Aircraft hanging structure and load calculation method thereof

Abstract

The invention provides an airplane hanging structure load calculation method, and belongs to the technical field of airplane structure strength calculation, the method comprises the following steps: determining a connection form of an airplane hanging structure, establishing a simplified mechanical model of the airplane hanging structure, the airplane hanging structure comprising a front joint, a rear joint, a left pull rod, a right pull rod, a left pull rod joint and a right pull rod joint; determining the loads of the front joint, the rear joint, the left pull rod and the right pull rod according to the connection form of the airplane hanging structure, and determining the position parameters of the front joint, the rear joint, the left pull rod and the right pull rod according to the geometric positions of all the parts of the airplane hanging structure; establishing a force balance equation and a distance balance equation of the aircraft hanging structure according to the load and position parameters of each component and the simplified mechanical model; and solving the force balance equation and the distance balance equation to obtain the load of each component in three directions, and further calculating the total load of each component in three directions, which is the load of the machine hanging structure. According to the invention, the load of the airplane hanging structure can be rapidly obtained.

Description

Technical Field

[0001] The present application belongs to the field of aircraft structure strength calculation, and in particular relates to an aircraft suspension structure and a load calculation method thereof. Background Art

[0002] The aircraft suspension structure is the only connection between the engine and the aircraft body. It mainly bears the engine inertia load, thrust and reverse thrust load, and transmits the load to the body. The engine thrust is mainly transmitted by the suspension joint and tie rod. Once the suspension joint is damaged, it will seriously endanger flight safety.

[0003] In the prior art, the load of aircraft suspension structure is generally calculated by finite element model. Although the accuracy meets the use requirements, the calculation process requires that each part and bolt must be calculated, which is complicated and inefficient. If the three-dimensional solid model of the engine connection area is brought into the whole aircraft model for whole aircraft solution, the scale of the whole aircraft model solution will be extremely large. Summary of the invention

[0004] The purpose of the present application is to provide an aircraft suspension structure and a load calculation method thereof to solve or alleviate at least one problem in the background technology.

[0005] The technical solution of the present application is: a method for calculating the load of an aircraft suspension structure, comprising:

[0006] Determine the connection form of the aircraft suspension structure, and establish a simplified mechanical model of the aircraft suspension structure, wherein the aircraft suspension structure includes a front joint, a rear joint, a left tie rod, a right tie rod, a left tie rod joint, and a right tie rod joint;

[0007] Determine the loads of the front joint, rear joint, left tie rod and right tie rod according to the connection form of the aircraft suspension structure, and determine the position parameters of the front joint, rear joint, left tie rod and right tie rod according to the geometric positions of the components of the aircraft suspension structure;

[0008] The force balance equation and distance balance equation of the aircraft suspension structure are established according to the load, position parameters and simplified mechanical model of each component;

[0009] The force balance equation and the distance balance equation are solved to obtain the loads of each component in three directions, and then the total load of each component in three directions is calculated. The total load is the load of the aircraft suspension structure.

[0010] In an optional embodiment of the present application, the aircraft suspension structure includes a front joint, a rear joint, a left tie rod, a right tie rod, a left tie rod joint and a right tie rod joint, the front joint and the rear joint respectively connect the front and rear ends of the upper side of the engine to the engine load-bearing structure, the left tie rod is connected to the left side of the engine and is connected to the engine load-bearing structure through the left tie rod joint, the right tie rod is connected to the right side of the engine and is connected to the engine load-bearing structure through the right tie rod joint, wherein the connection points of the left tie rod, the right tie rod and the engine and the connection point of the front joint and the engine are coplanar and the plane is perpendicular to the engine axis.

