A method for designing a single-double lug joint structure parameter in an aircraft landing gear

Abstract

The application belongs to the technical field of single-double lug joint parameter design in airplane landing gear, and particularly relates to a single-double lug joint structure parameter design method in airplane landing gear, which comprises the following steps: determining structure optimization parameters of the single-double lug joint and upper and lower limits thereof; calculating a target mass of the single-double lug joint based on the structure optimization parameters; calculating an optimization strength margin of the single-double lug joint based on the structure optimization parameters; under the condition that the optimization strength margin is greater than a constraint strength margin, seeking structure optimization parameters that minimize the target mass within the upper and lower limits of the structure optimization parameters as structure design parameters; normalizing the structure design parameters to obtain structure processing parameters; calculating a final strength margin of the single-double lug joint based on the structure processing parameters, and re-normalizing the structure design parameters when the final strength margin is less than the constraint strength margin.

Description

Technical Field

[0001] This application belongs to the technical field of single and double lug joint parameter design in aircraft landing gear, and specifically relates to a method for designing structural parameters of single and double lug joints in aircraft landing gear. Background Technology

[0002] Aircraft landing gear uses single and double lug joints for connection, mainly including single lug, double lug, pin, and bushing. The single lug and double lug are connected by a pin, and the bushing is set between the single lug, double lug and pin.

[0003] The single and double lug joints in aircraft landing gear are subjected to complex loads. In order to ensure that they can meet the strength requirements, the design parameters of each structure are generally conservative, resulting in a large overall volume and mass, which does not meet the current needs of aircraft weight reduction.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a method for designing structural parameters of single and double lug joints in aircraft landing gear, so as to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] A method for designing structural parameters of single and double lug joints in aircraft landing gear, comprising:

[0009] The width of the single earpiece of a single- or double-ear connector The thickness of a single earlobe The width of the earlobe The thickness of the earlobes , Single and double ear gap on one side g, inner diameter of ear plate Bushing thickness h, pin inner diameter As structural optimization parameters, determine the upper and lower limits of the structural optimization parameters;

[0010] Target mass of single and double ear connectors is calculated based on structural optimization parameters;

[0011] Calculate the optimized strength margin of single and double lug joints based on structural optimization parameters;

[0012] Under the condition that the optimization strength margin is greater than the constraint strength margin, within the upper and lower limits of the structural optimization parameters, find the structural optimization parameters that minimize the target mass and use them as structural design parameters.

[0013] The structural design parameters are regularized to obtain the structural fabrication parameters;

[0014] The final strength margin of the single and double lug joint is calculated based on the structural processing parameters. When the final strength margin is less than the constraint strength margin, the structural design parameters are readjusted.

[0015] Specifically, the target mass of the single / double lug connector is calculated based on structural optimization parameters as follows:

[0016] ;

[0017] ;

[0018] ;

[0019] ;

[0020] in,

[0021] The target quality for single and double ear connectors;

[0022] The target quality for a single ear;

[0023] The target quality for both ears;

[0024] The target quality for the pin;

[0025] This is the mass amplification factor for a single ear;

[0026] Density of a single ear;

[0027] The mass amplification factor for both ears;

[0028] The density of both ears;

[0029] This is the mass amplification factor for the pin shaft;

[0030] The density of the pins; the optimized strength margin of the single and double lug joints is calculated based on structural optimization parameters, including:

[0031] Calculate the tensile optimization stress margin for a single ear:

[0032] A single ear is subjected to axial tensile load. ;

[0033] A single ear is subjected to an oblique tensile load. ;

[0034] ;

[0035] ;

[0036] ;

[0037] ;

[0038] When a single ear is made of aluminum alloy, , ;

[0039] When a single ear is made of steel, , ;

[0040] When a single ear is made of other materials, , ;

[0041] in,

[0042] Optimize the stress margin for tensile stress in a single ear;

[0043] The form factor for a single ear subjected to axial tensile load;

[0044] This represents the tensile strength limit for a single ear.

[0045] The material coefficient for a single ear subjected to axial tensile load;

[0046] A special coefficient for single-ear stretching;

[0047] This represents the maximum tensile stress experienced by a single ear.

