CN113656891A - 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 modeling analysis method for dynamic characteristics of a liquid rocket 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 points, 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 to establish a coupling mass unit for acquiring the propellant; the coupling mass unit is used for performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm. By the method and the device, the technical problem that a propellant model changing along 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 the liquid rocket, when a rocket dynamic characteristic finite element model is built, not only the modeling accuracy is required, but also the modeling rapidity is required. Specifically, for a liquid rocket, mass characteristics of the rocket body are continuously changed along with continuous consumption of propellant in the flight process, and when dynamic characteristics of the liquid rocket at different moments are analyzed, different rocket body dynamic characteristic models (also called propellant models) need to be established according to propellant states at different moments.
In practice, the conventional liquid rocket dynamic characteristic modeling method considers the reasonability of mass distribution and also considers the matching of the mass center of the whole rocket and a model. In order to achieve the purpose, the accuracy of model establishment is ensured, repeated iteration is needed for the rocket body motion characteristic model of each second state, and the repeated work or modeling consumes a large amount of time and affects the rapidity of model establishment.
Disclosure of Invention
The embodiment of the application provides a modeling analysis method for dynamic characteristics of a liquid rocket, solves the technical problem that a propellant model changing along with time cannot be rapidly established in the prior art, and achieves rapidness and accuracy of modeling establishment.
In one aspect, the present application provides a modeling and analyzing method for dynamic characteristics of a liquid rocket according to an embodiment of the present application, where the method includes:
performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, 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, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass stations which are positioned below the liquid level height in the a mass stations, and n is a positive integer not exceeding a;
carrying out propellant modeling on the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
Optionally, said modeling propellant for said liquid rocket according to said indicator parameter to establish a coupled mass unit for said propellant further comprises:
and if the deviation value between the mass centroid of the propellant after modeling and the mass centroid of the propellant exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
Optionally, said modeling propellant for said liquid rocket according to said indicator parameter to establish a coupled mass unit for obtaining said propellant comprises:
establishing a coupling quality unit at the corresponding quality sub-station according to the liquid level of the propellant and the positions of the n target stations;
constructing a target function of mass distribution optimization by utilizing a particle swarm optimization algorithm according to the mass of the propellant, the mass center of the propellant and the height of the liquid level;
calculating the propellant quality of each of the n target stations by using the objective function;
and distributing corresponding propellants in the coupling quality unit according to the respective propellant qualities of the n target stations.
Optionally, the objective function is:
wherein object is the objective function, M is the propellant mass, xcogIs the center of mass of the propellant, miIs the propellant mass, x, of the ith target siteiIs the location of the ith target station, w1Is a preset mass weight, w2Is a preset centroid weight.
Optionally, the number of the populations used in the particle swarm optimization algorithm is n1S, the maximum iteration number is n2S; wherein n is1And n2And S is the number of target stations to be optimized at the front end and the rear end in the propellant quality of the n target stations.
Optionally, before the modeling the liquid rocket for propellant according to the index parameter, after the mass-splitting of the plurality of rocket body structures in the liquid rocket, the method further comprises:
calculating equivalent section parameters of the cabin section according to the sectional shape of the cabin section of the liquid rocket, wherein the equivalent section parameters of the cabin section comprise a tension and compression equivalent sectional area, a bending equivalent sectional inertia moment and a torque equivalent sectional polar inertia moment;
carrying out cabin section model establishment according to the a mass substation points and the cabin section equivalent section parameters to establish a plurality of beam units for obtaining the cabin section;
b beam units are established between two adjacent mass substations, 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 body structures;
wherein the mode information comprises a tension and 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 station corresponding to each arrow body structure to obtain the modal information of each arrow body structure includes:
splitting modal information of each station in each arrow body structure into modal components in a plurality of freedom directions;
and carrying out maximum component screening and modal analysis on the modal components of each station in each arrow body structure to obtain modal information of each arrow body structure.
In another aspect, the present application provides a liquid rocket dynamic characteristic modeling and analyzing apparatus according to an embodiment of the present application, where the apparatus includes: the system comprises a quality substation module, a parameter acquisition module and a modeling distribution module; wherein:
the mass substation module is used for performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substations, 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, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass station of the a mass stations below the liquid level height, and n is a positive integer not exceeding a;
the modeling distribution module is used for 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 performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
For the device described in the embodiment of the present application, reference may be made to the related descriptions in the foregoing method embodiments, and details are not repeated here.
