A method, device, equipment and medium for determining landing impact stiffness

Abstract

The present invention discloses a method, device, equipment, and medium for determining landing collision stiffness for designing a reusable rocket, comprising: constructing a landing model based on the design parameters of the reusable rocket; constructing a ground model based on preset parameters of the target recovery site of the reusable rocket; simulating the landing impact of the reusable rocket using the landing model and the ground model, and obtaining deformation parameters of the target model during the simulated landing impact process, wherein the target model includes the landing model and the ground model; and determining the target collision stiffness of the reusable rocket based on the deformation parameters. This application can determine the target collision stiffness of the reusable rocket, and further calculate the landing load in the early stages of the reusable rocket design, thereby providing clear input for the reusable rocket and improving the accuracy of the landing load of the reusable rocket in the early stages of the design.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a method, device, equipment and medium for determining landing collision stiffness. Background Art

[0002] A reusable rocket undergoes several key stages during recovery and landing, including engine shutdown, free fall, ground impact, buffering, and successful landing. The ground impact directly impacts the landing payload. During the reusable rocket design process, accurate landing payload calculations are crucial to ensure the final design, including the rocket's cabin and individual components, is not damaged.

[0003] In the early stages of reusable rocket design, no relevant tests were carried out, and the landing load of the rocket body could generally be calculated through a multi-body dynamics model, in which the collision stiffness between the rocket body and the ground directly determined the size of the landing load, and the collision stiffness was related to the landing mechanism and the physical properties of the ground.

[0004] In the related art, the collision stiffness in the early design stage is mainly determined based on the experience of technicians, resulting in low accuracy of the landing load of the reusable rocket in the early design stage. Summary of the Invention

[0005] The embodiments of the present application provide a method, device, equipment and medium for determining landing collision stiffness, thereby solving the technical problem in the prior art of relying on the experience of technicians to determine the collision stiffness in the early stages of design, resulting in low accuracy of the landing load of reusable rockets in the early stages of design. This achieves the technical effect of determining the collision stiffness in the early stages of design of reusable rockets to improve the accuracy of the landing load.

[0006] In a first aspect, the present application provides a method for determining landing collision stiffness for designing a reusable rocket, the method comprising:

[0007] Construct a landing model based on the design parameters of the reusable rocket;

[0008] Construct a ground model based on preset parameters of the target recovery site for reusable rockets;

[0009] The landing impact of a reusable rocket is simulated by using a landing model and a ground model to obtain deformation parameters of a target model during the simulated landing impact process. The target model includes the landing model and the ground model.

[0010] Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined.

[0011] Furthermore, a landing model is constructed based on the design parameters of the reusable rocket, including:

[0012] A landing model is constructed based on the design parameters of the landing touchdown components of the reusable rocket.

[0013] Furthermore, a landing model is constructed based on the design parameters of the reusable rocket, including:

[0014] A landing model is constructed according to the design parameters and first physical property parameters of the reusable rocket, where the first physical property parameters include a first elastic modulus and a first Poisson's ratio.

[0015] Furthermore, a ground model is constructed based on preset parameters of the target recovery site for the reusable rocket, including:

[0016] A ground model is constructed according to preset parameters and second physical property parameters of the target recovery site, where the second physical property parameters include a second elastic modulus and a second Poisson's ratio.

[0017] Furthermore, the landing model and ground model are used to simulate the landing impact of the reusable rocket, including:

[0018] Apply target loads to the landing model and displacement constraints to the ground model to simulate the reusable rocket landing impact.

[0019] Furthermore, before simulating the landing impact of the reusable rocket using the landing model and the ground model, the method further includes:

[0020] Using the target mesh, the landing model and the ground model are meshed with finite elements.

[0021] Furthermore, the deformation parameters of the target model during the simulated landing impact are obtained, including:

[0022] Obtain the maximum deformation parameters of the target model during the simulated landing impact process;

[0023] Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined, including:

[0024] According to the maximum deformation parameter, the target collision stiffness is determined.

[0025] In a second aspect, the present application provides a landing collision stiffness determination device for designing a reusable rocket, the device comprising:

[0026] A landing model building module is used to build a landing model according to the design parameters of the reusable rocket;

[0027] a ground model building module, configured to build a ground model according to preset parameters of a target recovery site for a reusable rocket;

[0028] A deformation parameter acquisition module is used to simulate the landing impact of a reusable rocket using a landing model and a ground model, and obtain deformation parameters of a target model during the simulated landing impact process. The target model includes the landing model and the ground model.

