CN111368391B - Model conversion method oriented to carrier rocket system simulation - Google Patents
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Abstract
The invention relates to a model conversion method oriented to carrier rocket system simulation, which comprises the following steps: constructing a system architecture model; extracting physical information of each component in the architecture model; comparing the imported architecture model with a history record in the automatic generation module; screening parameters in the architecture model; layout is carried out on the simulation model to be generated; and automatically connecting each component model in the simulation models after layout to form a complete system simulation model. The invention establishes a unified interface of information interaction between the architecture model and the system simulation model, and realizes automatic and rapid generation of the system simulation model by extracting the equipment names and the connection relations in the architecture model and comparing and matching the equipment names and the connection relations with the component models in the system simulation model, thereby avoiding low-efficiency repeated modeling and improving the efficiency of the system architecture design to simulation closed-loop verification.
Description
Technical Field
The invention belongs to the technical field of simulation of space product systems, and relates to a model conversion method for carrier rocket system simulation.
Background
Space product development is a very complex system engineering and is the result of cooperative work among typical multiple enterprises, multiple areas, multiple professions and multiple systems. At present, the traditional document-based mode is adopted by the main court of China for transmitting data and information, and the mode has great defects in terms of information accuracy and timeliness, and is difficult to adapt to the increasingly strong market competition and the development requirements of new-generation aerospace model products.
Therefore, research on product models and data collaborative technologies among different aerospace units has become an important subject for promoting the improvement of the development capacity of aerospace. Through research of a model and a data interaction mode based on unified specifications, a digital collaborative process and a conversion method between heterogeneous models of each stage are constructed and designed, the butt joint property and time variability of the models can be effectively enhanced, and therefore consistency and uniqueness of product data are guaranteed.
Because the carrier rocket product has fixed task scene (usually the effective load is transmitted to a certain track), the system composition and the configuration difference between various models are small, the characteristics of repeated use and the like are not considered, the system architecture design of the newly developed model is mainly inherited, and the work from the architecture forward design to the simulation closed loop verification is seldom developed. At present, the common practice at home and abroad is to directly embody the architecture information in the system simulation model instead of independently establishing the architecture model, so that the problem is that the system simulation model must be rebuilt when the system architecture is changed, and the design efficiency is low.
Disclosure of Invention
The invention solves the technical problems that: the model conversion method for the carrier rocket system simulation is provided, and the timeliness, accuracy and completeness of engineering development information interaction are better improved by establishing the association relationship between a system architecture model based on the model and a simulation model, so that verification and quality control of the development earlier stage are enhanced.
The solution of the invention is as follows:
a model conversion method for carrier rocket system simulation includes the steps:
step 1: constructing a system architecture model;
step 2, extracting physical information of each component in the architecture model, including mass flow information of gas and liquid, change information of temperature and transmission information of pressure, so as to obtain a component model;
step 3, identifying the composition, the equipment name, the equipment description, the connection relation and the position relation of the architecture model according to the physical information of each component and in combination with the agreed format;
step 4, comparing the imported architecture model with the history record in the automatic generation module by using the architecture model name as a unique identification mark to determine whether the imported architecture model is imported for the first time;
step 5, if the file is the first imported file, associating the equipment in the file with the model in the simulation model library, and performing one-to-one correspondence between the equipment in the architecture model and the component model in the simulation model library by taking the equipment name as a unique identification mark;
step 6, if the architecture model file is not imported for the first time, comparing the architecture model with the architecture model in the history record, determining a modified part in the newly-read architecture model, and performing incremental modification on the system simulation model;
step 7, screening parameters in the architecture model and correlating the parameters with the parameters in the simulation model; reading parameters contained in each device in the architecture model, taking the parameter name as a unique identification mark, and carrying out one-to-one correspondence on the parameters in the device and the parameters in the simulation model; if the parameters in the equipment correspond to the parameters in the simulation model, the corresponding parameters are removed, and the final data can be manually confirmed by a user;
step 8, comparing the composition and the position relation of the system architecture model, and laying out the simulation model to be generated, so as to ensure that the generated simulation model truly reflects the composition and the position relation of equipment in the system architecture model;
and 9, automatically connecting all the component models in the simulation models after layout, and connecting interfaces between the component models according to information provided by the architecture models to form a complete system simulation model.
