Static simulation method for aircraft landing gear based on simplified rod system model

Abstract

The invention discloses an aircraft landing gear statics simulation method based on a simplified bar system model. The simulation method comprises the following steps: S1, analyzing a landing gear structure and simplifying the bar system model; s2, statics analysis and formula derivation; s3, establishing a rod system simulation model; s4, a mechanical theory calculation result and a simulation analysis result are obtained; and S5, result verification and result output. By the adoption of the simulation method, the complex structure of the undercarriage is simplified into the rod system model, the rod system simulation model is established through statics analysis and formula derivation and mechanical simulation software, and on the premise that certain simulation precision is guaranteed, the method can be used for efficiently analyzing the mechanical performance of the undercarriage under the complex load working condition; the calculation efficiency can be remarkably improved, the modeling difficulty is reduced, parameterization analysis is conveniently achieved, an effective tool is provided for rapid design and optimization of the undercarriage, and the method is suitable for application and popularization.

Description

Technical Field

[0001] This invention relates to the field of aerospace structural dynamics simulation technology, specifically to a static simulation method for aircraft landing gear based on a simplified rod system model. Background Technology

[0002] Landing gear is an accessory device located at the bottom of an aircraft, used to support the aircraft during takeoff, landing, or taxiing and for ground movement. It is the only component that supports the entire aircraft; therefore, it is an indispensable part of the aircraft, without which the aircraft cannot move on the ground. After takeoff, the landing gear can be retracted depending on the aircraft's performance. To accommodate the needs of takeoff, landing, and ground taxiing, the lowest part of the landing gear is equipped with wheels with inflatable tires. A structural model of existing landing gear is shown below. Figure 1 As shown, the hidden single-sided tire model diagram is as follows. Figure 2 As shown, it includes a retraction and extension actuator, an outer cylinder, a rocker arm, a buffer support, and wheels.

[0003] In the design and development of aircraft landing gear, static simulation analysis is a crucial method for evaluating its structural strength, stability, and reliability. Aircraft landing gear is a typical rod-like structure. Traditional calculation methods often employ theoretical mechanics for stress analysis, which is complex. When the structure changes, recalculation is required, leading to low efficiency and long calculation times. Furthermore, while some landing gear static simulations typically use full 3D solid models, which can accurately simulate structural details, they have the following significant drawbacks:

[0004] First, the computational efficiency is low: the full three-dimensional solid model contains a large number of geometric elements and nodes, which requires a lot of computational resources and time when performing static analysis. Especially in multi-condition and multi-parameter optimization analysis, the calculation cycle is too long, which seriously affects the efficiency of design iteration.

[0005] Second, the model is highly complex: the landing gear structure is complex, containing numerous parts and connections. Building a full 3D solid model requires advanced modeling skills and a long modeling time, and the model is difficult to modify and adjust.

[0006] Third, parametric analysis is difficult: during the design optimization stage, multiple structural parameters need to be adjusted and analyzed. Full three-dimensional solid models are difficult to quickly achieve parametric modeling and analysis, which cannot meet the needs of rapid design iteration.

[0007] With the development of computer simulation technology, the preliminary theoretical model of landing gear adopts a simplified rod structure for static analysis. This can be used to efficiently analyze the mechanical performance of landing gear under complex load conditions. Therefore, it is very necessary to provide a static simulation method based on a simplified rod model. Summary of the Invention

[0008] The technical problem to be solved by this invention is to address the problems existing in the background technology, thereby providing a static simulation method based on a simplified linkage model. By simplifying the complex structure of the landing gear into a linkage model, this method can efficiently analyze the mechanical performance of the landing gear under complex load conditions while ensuring a certain level of simulation accuracy. It can significantly improve computational efficiency, reduce modeling difficulty, facilitate parametric analysis, and provide an effective tool for the rapid design and optimization of landing gear. Specifically, this invention provides a static simulation method for aircraft landing gear based on a simplified linkage model.

