Attachment joint arrangement optimization method and system for aircraft aileron control surface

Abstract

The invention belongs to the field of aircraft aileron control surface structure design, and particularly relates to an aircraft aileron control surface connection joint arrangement optimization method and system, and the method comprises the steps: dividing an aircraft aileron control surface into a plurality of subareas according to the plane where each connection joint is located; establishing a finite element model of the aileron control surface based on the shell unit, determining load distribution borne by the aileron control surface, and establishing constraint conditions of a connection joint; calculating the stress-strain distribution and displacement of the aileron control surface in a steady state, and extracting the maximum deformation value of each subarea; minimizing the difference between the maximum deformation values of the partitions as an optimization target, taking the position parameter of the plane where the connection joint is located as an optimization variable, and adopting a genetic algorithm to carry out optimization solution to obtain the optimal position parameter of the plane where the connection joint is located.

Description

Technical Field

[0001] This application belongs to the field of aircraft aileron control surface structure design, and specifically relates to a method and system for optimizing the arrangement of connecting joints of aircraft aileron control surfaces. Background Technology

[0002] Ailerons are lateral control surfaces located on either side of the wing's trailing edge. Their function is to provide sufficient rolling moment to ensure the aircraft's lateral controllability. Ailerons are typically connected to the fixed trailing edge of the wing via joints. By changing the placement of these joints, the stress characteristics of the aileron structure can be improved, its load-bearing capacity enhanced, material utilization increased, and its weight reduced. Currently, the placement of aileron joints often employs empirical methods or multi-support beam planar optimization methods. Empirical methods struggle to maximize material utilization, and multi-support beam planar optimization methods neglect the load distribution caused by the control airfoil, failing to achieve optimal design of the aileron control surface joint. Summary of the Invention

[0003] To address the aforementioned problems, this application provides a method for optimizing the arrangement of connection joints on aircraft aileron control surfaces, including:

[0004] Step S101: Establish a geometric model based on the shape of the aircraft aileron control surface, the shape including skin, tail edge, inner end rib, outer end rib, front spars and leading edge;

[0005] Step S102: Determine the number of connecting joints installed on the aircraft aileron control surface, determine the position parameters of the plane where each connecting joint is located, and divide the aircraft aileron control surface into multiple zones according to the plane where each connecting joint is located.

[0006] Step S103: Establish a finite element model of the aileron control surface based on shell elements, and parameterize the material properties of each component of the aileron control surface;

[0007] Step S104: Determine the load distribution on the aileron control surface and establish the constraint conditions at the connection joint;

[0008] Step S105: Calculate the stress-strain distribution and displacement of the aileron control surface under steady state, and extract the maximum deformation value of each partition;

[0009] Step S106: Establish an optimization equation with the goal of minimizing the difference between the maximum deformation values ​​of each partition;

[0010] Step S107: Using the plane position parameters of the connection joint as optimization variables, a genetic algorithm is used to optimize and solve the problem, and the optimal plane position parameters of the connection joint are obtained.

[0011] Preferably, the number of connecting joints is determined based on the aileron control surface size and load requirements, ranging from 2 to 6.

[0012] Preferably, the positional parameters of the plane containing each connecting joint include: the distance λ1 between the first connecting joint and the inner end rib, the distance λ2 between the second connecting joint and the inner end rib, and the distance λn between the nth connecting joint and the inner end rib. n , where n is the number of connection joints.

[0013] Preferably, the finite element modeling in step S103 includes:

[0014] The shell-unit discrete aileron control surface structure is adopted;

[0015] Parametric material thickness, including skin thickness, beam thickness, trailing edge thickness, inner and outer end rib thickness; joint connection plane thickness;

[0016] Assign material parameters to each component, including elastic modulus, Poisson's ratio, and density.

[0017] Preferably, the method for calculating the difference between the maximum deformation values ​​of each partition is as follows:

[0018] Calculate the difference between the maximum deformation values ​​of any two partitions, and then sum the differences.

