An aircraft landing gear dynamics model modeling method and landing simulation method thereof

Abstract

The application relates to a modeling method of an aircraft landing gear dynamics model, comprising the following steps: simulating the mechanical characteristics of a landing gear strut by using a rigid body unit; simulating the buffering characteristics of a landing gear tire by using a nonlinear spring damping unit, and constraining the movement of the landing gear tire by using a rigid body unit; simulating the buffering characteristics of a landing gear bumper by using a nonlinear spring damping unit, and constraining the movement of the landing gear bumper by using a rigid body unit; and constraining the movement of a torque arm by using an RBE2. In addition, the application relates to an aircraft landing simulation method, which is implemented based on the above-mentioned modeling method of the aircraft landing gear dynamics model.

Description

Technical Field

[0001] This application belongs to the field of aircraft landing simulation, specifically involving an aircraft landing gear dynamics modeling method and its landing simulation method. Background Technology

[0002] When an aircraft lands, the landing gear bears a significant impact load. To reduce the impact force on the landing gear strut 1, a landing gear damper 3 is installed between the landing gear strut 1 and the landing gear tire 2. To transfer the torque on the landing gear strut 1 to the landing gear tire 2 and to reduce the sway of the landing gear tire, a torque arm 4 is installed between the landing gear strut 1 and the landing gear tire 2. Figure 1 As shown.

[0003] When an aircraft makes an arrested landing, all parts of the aircraft will experience significant acceleration and stress. By simulating and analyzing the aircraft landing, we can obtain the acceleration and stress response of all parts of the aircraft during landing, which can provide data support for the structural design and improvement of the aircraft.

[0004] Currently, simulation analysis of aircraft landing is mostly conducted by establishing a full-aircraft structural elastic model and using the landing gear load input method, which has poor accuracy.

[0005] This application is made in view of the aforementioned technical deficiencies.

[0006] 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

[0007] The purpose of this application is to provide a modeling method for aircraft landing gear dynamics and a landing simulation method thereon, so as to overcome or mitigate at least one of the known technical defects.

[0008] The technical solution of this application is:

[0009] One aspect provides a modeling method for aircraft landing gear dynamics, including:

[0010] The mechanical characteristics of the landing gear struts are simulated using rigid body elements;

[0011] The buffering characteristics of the landing gear tires are simulated using nonlinear spring damping elements, and the motion of the landing gear tires is constrained using rigid body elements.

[0012] The buffering characteristics of the landing gear buffer are simulated by nonlinear spring damping elements, and the motion of the landing gear buffer is constrained by rigid body elements.

[0013] The motion of the torque arm is constrained by RBE2.

[0014] According to at least one embodiment of this application, in the above-described aircraft landing gear dynamics modeling method, the step of simulating the buffering characteristics of the landing gear tires using nonlinear spring damping units specifically includes:

[0015] The cushioning characteristics of landing gear tires are simulated using a one-dimensional nonlinear spring damping element.

[0016] According to at least one embodiment of this application, in the above-described aircraft landing gear dynamics modeling method, the constraint of the landing gear tire motion using rigid body elements specifically involves:

[0017] The mechanical properties of the landing gear tire tread and wheel hub are simulated using rigid body elements.

[0018] According to at least one embodiment of this application, in the above-described aircraft landing gear dynamics modeling method, the step of simulating the buffering characteristics of the landing gear buffer using a nonlinear spring damping unit specifically includes:

[0019] The buffering characteristics of the landing gear buffer are simulated using a one-dimensional nonlinear spring damping element.

[0020] According to at least one embodiment of this application, in the above-described aircraft landing gear dynamics modeling method, the constraint of the landing gear buffer motion by rigid body elements specifically involves...

[0021] The relative motion between the inner and outer cylinders of the landing gear buffer is defined using contact conditions.

[0022] On the other hand, an aircraft landing simulation method is provided, including:

[0023] Construct an aircraft landing gear dynamics model using any of the above-mentioned aircraft landing gear dynamics modeling methods;

[0024] Construct an organism dynamics model;

[0025] By combining the aircraft landing gear dynamics model and the airframe dynamics model, a full-aircraft landing simulation model is obtained;

[0026] Using a full-aircraft landing simulation model, the landing of the aircraft is simulated, and the acceleration and stress response of various parts of the aircraft during landing are obtained. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of an aircraft landing gear provided in an embodiment of this application;

[0028] Figure 2This is a schematic diagram of the aircraft landing gear dynamics model provided in the embodiments of this application;

[0029] in:

[0030] 1-Landing gear strut; 2-Landing gear tire; 3-Landing gear damper; 4-Torque arm.

[0031] 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

[0032] 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.

[0033] 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.

[0034] 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.

[0035] The following is in conjunction with the appendix Figures 1 to 2 This application will be described in further detail.

[0036] One aspect provides a modeling method for aircraft landing gear dynamics, including:

[0037] The mechanical characteristics of landing gear strut 1 are simulated using rigid body elements;

[0038] The buffering characteristics of the landing gear tire 2 are simulated by a nonlinear spring damping element, and the motion of the landing gear tire 2 is constrained by a rigid body element.

[0039] The buffering characteristics of the landing gear buffer 3 are simulated by a nonlinear spring damping element, and the motion of the landing gear buffer 3 is constrained by a rigid body element.

[0040] The motion of torque arm 4 is constrained by RBE2.