[0009] To solve the above-mentioned technical problems, the technical solution adopted by the present invention is: a static simulation method for aircraft landing gear based on a simplified linkage model, the simulation method comprising the following steps:

[0010] S1. Landing Gear Structural Analysis and Link System Model Simplification

[0011] First, the structure involved in the landing gear is analyzed. Based on the mechanical transmission path and key load-bearing components of the landing gear, and then combined with the axioms of statics and the force analysis of the object, the landing gear is simplified and decomposed into representative rod units to obtain the landing gear rod model.

[0012] S2. Static Analysis and Formula Derivation

[0013] The landing gear is set as a statically determinate structure in the lowered state. Based on the landing gear linkage model obtained after decomposition in step S1, and combined with the actual working conditions of the landing gear, the load conditions in different motion processes are determined. Static analysis and formula derivation are performed, and the mechanical equilibrium equation is established by torque balance static analysis using Newton's laws.

[0014] S3. Establishment of the pole system simulation model

[0015] Based on the landing gear linkage model obtained after decomposition in step S1, a landing gear linkage simulation model is established using mechanical simulation software. During the establishment of the linkage simulation model, the connection parts of the linkage are simplified into corresponding constraint conditions.

[0016] S4. Results of mechanical theoretical calculations and simulation analysis

[0017] Based on the mechanical equilibrium equations established in step S2 and the rod system simulation model established in step S3, the parameters of the landing gear and the corresponding load conditions are input according to the parameter values ​​and load conditions calculated by mechanical theory and simulation analysis, and the results of mechanical theory calculation and simulation analysis are obtained respectively.

[0018] S5. Result Verification and Result Output

[0019] The mechanical calculation results and simulation analysis results obtained in step S4 are compared and verified to evaluate the simulation accuracy of the simplified landing gear linkage model. If the comparison results are within the set deviation range, the results are output and the simulation analysis ends. If the comparison results exceed the set deviation, the process returns to step S1 to readjust and optimize the landing gear linkage model until the simulation accuracy meets the accuracy requirements of the set deviation.

[0020] Furthermore, the static simulation method for aircraft landing gear based on a simplified linkage model described in this invention is adopted. In the landing gear structure analysis and linkage model simplification stage in S1, the relative motion states of the retraction actuator, outer cylinder, rocker arm, buffer strut, and wheels involved in the landing gear during the aircraft's takeoff, landing, and taxiing processes are decomposed into five linkage units through structural simplification, thereby obtaining the landing gear linkage model. Finally, based on the obtained landing gear linkage model, static analysis and formula derivation are performed, and a linkage simulation model is established.

[0021] Furthermore, in the static simulation method for aircraft landing gear based on a simplified linkage model described in this invention, the static analysis and formula derivation stage in S2 involves applying the actual working conditions of the aircraft landing gear, including the vertical, horizontal, or lateral loads involved in takeoff, landing, and taxiing, to the linkage model according to their actual positions and directions. This ensures the accuracy and rationality of the load application, thereby obtaining the load conditions. Finally, the mechanical equilibrium equations are established through moment balance static analysis using Newton's laws.

[0022] Furthermore, in the static simulation method for aircraft landing gear based on a simplified linkage model described in this invention, the constraint conditions in the linkage simulation model establishment stage of S3 refer to the corresponding constraint settings for the connection parts between adjacent linkages in three-dimensional space, based on the actual operating conditions involved in the aircraft's takeoff, landing, and taxiing processes. These constraints include hinge constraints and fixed constraints.

[0023] Furthermore, in the static simulation method for aircraft landing gear based on a simplified linkage model described in this invention, during the linkage simulation model establishment stage in S3, the mechanical simulation software used is any one of LMS Virtual.Lab simulation software, ABAQUS simulation software, or ANSYS simulation software.

