CN113656891B - Liquid rocket dynamic characteristic modeling analysis method and terminal equipment - Google Patents
Liquid rocket dynamic characteristic modeling analysis method and terminal equipment Download PDFInfo
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Abstract
The invention discloses a liquid rocket dynamic characteristic modeling analysis method and terminal equipment, wherein the method comprises the following steps: performing mass substation on a plurality of rocket body structures in a liquid rocket to obtain a mass substation, acquiring index parameters of a propellant storage tank in the liquid rocket, and performing propellant modeling on the liquid rocket according to the index parameters so as to establish a coupling mass unit for obtaining the propellant; the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm. By adopting the method and the device, the technical problem that a propellant model which changes with time cannot be quickly established in the prior art can be solved.
Description
Technical Field
The invention relates to the technical field of carrier rockets, in particular to a liquid rocket dynamic characteristic modeling analysis method and terminal equipment.
Background
With the rapid development of liquid rockets, modeling accuracy is required and modeling rapidity is also required when rocket dynamic characteristic finite element models are built. Specifically, for a liquid rocket, as the propellant is continuously consumed during the flight, the rocket body quality characteristics are continuously changed, and when analyzing the movement characteristics of the liquid rocket at different moments, different rocket body movement characteristic models (also referred to as propellant models) need to be built for the propellant states at different moments.
In practice, the conventional liquid rocket dynamic characteristic modeling method considers the rationality of mass distribution and simultaneously considers the mass center of mass of the rocket and the matching property of the model. In order to achieve the purpose, the accuracy of model establishment is guaranteed, the arrow body characteristic model in each second state needs to iterate repeatedly, and repeated work or modeling consumes a great deal of time to influence the rapidity of model establishment.
Disclosure of Invention
According to the liquid rocket dynamic characteristic modeling analysis method, the technical problem that a propellant model which changes along with time cannot be quickly created in the prior art is solved, and the rapidity and the accuracy of modeling creation are realized.
In one aspect, the present application provides a method for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application, where the method includes:
carrying out mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, wherein a is a positive integer;
acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target sites, the target sites are any mass division site below the liquid level height in the a mass division sites, and n is a positive integer not exceeding a;
modeling the propellant of the liquid rocket according to the index parameters so as to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
Optionally, modeling the liquid rocket according to the index parameters to establish a coupled mass unit for obtaining the propellant further comprises:
and if the deviation value between the modeled propellant mass centroid and the propellant mass centroid exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
Optionally, modeling the liquid rocket according to the index parameters to establish a coupled mass unit for obtaining the propellant comprises:
according to the liquid level of the propellant and the positions of the n target stations, establishing coupling mass units at the corresponding mass sub-stations;
constructing an objective function of mass distribution optimization by using a particle swarm optimization algorithm according to the propellant mass, the propellant centroid and the liquid level;
calculating the respective propellant masses of the n target sites by using the target function;
and distributing corresponding propellant in the coupling quality unit according to the propellant quality of each of the n target stations.
Optionally, the objective function is:
wherein, objective is the objective function, M is the propellant mass, x cog For the propellant centroid, m i For the propellant mass, x of the ith target station i For the position of the ith target site, w 1 For a preset quality weight, w 2 Is a preset centroid weight.
Optionally, the population number adopted in the particle swarm optimization algorithm is n 1 S, the maximum iteration number is n 2 S, S; wherein n is 1 And n 2 And S is the number of target sites to be optimized, which are positioned at the front end and the rear end in the propellant mass of the n target sites.
Optionally, before modeling the propellant of the liquid rocket according to the index parameter, after the mass substation is performed on the plurality of rocket body structures in the liquid rocket, the method further comprises:
calculating cabin equivalent section parameters according to the cabin section shape of the liquid rocket, wherein the cabin section equivalent section parameters comprise a pulling-pressing equivalent sectional area, a bending equivalent section moment of inertia and a torque equivalent section polar moment of inertia;
establishing a cabin model according to the a mass division stations and the cabin equivalent section parameters so as to establish a plurality of beam units for obtaining the cabin;
and b beam units are established between two adjacent mass division stations, and b is a positive integer between 1 and 3.