On the other hand, the present application provides a terminal device according to an embodiment of the present application, where the terminal device includes: 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 mutual communication; the memory stores executable program code; the processor executes a program corresponding to the executable program code by reading the executable program code stored in the memory for a liquid rocket dynamics modeling analysis method as provided above.
In another aspect, the present application provides a computer-readable storage medium storing program code executed by a computing device, through an embodiment of the present application. The program code includes instructions for performing the liquid rocket dynamics modeling analysis method described above.
One or more technical solutions provided in the embodiments of the present application have at least the following technical effects or advantages: the method comprises the steps of performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, further obtaining index parameters of a propellant storage tank in the liquid rocket, then performing propellant modeling on the liquid rocket according to the index parameters to establish a coupling mass unit for obtaining the propellant, and finally performing mass distribution on the propellant in the propellant storage tank through an objective function constructed by the coupling mass unit through a particle swarm optimization algorithm. Therefore, the technical problem that a propellant model changing along with time cannot be quickly established in the prior art is solved, the rapidity and the accuracy of modeling establishment can be realized, the accuracy of modeling analysis of the mass and the mass center characteristic of the liquid rocket is effectively ensured, and the method has high engineering application value.
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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 modeling and analyzing method for dynamic characteristics of a liquid rocket, provided by an embodiment of the present application.
Fig. 2 is a schematic flow chart diagram of another liquid rocket dynamic characteristic modeling analysis method provided in the embodiment of the present application.
Fig. 3 is a schematic structural diagram of a liquid rocket dynamic characteristic modeling and analyzing device provided in 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 provides a modeling analysis method for dynamic characteristics of a liquid rocket, and solves the technical problem that a propellant model changing along with time cannot be quickly created in the prior art.
In order to solve the technical problems, the general idea of the embodiment of the application is as follows: performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, 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, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass stations which are positioned below the liquid level height in the a mass stations, and n is a positive integer not exceeding a; carrying out propellant modeling on the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant; the coupling mass unit is used for performing mass distribution 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 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.
The application provides an improved finite element modeling method for liquid rocket dynamic characteristic analysis, which has strong adaptability, and greatly improves the modeling efficiency of the liquid rocket, particularly the modeling efficiency of the propellant. The specific process comprises the steps of giving an overall index parameter of the propellant, then carrying out automatic modeling, and finally carrying out quantitative evaluation on the accuracy of the established model. The advantages of this improvement are: on one hand, a propellant dynamic characteristic model which changes along with time can be quickly established, on the other hand, the accuracy of the quality and the mass center characteristic can be effectively ensured, and the method has high engineering application value.
Please refer to fig. 1, which is a schematic flow chart of a modeling and analyzing method for 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, performing mass substation 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 described herein includes a plurality of rocket body structures, such as tanks, instrument pods, tail pods, and the like. According to the method, the structural mass substation can be carried out on the liquid rocket, the calculation precision and efficiency are comprehensively considered, the structural mass is distributed to a mass substations through the mass concentration unit CONM, and a is a positive integer.
For the section (arrow structure) with more uniform mass distribution, the distance between two adjacent mass sub-stations is preferably selected from 0.3m to 0.5m, namely the distance between two adjacent mass sub-stations is 0.3m to 0.5 m. On the contrary, for the section with uneven mass distribution, the distance between two adjacent mass sub-stations is preferably selected from 0.05m to 0.2 m. In other words, when the mass substation modeling is established (or the concentrated mass model is established), a rocket dynamic characteristic analysis is adopted for a second concentrated mass unit CONM2 in finite element Nastran software, and the distance between mass substations is selected to be within the range of 0.05 m-0.35 m according to the structural mass distribution characteristic.
S102, acquiring index parameters of a propellant storage tank in the liquid rocket, wherein the index parameters comprise the propellant mass, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass station in the a mass stations below the liquid level height, and n is a positive integer not exceeding a.
The indicator parameters for a propellant tank as described herein include, but are not limited to, the location of the tank (i.e., the location x of each mass-division point in the tank)i) Liquid level h of the tank (liquid level of the propellant), propellant mass M, propellant centroid xcogOr other index parameter.