[0024] Furthermore, the static simulation method for aircraft landing gear based on a simplified linkage model as described in this invention is characterized in that: in the stage of mechanical theory calculation results and simulation analysis results in S4, under constraints, the parameters of the landing gear and the loads applied to the linkage model under the corresponding states are input into the formula of the mechanical equilibrium equation to calculate the load results. At the same time, the corresponding parameter values ​​and load conditions are input into the linkage simulation model to calculate the load results, thereby obtaining the mechanical theory calculation results and simulation analysis results.

[0025] Furthermore, in the static simulation method for aircraft landing gear based on a simplified linkage model described in this invention, during the S5 result verification and output stage, the formula for calculating the deviation is as follows:

[0026] Deviation = (|Simulation result value - Theoretical calculation value|) / Theoretical calculation value × 100%

[0027] If the deviation between the calculation results based on mechanical theory and the simulation analysis results is less than 2%, the simulation accuracy is considered high and the simulation is reasonable; if the deviation is greater than 2%, return to step S1 and readjust and optimize the landing gear linkage model until the simulation accuracy meets the accuracy requirements of the set deviation.

[0028] The static simulation method for aircraft landing gear based on a simplified linkage model described in this invention has the following advantages compared with existing technologies: By simplifying the complex structure of the landing gear into a linkage model, static analysis and formula derivation are performed, and a linkage simulation model is established using mechanical simulation software. Under the premise of ensuring a certain level of simulation accuracy, this method can be used to efficiently analyze the mechanical performance of the landing gear under complex load conditions. It can significantly improve computational efficiency, reduce modeling difficulty, facilitate parametric analysis, and provide an effective tool for the rapid design and optimization of landing gear, making it suitable for widespread application. Attached Figure Description

[0029] The present invention will now be described in further detail with reference to the accompanying drawings.

[0030] Figure 1 This is a schematic diagram of the overall structure of the existing landing gear.

[0031] Figure 2 for Figure 1 The image shows a hidden single-sided tire model.

[0032] Figure 3 This is a schematic diagram of the technical route described in this invention;

[0033] Figure 4 This is a simplified model diagram of the landing gear linkage system described in this invention;

[0034] Figure 5 This is a static analysis diagram of the landing gear strut system model described in this invention;

[0035] Figure 6 Three views for static analysis of the landing gear strut model described in this invention Figure 1 ;

[0036] Figure 7 Three views for static analysis of the landing gear strut model described in this invention Figure 2 ;

[0037] Figure 8 Three views for static analysis of the landing gear strut model described in this invention Figure 3 ;

[0038] Figure 9 This is a dot diagram of the landing gear connection portion described in this invention;

[0039] Figure 10 This is a simulation model diagram of the landing gear linkage system described in this invention.

[0040] The diagram shows: 1-retracting actuator, 2-outer cylinder, 3-rocker arm, 4-buffer support, 5-wheel. Detailed Implementation

[0041] The following specific embodiments illustrate the implementation of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification.

[0042] It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are merely for illustrative purposes to aid those skilled in the art and to facilitate understanding. They are not intended to limit the scope of the invention and therefore have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to size, without affecting the effectiveness or purpose of the invention, should still fall within the scope of the disclosed technical content. Furthermore, the terms "upper," "lower," "left," and "right" used in this specification are merely for clarity and not intended to limit the scope of the invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of the invention's implementation.

[0043] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "connection" and "provided with" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0044] It should be noted that the term "comprising" or any other variation is intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such process, method, article, or apparatus.

[0045] This invention provides a static simulation method for aircraft landing gear based on a simplified linkage model. The simulation method includes the following steps:

[0046] S1. Landing Gear Structural Analysis and Link System Model Simplification

[0047] First, the structure involved in the landing gear is analyzed. Based on the mechanical transmission path and key load-bearing components of the landing gear, and then combined with static axioms and force analysis of the object, the landing gear is simplified and decomposed into representative linkage units to obtain the landing gear linkage model. Specifically, the relative motion states of the retraction actuator 1, outer cylinder 2, rocker arm 3, shock absorber strut 4, and wheel 5 involved in the landing gear during the aircraft's takeoff, landing, and taxiing processes are simplified and decomposed into five linkage units to obtain the landing gear linkage model. Finally, based on the obtained landing gear linkage model, static analysis and formula derivation are performed, and a linkage simulation model is established.