[0029] The target collision stiffness determination module is used to determine the target collision stiffness of the reusable rocket based on the deformation parameters.

[0030] In a third aspect, the present application provides an electronic device, comprising:

[0031] processor;

[0032] a memory for storing processor-executable instructions;

[0033] The processor is configured to execute to implement a landing collision stiffness determination method.

[0034] In a fourth aspect, the present application provides a non-temporary computer-readable storage medium, which, when the instructions in the storage medium are executed by a processor of an electronic device, enables the electronic device to implement a method for determining landing collision stiffness.

[0035] One or more technical solutions provided in the embodiments of this application have at least the following technical effects or advantages:

[0036] This application constructs a landing model based on the design parameters of the reusable rocket, and constructs a ground model based on the preset parameters of the target recovery site. Then, through the landing model and the ground model, the landing impact of the reusable rocket is simulated, and the deformation parameters of the landing model and the ground model during the target process can be obtained. Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined, and the landing load can be calculated in the early design stage of the reusable rocket, and clear input can be provided for the calculation of the landing load of the reusable rocket. The load calculation is relatively conservative, which improves the accuracy of the landing load of the reusable rocket in the early design stage and reduces the risk of repeated design schemes. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the description of the embodiments. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0038] Figure 1 A schematic flow chart of a method for determining landing impact stiffness provided in this application;

[0039] Figure 2A schematic diagram of a finite element model of a landing model and a ground model provided in this application;

[0040] Figure 3 for Figure 2 The schematic diagram of the deformation of the finite element model shown under unit load;

[0041] Figure 4 A schematic structural diagram of a landing impact stiffness determination device provided in this application;

[0042] Figure 5 This is a schematic diagram of the structure of an electronic device provided in this application. DETAILED DESCRIPTION

[0043] The embodiments of the present application provide a method for determining landing collision stiffness, thereby solving the technical problem in the prior art of relying on the experience of technicians to determine the collision stiffness in the early stages of design, resulting in low accuracy of the landing load of reusable rockets in the early stages of design.

[0044] The technical solution of the embodiment of the present application is to solve the above technical problems, and the overall idea is as follows:

[0045] A method for determining landing collision stiffness is disclosed for designing a reusable rocket. The method comprises: constructing a landing model based on design parameters of the reusable rocket; constructing a ground model based on preset parameters of a target recovery site for the reusable rocket; simulating the landing impact of the reusable rocket using the landing model and the ground model to obtain deformation parameters of the target model during the simulated landing impact, wherein the target model includes the landing model and the ground model; and determining the target collision stiffness of the reusable rocket based on the deformation parameters.

[0046] This embodiment constructs a landing model based on the design parameters of the reusable rocket, and constructs a ground model based on the preset parameters of the target recovery site. Then, through the landing model and the ground model, the landing impact of the reusable rocket is simulated, and the deformation parameters of the landing model and the ground model during the target process can be obtained. Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined, and the landing load can be calculated in the early design stage of the reusable rocket to provide clear input for the reusable rocket and improve the accuracy of the landing load of the reusable rocket in the early design stage.

[0047] In order to better understand the above technical solution, the above technical solution will be described in detail below with reference to the accompanying drawings and specific implementation methods.

[0048] First, the term "and / or" as used herein simply describes a relationship between associated objects, indicating that three possible relationships exist. For example, "A and / or B" can represent: A alone, A and B together, or B alone. Furthermore, the character " / " in this document generally indicates an "or" relationship between the associated objects.

[0049] In the early stages of reusable rocket design, before relevant testing is conducted, the landing loads are typically calculated using multibody dynamics models. The impact stiffness between the rocket and the ground directly determines the landing load, which is related to the landing mechanism and the physical properties of the ground. Related technologies rely primarily on the experience of technicians to determine this initial design impact stiffness, resulting in low accuracy in reusable rocket landing loads during this initial design phase.

[0050] In order to solve the above problems, this embodiment provides Figure 1 A method for determining landing impact stiffness is shown for designing a reusable rocket, and the method includes:

[0051] Step S11: construct a landing model according to the design parameters of the reusable rocket.

[0052] Specifically, a landing model is constructed based on the design parameters of the landing touchdown component of the reusable rocket, wherein the design parameters include the outer dimensions of the landing touchdown component.