[0019] Preferably, the load constraint application in step S104 includes:

[0020] The load distribution is determined based on flight conditions, including aerodynamic loads and inertial loads;

[0021] Constraints are applied at the connection joint to simulate the connection between the joint and the fixed trailing edge of the wing.

[0022] Establish multiple load conditions, including ultimate load and fatigue load conditions.

[0023] Preferably, the method for determining the maximum deformation value of a partition includes:

[0024] Static analysis was performed using finite element method software.

[0025] Extract the maximum deformation values ​​of the partitions: d1, d2, ..., d n ₊1, the deformation value is calculated based on the mesh node displacement; where d n The maximum deformation value is the point of maximum deformation at which the aileron control surface is divided into partitions by the plane containing the nth connection joint and the plane containing the n-1th connection joint before and after the application of load.

[0026] Preferably, the expression for minimizing the difference between the maximum deformation values ​​of each partition is:

[0027] .

[0028] Preferably, the method further includes step S108, applying the optimized joint arrangement to the detailed design, performing strength verification and weight assessment to ensure that the design requirements are met.

[0029] An aircraft aileron control surface connection joint arrangement optimization system is used to implement the aforementioned aircraft aileron control surface connection joint arrangement optimization method, comprising:

[0030] Geometric modeling module: used to create the geometric model of the aileron control surfaces;

[0031] Finite element analysis module: used for mechanical analysis;

[0032] Optimization Algorithm Module: Used to perform genetic algorithm optimization;

[0033] Results output module: Used to generate optimization reports and drawings.

[0034] Preferably, the system is integrated into a product lifecycle management platform and supports data exchange with CAD / CAE software.

[0035] The arrangement of the aileron control surface joints affects the load-bearing capacity, weight distribution, and handling efficiency of the aircraft control surfaces. Based on the finite element method and genetic algorithm, optimizing the arrangement of the aileron control surface joints can improve the load-bearing capacity of the aircraft's aileron control surfaces, reduce their weight, and improve fuel efficiency. Attached Figure Description

[0036] Figure 1 This is a schematic diagram of the shape of an aircraft aileron control surface according to a general invention.

[0037] Figure 2 It is a geometric model of the aileron control surface based on parameterization in this general invention.

[0038] Figure 3 This is a finite element model of the aileron control surface based on shell elements in this general invention.

[0039] Figure 4 This is an optimization process for the arrangement of aileron control surface connection joints established based on genetic algorithms and finite element methods in this general invention. Detailed Implementation

[0040] 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. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some embodiments of this application, not all embodiments. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain this application, and should not be construed as limiting this application. All other embodiments obtained by those skilled in the art based on the embodiments in this application without creative effort are within the scope of protection of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings. A method for optimizing the arrangement of connecting joints on an aircraft aileron control surface: including:

[0041] Based on the required shape of the aileron control surfaces, including the skin, trailing edge, inner end ribs, outer end ribs, front spars, and leading edge, such as... Figure 1 As shown;

[0042] The shape of the aircraft control surfaces is imported into the finite element software. The plane containing the aileron control surface connection joint is then established parametrically. The joint plane position parameters are obtained using... By intersecting the shape of this plane with that of the aileron control surface, the connecting surface of the aileron control surface is created;

[0043] Assign corresponding material parameters and shell thickness to the skin, trailing edge, inner end rib, outer end rib, control surface connection surface, and beam of the aileron control surface;

[0044] Establish the constraint equations for the aileron control surface at the control surface connection surface, and establish the load conditions for the aileron control surface;

[0045] Divide the aileron control surfaces into grids and determine the appropriate grid size and type;

[0046] Solve for the stress-strain distribution and displacement of the aileron control surface under different load conditions in steady state;

[0047] Extract the maximum displacement of the trailing edge between the planes containing different connection joint surfaces. ; where d n The maximum deformation value is the point of maximum deformation at which the aileron control surface is divided into partitions by the plane containing the nth connection joint and the plane containing the n-1th connection joint before and after the application of load.