[0048] S2. Static Analysis and Formula Derivation

[0049] The landing gear is set as a statically determinate structure in its lowered state. Based on the landing gear linkage model obtained after decomposition in step S1, and combined with the actual working conditions of the landing gear, the load conditions during different motion processes are determined. Static analysis and formula derivation are performed, and the mechanical equilibrium equation is established by torque balance static analysis using Newton's laws. Specifically, based on the actual working conditions of the landing gear applied to the aircraft, including the vertical, horizontal, or lateral loads involved in the aircraft's takeoff, landing, and taxiing processes, these loads are applied to the linkage model according to their actual positions and directions to ensure the accuracy and rationality of load application, thereby obtaining the load conditions. Finally, the mechanical equilibrium equation is established by torque balance static analysis using Newton's laws.

[0050] S3. Establishment of the pole system simulation model

[0051] Based on the landing gear linkage model obtained after decomposition in step S1, a landing gear linkage simulation model is established using mechanical simulation software (LMSVirtual.Lab, ABAQUS, or ANSYS). During the establishment of the linkage simulation model, the connection parts of the linkage are simplified into corresponding constraints. The constraints refer to the corresponding constraint settings for the connection parts between adjacent linkages in three-dimensional space in the established linkage simulation model, based on the actual operating conditions involved in the aircraft's takeoff, landing, and taxiing processes. These constraints include hinge constraints and fixed constraints.

[0052] S4. Results of mechanical theoretical calculations and simulation analysis

[0053] Based on the mechanical equilibrium equations established in step S2 and the linkage simulation model established in step S3, the parameters of the landing gear and the corresponding load conditions are input according to the parameter values ​​and load conditions calculated by mechanical theory and simulation analysis, respectively, to obtain the mechanical theory calculation results and simulation analysis results. Specifically, under the constraint conditions, the parameters of the landing gear and the loads applied to the linkage model under the corresponding state are used to input the corresponding parameter values ​​and load conditions into the formula of the mechanical equilibrium equation to calculate the load results. At the same time, the corresponding parameter values ​​and load conditions are input into the linkage simulation model to calculate the load results, thereby obtaining the mechanical theory calculation results and simulation analysis results.

[0054] S5. Result Verification and Result Output

[0055] The mechanical calculation results and simulation analysis results obtained in step S4 are compared and verified to evaluate the simulation accuracy of the simplified landing gear linkage model. If the comparison results are within the set deviation range, the results are output and the simulation analysis ends. If the comparison results exceed the set deviation, the process returns to step S1, and the landing gear linkage model is readjusted and optimized until the simulation accuracy meets the set deviation accuracy requirements. The formula for calculating the deviation is:

[0056] Deviation = (|Simulation result value - Theoretical calculation value|) / Theoretical calculation value × 100%

[0057] If the deviation between the calculation results based on mechanical theory and the simulation analysis results is less than 2%, the simulation accuracy is considered high and the simulation is reasonable; if the deviation is greater than 2%, return to step S1 and readjust and optimize the landing gear linkage model until the simulation accuracy meets the accuracy requirements of the set deviation.

[0058] Example

[0059] To further illustrate the static simulation method for aircraft landing gear based on a simplified linkage model as described in this invention, taking a certain type of rocker arm landing gear as an example, the technical approach involved in its simulation method is as follows: Figure 3 As shown, the specific steps include:

[0060] 1. Landing gear structural analysis and strut model simplification

[0061] The actual structure of a certain type of landing gear is as follows: Figure 1 and Figure 2 As shown, based on the mechanical transmission path and key load-bearing components of its structure, the landing gear is simplified and decomposed into several representative linkage units during static analysis. For example, the main load-bearing components of the landing gear, such as the retraction and extension actuator 1, outer cylinder 2, rocker arm 3, shock absorber strut 4, and wheel 5, are simplified into linkage units, and their simplified structures are as follows: Figure 4 As shown, its retraction and extension actuator 1 and buffer support 4 are simplified into two-force rods, the outer cylinder 2 and rocker arm 3 are simplified into a rod system according to the external structure and rotation axis, and the wheel 5 is simplified into a circle.