Optionally, the method can screen n target stations below the liquid level from a mass sorting stations corresponding to the storage tank, wherein n is a positive integer not exceeding a. The locations of the n target sites may be represented as { x }1 x2 … xnThe mass of propellant required to be dispensed for each target station can be expressed as m1 m2 … mn}。
S103, carrying out propellant modeling on the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant; the coupling mass unit is used for performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
According to the method, the coupling quality unit can be established at the corresponding quality division station according to index parameters (such as the position of the storage tank, the liquid level and the like) of the propellant storage tank, and then the coupling quality unit is utilized to carry out the quality distribution of the corresponding propellant in the storage tank by adopting the established optimization objective function. Specifically, the application can be based on propellant mass M and propellant mass center xcogAnd the liquid level h, using the pre-prepared particle swarmAn optimization algorithm constructs a target function object of quality distribution optimization; and optimizing and calculating the mass of the propellant required to be distributed by the n target stations (namely each mass sub-station) by using the objective function, and finally distributing the corresponding mass of the propellant in the corresponding coupling mass unit according to the corresponding mass of the propellant.
Optionally, the mass and centroid of the tank and the structural integrity are checked 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 between the two exceeds a preset deviation), then iterative adjustments and updates to the coupled mass units of the propellant are required. In order to improve the efficiency and accuracy of propellant modeling, the application provides an improved automatic propellant modeling method. The method comprises the following specific steps:
in a specific embodiment, the particle swarm optimization algorithm is used for optimization calculation, and an objective function constructed by the particle swarm optimization algorithm is shown in the following formula (1):
wherein object is the objective function, M is the propellant mass, xcogIs the center of mass of the propellant, miIs the propellant mass, x, of the ith target siteiIs the location of the ith target station, w1Is a preset mass weight, w2Is a preset centroid weight.
In the above formula (1), objective is a comprehensive objective function for modeling the quality characteristic, and the mass centroid weight in the formula can be approximately set by the following formula (2):
w1M＝w2xcogformula (2)
In order to reduce optimization parameters, the application can select n target sites { m1 m2 … mnIn the method, the total S target sites close to the front end and the rear end are subjected to quality optimization, and the quality of other sites not participating in the optimization is distributed into
Preferably, S is preferably taken approximately as
Optionally, when the quality optimization is performed by using the particle swarm optimization, the number P of the population and the maximum iteration number N adopted by the method need to be adjusted according to the number of sites participating in the optimization. Preferably, it is suitably determined using the following formula (3):
wherein n is1And n2Is a positive integer, n1Preferably in the range of 20 to 40, n2Preferably in the range of 80-120.
It should be noted that the propellant of the present application can be simulated using the first lumped mass unit, CONM1, in the Nastran software. When the propellant is modeled, due to the difference of the physical properties of liquid and solid, the rotation inertia of the propellant is ignored, and the translational mass properties of the propellant are the same in two transverse directions of the rocket; in the axial direction, the propellant mass is concentrated at the bottom of the tank.
The propellant modeling problem is converted into the optimization problem through the improved scheme to carry out rapid optimization modeling, and the propellant with different second states can be automatically modeled only by giving the overall parameters of the propellant. After modeling, quantitative evaluation can be carried out on modeling preparation of the propellant through the objective function.
In an alternative embodiment, please refer to fig. 2, which is a schematic flow chart of another liquid rocket dynamic characteristic modeling and analyzing method provided in the embodiments of the present application. The method (i.e., the finite element modeling process for liquid rocket dynamics analysis) shown in fig. 2 includes: quality substation modeling, cabin section modeling, propellant modeling, submission analysis, modal screening and result extraction. For the mass substation modeling and the propellant modeling, reference may be made to the related explanations in the foregoing steps S101 and S102, and details are not described here.
In the cabin modeling, a cabin model of the liquid rocket is established. The equivalent section parameters of the cabin section can be calculated according to the sectional shape of the cabin section of the liquid rocket, and the equivalent section parameters of the cabin section comprise a tension and compression equivalent sectional area A, a bending equivalent sectional inertia moment I and a torsion equivalent sectional polar inertia moment J. After determining the section parameters, the present application may also establish a plurality of beam units of the cabin segment corresponding thereto using the a mass substations determined in S101. Preferably, 1-3 beam units are preferably divided between two adjacent mass substations, and the rigidity characteristic of each beam unit is determined according to equivalent section parameters of the sections. The beam units can be simulated by CBEAM unit mechanical energy in Nastran software, and 2 beam units are established between two adjacent mass substations or are optimized.
