CN114297896A - Method, device, equipment and medium for determining landing collision stiffness - Google Patents
Method, device, equipment and medium for determining landing collision stiffness Download PDFInfo
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- CN114297896A CN114297896A CN202111649674.0A CN202111649674A CN114297896A CN 114297896 A CN114297896 A CN 114297896A CN 202111649674 A CN202111649674 A CN 202111649674A CN 114297896 A CN114297896 A CN 114297896A
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Abstract
The invention discloses a method, a device, equipment and a medium for determining landing collision stiffness, which are used for designing a reusable rocket and comprise the following steps: constructing a landing model according to design parameters of the reusable rocket; constructing a ground model according to preset parameters of a target recovery site of the reusable rocket; simulating the landing impact of the reusable rocket through a landing model and a ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model; and determining the target collision stiffness of the reusable rocket according to the deformation parameters. According to the method and the device, the target collision stiffness of the reusable rocket can be determined, and then the landing load can be calculated in the design initial stage of the reusable rocket, so that definite input is provided for the reusable rocket, and the accuracy of the landing load of the reusable rocket in the design initial stage is improved.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a method, a device, equipment and a medium for determining landing collision stiffness.
Background
The reusable rocket undergoes several major processes including engine shutdown, free fall, collision with the ground, buffer buffering, successful landing, etc. during recovery landing. Wherein the "collision with the ground" process will directly affect the rocket body landing load magnitude. In the design process of the reusable rocket, the landing load needs to be calculated accurately so as to ensure that the finally constructed rocket body cabin section or single machine and other equipment cannot be damaged.
In the early design stage of the reusable rocket, no relevant test is developed, and the landing load of the rocket body can be generally calculated through a multi-body dynamic model, wherein the collision rigidity of the rocket body and the ground directly determines the magnitude of the landing load, and the collision rigidity is relevant to the landing mechanism and the ground physical parameters.
In the related art, the crash stiffness in the initial stage of design is determined mainly depending on the experience of a technician, resulting in low accuracy of landing load of the reusable rocket in the initial stage of design.
Disclosure of Invention
The embodiment of the application provides a method, a device, equipment and a medium for determining landing collision stiffness, solves the technical problem that the accuracy of landing load of a reusable rocket at the initial design stage is low due to the fact that the collision stiffness in the initial design stage is determined by depending on the experience of technicians in the prior art, and achieves the technical effect of determining the collision stiffness at the initial design stage of the reusable rocket so as to improve the accuracy of the landing load.
In a first aspect, the present application provides a method for determining landing crash stiffness for designing a reusable rocket, the method comprising:
constructing a landing model according to design parameters of the reusable rocket;
constructing a ground model according to preset parameters of a target recovery site of the reusable rocket;
simulating the landing impact of the reusable rocket through a landing model and a ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model;
and determining the target collision stiffness of the reusable rocket according to the deformation parameters.
Further, according to the design parameters of the reusable rocket, a landing model is constructed, and the method comprises the following steps:
and constructing a landing model according to the design parameters of the landing touchdown part of the reusable rocket.
Further, according to the design parameters of the reusable rocket, a landing model is constructed, and the method comprises the following steps:
and constructing a landing model according to the design parameters and the first physical parameters of the reusable rocket, wherein the first physical parameters comprise a first elastic modulus and a first Poisson's ratio.
Further, according to preset parameters of a target recovery site of the reusable rocket, a ground model is constructed, and the method comprises the following steps:
and constructing a ground model according to the preset parameters and second physical parameters of the target recovery site, wherein the second physical parameters comprise a second elastic modulus and a second Poisson ratio.
Further, the landing impact of the reusable rocket is simulated through the landing model and the ground model, and the simulation comprises the following steps:
and applying target load to the land model, and applying displacement constraint to the ground model to simulate the landing impact of the reusable rocket.
Further, before simulating a reusable rocket landing impact via the landing model and the ground model, the method further comprises:
finite element meshing is performed on the land model and the ground model using the target mesh.
Further, obtaining deformation parameters of the target model in the process of simulating the landing impact, including:
acquiring a maximum deformation parameter of a target model in a simulated landing impact process;
determining a target crash stiffness of the reusable rocket based on the deformation parameters, comprising:
and determining the target collision stiffness according to the maximum deformation parameter.