[0053] More specifically, a landing model is constructed based on the design parameters and first physical parameters of the reusable rocket. The first physical parameters include a first elastic modulus and a first Poisson's ratio. An initial model can be constructed based on the design parameters of the reusable rocket, and then the first physical parameters are input into the initial model to obtain the landing model. Among them, the elastic modulus refers to the stress under a uniaxial stress state divided by the strain in that direction. The Poisson's ratio refers to the ratio of the absolute value of the lateral normal strain to the axial normal strain when the material is subjected to uniaxial tension or compression. The Poisson's ratio is also called the lateral deformation coefficient. It is an elastic constant that reflects the lateral deformation of the material.

[0054] For example, the landing contact member may be a square foot pad with an elastic modulus of E = 2.01 × 10 11 Pa, Poisson's ratio is σ = 0.3.

[0055] Step S12: constructing a ground model according to preset parameters of the target recovery site for the reusable rocket.

[0056] Specifically, a ground model is constructed according to preset parameters and second physical property parameters of the target recovery site, where the second physical property parameters include a second elastic modulus and a second Poisson's ratio.

[0057] For example, the target recovery site can be based on the design of the reusable rocket recovery site. When the target recovery site cannot be determined, the concrete floor can be used as the target recovery site. The concrete floor has a large ground stiffness and can cover most different ground materials. The elastic modulus of the concrete floor can be E = 3.08 × 10 10 Pa, Poisson's ratio is σ = 0.2.

[0058] After constructing the landing and ground models, the target mesh can be used to perform finite element meshing on them. The same meshing method must be used for both models to facilitate force and deformation analysis.

[0059] For example, if the landing contact component is a steel foot pad with dimensions of 0.26m in length, 0.2m in width, and 0.02m in thickness, the corresponding finite element models of the landing model and the ground model are as follows: Figure 2 As shown in the figure, the top portion is the footpad model, and the remaining portion is the ground model. Considering the square shape of the footpad, the finite element meshes for the footpad model and the ground model can be hexahedral to better simulate the deformation of the footpad and ground.

[0060] Step S13: Simulate the landing impact of the reusable rocket using the landing model and the ground model to obtain deformation parameters of the target model during the simulated landing impact process, where the target model includes the landing model and the ground model.

[0061] Specifically, target loads are applied to the landing model and displacement constraints are applied to the ground model to simulate the landing impact of a reusable rocket.

[0062] The target load primarily refers to the unit load, or force per unit area of the landing model. When the ground model collides with the landing model, some areas of the ground model will deform, while others will not. The boundary between the deformed and non-deformed areas can be considered to have zero displacement. Displacement constraints limit the deformation (or displacement) of the ground model.

[0063] For example, a unit load of 1 N (unit: Newton) is applied to the upper end surface of the landing model (i.e. Figure 2 The top of the model corresponds to the landing model), while the displacement constraint is applied to the bottom of the ground model (i.e. Figure 2 The bottom end of the figure is used to constrain the six degrees of freedom of the landing model and the ground model, and to simulate the deformation process of the landing touchdown components and the ground under unit load and displacement constraints.

[0064] During the simulation of the reusable rocket landing impact using the landing model and the ground model, both the landing model and the ground model will deform. Statics methods can be used to determine the deformation of the landing model and the ground model under unit load. The sum of the deformations of the landing model and the ground model is then used as the deformation parameter in step S13 of this embodiment.

[0065] Step S14: determining the target collision stiffness of the reusable rocket based on the deformation parameters.

[0066] Specifically, in the process of simulating the landing impact of a reusable rocket using the landing model and the ground model, the following can be obtained: Figure 3 The schematic diagram of the deformation of the finite element model under unit load is shown, and the maximum deformation parameters of the landing model and the ground model during the target process (the sum of the maximum deformation of the landing model and the maximum deformation of the ground model) can be obtained. Figure 3 The maximum deformation shown in the figure is 9.32×10 -11 m. According to the maximum deformation parameter, the target collision stiffness is determined, which can be seen in formula (1).

[0067]

[0068] Where, K: landing impact stiffness; l max : Maximum deformation parameter. According to the above formula, it can be calculated that under the current foot pad and concrete material, the landing collision stiffness is 1.07×10 10 N / m.

[0069] In summary, this embodiment constructs a landing model based on the design parameters of the reusable rocket, and constructs a ground model based on the preset parameters of the target recovery site. Then, through the landing model and the ground model, the landing impact of the reusable rocket is simulated, and the deformation parameters of the landing model and the ground model during the target process can be obtained. Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined, and the landing load can be calculated in the early design stage of the reusable rocket.