Optionally, the method further comprises:
analyzing the coupling quality unit of the propellant by utilizing rocket dynamic characteristic analysis finite element software to obtain modal information of each station corresponding to a plurality of rocket structures;
wherein the modal information includes a tension-compression mode, a bending mode, and a torque mode.
Optionally, the method further comprises:
and screening and analyzing the modal information of each station corresponding to each arrow body structure to obtain the modal information of each arrow body structure.
Optionally, the screening and analyzing the modal information of each site corresponding to each arrow structure to obtain the modal information of each arrow structure includes:
splitting the modal information of each site in each arrow body structure into modal components along the directions of a plurality of degrees of freedom;
and carrying out maximum component screening and modal analysis on a plurality of modal components of each site in each arrow body structure to obtain modal information of each arrow body structure.
In another aspect, the present application provides, by an embodiment of the present application, a liquid rocket dynamic characteristics modeling analysis device, the device including: the system comprises a quality substation module, a parameter acquisition module and a modeling distribution module; wherein:
the mass substation module is used for carrying out mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation stations, wherein a is a positive integer;
the parameter acquisition module is used for acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target stations, the target stations are any mass station below the liquid level height in the a mass station, and n is a positive integer not exceeding a;
the modeling distribution module is used for modeling the propellant of the liquid rocket according to the index parameters so as to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
The specific details of the apparatus described in the embodiments of the present application may be referred to in the foregoing method embodiments, which are not described herein.
In another aspect, the present application provides, by an embodiment of the present application, a terminal device, including: a processor, a memory, a communication interface, and a bus; the processor, the memory and the communication interface are connected through the bus and complete communication with each other; the memory stores executable program code; the processor runs a program corresponding to the executable program code by reading the executable program code stored in the memory, for use in a liquid rocket dynamic characteristics modeling analysis method as provided above.
In another aspect, the present application provides, by an embodiment of the present application, a computer-readable storage medium storing program code for execution by a computing device. The program code includes instructions for performing the liquid rocket motor dynamic characteristics modeling analysis method as described above.
One or more technical solutions provided in the embodiments of the present application at least have the following technical effects or advantages: according to the method, mass substations are carried out on a plurality of rocket body structures in the liquid rocket to obtain a mass substations, index parameters of a propellant storage tank in the liquid rocket are obtained, then propellant modeling is carried out on the liquid rocket according to the index parameters so as to establish a coupling mass unit for obtaining the propellant, and finally mass distribution of the propellant is carried out on the propellant storage tank through the coupling mass unit by utilizing an objective function constructed by a particle swarm optimization algorithm. Therefore, the method not only can solve the technical problem that a propellant model which changes along with time cannot be quickly created in the prior art, but also can realize the rapidity and the accuracy of modeling creation, efficiently ensure the accuracy of modeling analysis of the quality and the mass center characteristics of the liquid rocket, and has high engineering application value.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic flow chart of a method for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application.
Fig. 2 is a schematic flow chart of another method for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application.
Fig. 3 is a schematic structural diagram of a liquid rocket dynamic characteristic modeling analysis device according to an embodiment of the present application.
Fig. 4 is a schematic structural diagram of a terminal device according to an embodiment of the present application.
Detailed Description
The embodiment of the application solves the technical problem that a propellant model which changes along with time cannot be quickly established in the prior art by providing the liquid rocket dynamic characteristic modeling analysis method.
The technical scheme of the embodiment of the application aims to solve the technical problems, and the overall thought is as follows: carrying out mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, wherein a is a positive integer; acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target sites, the target sites are any mass division site below the liquid level height in the a mass division sites, and n is a positive integer not exceeding a; modeling the propellant of the liquid rocket according to the index parameters so as to establish a coupling quality unit for obtaining the propellant; the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
In order to better understand the above technical solutions, the following detailed description will refer to the accompanying drawings and specific embodiments.
First, the term "and/or" appearing herein is merely an association relationship describing associated objects, meaning that there may be three relationships, e.g., a and/or B, may represent: a exists alone, A and B exist together, and B exists alone. In addition, the character "/" herein generally indicates that the front and rear associated objects are an "or" relationship.