[0048] Based on the stiffness design principles of aircraft aileron control surface structures, the objectives for optimizing the planar joints of different connections are determined as follows: ;

[0049] Based on the optimization parameters Combine optimization objectives By incorporating these parameters into the genetic algorithm, the optimal parameters that can achieve the optimal objective are obtained step by step, thus yielding the optimal arrangement of the aircraft aileron control surface connection joints.

[0050] 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 for optimizing the arrangement of connecting joints on aircraft aileron control surfaces, characterized in that, include: Step S101: Establish a geometric model based on the shape of the aircraft aileron control surface, the shape including skin, tail edge, inner end rib, outer end rib, front spars and leading edge; Step S102: Determine the number of connecting joints installed on the aircraft aileron control surface, determine the position parameters of the plane where each connecting joint is located, and divide the aircraft aileron control surface into multiple zones according to the plane where each connecting joint is located. Step S103: Establish a finite element model of the aileron control surface based on shell elements, and parameterize the material properties of each component of the aileron control surface; Step S104: Determine the load distribution on the aileron control surface and establish the constraint conditions at the connection joint; Step S105: Calculate the stress-strain distribution and displacement of the aileron control surface under steady state, and extract the maximum deformation value of each partition; Step S106: Establish an optimization equation with the goal of minimizing the difference between the maximum deformation values ​​of each partition; Step S107: Using the plane position parameters of the connection joint as optimization variables, a genetic algorithm is used to optimize and solve the problem, and the optimal plane position parameters of the connection joint are obtained.

2. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that: The number of connection joints is determined based on the aileron control surface size and load requirements, ranging from 2 to 6.

3. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, The positional parameters of the plane containing each connector include: the distance λ1 between the first connector and the inner end rib, the distance λ2 between the second connector and the inner end rib, and the distance λ3 between the nth connector and the inner end rib. n , where n is the number of connection joints.

4. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, The finite element modeling described in step S103 includes: The shell-unit discrete aileron control surface structure is adopted; Parametric material thickness, including skin thickness, beam thickness, trailing edge thickness, inner and outer end rib thickness; joint connection plane thickness; Assign material parameters to each component, including elastic modulus, Poisson's ratio, and density.

5. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, The method for calculating the difference in maximum deformation values ​​between different zones is as follows: Calculate the difference between the maximum deformation values ​​of any two partitions, and then sum the differences.

6. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, The application of load constraints in step S104 includes: The load distribution is determined based on flight conditions, including aerodynamic loads and inertial loads; Constraints are applied at the connection joint to simulate the connection between the joint and the fixed trailing edge of the wing. Establish multiple load conditions, including ultimate load and fatigue load conditions.

7. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, Methods for determining the maximum deformation value of a partition include: Static analysis was performed using finite element method software. Extract the maximum deformation values ​​of the partitions: d1, d2, ..., d n ₊1, the deformation value is calculated based on the mesh node displacement; where d n The maximum deformation value is the point of maximum deformation at which the aileron control surface is divided into partitions by the plane containing the nth connection joint and the plane containing the n-1th connection joint before and after the application of load.

8. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 7, characterized in that, The expression for minimizing the difference between the maximum deformation values ​​of each partition is: 。 9. The method for optimizing the arrangement of connecting joints on aircraft aileron control surfaces as described in claim 1, characterized in that, The method further includes step S108, applying the optimized joint layout to the detailed design, performing strength verification and weight assessment to ensure that the design requirements are met.

10. An aircraft aileron control surface connection joint arrangement optimization system, used to implement the aircraft aileron control surface connection joint arrangement optimization method as described in any one of claims 1-9, characterized in that, include: Geometric modeling module: used to create the geometric model of the aileron control surfaces; Finite element analysis module: used for mechanical analysis; Optimization Algorithm Module: Used to perform genetic algorithm optimization; Results output module: Used to generate optimization reports and drawings.

11. The aircraft aileron control surface connection joint arrangement optimization system as described in claim 1, characterized in that, The aircraft aileron control surface connection joint arrangement optimization system as described in claim 13 is characterized in that the system is integrated into a product lifecycle management platform and supports data exchange with CAD / CAE software.

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