[0048] The efficiency coefficient for a single ear subjected to an oblique tensile load;

[0049] The material coefficient is given for a single ear subjected to an oblique tensile load.

[0050] For single and double lug connectors;

[0051] The angle at which a single ear is subjected to an oblique tensile load;

[0052] Calculate the optimal compressive stress margin for a single ear:

[0053] ;

[0054] ;

[0055] in,

[0056] Optimize stress margin for single-ear compression;

[0057] This represents the single-ear compressive strength limit.

[0058] A special coefficient for single-ear compression;

[0059] This represents the maximum compressive stress experienced by a single ear.

[0060] Calculate the tensile optimization stress margin for both ears:

[0061] Both ears are subjected to axial tensile load. ;

[0062] Both ears are subjected to an oblique tensile load. ;

[0063] ;

[0064] ;

[0065] ;

[0066] ;

[0067] When the ears are made of aluminum alloy, , ;

[0068] When the ears are made of steel, , ;

[0069] When the ears are made of other materials, , ;

[0070] in,

[0071] Optimize the stress margin for the stretching of both ears;

[0072] The shape factor for the two ears subjected to axial tensile load;

[0073] The tensile strength limit for both ears;

[0074] The material coefficient for both ears subjected to axial tensile load;

[0075] A special coefficient for the stretching of both ears;

[0076] This represents the maximum tensile stress experienced by both ears;

[0077] The efficiency coefficient for both ears subjected to oblique tensile load;

[0078] The material coefficient is given for both ears subjected to oblique tensile load.

[0079] For single and double lug connectors;

[0080] The angle at which both ears are subjected to an oblique tensile load;

[0081] Calculate the optimal compressive stress margin for both ears:

[0082] ;

[0083] ;

[0084] in,

[0085] Optimize the stress margin for compression of both ears;

[0086] This represents the maximum compressive strength of both ears;

[0087] A special coefficient for bilateral ear compression;

[0088] This represents the maximum compressive stress experienced by both ears.

[0089] Calculate the optimal stress margin for pin bending:

[0090] ;

[0091] ;

[0092] ;

[0093] ;

[0094] ;

[0095] in,

[0096] Optimize stress margin for pin bending;

[0097] The tensile strength limit of the pin;

[0098] This is a special coefficient for pin bending;

[0099] This represents the maximum bending stress experienced by the pin bearing.

[0100] This represents the maximum bending moment experienced by the pin bearing.

[0101] The moment of inertia of the pin section;

[0102] The lever arm of the pin bending moment;

[0103] Calculate the optimal stress margin for pin shear optimization:

[0104] ;

[0105] ;

[0106] ;

[0107] When the pin has a circular cross-section, ;

[0108] When the pin has a circular cross-section ;

[0109] in,

[0110] Optimize stress margin for pin shearing;

[0111] This is the shear coefficient for the pin; it equals 1 when the pin is solid and 0.975 when the pin is hollow.

[0112] The shear strength limit of the pin;

[0113] The stress concentration factor of the pin shaft section;

[0114] This is the special shear coefficient for the pin shaft;

[0115] This represents the maximum shear stress experienced by the pin.

[0116] Let be the cross-sectional area of ​​the pin.

[0117] Calculate the optimal stress margin for pin extrusion:

[0118] ;

[0119] ;

[0120] in,

[0121] Optimize stress margin for pin extrusion;

[0122] The limit of the compressive strength of the pin;

[0123] This refers to the special extrusion coefficient for the pin shaft;

[0124] This represents the maximum compressive stress experienced by the pin. Attached Figure Description

[0125] Figure 1 This is a schematic diagram of the design method for the structural parameters of single and double lug joints in aircraft landing gear provided in the embodiments of this application;

[0126] Figure 2 This is a schematic diagram of a single / double lug connector in an aircraft landing gear according to an embodiment of this application;

[0127] Figure 3 This is a schematic diagram of the force analysis of the single and double lug joints in the aircraft landing gear provided in the embodiments of this application.