The improved finite element modeling method for the dynamic characteristics analysis of the liquid rocket with strong adaptability is provided, and modeling of the liquid rocket, particularly modeling efficiency of a propellant is greatly improved. The specific process comprises the steps of giving the overall index parameters of the propellant, then carrying out automatic modeling, and finally carrying out quantitative evaluation on the accuracy of the built model. The advantage of this improvement is: on one hand, the method can quickly establish a propellant dynamic characteristic model which changes along with time, on the other hand, the accuracy of mass and mass center characteristics can be effectively ensured, and the method has high engineering application value.
Fig. 1 is a schematic flow chart of a method for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application. The method as shown in fig. 1 comprises the following implementation steps:
s101, mass substation is carried out on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, wherein a is a positive integer.
The liquid rocket includes a plurality of rocket body structures, such as a storage tank, an instrument cabin, a tail cabin and the like. The method can carry out structural mass substations on the liquid rocket, comprehensively consider calculation precision and efficiency, and distribute structural mass to a mass substations through the concentrated mass unit CONM, wherein a is a positive integer.
For a section (arrow structure) with a relatively uniform mass distribution, the distance between two adjacent mass distribution points is preferably selected between 0.3m and 0.5m, i.e. the distance between two adjacent mass distribution points is between 0.3m and 0.5m. On the contrary, for a section with uneven mass distribution, the distance between two adjacent mass division stations is preferably selected between 0.05m and 0.2 m. In other words, when modeling mass substations (or building a centralized mass model), rocket motor characteristics are adopted to analyze a second centralized mass unit CONM2 in finite element Nastran software, and the distance between the mass substations is selected to be within the interval of 0.05 m-0.35 m according to the structure mass distribution characteristics.
S102, acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target sites, the target sites are any mass division site below the liquid level height in the a mass division sites, and n is a positive integer not exceeding a.
Index parameters for the propellant tanks described herein include, but are not limited to, tank location (i.e., location x of each mass fraction station in the tank i ) The liquid level h of the storage tank (the liquid level of the propellant), the propellant mass M and the propellant mass center x cog Or other index parameter.
Optionally, the method can screen n target stations below the liquid level from a mass separation stations corresponding to the storage tank, wherein n is a positive integer not exceeding a. The locations of the n target sites may be expressed as { x } 1 x 2 … x n The mass of propellant to be dispensed for each targeted site can be expressed as { m } 1 m 2 … m n }。
S103, carrying out propellant modeling on the liquid rocket according to the index parameters so as to establish a coupling quality unit for obtaining the propellant; the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
The method can establish the coupling mass units at the corresponding mass division stations according to index parameters (such as storage tank positions, liquid levels and the like) of the propellant storage tanks, and then utilize the coupling mass units to carry out mass distribution of corresponding propellants in the storage tanks by adopting the constructed optimized objective function. In particular, the present application may be based on the mass M of the propellant, the mass x of the propellant cog And the liquid level h, constructing an objective function objective of mass distribution optimization by using a pre-configured particle swarm optimization algorithm; further optimizing and calculating the propellant mass to be distributed for n target sites (i.e. each mass division site) by using the objective function, and finally carrying out corresponding propellant in corresponding coupling mass units according to the corresponding propellant massAnd (5) distributing quality.
Optionally, the structural integrity and the mass and centroid of the tank are inspected after the tank is built, and if the modeled mass centroid of the propellant deviates significantly from the actual mass centroid of the propellant (e.g., the deviation value between the two exceeds a preset deviation value), then iterative adjustments and updates of the coupled mass units of the propellant are required. In order to improve the efficiency and accuracy of propellant modeling, the application proposes an improved propellant automatic modeling method. The method comprises the following steps:
in a specific embodiment, the application adopts a particle swarm optimization algorithm to perform optimization calculation, and the objective function constructed by the particle swarm optimization algorithm is shown in the following formula (1):
wherein, objective is the objective function, M is the propellant mass, x cog For the propellant centroid, m i For the propellant mass, x of the ith target station i For the position of the ith target site, w 1 For a preset quality weight, w 2 Is a preset centroid weight.
In the above formula (1), the objective is to model the composite objective function for the quality characteristics, and the mass centroid weight in the formula can be approximately set by the following formula (2):
w 1 M＝w 2 x cog formula (2)
To reduce the optimization parameters, the application can select n target sites { m } 1 m 2 … m n In the method, S target sites close to the front end and the rear end are subjected to quality optimization, and the quality distribution of other sites which do not participate in optimization is as followsPreferably, S is approximately taken as +.>
Optionally, when the particle swarm algorithm is used for quality optimization, the number of the adopted population P and the maximum iteration number N need to be adjusted according to the number of stations participating in optimization. Preferably, it is determined using the following equation (3):
wherein n is 1 And n 2 Is a positive integer, n 1 Preferably selected in the range of 20 to 40, n 2 Preferably in the range of 80 to 120.