The coupling mass unit obtained by propellant modeling can be submitted to Nastran software for analysis so as to carry out modal identification and screening of corresponding structures of the liquid rocket. Specifically, the method can utilize Nastran software to analyze the coupling mass unit of the propellant so as to obtain the modal information of each station of each rocket body structure in the liquid rocket, and output the modal information to a Punch file. The modal information includes, but is not limited to, a tension mode, a bending mode, a torque mode, and the like.
In a specific embodiment, the application can screen modal information (which may be referred to as an output mode of the arrow body structure) of each station of each arrow body structure, specifically split the modal information into modal components along a plurality of degrees of freedom directions, and then perform maximum component screening and modal analysis on the modal components to obtain the modal information of each arrow body structure. In the ith order mode
For example, the present application can split the three-dimensional motion into 6 modal components according to the degrees of freedom (e.g., three-directional translation and three-directional rotation)
In the i-order mode, the following formula (4) is adopted by the application to determine the i-orderModal information of the structure corresponding to the vibration mode:
wherein the content of the first and second substances,
is composed of
A normal 1 norm.
In the result extraction process, the corresponding modal information can be selected according to the actual working requirement for subsequent calculation and analysis. For example, the present application may utilize bending modes to calculate the generalized aerodynamic loading of a liquid rocket, and the like.
By implementing the method, a mass substation is obtained by performing mass substation on a plurality of rocket body structures in the liquid rocket, index parameters of a propellant storage tank in the liquid rocket are further obtained, then propellant modeling is performed on the liquid rocket according to the index parameters to establish a coupling mass unit for obtaining the propellant, and finally the mass distribution of the propellant is performed in the propellant storage tank through an objective function constructed by the coupling mass unit through a particle swarm optimization algorithm. Therefore, the technical problem that a propellant model changing along with time cannot be quickly established in the prior art is solved, the rapidity and the accuracy of modeling establishment can be realized, the accuracy of modeling analysis of the mass and the mass center characteristic of the liquid rocket is effectively ensured, and the method has high engineering application value.
Please refer to fig. 3, which is a modeling and analyzing apparatus for dynamic characteristics of a liquid rocket according to an embodiment of the present application, the apparatus includes: a quality substation module 301, a parameter acquisition module 302 and a modeling distribution module 303; wherein:
the mass substation module 301 is configured to perform mass substation on a plurality of rocket body 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 index parameters of a propellant tank in the liquid rocket, where the index parameters include a propellant mass of the propellant, a propellant centroid, a liquid level height, and positions of n target stations, where the target stations are any one of the a mass substations located below the liquid level height, 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 to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for performing mass distribution 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 coupling mass unit of the propellant if a deviation value between the modeled mass center of the propellant and the mass center of the propellant exceeds a preset deviation value.
Optionally, the modeling assignment module 303 is specifically configured to:
establishing a coupling quality unit at the corresponding quality sub-station according to the liquid level of the propellant and the positions of the n target stations;
constructing a target function of mass distribution optimization by utilizing a particle swarm optimization algorithm according to the mass of the propellant, the mass center of the propellant and the height of the liquid level;
calculating the propellant quality of each of the n target stations by using the objective function;
and distributing corresponding propellants in the coupling quality unit according to the respective propellant qualities of the n target stations.
Optionally, the objective function is:
wherein object is theAn objective function, M being the propellant mass, xcogIs the center of mass of the propellant, miIs the propellant mass, x, of the ith target siteiIs the location of the ith target station, w1Is a preset mass weight, w2Is a preset centroid weight.
Optionally, the number of the populations used in the particle swarm optimization algorithm is n1S, the number of iterations is n2S; wherein n is1And n2And S is the number of target stations to be optimized at the front end and the rear end in the propellant quality of the n target stations.
Optionally, the apparatus further comprises a calculation module 305 and a building module 306, wherein:
the calculation module 305 is configured to calculate cabin equivalent section parameters according to a cabin section cross-sectional shape of the liquid rocket, where the cabin equivalent section parameters include a tension-compression equivalent sectional area, a bending equivalent sectional inertia moment, and a torque equivalent sectional polar inertia moment;
the establishing module 306 is configured to establish a cabin section model according to the a mass substations and the cabin section equivalent section parameters, so as to establish a plurality of beam units for obtaining the cabin section;
b beam units are established between two adjacent mass substations, 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 plurality of rocket body structures;
optionally, the analysis module 307 is further configured to perform screening analysis on the modal information of each station corresponding to each arrow body structure to obtain the modal information of each arrow body structure.