[0128] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual size of the product. Furthermore, the accompanying drawings are for illustrative purposes only and should not be construed as limiting this patent. Detailed Implementation

[0129] 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. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0130] 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 terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0131] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0132] The following is in conjunction with the appendix Figures 1 to 3 This application will be described in further detail.

[0133] A method for designing structural parameters of single and double lug joints in aircraft landing gear, comprising:

[0134] The width of the single earpiece of a single- or double-ear connector The thickness of a single earlobe The width of the earlobe The thickness of the earlobes , Single and double ear gap on one side g, inner diameter of ear plate Bushing thickness h, pin inner diameter As structural optimization parameters, determine the upper and lower limits of the structural optimization parameters;

[0135] Target mass of single and double ear connectors is calculated based on structural optimization parameters;

[0136] Calculate the optimized strength margin of single and double lug joints based on structural optimization parameters;

[0137] Under the condition that the optimization strength margin is greater than the constraint strength margin, within the upper and lower limits of the structural optimization parameters, find the structural optimization parameters that minimize the target mass and use them as structural design parameters.

[0138] The structural design parameters are regularized to obtain the structural processing parameters, so as to facilitate processing in engineering.

[0139] The final strength margin of the single and double lug joint is calculated based on the structural processing parameters. When the final strength margin is less than the constraint strength margin, the structural design parameters are readjusted.

[0140] Specifically, the target mass of the single / double lug connector is calculated based on structural optimization parameters as follows:

[0141] ;

[0142] ;

[0143] ;

[0144] ;

[0145] in,

[0146] The target quality for single and double ear connectors;

[0147] The target quality for a single ear;

[0148] The target quality for both ears;

[0149] The target quality for the pin;

[0150] This is the mass amplification factor for a single ear;

[0151] Density of a single ear;

[0152] The mass amplification factor for both ears;

[0153] The density of both ears;

[0154] This is the mass amplification factor for the pin shaft;

[0155] The density of the pins; the optimized strength margin of the single and double lug joints is calculated based on structural optimization parameters, including:

[0156] Calculate the tensile optimization stress margin for a single ear:

[0157] A single ear is subjected to axial tensile load. ;

[0158] A single ear is subjected to an oblique tensile load. ;

[0159] ;

[0160] ;

[0161] ;

[0162] ;

[0163] When a single ear is made of aluminum alloy, , ;

[0164] When a single ear is made of steel, , ;

[0165] When a single ear is made of other materials, , ;

[0166] in,

[0167] Optimize the stress margin for tensile stress in a single ear;

[0168] The form factor for a single ear subjected to axial tensile load;

[0169] This represents the tensile strength limit for a single ear.

[0170] The material coefficient for a single ear subjected to axial tensile load;

[0171] A special coefficient for single-ear stretching;

[0172] This represents the maximum tensile stress experienced by a single ear.

[0173] The efficiency coefficient for a single ear subjected to an oblique tensile load;

[0174] The material coefficient is given for a single ear subjected to an oblique tensile load.

[0175] For single and double lug connectors;

[0176] The angle at which a single ear is subjected to an oblique tensile load;

[0177] Calculate the optimal compressive stress margin for a single ear:

[0178] ;

[0179] ;

[0180] in,

[0181] Optimize stress margin for single-ear compression;

[0182] This represents the single-ear compressive strength limit.

[0183] A special coefficient for single-ear compression;

[0184] This represents the maximum compressive stress experienced by a single ear.

[0185] Calculate the tensile optimization stress margin for both ears:

[0186] Both ears are subjected to axial tensile load. ;

[0187] Both ears are subjected to an oblique tensile load. ;

[0188] ;

[0189] ;

[0190] ;

[0191] ;

[0192] When the ears are made of aluminum alloy, , ;

[0193] When the ears are made of steel, , ;

[0194] When the ears are made of other materials, , ;

[0195] in,

[0196] Optimize the stress margin for the stretching of both ears;

[0197] The shape factor for the two ears subjected to axial tensile load;

[0198] The tensile strength limit for both ears;

[0199] The material coefficient for both ears subjected to axial tensile load;

[0200] A special coefficient for the stretching of both ears;

[0201] This represents the maximum tensile stress experienced by both ears;

[0202] The efficiency coefficient for both ears subjected to oblique tensile load;

[0203] The material coefficient is given for both ears subjected to oblique tensile load.

