A method for screening test load conditions of an integrated aircraft flap antenna structure

Abstract

The application relates to a kind of integrated aircraft flap antenna structure test load working condition screening methods, comprising: step one, the finite element model of integrated aircraft flap antenna structure is established;Step two, various flight load working conditions are applied, and the finite element analysis is carried out on integrated aircraft flap antenna structure;Step three, based on the finite element analysis result of integrated aircraft flap antenna structure, the strength screening is carried out on flight load working condition;Step four, based on the finite element analysis result of integrated aircraft flap antenna structure, the stiffness screening is carried out on flight load working condition;Step five, the strength serious working condition of integrated aircraft flap antenna structure, stiffness serious working condition, take the set, and obtain test load working condition.

Description

Technical Field

[0001] This application belongs to the field of aircraft structural strength testing, specifically involving a method for screening test load conditions for an integrated aircraft flap antenna structure. Background Technology

[0002] From takeoff and climb to cruise, glide, and landing, an aircraft is constantly subjected to flight loads. Based on the requirements of various aircraft maneuvers, calculations are performed on combinations of weight, center of gravity, moment of inertia, speed, altitude, and other factors, resulting in thousands of flight load conditions.

[0003] Test load conditions are specific combinations of loads and boundary conditions set to verify structural strength, stiffness, and fatigue life. The determination process follows a logical chain of "design load → test load → test condition". To meet engineering feasibility and cost control requirements, only dozens to hundreds of key conditions can be selected for testing. Through statistical analysis, load envelope compression, and screening of the "most dangerous combination", the infinitely diverse flight environment is condensed into a finite number of repeatable, monitorable, and loadable standardized test scenarios, achieving the engineering goal of "verifying the infinite with the finite".

[0004] Determining the test load conditions for integrated aircraft flap antenna structures is a core aspect of their strength testing, directly impacting the reliability of the structural design and flight safety. A pressing issue is how to quickly select a limited set of test load conditions from thousands of flight load conditions to guide the strength physical testing and virtual test load design of integrated aircraft flap antenna structures, ensuring the structure meets strength verification requirements while reducing workload. Therefore, this application is submitted. Summary of the Invention

[0005] The purpose of this application is to provide a method for screening test load conditions for integrated aircraft flap antenna structures, which can guide the design of strength physical tests and virtual test loads for integrated aircraft flap antenna structures, ensure that the structure meets the strength verification requirements, and reduce workload.

[0006] The technical solution of this application is:

[0007] A method for screening test load conditions for an integrated aircraft flap antenna structure, comprising:

[0008] Step 1: Establish a finite element model of the integrated aircraft flap antenna structure;

[0009] Step 2: Apply various flight load conditions and perform finite element analysis on the integrated aircraft flap antenna structure;

[0010] Step 3: Based on the finite element analysis results of the integrated aircraft flap antenna structure, strength screening is performed for flight load conditions:

[0011] Select the maximum stress or strain of each material structure in the aircraft structure;

[0012] For each material structure, the maximum stress or strain is divided by the allowable value of the material minus one to obtain the safety margin.

[0013] The union of the flight load conditions corresponding to the minimum safety margin of each material structure is taken as the severe strength condition of the aircraft structure.

[0014] Step 4: Based on the finite element analysis results of the integrated aircraft flap antenna structure, stiffness selection is performed for flight load conditions:

[0015] The maximum deformation of the integrated aircraft flap antenna structure was selected.

[0016] Select the maximum torsion angle of the integrated aircraft flap antenna structure;

[0017] The union of the flight load conditions corresponding to the maximum deformation and maximum torsion angle of the integrated aircraft flap antenna structure is taken as the severe stiffness condition of the integrated aircraft flap antenna structure.

[0018] Step 5: Take the union of the severe strength and severe stiffness conditions of the integrated aircraft flap antenna structure to obtain the test load conditions.

[0019] Optionally, in the above-mentioned method for screening test load conditions of integrated aircraft flap antenna structure, in step one, quadrilateral and triangular units are used for multifunctional skin, reflector, network mounting plate and structural reinforcing beam; the gradient absorbing structure is divided into tetrahedral units; and the conformal antenna is divided into tetrahedral units.

[0020] Optionally, in the above-mentioned method for screening test load conditions for integrated aircraft flap antenna structure, in step two, based on the finite element model, accurate boundary conditions are applied to constrain the integrated aircraft flap antenna structure, and then various flight load conditions are applied to perform finite element linear analysis and eliminate local stress concentration elements.