[0070] In engineering, especially in the early stages of design when there are no tests or empirical data, the calculation model for reusable rocket landing loads can be described by a simple spring-proton model, where collision stiffness and collision damping represent the magnitude of the restoring force and damping force, respectively, and thus the load. Collision damping is generally much smaller than collision stiffness, meaning that the damping force accounts for a relatively small proportion of the landing load. Therefore, the landing load is primarily determined by the restoring force, which is the product of collision stiffness and deformation.

[0071] The above method provides clear input for the calculation of reusable rocket landing payload. The payload calculation is relatively conservative, which improves the accuracy of the reusable rocket landing payload in the early stage of design and reduces the risk of repeated design.

[0072] Based on the same inventive concept, this embodiment provides Figure 4 A landing impact stiffness determination device is shown, which is used for designing a reusable rocket. The device includes:

[0073] A landing model construction module 41 is used to construct a landing model according to the design parameters of the reusable rocket;

[0074] a ground model building module 42 for building a ground model according to preset parameters of a target recovery site for a reusable rocket;

[0075] a deformation parameter acquisition module 43 for simulating a landing impact of a reusable rocket using a landing model and a ground model, and acquiring deformation parameters of a target model during the simulated landing impact process, wherein the target model includes the landing model and the ground model;

[0076] The target collision stiffness determination module 44 is used to determine the target collision stiffness of the reusable rocket based on the deformation parameters.

[0077] Furthermore, the landing model building module 41 includes:

[0078] The landing model construction submodule is used to construct a landing model according to the design parameters of the landing and touchdown components of the reusable rocket.

[0079] Furthermore, the landing model building module 41 includes:

[0080] The landing model construction submodule is used to construct a landing model based on the design parameters and first physical properties of the reusable rocket, where the first physical properties include a first elastic modulus and a first Poisson's ratio.

[0081] Furthermore, the ground model building module 42 includes:

[0082] The ground model construction submodule is used to construct a ground model according to preset parameters and second physical property parameters of the target recovery site, where the second physical property parameters include a second elastic modulus and a second Poisson's ratio.

[0083] Furthermore, the deformation parameter acquisition module 43 includes:

[0084] The simulation submodule is used to apply target loads to the landing model and displacement constraints to the ground model to simulate the landing impact of a reusable rocket.

[0085] Furthermore, the device also includes a grid division module, which is used to:

[0086] Before simulating the landing impact of a reusable rocket through the landing model and the ground model, the landing model and the ground model are meshed with finite elements using the target mesh.

[0087] Furthermore, the deformation parameter acquisition module 44 includes:

[0088] The maximum deformation parameter acquisition submodule is used to obtain the maximum deformation parameters of the landing model and the ground model during the target process;

[0089] The target collision stiffness determination module 44 includes:

[0090] The target collision stiffness determination submodule is used to determine the target collision stiffness according to the maximum deformation parameter.

[0091] Based on the same inventive concept, this embodiment provides Figure 5 An electronic device as shown includes:

[0092] Processor 51;

[0093] a memory 52 for storing instructions executable by the processor 51;

[0094] The processor 51 is configured to execute to implement a landing collision stiffness determination method.

[0095] Based on the same inventive concept, this embodiment provides a non-transitory computer-readable storage medium. When the instructions in the storage medium are executed by the processor 51 of the electronic device, the electronic device can implement a method for determining landing collision stiffness.

[0096] Since the electronic device described in this embodiment is an electronic device used to implement the information processing method in the embodiment of this application, based on the information processing method described in the embodiment of this application, those skilled in the art will be able to understand the specific implementation of the electronic device of this embodiment and its various variations, so how the electronic device implements the method in the embodiment of this application will not be described in detail here. As long as those skilled in the art implement the electronic device used by the information processing method in the embodiment of this application, it falls within the scope of protection to be provided by this application.

[0097] The technical solutions in the above embodiments of the present application have at least the following technical effects or advantages:

[0098] This embodiment constructs a landing model based on the design parameters of the reusable rocket, and constructs a ground model based on the preset parameters of the target recovery site. Then, through the landing model and the ground model, the landing impact of the reusable rocket is simulated, and the deformation parameters of the landing model and the ground model during the target process can be obtained. Based on the deformation parameters, the target collision stiffness of the reusable rocket is determined, and the landing load can be calculated in the early design stage of the reusable rocket to provide clear input for the reusable rocket and improve the accuracy of the landing load of the reusable rocket in the early design stage.

[0099] It will be understood by those skilled in the art that embodiments of the present invention may be provided as methods, systems, or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0100] The present invention is described with reference to flowcharts and / or block diagrams of methods, devices (systems), and computer program products according to embodiments of the present invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to a processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing device to produce a machine, so that the instructions executed by the processor of the computer or other programmable data processing device generate instructions for implementing the processes in the flowcharts and / or block diagrams. Figure 1 a process or multiple processes and / or boxes Figure 1 A device that provides the functions specified in a block or multiple blocks.