In a second aspect, the present application provides a landing crash stiffness determination apparatus for designing a reusable rocket, the apparatus comprising:
the landing model building module is used for building a landing model according to the design parameters of the reusable rocket;
the ground model building module is used for building a ground model according to preset parameters of a target recovery field of the reusable rocket;
the deformation parameter acquisition module is used for simulating the landing impact of the reusable rocket through the landing model and the ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model;
and the target collision stiffness determining module is used for determining the target collision stiffness of the reusable rocket according to the deformation parameters.
In a third aspect, the present application provides an electronic device, comprising:
a processor;
a memory for storing processor-executable instructions;
wherein the processor is configured to execute to implement a method of landing impact stiffness determination.
In a fourth aspect, the present application provides a non-transitory computer readable storage medium having instructions that, when executed by a processor of an electronic device, enable the electronic device to perform implementing a method for determining a stiffness to landing impact.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages:
according to the method, the landing model is built according to the design parameters of the reusable rocket, the ground model is built according to the preset parameters of the target recovery field, the landing impact of the reusable rocket is simulated through the landing model and the ground model, the deformation parameters of the landing model and the ground model in the target process can be acquired, the target impact rigidity of the reusable rocket is determined according to the deformation parameters, the landing load can be calculated in the initial design stage of the reusable rocket, clear input can be provided for the landing load calculation of the reusable rocket, the load calculation is conservative, the accuracy of the landing load of the reusable rocket is improved in the initial design stage, and the repeated risk of scheme design is reduced.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments are briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on the drawings without creative efforts.
FIG. 1 is a schematic flow chart of a method for determining stiffness for landing collision according to the present application;
FIG. 2 is a schematic diagram of a finite element model of a landing model and a ground model provided herein;
FIG. 3 is a schematic view of the finite element model of FIG. 2 corresponding to deformation under unit load;
FIG. 4 is a schematic structural diagram of a landing impact stiffness determination apparatus provided in the present application;
fig. 5 is a schematic structural diagram of an electronic device provided in the present application.
Detailed Description
The embodiment of the application provides a method for determining landing impact stiffness, and solves the technical problem that the accuracy of landing load of a reusable rocket at the initial design stage is low due to the fact that the impact stiffness at the initial design stage is determined by means of experience of technicians in the prior art.
In order to solve the technical problems, the general idea of the embodiment of the application is as follows:
a landing crash stiffness determination method for designing a reusable rocket, the method comprising: constructing a landing model according to design parameters of the reusable rocket; constructing a ground model according to preset parameters of a target recovery site of the reusable rocket; simulating the landing impact of the reusable rocket through a landing model and a ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model; and determining the target collision stiffness of the reusable rocket according to the deformation parameters.
According to the method, the landing model is built according to the design parameters of the reusable rocket, the ground model is built according to the preset parameters of the target recovery site, the landing impact of the reusable rocket is simulated through the landing model and the ground model, the deformation parameters of the landing model and the ground model in the target process can be obtained, the target impact stiffness of the reusable rocket is determined according to the deformation parameters, the landing load can be calculated in the initial design stage of the reusable rocket, clear input is provided for the reusable rocket, and the accuracy of the landing load of the reusable rocket in the initial design stage is improved.
In order to better understand the technical solution, the technical solution will be described in detail with reference to the drawings and the specific embodiments.
First, it is stated that the term "and/or" appearing herein is merely one type of associative relationship that describes an associated object, meaning that three types of relationships may exist, e.g., a and/or B may mean: a exists alone, A and B exist simultaneously, and B exists alone. In addition, the character "/" herein generally indicates that the former and latter related objects are in an "or" relationship.
In the early design stage of the reusable rocket, no relevant test is developed, and the landing load of the rocket body can be generally calculated through a multi-body dynamic model, wherein the collision rigidity of the rocket body and the ground directly determines the magnitude of the landing load, and the collision rigidity is relevant to the landing mechanism and the ground physical parameters. In the related art, the crash stiffness in the initial stage of design is determined mainly depending on the experience of a technician, resulting in low accuracy of landing load of the reusable rocket in the initial stage of design.