[0021] Optionally, in the above-mentioned method for screening test load conditions for integrated aircraft flap antenna structures, step three involves selecting the maximum stress or strain of each material structure within the integrated aircraft flap antenna structure:

[0022] For cellular structures, select the maximum stress, including compressive stress, L-direction shear compressive stress, and W-direction shear stress;

[0023] For composite material structures, the maximum strain is selected, including tensile strain, compressive strain, and shear strain;

[0024] For adhesive layer structures, the maximum stress is selected, including the maximum shear stress, the maximum peel stress, and the maximum tensile stress.

[0025] Optionally, in the above-mentioned method for screening test load conditions of integrated aircraft flap antenna structure, in step four, the maximum deformation of the integrated aircraft flap antenna structure is selected, including the maximum deformation of upward bending and the maximum deformation of downward bending.

[0026] The maximum torsion angle of the integrated aircraft flap antenna structure is selected, including the maximum positive torsion angle and the maximum negative torsion angle.

[0027] Optionally, in the above-mentioned method for screening test load conditions of integrated aircraft flap antenna structure, in step five, the total force and total moment of the severe strength and stiffness conditions of the integrated aircraft flap antenna structure are calculated, and conditions with similar ratios of total force and total moment are merged, and the condition with the larger total load is selected as representative.

[0028] This application has at least the following beneficial technical effects:

[0029] This paper presents a method for screening test load conditions for integrated aircraft flap antenna structures. This method can quickly select severe conditions as representative from thousands of flight load conditions, thereby reducing the load conditions required for testing and verifying integrated aircraft flap antenna structures. It can reduce workload and improve design efficiency while ensuring that the structure meets strength requirements. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the test load condition screening method for the integrated aircraft flap antenna structure provided in the embodiments of this application;

[0031] Figure 2 This is a schematic diagram illustrating the strength screening of load conditions provided in an embodiment of this application;

[0032] Figure 3 This is a schematic diagram of stiffness screening for load conditions provided in an embodiment of this application.

[0033] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0034] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0035] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0036] A method for screening test load conditions for an integrated aircraft flap antenna structure, such as... Figure 1 As shown, the load conditions of the integrated aircraft flap antenna structure under severe loads are screened. The load conditions selected by the strength screening method and the stiffness screening method are combined and the total force and total moment are calculated. Load conditions with similar ratios of total force and total moment are merged and the load condition with the larger total load is selected as the representative of the other similar load conditions to obtain the test load conditions.

[0037] Step 1: Establish a finite element model of the integrated aircraft flap antenna structure.

[0038] The multifunctional skin, reflector, network mounting plate, and structural reinforcement beams adopt quadrilateral and triangular units; the gradient absorbing structure has complex structural features and is divided into tetrahedral units; the conformal antenna is divided into tetrahedral units; the adhesive interface and adhesive layer thickness are established between the various structures to connect them.

[0039] Step 2: Apply various flight load conditions and perform finite element analysis on the integrated aircraft flap antenna structure.

[0040] Based on the finite element model, accurate boundary conditions are applied to constrain the integrated aircraft flap antenna structure. Then, various flight load conditions are applied, and finite element linear analysis is performed to eliminate local stress concentration elements.

[0041] Step 3: Based on the finite element analysis results of the integrated aircraft flap antenna structure, strength screening is performed on the flight load conditions, such as... Figure 2 As shown:

[0042] Select the maximum stress or strain of each material structure in the integrated aircraft flap antenna structure:

[0043] For cellular structures, select the maximum stress, including compressive stress, L-direction shear compressive stress, W-direction shear stress, etc.

[0044] For composite material structures, the maximum strain is selected, including tensile strain, compressive strain, shear strain, etc.

[0045] For adhesive layer structures, the maximum stress is selected, including the maximum shear stress, maximum peel stress, and maximum tensile stress.

[0046] The maximum stress or strain of each material structure is divided by the allowable value of the material minus one, and then normalized to obtain a safety margin for comparison.

[0047] The union of the flight load conditions corresponding to the minimum safety margin of each material structure is taken as the severe strength condition of the integrated aircraft flap antenna structure.

[0048] Step 4: Based on the finite element analysis results of the integrated aircraft flap antenna structure, stiffness screening is performed for flight load conditions, such as... Figure 3 As shown:

[0049] The maximum deformation of the integrated aircraft flap antenna structure was selected, including the maximum deformation when bending upwards and the maximum deformation when bending downwards.