[0062] 2. Static Analysis and Formula Derivation

[0063] A certain type of landing gear is a statically determinate structure in its lowered state. Based on the simplified linkage model obtained in step 1, a force analysis is performed on the landing gear linkage model. According to the actual working conditions of the aircraft landing gear, several typical load conditions are defined, including vertical loads, horizontal loads, and lateral loads during takeoff, landing, and taxiing. These loads are applied to the linkage model according to their actual positions and directions to ensure the accuracy and rationality of load application.

[0064] For example, the loads Px (Px is the load acting on point O of the rocker arm axis pointing in the reverse direction of the aircraft along the X-axis), Py (Py is the load acting on point O of the rocker arm axis pointing vertically upward along the Y-axis), and Pz (Pz is the lateral load acting on points F and F′ at the tire contact points of wheel 5) are applied to the simplified landing gear linkage model, respectively. The landing gear coordinate system is defined as follows: X-axis is the aircraft heading, Y-axis is the vertical direction, and Z-axis is the rotation axis of wheel 5. Then the static analysis of this landing gear linkage model is as follows: Figure 5 As shown, the three views of the static analysis of the landing gear linkage model are as follows: Figures 6 to 8 As shown.

[0065] In the diagram, points A, B, C, C′, D, D′, E, G, and G′ represent the connection points. Points A and B are the two joint load points of the outer cylinder 2, and C′ is the joint load point of the retracting and extending actuator cylinder 1. NAx, NAy, NAz, NBx, NBy, and NBz are the X, Y, and Z component forces of the reaction loads generated at the two joint load points A and B of the outer cylinder 2, respectively. NC is the resultant force of the reaction load generated by the retracting and extending actuator cylinder 1 on the outer cylinder 2 at the connection point C (NC is equal to the resultant force NC′ of the reaction load generated at the joint load point C′ of the retracting and extending actuator cylinder 1). α is the angle between the buffer support 4 and the Y-axis, β is the angle between the projection of Nc on the XZ plane and the Z-axis, and γ is the angle between Nc and the XZ plane.

[0066] The mechanical equilibrium equations are established through static analysis of moment balance. By deriving the formulas, the loads at joints A, B, and C′ are obtained as NC, NAx, NAy, NAz, NBx, NBy, and NBz, respectively. The calculation formula is then given.

[0067]

[0068]

[0069] 3. Establishment of the pole system simulation model

[0070] Based on the simplified rod system model results from step 1, a simulation model of the landing gear rod system is established using mechanical simulation software (such as LMS Virtual.Lab, ABAQUS, or ANSYS). During the model establishment process, connections (such as joint bearing connections, bolted connections, etc.) are simplified to corresponding constraints, such as hinge constraints or fixed constraints.

[0071] The landing gear has a total of 9 connection points, and its structure is as follows: Figure 9 As shown, points A, B, C, C′, D, D′, E, G, and G′ represent the following connections: A and B are the connection points between the outer cylinder 2 and the globally fixed component; C is the connection point between the outer cylinder 2 and the retraction / extension actuation cylinder 1; C′ is the connection point between the retraction / extension actuation cylinder 1 and the globally fixed component; D is the connection point between the outer cylinder 2 and the buffer strut 4; D′ is the connection point between the buffer strut 4 and the rocker arm 3; E is the connection point between the outer cylinder 2 and the rocker arm 3; and G and G′ are the connection points between the rocker arm 3 and the wheel 5. Based on the actual conditions of each connection point, corresponding constraints are set to establish the landing gear linkage simulation model, as shown below. Figure 10 As shown.