It should be noted that the propellant of the present application may be simulated by using the first concentrated mass unit CONM1 in Nastran software. When modeling the propellant, the rotation inertia of the propellant is ignored due to the difference of physical properties of liquid and solid, and the translational mass characteristics of the propellant are the same in two directions of the transverse direction of the rocket; in the axial direction, the propellant mass is concentrated at the bottom of the reservoir.
According to the method, the propellant modeling problem is converted into the optimization problem through the improved scheme to perform rapid optimization modeling, and for the propellants in different second states, automatic modeling can be performed only by giving the overall parameters of the propellants. After modeling, the propellant modeling preparation can be quantitatively evaluated through an objective function.
In an alternative embodiment, please refer to fig. 2, which is a schematic flow chart of another method for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application. The method shown in fig. 2 (i.e., the finite element modeling flow for liquid rocket dynamics analysis) includes: mass substation modeling, cabin modeling, propellant modeling, submission analysis, modal screening and result extraction. The mass substation modeling and the propellant modeling can be specifically referred to in the foregoing descriptions of steps S101 and S102, and will not be described herein.
In cabin modeling, namely, a cabin model of the liquid rocket is established. According to the method, the cabin section equivalent section parameters can be calculated according to the cabin section shape of the liquid rocket, and the cabin section equivalent section parameters comprise a pulling and pressing equivalent sectional area A, a bending equivalent section moment of inertia I and a torsion equivalent section polar moment of inertia J. After determining the section parameters, the present application may also use the a mass substations determined in S101 to build a plurality of beam units of the cabin segment corresponding thereto. Preferably, between two adjacent mass division stations, 1 to 3 beam units are divided, and the stiffness characteristic of each beam unit is determined according to the section equivalent section parameters. The beam units can be simulated by adopting the mechanical energy of the CBEAM units in Nastran software, and 2 beam units are built or adopted between two adjacent mass sub-stations to be optimal.
The coupling quality unit obtained by propellant modeling can be submitted to Nastran software for analysis, so that modal identification and screening of the corresponding structure of the liquid rocket can be performed. Specifically, the coupling quality unit of the propellant can be analyzed by using Nastran software to obtain the modal information of each station of each rocket body structure in the liquid rocket, and the modal information is output to the Punch file. The modal information includes, but is not limited to, tension and compression modes, bending modes, torque modes, and the like.
In a specific embodiment, the present application may screen the modal information of each site of each arrow structure (which may be referred to as an output mode of the arrow structure), specifically split the modal information into modal components along multiple degrees of freedom directions, and further perform maximum component screening and modal analysis on the modal components, so as to obtain the modal information of each arrow structure. In the ith order mode of vibrationFor example, the application can split the motion vector into 6 modal components according to the degrees of freedom (such as three-direction translation and three-direction rotation)>In the i-order vibration mode, the mode information of the structure corresponding to the i-order vibration mode can be determined by adopting the following formula (4):
wherein,is->1 norm of direction.
In the result extraction, the method and the device can select corresponding mode information to carry out subsequent calculation and analysis according to actual working requirements. For example, the present application may utilize bending modes to calculate generalized aerodynamic loads of a liquid rocket, and the like.
According to the method, a mass substation is carried out on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, index parameters of a propellant storage tank in the liquid rocket are obtained, then propellant modeling is carried out on the liquid rocket according to the index parameters to establish a coupling mass unit for obtaining the propellant, and finally mass distribution of the propellant is carried out on the propellant storage tank through the coupling mass unit by utilizing an objective function constructed by a particle swarm optimization algorithm. Therefore, the method not only can solve the technical problem that a propellant model which changes along with time cannot be quickly created in the prior art, but also can realize the rapidity and the accuracy of modeling creation, efficiently ensure the accuracy of modeling analysis of the quality and the mass center characteristics of the liquid rocket, and has high engineering application value.