Preferably, the method for constructing the system architecture model is as follows:
(1) Modeling of top-level physical structure
According to the top layer file of the carrier rocket, establishing a relationship between an internal physical system and an external physical system physical module, and establishing a physical structure model of the power system according to the specific association relationship between the physical modules;
(2) System attribute parameter modeling
After a top physical structure model of the system is established, supplementing attribute information of a single-machine module in a pressurizing subsystem in the power system, wherein the single-machine module comprises an electromagnetic valve single-machine module, an orifice single-machine module, a one-way valve single-machine module and a storage tank single-machine module;
(3) Modeling of physical structure of pressurizing conveying system
According to a principle diagram of the pressurizing and conveying system, a defining physical module of the pressurizing and conveying system is extracted, and a physical structure composition model of the power system is built according to the specific mutual position relation among the modules and the relation of the existence of interaction interfaces;
(4) An architecture model is derived.
Preferably, the modeling method of the system attribute parameter in the step (2) is as follows:
(2.1) naming the attribute of each system and assigning an initial value to construct a value attribute;
(2.2) determining a value range for the value attribute, adding a new value attribute to the value range, and associating the value range with a related system block;
(2.3) defining the system attribute related units and the affiliated dimensions.
Preferably, in step (2.2), the method for determining the value range for the value attribute is as follows:
when the attribute range is clear, an upper limit value and a lower limit value of the attribute value are required to be established;
when the attribute range provides only a maximum or minimum, then defining the minimum or maximum of the attribute;
when the attribute range is defined as an initial value and a deviation, an upper limit value and a lower limit value of the attribute are calculated and defined.
Preferably, in step (2.3), the defining system attribute related units and the dimension methods are as follows:
binding the units to the corresponding dimension;
each value attribute is associated with its specific unit type and a type is defined for the tag within that value attribute.
Preferably, the agreed format includes: model and description, model object instance and interfacing relationships.
Preferably, the top-level documents include interface relationships between rocket power systems and structural systems, electrical systems, ground emission support systems, engine thrust magnitude, engine mounting angle magnitude.
Compared with the prior art, the invention has the beneficial effects that:
(1) The invention is based on a unified standard model and a data interaction mode to construct a digital collaborative process and conversion among heterogeneous models of each stage, and can effectively enhance the butt joint property and time variability of the models, thereby ensuring the consistency and uniqueness of product data;
(2) The invention establishes a unified interface of information interaction between the architecture model and the system simulation model, and realizes automatic and rapid generation of the system simulation model by extracting the equipment names and the connection relations in the architecture model and comparing and matching the equipment names and the connection relations with the component models in the system simulation model, thereby avoiding low-efficiency repeated modeling and improving the efficiency of the system architecture design to simulation closed-loop verification.
Drawings
FIG. 1 is a flow chart of the present invention.
FIG. 2 is a schematic diagram of a pressurized delivery system according to the present invention;
fig. 3 is a flow chart of detecting a read-in architecture model file according to the present invention.
Detailed Description
The invention is further illustrated below with reference to examples.