[0041] Regarding the aircraft landing gear dynamics modeling method disclosed in the above embodiments, those skilled in the art will understand that its design uses nonlinear spring damping elements to simulate the buffering characteristics of the landing gear tires 2 and landing gear buffers 3, nonlinear spring damping elements to simulate the damping characteristics of the return damper 3, shell elements to simulate the mechanical characteristics of the arresting hook 4 hook arm, rigid body elements to simulate the mechanical characteristics of the arresting hook 4 hook head, and rigid body elements to simulate the mechanical characteristics of the landing gear strut 1. This can accurately simulate the dynamic characteristics of the landing gear. Combined with the airframe dynamics model, a full-aircraft landing simulation model can be obtained. By simulating the aircraft landing, the acceleration and stress response of various parts of the aircraft during arrested landing can be accurately obtained, providing reliable data support for the structural design and improvement of the aircraft. In addition, the design uses rigid body elements to constrain the motion of the landing gear tires 2 and landing gear buffers 3, and uses RBE2 to constrain the motion of the torque arm 4, which can ensure the stability of the simulation results of the aircraft landing.

[0042] In some optional embodiments, in the above-described aircraft landing gear dynamics modeling method, the step of simulating the cushioning characteristics of the landing gear tire 2 using a nonlinear spring damping unit specifically involves:

[0043] The buffering characteristics of the landing gear tire 2 are simulated by a one-dimensional nonlinear spring damping element. The landing gear tire 2 is simplified to only release the degree of freedom of the axial movement of the landing gear, so as to facilitate simulation calculation.

[0044] In some optional embodiments, in the above-described aircraft landing gear dynamics modeling method, the constraint of the motion of the landing gear tire 2 by rigid body elements specifically includes:

[0045] Rigid body elements are used to simulate the mechanical properties of the tread and hub of the landing gear tire 2 in order to simplify the model and facilitate simulation calculations.

[0046] In some optional embodiments, in the above-described aircraft landing gear dynamics modeling method, the step of simulating the buffering characteristics of the landing gear buffer 3 using a nonlinear spring damping unit specifically involves:

[0047] The buffering characteristics of the landing gear buffer 3 are simulated by a one-dimensional nonlinear spring damping element. The landing gear buffer 3 is simplified to only release the degree of freedom of the axial movement of the landing gear, so as to facilitate simulation calculation.

[0048] In some optional embodiments, in the above-described aircraft landing gear dynamics modeling method, the constraint of the motion of the landing gear buffer 3 by rigid body elements specifically involves...

[0049] The relative motion between the inner and outer cylinders of the landing gear buffer 3 is defined using contact conditions.

[0050] On the other hand, an aircraft landing simulation method is provided, including:

[0051] Construct an aircraft landing gear dynamics model using any of the above-mentioned aircraft landing gear dynamics modeling methods;

[0052] Construct an organism dynamics model;

[0053] By combining the aircraft landing gear dynamics model and the airframe dynamics model, a full-aircraft landing simulation model is obtained;

[0054] Using a full-aircraft landing simulation model, the landing of the aircraft is simulated, and the acceleration and stress response of various parts of the aircraft during landing are obtained.

[0055] The aircraft landing simulation method disclosed in the above embodiments is implemented based on the aircraft landing gear dynamics modeling method disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description in the section on aircraft landing gear dynamics modeling method. The technical effects can also be referred to the relevant section on aircraft landing gear dynamics modeling method. It will not be repeated here.

[0056] 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.

[0057] 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 of modeling an aircraft landing gear dynamic model, characterized in that, include: The mechanical characteristics of the landing gear strut (1) are simulated using rigid body elements; The buffering characteristics of the landing gear tire (2) are simulated by a nonlinear spring damping element, and the motion of the landing gear tire (2) is constrained by a rigid body element. The buffering characteristics of the landing gear buffer (3) are simulated by a nonlinear spring damping element, and the motion of the landing gear buffer (3) is constrained by a rigid body element. The motion of the torque arm (4) is constrained by RBE2; The buffering characteristics of the landing gear buffer (3) simulated by the nonlinear spring damping unit are as follows: The buffering characteristics of the landing gear buffer (3) are simulated by a one-dimensional nonlinear spring damping unit; The constraint of the motion of the landing gear buffer (3) by the rigid body element is specifically as follows: The relative motion between the inner and outer cylinders of the landing gear buffer (3) is defined by contact conditions.

2. The aircraft landing gear dynamics modeling method according to claim 1, characterized in that, The method of simulating the buffering characteristics of the landing gear tire (2) using a nonlinear spring damping unit is as follows: The buffering characteristics of the landing gear tire (2) are simulated by a one-dimensional nonlinear spring damping unit.

3. The aircraft landing gear dynamics modeling method according to claim 1, characterized in that, The constraint of the motion of the landing gear tires (2) by rigid body elements is specifically as follows: The mechanical properties of the tread and hub of the landing gear tire (2) are simulated using rigid body elements.

4. An aircraft landing simulation method, characterized in that, include: An aircraft landing gear dynamic model is constructed using the aircraft landing gear dynamic model modeling method described in any one of claims 1-3; Construct an organism dynamics model; By combining the aircraft landing gear dynamics model and the airframe dynamics model, a full-aircraft landing simulation model is obtained; Using a full-aircraft landing simulation model, the landing of the aircraft is simulated, and the acceleration and stress response of various parts of the aircraft during landing are obtained.

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