[0072] The constraints at points A and B are: release the rotational degree of freedom along the X-axis;

[0073] The constraints at points C, C′, and D′ are: release the rotational degrees of freedom of the X, Y, and Z axes;

[0074] The constraint at points D and E is to release the rotational degree of freedom along the Z-axis.

[0075] The constraints at points G and G′ are: completely fixed constraints.

[0076] 4. Results of mechanical theoretical calculations and simulation analysis

[0077] The parameters and load conditions for mechanical theoretical calculation and simulation analysis are input as follows, taking the parameters of this landing gear and a certain load condition as an example. The parameter data are: α=14.02°, β=16.64°, γ=22.404°, LAB=482.537mm, L1=88.9mm, L2=355.6mm, L3=1450.868mm, L4=3.492mm, L5=33.081mm, L6=449.46mm, R=418mm; the load conditions are: Px=20000N, Py=240000, Pz=10000N.

[0078] Based on the joint load formula derived in step 2, the landing gear parameters and load conditions are input into the formula to calculate the load results of joints A, B, and C′, specifically: NC′=66039.08N, NAx=18742.202N, NAy=-50729.378N, NAz=125177.131N, NBx=18742.202N, NBy=-89654.850N, NBz=2231.346N.

[0079] Based on the linkage simulation model established in step 3, the load condition of the landing gear is applied to the linkage simulation model for simulation analysis. The load results of joints A, B, and C′ are extracted as follows: NC′=66037.696N, NAx=18740.084N, NAy=-50727.887N, NAz=125178.43N, NBx=18740.063N, NBy=-89652.516N, NBz=2230.527N.

[0080] 5. Result Verification and Output

[0081] The simulation results of the linkage model are compared and verified with the theoretical calculation results to evaluate the simulation accuracy of the linkage model. If the results deviate significantly, it is necessary to analyze the cause and return to the beginning of the landing gear structure analysis. The linkage model should be simplified, adjusted, and optimized step by step, checking each item individually, such as correcting the linkage coordinate positions or adjusting constraints, until the simulation results meet the accuracy requirements. Simultaneously, based on the joint load analysis results, the landing gear structure is optimized, such as adjusting the angle of the linkage units and the structural layout, to improve structural performance.

[0082] For example: the simulation accuracy of this landing gear is considered high if the deviation is less than 2%. The formula for calculating the deviation is:

[0083]

[0084] Based on the mechanical calculation results and simulation analysis results from step 4, the errors of NC are 0.002%, NAx is 0.011%, NAy is 0.003%, NAz is 0.001%, NBx is 0.011%, NBy is 0.003%, and NBz is 0.037%. After comparing and verifying the results, the simulation model of the linkage landing gear shows high accuracy and reasonable simulation.

[0085] Therefore, the simulation method described in this invention simplifies the complex landing gear structure into a rod system model. Through static analysis and formula derivation, and by using mechanical simulation software to establish a rod system simulation model, it can be used to efficiently analyze the mechanical performance of the landing gear under complex load conditions while ensuring a certain level of simulation accuracy. This significantly improves computational efficiency, reduces modeling difficulty, and facilitates parametric analysis. It provides an effective tool for the rapid design and optimization of landing gear and is suitable for widespread application.

[0086] Other aspects of this invention that are not detailed herein are all conventional techniques known to those skilled in the art.

[0087] The scope of protection of this invention is not limited to the technical solutions disclosed in the specific embodiments. The above description is only a preferred embodiment of this invention and does not limit this invention. Any minor modifications, equivalent substitutions and improvements made based on the technical solutions of this invention should be included within the scope of protection of the technical solutions of this invention.