Please refer to fig. 3, which is a device for modeling and analyzing dynamic characteristics of a liquid rocket according to an embodiment of the present application, the device includes: a quality substation module 301, a parameter acquisition module 302 and a modeling allocation module 303; wherein:
the mass substation module 301 is configured to perform mass substation on a plurality of rocket structures in the liquid rocket to obtain a mass substations, where a is a positive integer;
the parameter obtaining module 302 is configured to obtain an index parameter of a propellant tank in the liquid rocket, where the index parameter includes a propellant mass of the propellant, a propellant centroid, a liquid level, and positions of n target sites, where the target sites are any mass site of the a mass sites that is below the liquid level, and n is a positive integer not exceeding a;
the modeling distribution module 303 is configured to perform propellant modeling on the liquid rocket according to the index parameter, so as to establish a coupled mass unit for obtaining the propellant;
the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
Optionally, the apparatus further comprises an update module 304;
the updating module 304 is configured to iteratively update the coupled mass unit of the propellant if the deviation value between the modeled mass centroid of the propellant and the mass centroid of the propellant exceeds a preset deviation value.
Optionally, the modeling allocation module 303 is specifically configured to:
according to the liquid level of the propellant and the positions of the n target stations, establishing coupling mass units at the corresponding mass sub-stations;
constructing an objective function of mass distribution optimization by using a particle swarm optimization algorithm according to the propellant mass, the propellant centroid and the liquid level;
calculating the respective propellant masses of the n target sites by using the target function;
and distributing corresponding propellant in the coupling quality unit according to the propellant quality of each of the n target stations.
Optionally, the objective function is:
wherein, objective is the objective function, M is the propellant mass, x cog For the propellant centroid, m i For the propellant mass, x of the ith target station i For the position of the ith target site, w 1 For a preset quality weight, w 2 Is a preset centroid weight.
Optionally, the population number adopted in the particle swarm optimization algorithm is n 1 S, the iteration times are n 2 S, S; wherein n is 1 And n 2 And S is the number of target sites to be optimized, which are positioned at the front end and the rear end in the propellant mass of the n target sites.
Optionally, the apparatus further comprises a calculation module 305 and a setup module 306, wherein:
the calculating module 305 is configured to calculate cabin equivalent section parameters according to a cabin section shape of the liquid rocket, where the cabin section equivalent section parameters include a pulling-pressing equivalent sectional area, a bending equivalent section moment of inertia, and a torque equivalent section polar moment of inertia;
the building module 306 is configured to perform a cabin model building according to the a mass division sites and the cabin equivalent section parameters, so as to build a plurality of beam units for obtaining the cabin;
and b beam units are established between two adjacent mass division stations, and b is a positive integer between 1 and 3.
Optionally, the apparatus further comprises an analysis module 307, wherein:
the analysis module 307 is configured to analyze the coupling quality unit of the propellant by using rocket dynamic characteristic analysis finite element software to obtain modal information of each station corresponding to the rocket structure;
optionally, the analysis module 307 is further configured to perform screening analysis on the modal information of each site corresponding to each arrow structure, so as to obtain the modal information of each arrow structure.
Optionally, the analysis module 307 is specifically configured to:
splitting the modal information of each site in each arrow body structure into modal components along the directions of a plurality of degrees of freedom;
and carrying out maximum component screening and modal analysis on a plurality of modal components of each site in each arrow body structure to obtain modal information of each arrow body structure.
Fig. 4 is a schematic structural diagram of a terminal device according to an embodiment of the present application. The terminal device as shown in fig. 4 includes: at least one processor 401, communication interface 402, user interface 403, and memory 404, the processor 401, communication interface 402, user interface 403, and memory 404 may be connected by a bus or otherwise, as exemplified by the embodiments of the present invention being connected by bus 405. Wherein,
the processor 401 may be a general-purpose processor such as a central processing unit (Central Processing Unit, CPU).
The communication interface 402 may be a wired interface (e.g., an ethernet interface) or a wireless interface (e.g., a cellular network interface or using a wireless local area network interface) for communicating with other terminals or websites. The user interface 403 may be a touch panel, including a touch screen and a touch screen, for detecting an operation instruction on the touch panel, and the user interface 403 may be a physical key or a mouse. The user interface 403 may also be a display screen for outputting, displaying images or data.