[0101] These computer program instructions may also be stored in a computer readable memory that can direct a computer or other programmable data processing device to work in a specific manner, so that the instructions stored in the computer readable memory produce an article of manufacture comprising an instruction device, which implements the process Figure 1 a process or multiple processes and / or boxes Figure 1 The function specified in one or more boxes.

[0102] These computer program instructions can also be loaded onto a computer or other programmable data processing device so that a series of operational steps are executed on the computer or other programmable device to produce a computer-implemented process, thereby providing the instructions executed on the computer or other programmable device for implementing the process. Figure 1 a process or multiple processes and / or boxes Figure 1A step that specifies a function in one or more boxes.

[0103] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments once they have learned the basic creative concept. Therefore, the appended claims are intended to be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0104] Obviously, those skilled in the art may make various changes and modifications to the present invention without departing from the spirit and scope of the present invention. Thus, if such changes and modifications fall within the scope of the claims and their equivalents, the present invention is intended to include such changes and modifications.

Claims

1. A method for determining landing impact stiffness, characterized in that: The method is used for designing a reusable rocket, and is applied to the initial design stage of a reusable rocket without any tests or experience. The method includes: constructing a landing model according to the design parameters of the reusable rocket; constructing a ground model according to preset parameters of a target recovery site for the reusable rocket; Simulating a landing impact of the reusable rocket using the landing model and the ground model to obtain deformation parameters of a target model during the simulated landing impact, wherein the target model includes the landing model and the ground model; wherein the deformations of the landing model and the ground model under a unit load are determined using a statics method, and the sum of the deformations of the landing model and the ground model is used as the deformation parameter; Determining a target collision stiffness of the reusable rocket according to the deformation parameter includes: Where, K is the landing impact stiffness; is the maximum deformation parameter, 1 means the unit load is 1N.

2. The method according to claim 1, wherein The step of constructing a landing model according to the design parameters of the reusable rocket comprises: A landing model is constructed according to the design parameters of the landing touchdown components of the reusable rocket.

3. The method according to claim 1, wherein The step of constructing a landing model according to the design parameters of the reusable rocket comprises: The landing model is constructed based on the design parameters and first physical properties of the reusable rocket, where the first physical properties include a first elastic modulus and a first Poisson's ratio.

4. The method according to claim 1, wherein The step of constructing a ground model according to preset parameters of the target recovery site of the reusable rocket comprises: The ground model is constructed according to preset parameters and second physical property parameters of the target recycling site, where the second physical property parameters include a second elastic modulus and a second Poisson's ratio.

5. The method according to claim 1, wherein The simulating the landing impact of the reusable rocket by using the landing model and the ground model includes: A target load is applied to the landing model, and a displacement constraint is applied to the ground model to simulate the landing impact of the reusable rocket.

6. The method according to claim 1, wherein Before simulating the landing impact of the reusable rocket using the landing model and the ground model, the method further includes: Finite element meshing is performed on the landing model and the ground model using the target mesh.

7. A landing collision stiffness determination device, characterized in that: Used for designing reusable rockets, and applied to the initial design stage of reusable rockets without any tests or experience, the device includes: a landing model construction module, configured to construct a landing model according to design parameters of the reusable rocket; a ground model construction module, configured to construct a ground model according to preset parameters of a target recovery site for the reusable rocket; a deformation parameter acquisition module, configured to simulate a landing impact of the reusable rocket using the landing model and the ground model, and acquire deformation parameters of a target model during the simulated landing impact, wherein the target model includes the landing model and the ground model; wherein the deformations of the landing model and the ground model under a unit load are determined using a statics method, and the sum of the deformations of the landing model and the ground model is used as the deformation parameter; A target collision stiffness determination module is used to determine the target collision stiffness of the reusable rocket based on the deformation parameter, including: Where, K is the landing impact stiffness; is the maximum deformation parameter, 1 means the unit load is 1N.

8. An electronic device, characterized in that: include: processor; a memory for storing instructions executable by the processor; The processor is configured to execute and implement a landing collision stiffness determination method according to any one of claims 1 to 6.

9. A non-transitory computer-readable storage medium, which, when instructions in the storage medium are executed by a processor of an electronic device, enables the electronic device to implement a landing collision stiffness determination method according to any one of claims 1 to 6.

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