In order to solve the above problem, the present embodiment provides a method for determining a landing collision stiffness as shown in fig. 1, which is used for designing a reusable rocket, and includes:
and step S11, constructing a landing model according to the design parameters of the reusable rocket.
Specifically, a landing model is constructed according to design parameters of a landing touchdown member of the reusable rocket. Wherein the design parameters include the physical dimensions of the landing ground contacting member.
More specifically, a landing model is constructed based on design parameters of the reusable rocket and first physical parameters, the first physical parameters including a first modulus of elasticity and a first poisson's ratio. The initial model can be constructed according to the design parameters of the reusable rocket, and then the first physical property parameters are input into the initial model to obtain the landing model. The elastic modulus is the stress divided by the strain in the direction under unidirectional stress. The poisson ratio is the ratio of the absolute value of transverse positive strain and axial positive strain when a material is unidirectionally pulled or pressed, and is also called a transverse deformation coefficient, which is an elastic constant reflecting the transverse deformation of the material.
For example, the landing ground engaging member may be a square foot pad having an elastic modulus E of 2.01 × 1011Pa, Poisson's ratio of σ＝0.3。
And step S12, constructing a ground model according to the preset parameters of the target recovery site of the reusable rocket.
Specifically, a ground model is constructed according to preset parameters and second physical parameters of the target recovery site, wherein the second physical parameters comprise a second elastic modulus and a second Poisson's ratio.
For example, the target recovery site can be recovered according to the design of the reusable rocket, when the target recovery site cannot be determined, the concrete ground can be used as the target recovery site, the ground rigidity of the concrete ground is high, and most of the grounds made of different materials can be wrapped. The elastic modulus of the concrete floor can be 3.08 × 10 ═ E10Pa, poisson's ratio σ is 0.2.
After the landing model and the ground model are constructed, finite element meshing may be performed against the land model and the ground model using the target mesh. Aiming at the landing model and the ground model, the same grid needs to be adopted for division so as to facilitate the stress analysis and the deformation analysis of the landing model and the ground model.
For example, if the landing ground contacting member is a steel foot pad, the dimensions are 0.26m long, 0.2m wide, and 0.02m thick, and the finite element models of the corresponding landing model and ground model are shown in fig. 2. Wherein, the top is a foot pad model, and the rest is a ground model. Considering the foot pad as square, the finite element mesh of the foot pad model and the ground model can be hexahedral mesh for better simulating the foot pad and ground deformation.
And step S13, simulating the landing impact of the reusable rocket through the landing model and the ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model.
Specifically, a target load is applied to the land model and displacement constraints are applied to the ground model to simulate a reusable rocket landing impact.
The target load mainly refers to a unit load, i.e., a force received per unit area in the landing model. When the ground model collides with the landing model, a partial region of the ground model is deformed, another partial region is not deformed, and a boundary region where the deformation occurs and the deformation does not occur may be regarded as a displacement of 0. The displacement constraint is defined as the deformation (or displacement) of the ground model.
For example, a unit load 1N (unit: cattle) is applied to the upper end surface of the landing model (namely, the landing model corresponding to the top in FIG. 2), and a displacement constraint is applied to the lowest end (namely, the bottom end in FIG. 2) of the ground model, so as to constrain the six degrees of freedom of the landing model and the ground model, and the six degrees of freedom are used for simulating the deformation process of the landing ground contacting component and the ground under the unit load and the displacement constraint.
In the process of simulating landing impact of the reusable rocket by using the landing model and the ground model, the landing model and the ground model are both deformed, the deformation of the landing model and the ground model under unit load can be determined by using a statics method, and then the sum of the deformation of the landing model and the deformation of the ground model is taken as the deformation parameter of the step S13 in the embodiment.
And step S14, determining the target collision stiffness of the reusable rocket according to the deformation parameters.
Specifically, in the process of simulating the reusable rocket landing impact by the landing model and the ground model, a schematic diagram corresponding to the deformation of the finite element model under the unit load as shown in fig. 3 can be obtained, and then the maximum deformation parameters (the sum of the maximum deformation of the landing model and the maximum deformation of the ground model) of the landing model and the ground model in the target process can be obtained. The maximum deformation shown in fig. 3 is 9.32 × 10-11And m is selected. And determining the target collision stiffness according to the maximum deformation parameter, which can be seen in formula (1).