[0204] For single and double lug connectors;

[0205] The angle at which both ears are subjected to an oblique tensile load;

[0206] Calculate the optimal compressive stress margin for both ears:

[0207] ;

[0208] ;

[0209] in,

[0210] Optimize the stress margin for compression of both ears;

[0211] This represents the maximum compressive strength of both ears;

[0212] A special coefficient for bilateral ear compression;

[0213] This represents the maximum compressive stress experienced by both ears.

[0214] Calculate the optimal stress margin for pin bending:

[0215] ;

[0216] ;

[0217] ;

[0218] ;

[0219] ;

[0220] in,

[0221] Optimize stress margin for pin bending;

[0222] The tensile strength limit of the pin;

[0223] This is a special coefficient for pin bending;

[0224] This represents the maximum bending stress experienced by the pin bearing.

[0225] This represents the maximum bending moment experienced by the pin bearing.

[0226] The moment of inertia of the pin section;

[0227] The lever arm of the pin bending moment;

[0228] Calculate the optimal stress margin for pin shear optimization:

[0229] ;

[0230] ;

[0231] ;

[0232] When the pin has a circular cross-section, ;

[0233] When the pin has a circular cross-section ;

[0234] in,

[0235] Optimize stress margin for pin shearing;

[0236] This is the shear coefficient for the pin; it equals 1 when the pin is solid and 0.975 when the pin is hollow.

[0237] The shear strength limit of the pin;

[0238] The stress concentration factor of the pin shaft section;

[0239] This is the special shear coefficient for the pin shaft;

[0240] This represents the maximum shear stress experienced by the pin.

[0241] Let be the cross-sectional area of ​​the pin.

[0242] Calculate the optimal stress margin for pin extrusion:

[0243] ;

[0244] ;

[0245] in,

[0246] Optimize stress margin for pin extrusion;

[0247] The limit of the compressive strength of the pin;

[0248] This refers to the special extrusion coefficient for the pin shaft;

[0249] This represents the maximum compressive stress experienced by the pin.

[0250] Regarding the structural parameter design method for single and double lug joints in aircraft landing gear disclosed in the above embodiments, those skilled in the art will understand that, under the condition that the optimized strength margin is greater than the constraint strength margin, the design seeks structural optimization parameters that minimize the target mass within the upper and lower limits of the structural optimization parameters, and uses these as structural design parameters. The structural design parameters are then regularized to obtain structural processing parameters. Based on the structural processing parameters, the final strength margin of the single and double lug joint is calculated. When the final strength margin is less than the constraint strength margin, the structural design parameters are readjusted until the final strength margin is greater than the constraint strength margin. This allows for rapid iterative design of the parameters for single and double lug joints in aircraft landing gear, ensuring that they meet strength requirements while having a relatively small volume and mass.

[0251] In a specific embodiment, the structural parameter design conditions for the single / double lug joint in the aircraft landing gear are as follows:

[0252]

[0253] The design method for single and double lug joint structures in aircraft landing gear disclosed in the above embodiments was used, and the results are compared as follows:

[0254]

[0255] As can be seen from the above, by using the structural parameter design method for single and double lug joints in aircraft landing gear disclosed in the above embodiments, the resulting structural processing parameters can reduce the mass of the single and double lug joints from 16.32 to 13.10 while ensuring strength, which is beneficial for reducing the weight of the aircraft.

