Aircraft suspension structure and method for calculating load thereof

Abstract

The application provides an aircraft suspension structure load calculation method, and belongs to the technical field of aircraft structure strength calculation. The method comprises the following steps: determining the connection form of the aircraft suspension structure, establishing a simplified mechanical model of the aircraft suspension structure, and determining the load of the front joint, the rear joint, the left pull rod and the right pull rod according to the connection form of the aircraft suspension 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 the components of the aircraft suspension structure. The load balance equation and the distance balance equation of the aircraft suspension structure are established according to the load, the position parameters and the simplified mechanical model of the components. The load of each component in three directions is obtained by solving the load balance equation and the distance balance equation, and then the total load of each component in three directions is calculated, which is the load of the aircraft suspension structure. The load of the aircraft suspension structure can be quickly obtained.

Description

Technical Field

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

[0002] The aircraft pylon structure is the sole connection between the engine and the aircraft body. It primarily bears the engine's inertial loads, thrust, and reverse thrust, and transmits these loads to the aircraft body. Engine thrust is primarily transmitted through pylon joints and tie rods. Damage to these joints can seriously compromise flight safety.

[0003] Existing technology typically calculates aircraft suspension structure loads using finite element models. While this approach achieves sufficient accuracy, the calculation process requires individual components and bolts to be calculated, resulting in complex and inefficient calculations. If the 3D solid model of the engine connection area were incorporated into the full aircraft model for a complete solution, the overall solution would be prohibitively large. Summary of the Invention

[0004] The purpose of this 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 this application is: a method for calculating the load of an aircraft suspension structure, comprising:

[0006] Determining a connection form of an aircraft suspension structure and establishing 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 various components of the aircraft suspension structure;

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

[0009] Solving the force balance equation and the distance balance equation yields the loads on each component in three directions, and then calculating the total load on each component in three directions. This total load is the load on the aircraft's 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 are respectively connected to the front and rear ends of the upper side of the engine and 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 embodiment of the present application, the process of establishing the simplified mechanical model of the aircraft suspension structure is as follows:

[0012] Construct a coordinate system with the engine's center of gravity G as the origin, the aircraft's heading as the X-axis, the horizontal direction perpendicular to the aircraft's heading as the Y-axis, and the longitudinal direction perpendicular to the aircraft's 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, and is recorded as point A, point B, point C1 and point C2 respectively.

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

[0017] The heading distance X between the engine center of gravity point G and the front joint point A 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 embodiment 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] Where, 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 embodiment 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 embodiment of the present application, the loads on 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 solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this 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, this 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 pylon structure and establishing a simplified mechanical model of the aircraft pylon structure.

[0053] Figure 2 shows a schematic diagram of the connection form of the aircraft suspension structure in this application. 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 respectively connect the front and rear ends of the upper side of the engine 7 to the engine load-bearing structure. The left tie rod 3 connects 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 connects to the right side of the engine 7 and is connected to the engine load-bearing structure through the right tie rod joint 6. The connection points of the left and right tie rods with the engine 7 are coplanar with the connection point of the front joint 1 with the engine 7, and this 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, construct a coordinate system with the center of gravity G of engine 7 as the origin, the aircraft heading as the X-axis, the horizontal direction perpendicular to the aircraft heading as the Y-axis, and the longitudinal direction perpendicular to the aircraft heading as the Z-axis;

[0056] S12, simplify the engine 7 into a rigid body, with the center of gravity of the engine 7 as point G. The front joint 1, rear joint 2, left tie rod 3, and right tie rod 5 are each simplified to a point, 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, rear joint, and left and right tie rods according to the connection form of the aircraft suspension structure, and determining the position parameters of the front joint, rear joint, and tie rods according to the geometric positions of the components in the aircraft suspension structure.

[0058] Combine Figure 2 and Figure 3As shown, based on the aircraft pylon structure's connection configuration, point A at the front joint 1 bears the axial and lateral loads, point B at the rear joint 2 bears the lateral and vertical loads, and point C1 at the left tie rod 3 and point C2 at the right tie rod 5 bear the vertical load. Based on the aircraft pylon structure's geometric position, the distances between the front joint 1, rear joint 2, and left and right tie rods and the engine's center of gravity G, including the axial, lateral, and vertical distances, as well as the angles between the left and right tie rods and the Z axis, can be determined.

[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 rods are symmetrical, F C1Z =F C2Z (4)

[0066] Where, 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 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 at 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 the calculation object, and the aircraft suspension structure load calculation method of the present application is described in more detail.

[0079] First, 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 center of gravity 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 aircraft heading as the Y-axis, and the longitudinal direction perpendicular to the aircraft 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 0mm and vertical distance Z GB The distance between the engine's 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, 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 description is merely a specific embodiment of the present application, but the scope of protection of the present application is not limited thereto. Any changes or substitutions that can be easily conceived by a person skilled in the art within the technical scope disclosed in this application should be included in the scope of protection of the present application. Therefore, the scope of protection of the present application should be based on the scope of protection of the claims.

Claims

1. A method for calculating aircraft suspension structure load, characterized in that: include: Determining a connection form of an aircraft suspension structure and establishing 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. The process includes: constructing a coordinate system 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; simplifying the engine into a rigid body, and simplifying the front joint, the rear joint, and the left tie rod and the right tie rod into a point, respectively, located at the intersection of each structure and the engine, and denoted as point A, point B, point C1, and point C2, respectively; The loads of the front joint, rear joint, left tie rod and right tie rod are determined according to the connection form of the aircraft suspension structure. The loads of the front joint, rear joint, left tie rod and right tie rod include the heading 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. The position parameters of the front joint, rear joint, left tie rod and right tie rod are determined according to the geometric positions of the components of the aircraft suspension structure. The position parameters of the front joint, rear joint, left tie rod and right tie rod include: the heading distance X between the engine center of gravity point G and the front joint point A; 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 ; The force balance equation and moment balance equation of the aircraft suspension structure are established based on the load, position parameters and simplified mechanical model of each component. 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 Where, 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 is the vertical load at the two tie rods; The moment 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; Solving the force balance equation and the moment balance equation yields the loads of each component in three directions, and then calculating the total load of each component in three directions. This total load is the load of the aircraft suspension structure.

2. The aircraft suspension structure load calculation method according to claim 1, 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. The front joint and the rear joint are respectively connected to the front and rear ends of the upper side of the engine and 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. 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 aircraft suspension structure load calculation method according to claim 2, wherein: The loads of the components in three directions are: F AX =-F GX 4. The aircraft suspension structure load calculation method according to claim 3, wherein: 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.

5. 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 4.

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