The Memory 404 may include Volatile Memory (RAM), such as random access Memory (Random Access Memory); the Memory may also include a Non-Volatile Memory (Non-Volatile Memory), such as a Read-Only Memory (ROM), a Flash Memory (Flash Memory), a Hard Disk (HDD), or a Solid State Drive (SSD); memory 404 may also include a combination of the above types of memory. The memory 404 is used for storing a set of program codes, and the processor 401 is used for calling the program codes stored in the memory 404 to perform the following operations:
carrying out mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, wherein a is a positive integer;
acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target sites, the target sites are any mass division site below the liquid level height in the a mass division sites, and n is a positive integer not exceeding a;
modeling the propellant of the liquid rocket according to the index parameters so as to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for distributing the mass of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
Optionally, modeling the liquid rocket according to the index parameters to establish a coupled mass unit for obtaining the propellant further comprises:
and if the deviation value between the modeled propellant mass centroid and the propellant mass centroid exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
Optionally, modeling the liquid rocket according to the index parameters to establish a coupled mass unit for obtaining the propellant comprises:
according to the liquid level of the propellant and the positions of the n target stations, establishing coupling mass units at the corresponding mass sub-stations;
constructing an objective function of mass distribution optimization by using a particle swarm optimization algorithm according to the propellant mass, the propellant centroid and the liquid level;
calculating the respective propellant masses of the n target sites by using the target function;
and distributing corresponding propellant in the coupling quality unit according to the propellant quality of each of the n target stations.
Optionally, the objective function is:
wherein, objective is the objective function, M is the propellant mass, x cog For the propellant centroid, m i For the propellant mass, x of the ith target station i To be the instituteThe position of the ith target site, w 1 For a preset quality weight, w 2 Is a preset centroid weight.
Optionally, the population number adopted in the particle swarm optimization algorithm is n 1 S, the iteration times are n 2 S, S; wherein n is 1 And n 2 And S is the number of target sites to be optimized, which are positioned at the front end and the rear end in the propellant mass of the n target sites.
Optionally, before the propellant modeling of the liquid rocket according to the index parameter, after the mass substation of the plurality of rocket body structures in the liquid rocket, the processor 401 is further configured to:
calculating cabin equivalent section parameters according to the cabin section shape of the liquid rocket, wherein the cabin section equivalent section parameters comprise a pulling-pressing equivalent sectional area, a bending equivalent section moment of inertia and a torque equivalent section polar moment of inertia;
establishing a cabin model according to the a mass division stations and the cabin equivalent section parameters so as to establish a plurality of beam units for obtaining the cabin;
and b beam units are established between two adjacent mass division stations, and b is a positive integer between 1 and 3.
Optionally, the method further comprises:
analyzing the coupling quality unit of the propellant by utilizing rocket dynamic characteristic analysis finite element software to obtain modal information of each station corresponding to a plurality of rocket structures;
wherein the modal information includes a tension-compression mode, a bending mode, and a torque mode.
Optionally, the processor 401 is further configured to:
and screening and analyzing the modal information of each station corresponding to each arrow body structure to obtain the modal information of each arrow body structure.
Optionally, the screening and analyzing the modal information of each site corresponding to each arrow structure to obtain the modal information of each arrow structure includes:
splitting the modal information of each site in each arrow body structure into modal components along the directions of a plurality of degrees of freedom;
and carrying out maximum component screening and modal analysis on a plurality of modal components of each site in each arrow body structure to obtain modal information of each arrow body structure.
The embodiment of the invention also provides a computer storage medium, wherein the computer storage medium can store a program, and the program can include part or all of the steps of the method described in the method embodiment when being executed.
Since the terminal described in this embodiment is a terminal device used for implementing the method for modeling and analyzing the dynamic characteristics of the liquid rocket in this embodiment, based on the method described in this embodiment, those skilled in the art can understand the specific implementation manner of the terminal and various modifications thereof, so how the terminal is implemented in this embodiment will not be described in detail herein. The terminals used by those skilled in the art to implement the methods in the embodiments of the present application are all within the scope of protection intended by the present application.