[0011] In an optional implementation manner of the present application, the process of establishing the simplified mechanical model of the aircraft suspension structure is as follows:

[0012] A coordinate system is constructed with the engine center of gravity G as the origin, the aircraft heading as the X-axis, the horizontal direction perpendicular to the fuselage heading as the Y-axis, and the longitudinal direction perpendicular to the fuselage heading as the Z-axis;

[0013] The engine is simplified into a rigid body, and the front joint, rear joint, left tie rod and right tie rod are simplified into a point respectively. The point is located at the intersection of each structure and the engine, which are respectively recorded as point A, point B, point C1 and point C2.

[0014] In an optional embodiment of the present application, the loads of the front joint, the rear joint, the left tie rod and the right tie rod include:

[0015] The axial load and lateral load borne by point A of the front joint, the lateral load and vertical load borne by point B of the rear joint, and the vertical load borne by point C1 of the left tie rod and point C2 of the right tie rod.

[0016] In an optional implementation manner of the present application, the position parameters of the front joint, the rear joint, the left tie rod and the right tie rod include:

[0017] The heading distance between the engine center of gravity point G and the front joint point A is X GA , lateral distance Y GA and vertical distance Z GA ;

[0018] The heading distance X between the engine center of gravity point G and the rear joint point B GB , lateral distance Y GB and vertical distance Z GB ;

[0019] The heading distance X between the engine center of gravity point G and the left tie rod point C1 and the right tie rod point C2 GC1 and X GC2 , lateral distance Y GC1 and Y GC2 , vertical distance Z GC1 and Z GC2 .

[0020] In an optional implementation manner of the present application, the force balance equation is:

[0021] F GX +F AX =0

[0022] F GY +F AY +F BY =0

[0023] F GZ +F BZ +F C1Z +F C2Z =0

[0024] F C1Z =F C2Z

[0025] In the formula, F GX 、F GY 、F GZ is the load in three directions at the engine center of gravity, F AX 、F AY is the heading load and lateral load at the front joint, F BY 、F BZ is the lateral load and vertical load at the rear joint, F C1Z 、F C2Z are the vertical loads at the two tie rods.

[0026] In an optional implementation manner of the present application, the distance balance equation is:

[0027] F GY ×X GA +F BY ×(X GA +X GB )=0

[0028] F GZ ×X GB +F C1Z ×(X GA +X GB )+F C2Z ×(X GA +X GB )=0.

[0029] In an optional implementation manner of the present application, the loads of the components in three directions are:

[0030] F AX =-F GX

[0031]

[0032] In an optional embodiment of the present application, the total load of each component in three directions is

[0033]

[0034] Among them, F A is the total load at the front joint, F B is the total load at the rear joint, F C1 、F C2 are the total loads at the two rods, and α is the angle between the rod and the Y axis.

[0035] Finally, the present application also provides an aircraft suspension structure, which is calculated using any of the above-mentioned aircraft suspension structure load calculation methods.

[0036] The method of the present application can quickly obtain the load of the aircraft suspension structure, and the calculation accuracy meets engineering requirements, which can significantly shorten the calculation time and improve the calculation efficiency. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present application.

[0038] Figure 1 Schematic diagram of the method of this application.

[0039] Figure 2 This is a schematic diagram of the aircraft suspension structure connection form in this application.

[0040] Figure 3 This is a schematic diagram of the simplified model of the aircraft suspension structure mechanics in this application.

[0041] Reference numerals:

[0042] 1-Front connector

[0043] 2-Rear connector

[0044] 3-Left lever

[0045] 4-Left tie rod joint

[0046] 5-Right lever

[0047] 6-Right tie rod joint

[0048] 7-Engine DETAILED DESCRIPTION

[0049] In order to make the purpose, technical solutions and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below in conjunction with the drawings in the embodiments of this application.

[0050] In order to solve the technical problems of complex process and low calculation efficiency in the current calculation of aircraft suspension joints, the present application provides a calculation method that can quickly and accurately obtain the aircraft suspension joint load to meet engineering needs, thereby significantly shortening the calculation time and improving the calculation efficiency.