Optionally, the analysis module 307 is specifically configured to:
splitting modal information of each station in each arrow body structure into modal components in a plurality of freedom directions;
and carrying out maximum component screening and modal analysis on the modal components of each station in each arrow body structure to obtain modal information of each arrow body structure.
Please refer to fig. 4, which is a schematic structural diagram of a terminal device according to an embodiment of the present application. The terminal device shown in fig. 4 includes: at least one processor 401, a communication interface 402, a user interface 403 and a memory 404, wherein the processor 401, the communication interface 402, the user interface 403 and the memory 404 may be connected by a bus or other means, and the embodiment of the present invention is exemplified by being connected by a bus 405. Wherein the content of the first and second substances,
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 also be a physical button 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 (Volatile Memory), such as Random Access Memory (RAM); 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 (Hard Disk Drive, HDD), or a Solid-State Drive (SSD); the memory 404 may also comprise a combination of memories of the kind described above. 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 and executing the following operations:
performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, 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, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass stations which are positioned below the liquid level height in the a mass stations, and n is a positive integer not exceeding a;
carrying out propellant modeling on the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
Optionally, said modeling propellant for said liquid rocket according to said indicator parameter to establish a coupled mass unit for said propellant further comprises:
and if the deviation value between the mass centroid of the propellant after modeling and the mass centroid of the propellant exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
Optionally, said modeling propellant for said liquid rocket according to said indicator parameter to establish a coupled mass unit for obtaining said propellant comprises:
establishing a coupling quality unit at the corresponding quality sub-station according to the liquid level of the propellant and the positions of the n target stations;
constructing a target function of mass distribution optimization by utilizing a particle swarm optimization algorithm according to the mass of the propellant, the mass center of the propellant and the height of the liquid level;
calculating the propellant quality of each of the n target stations by using the objective function;
and distributing corresponding propellants in the coupling quality unit according to the respective propellant qualities of the n target stations.
Optionally, the objective function is:
wherein object is the objective function, M is the propellant mass, xcogIs the center of mass of the propellant, miIs the propellant mass, x, of the ith target siteiIs the location of the ith target station, w1Is a preset mass weight, w2Is a preset centroid weight.
Optionally, the number of the populations used in the particle swarm optimization algorithm is n1S, the number of iterations is n2S; wherein n is1And n2And S is the number of target stations to be optimized at the front end and the rear end in the propellant quality of the n target stations.
Optionally, before the modeling the liquid rocket for propellant according to the index parameter, after the mass-splitting of the plurality of rocket body structures in the liquid rocket, the processor 401 is further configured to:
calculating equivalent section parameters of the cabin section according to the sectional shape of the cabin section of the liquid rocket, wherein the equivalent section parameters of the cabin section comprise a tension and compression equivalent sectional area, a bending equivalent sectional inertia moment and a torque equivalent sectional polar inertia moment;
carrying out cabin section model establishment according to the a mass substation points and the cabin section equivalent section parameters to establish a plurality of beam units for obtaining the cabin section;
b beam units are established between two adjacent mass substations, 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 body structures;
wherein the mode information comprises a tension and 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 station corresponding to each arrow body structure to obtain the modal information of each arrow body structure includes:
splitting modal information of each station in each arrow body structure into modal components in a plurality of freedom directions;
and carrying out maximum component screening and modal analysis on the modal components of each station in each arrow body structure to obtain modal information of each arrow body structure.
An embodiment of the present invention further provides a computer storage medium, where the computer storage medium may store a program, and the program includes, when executed, some or all of the steps of the method described in the above method embodiment.
Since the terminal described in this embodiment is a terminal device used for implementing the modeling and analyzing method for liquid rocket dynamics characteristics in this embodiment, based on the method described in this embodiment, a person skilled in the art can understand the specific implementation of the terminal of this embodiment and various variations thereof, and therefore, a detailed description of how to implement the method in this embodiment by the terminal is omitted here. The terminal used by those skilled in the art to implement the method in the embodiments of the present application is within the scope of the protection intended by the present application.