[0256] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0257] 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 designing structural parameters of single and double lug joints in aircraft landing gear, characterized in that, include: The width of the single earpiece of a single- or double-ear connector The thickness of a single earlobe The width of the earlobe The thickness of the earlobes , Single and double ear gap on one side g, inner diameter of ear plate Bushing thickness h, pin inner diameter As structural optimization parameters, determine the upper and lower limits of the structural optimization parameters; Target mass of single and double ear connectors is calculated based on structural optimization parameters; Calculate the optimized strength margin of single and double lug joints based on structural optimization parameters; Under the condition that the optimization strength margin is greater than the constraint strength margin, within the upper and lower limits of the structural optimization parameters, find the structural optimization parameters that minimize the target mass and use them as structural design parameters. The structural design parameters are regularized to obtain the structural fabrication parameters; The final strength margin of the single and double lug joint is calculated based on the structural processing parameters. When the final strength margin is less than the constraint strength margin, the structural design parameters are readjusted. in, The target mass of the single and double lug connectors is calculated based on structural optimization parameters, specifically: ； ； ； ； in, The target quality for single and double ear connectors; The target quality for a single ear; The target quality for both ears; The target quality for the pin; This is the mass amplification factor for a single ear; Density of a single ear; The mass amplification factor for both ears; The density of both ears; This is the mass amplification factor for the pin shaft; The density of the pin; The optimized strength margin of single and double lug joints is calculated based on structural optimization parameters, including: Calculate the tensile optimization stress margin for a single ear: A single ear is subjected to axial tensile load. ; A single ear is subjected to an oblique tensile load. ; ； ； ； ； When a single ear is made of aluminum alloy, , ; When a single ear is made of steel, , ; When a single ear is made of other materials, , ; in, Optimize the stress margin for tensile stress in a single ear; The form factor for a single ear subjected to axial tensile load; This represents the tensile strength limit for a single ear. The material coefficient for a single ear subjected to axial tensile load; A special coefficient for single-ear stretching; This represents the maximum tensile stress experienced by a single ear. The efficiency coefficient for a single ear subjected to an oblique tensile load; The material coefficient is given for a single ear subjected to an oblique tensile load. For single and double lug connectors; The angle at which a single ear is subjected to an oblique tensile load; Calculate the optimal compressive stress margin for a single ear: ； ； in, Optimize stress margin for single-ear compression; This represents the single-ear compressive strength limit. A special coefficient for single-ear compression; This represents the maximum compressive stress experienced by a single ear. Calculate the tensile optimization stress margin for both ears: Both ears are subjected to axial tensile load. ; Both ears are subjected to an oblique tensile load. ; ； ； ； ； When the ears are made of aluminum alloy, , ; When the ears are made of steel, , ; When the ears are made of other materials, , ; in, Optimize the stress margin for the stretching of both ears; The shape factor for the two ears subjected to axial tensile load; The tensile strength limit for both ears; The material coefficient for both ears subjected to axial tensile load; A special coefficient for the stretching of both ears; This represents the maximum tensile stress experienced by both ears; The efficiency coefficient for both ears subjected to oblique tensile load; The material coefficient is given for both ears subjected to oblique tensile load. The angle at which both ears are subjected to an oblique tensile load; Calculate the optimal compressive stress margin for both ears: ； ； in, Optimize the stress margin for compression of both ears; This represents the maximum compressive strength of both ears; A special coefficient for bilateral ear compression; This represents the maximum compressive stress experienced by both ears; Calculate the optimal stress margin for pin bending: ； ； ； ； ； in, Optimize stress margin for pin bending; The tensile strength limit of the pin; This is a special coefficient for pin bending; This represents the maximum bending stress experienced by the pin bearing. This represents the maximum bending moment experienced by the pin bearing. The moment of inertia of the pin section; The lever arm of the pin bending moment; Calculate the optimal stress margin for pin shear optimization: ； ； ； When the pin has a circular cross-section, ; When the pin has a circular cross-section ; in, Optimize stress margin for pin shearing; This is the shear coefficient for the pin; it equals 1 when the pin is solid and 0.975 when the pin is hollow. The shear strength limit of the pin; The stress concentration factor of the pin shaft section; This is the special shear coefficient for the pin. This represents the maximum shear stress experienced by the pin. Let be the cross-sectional area of ​​the pin. Calculate the optimal stress margin for pin extrusion: ； ； in, Optimize stress margin for pin extrusion; The limit of the compressive strength of the pin; This refers to the special extrusion coefficient for the pin shaft; This represents the maximum compressive stress experienced by the pin. The mass amplification factor n_bolt1 for a single ear is set to 1.2; The mass amplification factor n_bolt2 for both ears is set to 1; The mass amplification factor n_axle of the pin is set to 1.

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