[0050] The maximum torsion angle of the integrated aircraft flap antenna structure is selected, including the maximum positive torsion angle and the maximum negative torsion angle.

[0051] The union of the flight load conditions corresponding to the maximum deformation and maximum torsion angle of the integrated aircraft flap antenna structure is taken as the severe stiffness condition of the integrated aircraft flap antenna structure.

[0052] Step 5: Take the union of the severe strength and severe stiffness conditions of the integrated aircraft flap antenna structure to obtain the test load conditions.

[0053] The total force and total moment of the integrated aircraft flap antenna structure under severe strength and stiffness conditions can be further calculated. Load conditions with similar ratios of total force and total moment can be merged, and the condition with the larger total load can be selected as the representative of the other similar conditions.

[0054] The integrated aircraft flap antenna structure test load condition screening method disclosed in the above embodiments can quickly screen out severe conditions from thousands of flight load conditions for representative conditions. This can reduce the load conditions for integrated aircraft flap antenna structure test verification, and reduce workload and improve design efficiency while ensuring the structure meets strength requirements.

[0055] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A method for screening test load conditions for an integrated aircraft flap antenna structure, characterized in that, include: Step 1: Establish a finite element model of the integrated aircraft flap antenna structure; Step 2: Apply various flight load conditions and perform finite element analysis on the integrated aircraft flap antenna structure; Step 3: Based on the finite element analysis results of the integrated aircraft flap antenna structure, strength screening is performed for flight load conditions: Select the maximum stress or strain of each material structure in the aircraft structure; For each material structure, the maximum stress or strain is divided by the allowable value of the material minus one to obtain the safety margin. The union of the flight load conditions corresponding to the minimum safety margin of each material structure is taken as the severe strength condition of the aircraft structure. Step 4: Based on the finite element analysis results of the integrated aircraft flap antenna structure, stiffness selection is performed for flight load conditions: The maximum deformation of the integrated aircraft flap antenna structure was selected. Select the maximum torsion angle of the integrated aircraft flap antenna structure; The union of the flight load conditions corresponding to the maximum deformation and maximum torsion angle of the integrated aircraft flap antenna structure is taken as the severe stiffness condition of the integrated aircraft flap antenna structure. Step 5: Take the union of the severe strength and severe stiffness conditions of the integrated aircraft flap antenna structure to obtain the test load conditions.

2. The method for screening test load conditions for the integrated aircraft flap antenna structure according to claim 1, characterized in that, In step one, quadrilateral and triangular units are used for the multifunctional skin, reflector, network mounting plate and structural reinforcement beam; the gradient absorbing structure is divided into tetrahedral units; and the conformal antenna is divided into tetrahedral units.

3. The method for screening test load conditions for the integrated aircraft flap antenna structure according to claim 2, characterized in that, In step two, based on the finite element model, accurate boundary conditions are applied to constrain the integrated aircraft flap antenna structure. Then, various flight load conditions are applied, and finite element linear analysis is performed to eliminate local stress concentration elements.

4. The method for screening test load conditions for the integrated aircraft flap antenna structure according to claim 3, characterized in that, In step three, the maximum stress or strain of each material structure in the integrated aircraft flap antenna structure is selected: For cellular structures, select the maximum stress, including compressive stress, L-direction shear compressive stress, and W-direction shear stress; For composite material structures, the maximum strain is selected, including tensile strain, compressive strain, and shear strain; For adhesive layer structures, the maximum stress is selected, including the maximum shear stress, the maximum peel stress, and the maximum tensile stress.

5. The method for screening test load conditions for the integrated aircraft flap antenna structure according to claim 4, characterized in that, In step four, the maximum deformation of the integrated aircraft flap antenna structure is selected, including the maximum deformation of the upward bend and the maximum deformation of the downward bend. The maximum torsion angle of the integrated aircraft flap antenna structure is selected, including the maximum positive torsion angle and the maximum negative torsion angle.

6. The method for screening test load conditions for the integrated aircraft flap antenna structure according to claim 5, characterized in that, In step five, the total force and total moment of the integrated aircraft flap antenna structure under severe strength and severe stiffness conditions are calculated. Conditions with similar ratios of total force and total moment are merged, and the condition with the larger total load is selected as representative.

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