According to the method, a mass substation is carried out on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, index parameters of a propellant storage tank in the liquid rocket are obtained, then propellant modeling is carried out on the liquid rocket according to the index parameters to establish a coupling mass unit for obtaining the propellant, and finally mass distribution of the propellant is carried out on the propellant storage tank through the coupling mass unit by utilizing an objective function constructed by a particle swarm optimization algorithm. Therefore, the method not only can solve the technical problem that a propellant model which changes along with time cannot be quickly created in the prior art, but also can realize the rapidity and the accuracy of modeling creation, efficiently ensure the accuracy of modeling analysis of the quality and the mass center characteristics of the liquid rocket, and has high engineering application value.
It will be appreciated by those skilled in the art that 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 flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations 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. It is therefore intended that the following claims be interpreted as including the 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 modifications and variations can be made to the present invention without departing from the spirit or scope of the invention. Thus, it is intended that the present invention also include such modifications and alterations insofar as they come within the scope of the appended claims or the equivalents thereof.
Claims (8)
1. A method for modeling and analyzing dynamic characteristics of a liquid rocket, the method comprising:
carrying out mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation, wherein a is a positive integer;
acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass of the propellant, the propellant mass center, the liquid level height and the positions of n target sites, the target sites are any mass division site below the liquid level height in the a mass division sites, and n is a positive integer not exceeding a;
modeling the propellant of the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant, wherein the coupling quality unit comprises:
according to the liquid level of the propellant and the positions of the n target stations, establishing coupling mass units at the corresponding mass sub-stations;
constructing an objective function of mass distribution optimization by using a particle swarm optimization algorithm according to the propellant mass, the propellant centroid and the liquid level;
calculating the respective propellant masses of the n target sites by using the target function;
distributing corresponding propellants according to the respective propellant masses of the n target sites in the coupling mass unit;
the coupling mass unit is used for carrying out mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm;
the objective function is:
wherein, objective is the objective function, M is the propellant mass, x cog For the propellant centroid, m i For the propellant mass, x of the ith said target site i For the i-th position of the target site, w 1 For a preset quality weight, w 2 Is a preset centroid weight.
2. The method of claim 1, wherein modeling the liquid rocket for a propellant based on the index parameters to establish a coupled mass unit for obtaining the propellant further comprises:
and if the deviation value between the modeled propellant mass centroid and the propellant mass centroid exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
3. The method of claim 1, wherein the population number employed in the particle swarm optimization algorithm is n 1 S, the iteration times are n 2 S, S; wherein n is 1 And n 2 And S is the number of target sites to be optimized, which are positioned at the front end and the rear end in the propellant mass of the n target sites.
4. The method of claim 1, wherein prior to modeling the liquid rocket as a propellant based on the index parameters, the method further comprises, after mass-separating a plurality of rocket body structures in the liquid rocket:
calculating cabin equivalent section parameters according to the cabin section shape of the liquid rocket, wherein the cabin section equivalent section parameters comprise a pulling-pressing equivalent sectional area, a bending equivalent section moment of inertia and a torque equivalent section polar moment of inertia;
establishing a cabin model according to the a mass division stations and the cabin equivalent section parameters so as to establish a plurality of beam units for obtaining the cabin;
and b beam units are established between two adjacent mass division stations, and b is a positive integer between 1 and 3.
5. The method according to claim 1, wherein the method further comprises:
analyzing the coupling quality unit of the propellant by utilizing rocket dynamic characteristic analysis finite element software to obtain modal information of each station corresponding to a plurality of rocket structures;
wherein the modal information includes a tension-compression mode, a bending mode, and a torque mode.
6. The method of claim 5, wherein the method further comprises:
and screening and analyzing the modal information of each station corresponding to each arrow body structure to obtain the modal information of each arrow body structure.
7. The method according to claim 6, wherein the screening the modal information of each site corresponding to each arrow structure to obtain the modal information of each arrow structure includes:
splitting the modal information of each site in each arrow body structure into modal components along the directions of a plurality of degrees of freedom;
and carrying out maximum component screening and modal analysis on a plurality of modal components of each site in each arrow body structure to obtain modal information of each arrow body structure.
8. A terminal device, comprising: a processor, a memory, a communication interface, and a bus; the processor, the memory and the communication interface are connected through the bus and complete communication with each other; the memory stores executable program code; the processor runs a program corresponding to the executable program code by reading the executable program code stored in the memory for performing the liquid rocket motor performance modeling analysis method according to any one of claims 1-7.
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