Wherein, K: landing impact stiffness; lmax: a maximum deformation parameter. According to the formula, the landing impact rigidity can be calculated to be 1.07 multiplied by 10 under the current foot pad and concrete material10N/m。
In summary, in the embodiment, the landing model is constructed according to the design parameters of the reusable rocket, the ground model is constructed according to the preset parameters of the target recovery site, the landing impact of the reusable rocket is simulated through the landing model and the ground model, the deformation parameters of the landing model and the ground model in the target process can be further obtained, the target impact stiffness of the reusable rocket is determined according to the deformation parameters, and the landing load can be further calculated in the initial design stage of the reusable rocket.
In engineering, especially in the case of no experimental inexperienced values at the initial design stage, the reusable rocket landing load calculation model can be described by a simple spring proton model, wherein the collision stiffness and the collision damping respectively represent the magnitude of the restoring force and the damping force, namely the magnitude of the load. Crash damping is generally much less than crash stiffness, i.e. the damping force is smaller in the landing load, so the magnitude of the landing load is mainly determined by the restoring force, i.e. the product of crash stiffness and deformation.
The method provides clear input for the landing load calculation of the reusable rocket, the load calculation is conservative, the landing load accuracy of the reusable rocket is improved in the initial design stage, and the repeated risk of scheme design is reduced.
Based on the same inventive concept, the present embodiment provides a landing collision stiffness determination apparatus as shown in fig. 4, for designing a reusable rocket, the apparatus including:
a landing model construction module 41, configured to construct a landing model according to design parameters of the reusable rocket;
a ground model construction module 42, configured to construct a ground model according to preset parameters of a target recycling site of the reusable rocket;
a deformation parameter obtaining module 43, configured to simulate the landing impact of the reusable rocket through a landing model and a ground model, and obtain a deformation parameter of a target model in a simulated landing impact process, where the target model includes the landing model and the ground model;
and a target collision stiffness determination module 44 for determining a target collision stiffness of the reusable rocket according to the deformation parameter.
Further, the landing model building module 41 includes:
and the landing model building submodule is used for building a landing model according to the design parameters of the landing touchdown part of the reusable rocket.
Further, the landing model building module 41 includes:
and the landing model building submodule is used for building a landing model according to the design parameters and the first physical parameters of the reusable rocket, and the first physical parameters comprise a first elastic modulus and a first Poisson's ratio.
Further, the ground model building module 42 includes:
and the ground model building submodule is used for building a ground model according to the preset parameters and the second physical parameters of the target recovery site, and the second physical parameters comprise a second elastic modulus and a second Poisson ratio.
Further, the deformation parameter obtaining module 43 includes:
and the simulation submodule is used for applying target load to the land model and applying displacement constraint to the ground model so as to simulate the landing impact of the reusable rocket.
Further, the apparatus further comprises a meshing module configured to:
before simulating landing impact of the reusable rocket through the landing model and the ground model, finite element meshing is carried out on the land model and the ground model by using a target mesh.
Further, the deformation parameter obtaining module 44 includes:
the maximum deformation parameter acquisition submodule is used for acquiring the maximum deformation parameters of the landing model and the ground model in the target process;
a target crash stiffness determination module 44 comprising:
and the target collision stiffness determining submodule is used for determining the target collision stiffness according to the maximum deformation parameter.
Based on the same inventive concept, the present embodiment provides an electronic device as shown in fig. 5, including:
a processor 51;
a memory 52 for storing instructions executable by the processor 51;
wherein the processor 51 is configured to execute to implement a landing impact stiffness determination method.
Based on the same inventive concept, the present embodiment provides a non-transitory computer-readable storage medium, when instructions in the storage medium are executed by the processor 51 of the electronic device, so that the electronic device can perform the method of implementing a landing impact stiffness determination method.
Since the electronic device described in this embodiment is an electronic device used for implementing the method for processing information in this embodiment, a person skilled in the art can understand the specific implementation manner of the electronic device of this embodiment and various variations thereof based on the method for processing information described in this embodiment, and therefore, how to implement the method in this embodiment by the electronic device is not described in detail here. Electronic devices used by those skilled in the art to implement the method for processing information in the embodiments of the present application are all within the scope of the present application.