By implementing the method, a mass substation is obtained by performing mass substation on a plurality of rocket body structures in the liquid rocket, index parameters of a propellant storage tank in the liquid rocket are further obtained, then propellant modeling is performed on the liquid rocket according to the index parameters to establish a coupling mass unit for obtaining the propellant, and finally the mass distribution of the propellant is performed in the propellant storage tank through an objective function constructed by the coupling mass unit through a particle swarm optimization algorithm. Therefore, the technical problem that a propellant model changing along with time cannot be quickly established in the prior art is solved, the rapidity and the accuracy of modeling establishment can be realized, the accuracy of modeling analysis of the mass and the mass center characteristic of the liquid rocket is effectively ensured, and the method has high engineering application value.
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 modeling and analyzing method for dynamic characteristics of a liquid rocket is characterized by comprising the following steps:
performing mass substation on a plurality of rocket body structures in the liquid rocket to obtain a mass substation points, 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, the propellant mass center, the liquid level height and the positions of n target stations of the propellant, the target stations are any mass stations which are positioned below the liquid level height in the a mass stations, and n is a positive integer not exceeding a;
carrying out propellant modeling on the liquid rocket according to the index parameters to establish a coupling quality unit for obtaining the propellant;
the coupling mass unit is used for performing mass distribution of the propellant in the propellant storage tank by utilizing an objective function constructed by a particle swarm optimization algorithm.
2. The method of claim 1, wherein said modeling the liquid rocket for propellant based on the target parameter to establish a coupled mass unit to obtain the propellant further comprises:
and if the deviation value between the mass centroid of the propellant after modeling and the mass centroid of the propellant exceeds a preset deviation value, iteratively updating the coupling mass unit of the propellant.
3. The method of claim 2, wherein the modeling the liquid rocket for propellant based on the index parameter to establish a coupled mass unit to obtain the propellant comprises:
establishing a coupling quality unit at the corresponding quality sub-station according to the liquid level of the propellant and the positions of the n target stations;
constructing a target function of mass distribution optimization by utilizing a particle swarm optimization algorithm according to the mass of the propellant, the mass center of the propellant and the height of the liquid level;
calculating the propellant quality of each of the n target stations by using the objective function;
and distributing corresponding propellants in the coupling quality unit according to the respective propellant qualities of the n target stations.
4. The method of claim 3, wherein the objective function is:
wherein object is the objective function, M is the propellant mass, xcogIs the center of mass of the propellant, miIs the propellant mass, x, of the ith target siteiIs the location of the ith target station, w1Is a preset mass weight, w2Is a preset centroid weight.
5. The method of claim 4, wherein the number of populations employed in the particle swarm optimization algorithm is n1S, the number of iterations is n2S; wherein n is1And n2And S is the number of target stations to be optimized at the front end and the rear end in the propellant quality of the n target stations.
6. A method as recited in claim 1, wherein prior to said modeling propellant for the liquid rocket as a function of the target parameter, after said mass-splitting of a plurality of rocket body structures in the liquid rocket, the method further comprises:
calculating equivalent section parameters of the cabin section according to the sectional shape of the cabin section of the liquid rocket, wherein the equivalent section parameters of the cabin section comprise a tension and compression equivalent sectional area, a bending equivalent sectional inertia moment and a torque equivalent sectional polar inertia moment;
carrying out cabin section model establishment according to the a mass substation points and the cabin section equivalent section parameters to establish a plurality of beam units for obtaining the cabin section;
b beam units are established between two adjacent mass substations, and b is a positive integer between 1 and 3.
7. The method of claim 1, further comprising:
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 body structures;
wherein the mode information comprises a tension and compression mode, a bending mode and a torque mode.
8. The method of claim 7, further comprising:
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.
9. The method according to claim 8, wherein the step of performing screening analysis on the modal information of the stations corresponding to each arrow body structure to obtain the modal information of each arrow body structure comprises the steps of:
splitting modal information of each station in each arrow body structure into modal components in a plurality of freedom directions;
and carrying out maximum component screening and modal analysis on the modal components of each station in each arrow body structure to obtain modal information of each arrow body structure.
10. 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 mutual communication; the memory stores executable program code; the processor executes a program corresponding to the executable program code by reading the executable program code stored in the memory for performing the liquid rocket dynamics modeling analysis method according to any one of claims 1-9 above.
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