values;

[0041] According to the deformation of the fuselage and the installation dimensions of the lateral loading point, the deflection angle of the lateral load force line is calculated;

[0042] A new lateral load instruction is calculated according to the original lateral load instruction and the deflection angle;

[0043] Calculate a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle;

[0044] The fuselage loads are applied in the aircraft strength test according to the new lateral load instructions and the new vertical load instructions.

[0045] The aircraft strength test fuselage compensation loading method of the present application calculates the deflection angle α of the lateral load force line under different load values ​​according to the fuselage deformation h and the installation size L of the lateral loading point. Figure 1 The relationship between the various parameters shown in the figure can be obtained:

[0046] The deflection angle α of the lateral load force line is:

[0047] α=arctan(h / L)

[0048] Among them, α is the deflection angle, h is the deformation of the fuselage, and L is the installation size of the lateral loading point.

[0049] The aircraft strength test fuselage compensation loading method of the present application, after obtaining the deflection angle α, calculates a new lateral load instruction F0' according to the original lateral load instruction F0 and the deflection angle α, including:

[0050] The original lateral load instruction F0 is divided by the cosine value of the current deflection angle α, and the load value obtained is used as the new lateral load point instruction F0'. The new lateral load instruction F0' is:

[0051] F0'=F0 / cosα

[0052] Among them, F0' is the new lateral load instruction, and F0 is the original lateral load instruction.

[0053] The aircraft strength test fuselage compensation loading method of the present application calculates a new vertical load instruction according to a new lateral load instruction, an original vertical load instruction and a deflection angle, including:

[0054] According to the new lateral load instruction and the deflection angle, the new vertical load component is calculated;

[0055] The new vertical load component is superimposed on the original vertical load instruction to obtain a new vertical load instruction.

[0056] Specifically, the new lateral load point instruction F0' is multiplied by the sine value of the current deflection angle α to obtain the new vertical load component F 1分 ', then the new vertical load component F 1分 'for:

[0057] F 1分 '=F0'×sinα

[0058] Among them, F 1分 ' is the new vertical load component.

[0059] The new vertical load component F 1分 ' is superimposed with the original vertical load instruction F1 to obtain a new vertical load instruction F1', then the new vertical load instruction F1' is:

[0060] F1'=F1+F 1分 '

[0061] Right now:

[0062] F1'=F1+F0'×sinα

[0063] Among them, F1' is the new vertical load instruction.

[0064] The aircraft strength test fuselage compensation loading method of the present application adjusts the vertical and lateral load values ​​according to the fuselage deformation data and the geometric installation dimensions of the loading point, so as to achieve accurate application of the fuselage load.

[0065] The aircraft strength test fuselage compensation loading method of the present application has the following beneficial effects:

[0066] a) By using this method to load the fuselage, the accuracy of the lateral and vertical loads can be guaranteed under large vertical deformation of the fuselage;

[0067] b) This loading method does not require any additional hardware investment;

[0068] c) This loading method does not generate additional test risks;

[0069] d) The method is simple in principle and has certain universality.

[0070] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A fuselage compensation loading method for aircraft strength test, characterized in that: include: Obtain the fuselage deformation and the installation dimensions of the lateral loading points under different load values; Calculating the deflection angle of the lateral load force line according to the fuselage deformation and the installation size of the lateral loading point; Calculating a new lateral load instruction according to the original lateral load instruction and the deflection angle; Calculating a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle; The fuselage load of the aircraft strength test is applied according to the new lateral load instruction and the new vertical load instruction.

2. The aircraft strength test fuselage compensation loading method according to claim 1, characterized in that: According to the deformation of the fuselage and the installation size of the lateral loading point, the deflection angle of the lateral load force line is calculated, including: The deflection angle of the lateral load force line is: α=arctan(h / L) Among them, α is the deflection angle, h is the deformation of the fuselage, and L is the installation size of the lateral loading point.

3. The aircraft strength test fuselage compensation loading method according to claim 2 is characterized in that: According to the original lateral load instruction and the deflection angle, a new lateral load instruction is calculated, including: The new side load instructions are: F0′=F0 / cosα Among them, F0' is the new lateral load instruction, and F0 is the original lateral load instruction.

4. The aircraft strength test fuselage compensation loading method according to claim 3 is characterized in that: Calculating a new vertical load instruction according to the new lateral load instruction, the original vertical load instruction and the deflection angle includes: Calculating a new vertical load component according to the new lateral load instruction and the deflection angle; The new vertical load component is superimposed on the original vertical load instruction to obtain a new vertical load instruction.

5. The aircraft strength test fuselage compensation loading method according to claim 4, characterized in that: According to the new lateral load instruction and the deflection angle, a new vertical load component is calculated, including: The new vertical load components are: F 1分 ′=F0′×sinα Among them, F 1分 ' is the new vertical load component.

6. The aircraft strength test fuselage compensation loading method according to claim 5, characterized in that: The new vertical load component is superimposed on the original vertical load instruction to obtain a new vertical load instruction, including: The new vertical load instructions are: F1′=F1+F 1分 ′ Right now: F1′=F1+F0′×sinα Among them, F1' is the new vertical load instruction.

Images