The technical scheme in the embodiment of the application at least has the following technical effects or advantages:
according to the method, the landing model is built according to the design parameters of the reusable rocket, the ground model is built according to the preset parameters of the target recovery site, the landing impact of the reusable rocket is simulated through the landing model and the ground model, the deformation parameters of the landing model and the ground model in the target process can be obtained, the target impact stiffness of the reusable rocket is determined according to the deformation parameters, the landing load can be calculated in the initial design stage of the reusable rocket, clear input is provided for the reusable rocket, and the accuracy of the landing load of the reusable rocket in the initial design stage is improved.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
While preferred embodiments of the present invention have been described, additional variations and modifications in those embodiments may occur to those skilled in the art once they learn of the basic inventive concepts. Therefore, it is intended that the appended claims be interpreted as including preferred embodiments and all such alterations and modifications as fall within the scope of the invention.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present invention without departing from the spirit and scope of the invention. Thus, if such modifications and variations of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is also intended to include such modifications and variations.
Claims (10)
1. A method for determining landing crash stiffness for designing a reusable rocket, the method comprising:
constructing a landing model according to the design parameters of the reusable rocket;
constructing a ground model according to preset parameters of the target recovery site of the reusable rocket;
simulating the landing impact of the reusable rocket through the landing model and the ground model, and acquiring deformation parameters of a target model in the process of simulating the landing impact, wherein the target model comprises the landing model and the ground model;
and determining the target collision stiffness of the reusable rocket according to the deformation parameters.
2. The method of claim 1, wherein constructing a landing model based on design parameters of the reusable rocket comprises:
and constructing a landing model according to the design parameters of the landing touchdown part of the reusable rocket.
3. The method of claim 1, wherein constructing a landing model based on design parameters of the reusable rocket comprises:
and constructing the landing model according to the design parameters and first physical parameters of the reusable rocket, wherein the first physical parameters comprise a first elastic modulus and a first Poisson's ratio.
4. The method of claim 1, wherein constructing a ground model based on preset parameters of a target recovery site of the reusable rocket comprises:
and constructing the ground model according to preset parameters and second physical parameters of the target recovery site, wherein the second physical parameters comprise a second elastic modulus and a second Poisson ratio.
5. The method of claim 1, wherein the simulating the reusable rocket landing impact via the landing model and the ground model comprises:
applying a target load to the landing model and applying displacement constraints to the ground model to simulate the reusable rocket landing impact.
6. The method of claim 1, wherein prior to simulating the reusable rocket landing impact via the landing model and the ground model, the method further comprises:
using a target mesh, performing finite element meshing on the landing model and the ground model.
7. The method of claim 1, wherein obtaining deformation parameters for the target model during the simulated landing impact comprises:
acquiring a maximum deformation parameter of the target model in a simulated landing impact process;
determining a target crash stiffness of the reusable rocket based on the deformation parameters, comprising:
and determining the target collision stiffness according to the maximum deformation parameter.
8. A landing impact stiffness determination apparatus for designing a reusable rocket, the apparatus comprising:
the landing model building module is used for building a landing model according to the design parameters of the reusable rocket;
the ground model building module is used for building a ground model according to preset parameters of a target recovery field of the reusable rocket;
a deformation parameter obtaining module, configured to simulate the landing impact of the reusable rocket through the landing model and the ground model, and obtain a deformation parameter of a target model in a simulated landing impact process, where the target model includes the landing model and the ground model;
and the target collision stiffness determining module is used for determining the target collision stiffness of the reusable rocket according to the deformation parameters.
9. An electronic device, comprising:
a processor;
a memory for storing the processor-executable instructions;
wherein the processor is configured to execute to implement a landing impact stiffness determination method as claimed in any one of claims 1 to 7.
10. A non-transitory computer readable storage medium having instructions therein which, when executed by a processor of an electronic device, enable the electronic device to perform implementing a landing impact stiffness determination method as claimed in any one of claims 1 to 7.
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| CN202111649674.0A CN114297896A (en) | 2021-12-29 | 2021-12-29 | Method, device, equipment and medium for determining landing collision stiffness |
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