A model conversion method for carrier rocket system simulation is shown in figure 1, and comprises the following steps:
step 1: constructing a system architecture model;
step 2, extracting physical information of each component in the architecture model, including mass flow information of gas and liquid, change information of temperature and transmission information of pressure, so as to obtain a component model;
step 3, identifying the composition, the equipment name, the equipment description, the connection relation and the position relation of the architecture model according to the physical information of each component and in combination with the agreed format;
step 4, detecting the architecture model file to determine whether the architecture model file is a first imported file;
comparing the imported architecture model with the history record in the automatic generation module by taking the architecture model name as a unique identification mark to determine whether the imported architecture model is imported for the first time;
step 5, if the file is the first imported file, associating the equipment in the file with the model in the simulation model library, and performing one-to-one correspondence between the equipment in the architecture model and the component model in the simulation model library by taking the equipment name as a unique identification mark;
step 6, if the architecture model file is not imported for the first time, comparing the architecture model with the architecture model in the history record, determining a modified part in the newly-read architecture model, and performing incremental modification on the system simulation model;
step 7, screening parameters in the architecture model and correlating the parameters with the parameters in the simulation model; reading parameters contained in each device in the architecture model, taking the parameter name as a unique identification mark, and carrying out one-to-one correspondence on the parameters in the device and the parameters in the simulation model; if the parameters in the equipment correspond to the parameters in the simulation model, the corresponding parameters are removed, and the final data can be manually confirmed by a user;
step 8, comparing the composition and the position relation of the system architecture model, and laying out the simulation model to be generated, so as to ensure that the generated simulation model truly reflects the composition and the position relation of equipment in the system architecture model;
and 9, automatically connecting all the component models in the simulation models after layout, and connecting interfaces between the component models according to information provided by the architecture models to form a complete system simulation model.
The method for constructing the system architecture model comprises the following steps:
(1) Modeling of top-level physical structure
According to the top layer file of the carrier rocket, the relationship between the physical modules of the internal physical system and the external physical system is established, and according to the specific association relationship between the physical modules, a physical structure model of the power system is established, wherein the model expresses the composition relationship of the structure in a schematic form, for example, the model is expressed in a VISIO diagram form: the power system consists of a supercharging conveying subsystem and an engine subsystem;
(2) System attribute parameter modeling
After the physical structure model of the top layer of the system is established, a single module in a supercharging subsystem in the power system is supplemented, and the system comprises: the device comprises an electromagnetic valve single-unit module, an orifice plate single-unit module, a one-way valve single-unit module and a storage tank single-unit module, wherein the attribute information comprises the up-down deviation of an installation angle, the transverse deviation and the inclined deviation of a thrust line; taking a single storage tank module as an example, the method comprises the following steps: the volume of the storage tank, the density of the gas in the storage tank, the temperature of the gas and the like.
The system attribute parameter modeling steps are as follows:
(2.1) naming the attribute of each system and assigning an initial value to construct a value attribute;
(2.2) determining a value range for the value attribute, adding a new value attribute to the value range, and associating related system blocks, wherein the module of which system the value attribute belongs to can be manually appointed;
(2.3) defining a system attribute related unit and a dimension to which the system attribute related unit belongs;
(3) Modeling of physical structure of pressurizing conveying system
According to a principle diagram of the pressurizing and conveying system, a pressurizing and conveying system/single machine is extracted to define physical modules, and a physical structure composition model of the power system is built according to the specific mutual position relation among the modules and the relation of the existence of interaction interfaces;
(4) Deriving an architecture model
The main innovation point of the patent is a method for generating a system simulation model through a physical architecture model, wherein step 1 mainly defines detailed information such as the composition and interrelation of a single module carrying a rocket power system physical architecture model, the relevant attribute of each module and the like, provides input conditions for subsequent steps, and comprises the following steps:
providing names and descriptions of single machine modules in the architecture model; providing the composition of the architecture model, the names, descriptions and connection relations of the single-machine modules; providing the name of the architecture model; providing the name of the single machine module; providing the composition of the architecture model, the names, descriptions and connection relations of the single-machine modules; providing parameter information in the architecture model; providing a single machine module composition and a position relation in the architecture model; and providing the connection relation of the single module in the architecture model.