Claims

1. A static simulation method for aircraft landing gear based on a simplified linkage model, characterized in that, The simulation method includes the following steps: S1. Landing Gear Structural Analysis and Link System Model Simplification First, the structure involved in the landing gear is analyzed. Based on the mechanical transmission path and key load-bearing components of the landing gear, and then combined with the axioms of statics and the force analysis of the object, the landing gear is simplified and decomposed into representative rod units to obtain the landing gear rod model. S2. Static Analysis and Formula Derivation The landing gear is set as a statically determinate structure in the lowered state. Based on the landing gear linkage model obtained after decomposition in step S1, and combined with the actual working conditions of the landing gear, the load conditions in different motion processes are determined. Static analysis and formula derivation are performed, and the mechanical equilibrium equation is established by torque balance static analysis using Newton's laws. S3. Establishment of the pole system simulation model Based on the landing gear linkage model obtained after decomposition in step S1, a landing gear linkage simulation model is established using mechanical simulation software. During the establishment of the linkage simulation model, the connection parts of the linkage are simplified into corresponding constraint conditions. S4. Results of mechanical theoretical calculations and simulation analysis Based on the mechanical equilibrium equations established in step S2 and the rod system simulation model established in step S3, the parameters of the landing gear and the corresponding load conditions are input according to the parameter values ​​and load conditions calculated by mechanical theory and simulation analysis, and the results of mechanical theory calculation and simulation analysis are obtained respectively. S5. Result Verification and Result Output The mechanical calculation results and simulation analysis results obtained in step S4 are compared and verified to evaluate the simulation accuracy of the simplified landing gear linkage model. If the comparison results are within the set deviation range, the results are output and the simulation analysis ends. If the comparison results exceed the set deviation, the process returns to step S1 to readjust and optimize the landing gear linkage model until the simulation accuracy meets the accuracy requirements of the set deviation.

2. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: The landing gear structure analysis and linkage model simplification stage in S1 involves simplifying the landing gear components, such as the retraction actuator (1), outer cylinder (2), rocker arm (3), buffer strut (4), and wheels (5), during takeoff, landing, and taxiing. By simplifying the structure, the relative motion states between the retraction actuator (1), outer cylinder (2), rocker arm (3), buffer strut (4), and wheels (5) are decomposed into different linkage units. The landing gear linkage model is constructed using the decomposed linkage units. Finally, based on the obtained landing gear linkage model, static analysis and formula derivation are performed, and a linkage simulation model is established.

3. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: The static analysis and formula derivation stage in S2 involves applying the actual working conditions of the aircraft landing gear, including the vertical, horizontal, or lateral loads involved in the aircraft's takeoff, landing, and taxiing processes, to the linkage model according to their actual positions and directions. This ensures the accuracy and rationality of the load application, thereby obtaining the load conditions. Finally, Newton's laws are used to establish the mechanical equilibrium equations through torque balance static analysis.

4. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: In the linkage simulation model establishment stage of S3, the constraint conditions refer to the corresponding constraint settings for the connection parts between adjacent linkages in the established linkage simulation model in three-dimensional space, based on the actual operating conditions involved in the aircraft's takeoff, landing, and taxiing processes. These constraints include hinge constraints and fixed constraints.

5. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: In the stage of establishing the rod system simulation model in S3, the mechanical simulation software used is any one of LMS Virtual.Lab simulation software, ABAQUS simulation software, or ANSYS simulation software.

6. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: The mechanical theory calculation results and simulation analysis results stage in S4 involves, under constrained conditions, applying the parameters of the landing gear and the loads applied to the linkage model under the corresponding state, inputting the corresponding parameter values ​​and load conditions into the formula of the mechanical equilibrium equation to calculate the load results, and simultaneously inputting the corresponding parameter values ​​and load conditions into the linkage simulation model to calculate the load results, thereby obtaining the mechanical theory calculation results and simulation analysis results.

7. The static simulation method for aircraft landing gear based on a simplified linkage model according to claim 1, characterized in that: In the S5 result verification and result output stage, the formula for calculating the deviation is: Deviation = (|Simulation result value - Theoretical calculation value|) / Theoretical calculation value × 100% If the deviation between the calculation results based on mechanical theory and the simulation analysis results is less than 2%, then the simulation accuracy is considered high and the simulation is reasonable. If the deviation is greater than 2%, return to step S1 and readjust and optimize the landing gear linkage model until the simulation accuracy meets the accuracy requirements of the set deviation.

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