[0051] like Figure 1 As shown, the aircraft suspension structure load calculation method provided in this application includes the following process:

[0052] Step S10, determining the connection form of the aircraft suspension structure and establishing a simplified mechanical model of the aircraft suspension structure.

[0053] As shown in Figure 2, it is a schematic diagram of the connection form of the aircraft suspension structure in the present application, and the aircraft suspension structure includes a front joint 1, a rear joint 2, a left tie rod 3, a right tie rod 5, a left tie rod joint 4, and a right tie rod joint 6. The front joint 1 and the rear joint 2 are respectively connected to the front and rear ends of the upper side of the engine 7 and the engine load-bearing structure, the left tie rod 3 is connected to the left side of the engine 7 and is connected to the engine load-bearing structure through the left tie rod joint 4, the right tie rod 5 is connected to the right side of the engine 7 and is connected to the engine load-bearing structure through the right tie rod joint 6, and the connection points of the left and right tie rods with the engine 7 and the connection points of the front joint 1 with the engine 7 are coplanar, and the plane is perpendicular to the engine axis.

[0054] like Figure 3 As shown, the process of establishing a simplified mechanical model of the aircraft suspension structure in this application is as follows:

[0055] S11, constructing a coordinate system with the center of gravity G of the engine 7 as the origin, the heading of the aircraft as the X-axis, the horizontal direction perpendicular to the heading of the fuselage as the Y-axis, and the longitudinal direction perpendicular to the heading of the fuselage as the Z-axis;

[0056] S12, simplify the engine 7 into a rigid body, the center of gravity of the engine 7 is point G, the front joint 1, the rear joint 2, the left tie rod 3, and the right tie rod 5 are simplified to a point respectively, which is located at the intersection of each structure and the engine, and is recorded as point A, point B, point C1 and point C2 respectively.

[0057] Step S20, determining the loads of the front joint, the rear joint and the left and right tie rods according to the connection form of the aircraft suspension structure, and determining the position parameters of the front joint, the rear joint and the tie rods according to the geometric positions of the components in the aircraft suspension structure.

[0058] Combination Figure 2 and Figure 3As shown, according to the connection form of the aircraft suspension structure, it can be determined that point A at the front joint 1 bears the heading load and lateral load, point B at the rear joint 2 bears the lateral load and vertical load, and point C1 at the left tie rod 3 and point C2 at the right tie rod 5 bear the vertical load. According to the geometric position of the aircraft suspension structure, the distances between the front joint 1, the rear joint 2 and the left and right tie rods and the center of gravity G of the engine can be determined, including the heading distance, lateral distance and vertical distance and the angles between the left and right tie rods and the Z axis.

[0059] Step S30, establishing a force balance equation and a distance balance equation of the aircraft suspension structure according to the loads and position parameters of each component and a simplified mechanical model.

[0060] In the simplified mechanical model of the aircraft suspension structure of the present application, the engine center of gravity point G is the external load application point, and points A, B, C1 and C2 are constraint points, among which point A constrains the heading and lateral direction, point B constrains the lateral direction and vertical direction, and the pull rod points C1 and C2 constrain the vertical direction.

[0061] In this application, the force balance equation is:

[0062] F GX +F AX =0 (1)

[0063] F GY +F AY +F BY =0 (2)

[0064] F GZ +F BZ +F C1Z +F C2Z =0 (3)

[0065] Since the two tie rods are symmetrical, therefore: F C1Z =F C2Z (4)

[0066] In the formula, F GX 、F GY 、F GZ is the load in three directions at the engine center of gravity, F AX 、F AY is the heading load and lateral load at the front joint, F BY 、F BZ is the lateral load and vertical load at the rear joint, F C1Z 、F C2Z are the vertical loads at the two tie rods.

[0067] In this application, the distance balance equation is:

[0068] F GY ×X GA +FBY ×(X GA +X GB )=0 (5)

[0069] F GZ ×X GB +F C1Z ×(X GA +X GB )+F C2Z ×(X GA +X GB )=0. (6)

[0070] Step S40, solving the force balance equation and the distance balance equation of the aircraft suspension structure to obtain the loads in the three directions of the front joint, the rear joint and the pull rod, and calculating the total load of the loads in the three directions of the front joint, the rear joint and the pull rod. The total load is the load of the aircraft suspension structure.

[0071] In this application, the constraint reaction forces at points A, B, C1 and C2 are solved to obtain the loads at each point. By combining formulas (1) to (6), we can obtain:

[0072] F AX =-F GX (7)

[0073]

[0074] According to the constraint reaction force of each point obtained in the above steps, the total load of each point can be obtained:

[0075]

[0076] Among them, F A is the total load at the front joint, F B is the total load at the rear joint, F C1 、F C2 are the total loads at the two rods, and α is the angle between the rod and the Y axis.

[0077] The method of the present application can quickly obtain the load of the aircraft suspension structure, and the calculation accuracy meets engineering requirements, which can significantly shorten the calculation time and improve the calculation efficiency.

[0078] The following Figure 2 The aircraft suspension structure shown is a calculation object, and the aircraft suspension structure load calculation method of the present application is described in more detail.

[0079] Firstly, according to the connection form of the aircraft suspension structure, the following Figure 3 The simplified mechanical model shown in the figure, where points A, B, C1 and C2 are constraint points, the engine gravity center point G is the loading point, point A constrains the heading and lateral direction, point B constrains the vertical and lateral direction, and points C1 and C2 constrain the vertical direction;

[0080] Then, a coordinate system is established with point G as the origin, the aircraft heading as the X-axis, the horizontal direction perpendicular to the fuselage heading as the Y-axis, and the longitudinal direction perpendicular to the fuselage heading as the Z-axis;

[0081] Then determine the heading distance X between the engine center of gravity point G and the front joint point A GA 1000mm, lateral distance Y GA 0mm and vertical distance Z GA 1500mm; the heading distance between the engine center of gravity point G and the rear joint point B is X GB 2000mm, lateral distance Y GB is 0mm and the vertical distance Z GB 2000mm; the heading distance between the engine center of gravity point G and the left tie rod point C1 and the right tie rod point C2 is X GC1 1000mm and X GC2 1000mm, lateral distance Y GC1 300mm and Y GC2 300mm, vertical distance Z GC1 500mm and Z GC2 500mm;

[0082] Then, according to the force balance equations (1) to (4), the loads F in three directions at the center of gravity of the engine are calculated: GX 、F GY 、F GZ They are 200000N, 30000N and 120000N respectively; combined with the distance balance equation, we can get:

[0083] F AX =-F GX =-200000N

[0084]

[0085] Finally, the constraint reaction force at each point is obtained according to equations (12) to (14), and the total load at each point can be obtained:

[0086]

[0087] Among them, F A is the total load at the front joint, F B is the total load at the rear joint, F C1 、F C2 are the total loads at the two tie rods respectively, and α is the angle between the tie rod and the Y axis, which is 60°.

[0088] On this basis, the present application also provides an aircraft suspension structure, which is calculated using the aircraft suspension structure load calculation method mentioned above in the present application.

[0089] 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 method for calculating aircraft suspension structure load, characterized in that: include: Determine the connection form of the aircraft suspension structure, and establish a simplified mechanical model of the aircraft suspension structure, wherein the aircraft suspension structure includes a front joint, a rear joint, a left tie rod, a right tie rod, a left tie rod joint, and a right tie rod joint; Determine the loads of the front joint, rear joint, left tie rod and right tie rod according to the connection form of the aircraft suspension structure, and determine the position parameters of the front joint, rear joint, left tie rod and right tie rod according to the geometric positions of the components of the aircraft suspension structure; The force balance equation and distance balance equation of the aircraft suspension structure are established according to the load, position parameters and simplified mechanical model of each component; The force balance equation and the distance balance equation are solved to obtain the loads of each component in three directions, and then the total load of each component in three directions is calculated. The total load is the load of the aircraft suspension structure.

2. The aircraft suspension structure load calculation method according to claim 1, characterized in that: The aircraft suspension structure includes a front joint, a rear joint, a left tie rod, a right tie rod, a left tie rod joint and a right tie rod joint, wherein the front joint and the rear joint respectively connect the front and rear ends of the upper side of the engine with the engine load-bearing structure, the left tie rod is connected to the left side of the engine and is connected to the engine load-bearing structure through the left tie rod joint, and the right tie rod is connected to the engine load-bearing structure through the right tie rod joint, wherein the connection points of the left tie rod, the right tie rod and the engine and the connection point of the front joint and the engine are coplanar, and the plane is perpendicular to the engine axis.

3. The method for calculating the aircraft suspension structure load according to claim 2, characterized in that: The process of establishing the simplified mechanical model of the aircraft suspension structure is as follows: A coordinate system is constructed with the engine center of gravity G as the origin, the aircraft heading as the X-axis, the horizontal direction perpendicular to the fuselage heading as the Y-axis, and the longitudinal direction perpendicular to the fuselage heading as the Z-axis; The engine is simplified into a rigid body, and the front joint, rear joint, left tie rod and right tie rod are simplified into a point respectively. The point is located at the intersection of each structure and the engine, which are respectively recorded as point A, point B, point C1 and point C2.

4. The method for calculating the aircraft suspension structure load according to claim 3, characterized in that: The loads of the front joint, rear joint, left tie rod and right tie rod include: The axial load and lateral load borne by point A of the front joint, the lateral load and vertical load borne by point B of the rear joint, and the vertical load borne by point C1 of the left tie rod and point C2 of the right tie rod.

5. The aircraft suspension structure load calculation method according to claim 4, characterized in that: The position parameters of the front joint, rear joint, left tie rod and right tie rod include: The heading distance between the engine center of gravity point G and the front joint point A is X GA , lateral distance Y GA and vertical distance Z GA ; The heading distance X between the engine center of gravity point G and the rear joint point B GB , lateral distance Y GB and vertical distance Z GB ; The heading distance X between the engine center of gravity point G and the left tie rod point C1 and the right tie rod point C2 GC1 and X GC2 , lateral distance Y GC1 and Y GC2 , vertical distance Z GC1 and Z GC2 .

6. The method for calculating the aircraft suspension structure load according to claim 5, characterized in that: The force balance equation is: F GX +F AX =0 F GY +F AY +F BY =0 F GZ +F BZ +F C1Z +F C2Z =0 F C1Z =F C2Z In the formula, F GX 、F GY 、F GZ is the load in three directions at the engine center of gravity, F AX 、F AY is the heading load and lateral load at the front joint, F BY 、F BZ is the lateral load and vertical load at the rear joint, F C1Z 、F C2Z are the vertical loads at the two tie rods.

7. The method for calculating the aircraft suspension structure load according to claim 6, characterized in that: The distance balance equation is: F GY ×X GA +F BY ×(X GA +X GB )=0 F GZ ×X GB +F C1Z ×(X GA +X GB )+F C2Z ×(X GA +X GB )=0。 8. The method for calculating the aircraft suspension structure load according to claim 7, characterized in that: The loads of the components in three directions are: F AX =-F GX 9. The method for calculating the aircraft suspension structure load according to claim 8, characterized in that: The total load of each component in three directions is Among them, F A is the total load at the front joint, F B is the total load at the rear joint, F C1 、F C2 are the total loads at the two rods, and α is the angle between the rod and the Y axis.

10. An aircraft hanging structure, characterized in that: The aircraft suspension structure is calculated using the aircraft suspension structure load calculation method described in any one of claims 1 to 9.

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