In the step (2.2), the method for determining the value range for the value attribute is as follows:
when the attribute range is clear, an upper limit value and a lower limit value of the attribute value are required to be established;
when the attribute range provides only a maximum or minimum, then defining the minimum or maximum of the attribute;
when the attribute range is defined as an initial value and a deviation, an upper limit value and a lower limit value of the attribute are calculated and defined.
In the step (2.3), the system attribute related units and the dimension methods are defined as follows:
binding the units to the corresponding dimension;
associating a specific unit type for each value attribute and defining a type for a tag within the value attribute; labels fall into two categories, one category being unquantized, such as: a valve pattern; one class is quantized, such as: and the upper and lower limits of the deviation value.
The agreed format includes: model and description, model object instance and interfacing relationships.
The top file comprises interface relation between a rocket power system and a structural system, an electric system and a ground emission support system, engine thrust and engine mounting angle.
Examples
Taking a pressurizing and conveying subsystem in a carrier rocket power system as an object, taking the realization of a pressure supplementing function as an example, describing the conversion process from a system architecture model to a system simulation model, wherein 7 single-machine modules are involved, namely an energy dissipater, a storage tank, a pressure annunciator, a safety valve, a pipeline, an electromagnetic valve and a gas cylinder.
The patent first proposes the naming convention for the stand-alone modules as follows:
the single machine module is named as three parts, and is connected by the following underlines in sequence: "stand-alone type abbreviation_stage conventions_function descriptions, such as: "dcf_2y_zszy" stands for "secondary oxidant autogenous boost solenoid valve".
(1) The stand-alone modules in this embodiment are described as:
secondary combustion agent boost energy dissipater: XNQ _2R_ZY
Secondary combustion agent tank: ZX_2R
Secondary combustion agent tank pressure sensor: XHQ _2R_ZXY
Secondary combustion agent tank safety valve: AQF_2R_ZX
Secondary combustion agent exhaust line: GL_2R_PQ
Second-stage combustion agent pressurization line: GL_2R_ZY
Secondary combustion agent pressure compensating pipeline: GL_2R_BY
Secondary-combustion-agent pressure-compensating solenoid valve: DCF_2R_BY
Make-up gas cylinder: QP_BY
(2) On this basis, the corresponding connection relationships are described as follows:
the secondary combustion agent supercharging energy absorber is connected with the secondary combustion agent storage tank: XNQ _2R_ZY_to_ZX_2R
The secondary combustion agent reservoir is connected to the secondary combustion agent reservoir pressure sensor: ZX_2R_to_XHQ_2R_ZXY
The secondary combustion agent tank is connected with a secondary combustion agent tank safety valve: ZX_2R_to_AQF_2R_ZX
The secondary-combustion-agent exhaust line is connected to a secondary-combustion-agent tank safety valve: GL_2R_PQ_to_AQF_2R_ZX
The secondary combustion agent pressurizing pipeline is connected with the secondary combustion agent pressurizing energy absorber: GL_2R_ZY_to_XNQ_2R_ZY
The secondary combustion agent pressure-compensating pipeline is connected with a secondary combustion agent pressure-compensating electromagnetic valve: GL_2R_BY_to_DCF_2R_BY
The secondary combustion agent pressurizing pipeline is connected with the secondary combustion agent pressure supplementing pipeline: GL_2R_ZY_to_GL_2R_BY
The secondary combustion agent pressure-supplementing electromagnetic valve is connected with the pressure-supplementing gas cylinder: DCF_2R_BY_to_QP_BY
(3) And building an architecture model of the pressurizing and conveying system according to the single machine composition and the connection relation, as shown in fig. 2.
Step 1, automatically importing an architecture model into a simulation model generation module, wherein the simulation model generation module identifies and reads in the architecture model according to a contracted format, and the architecture model comprises components of the architecture model, names of single machine modules and connection relations;
step 3, detecting the read architecture model file to determine whether the read architecture model file is a first imported file; comparing the imported architecture model with the history record in the automatic generation module by taking the architecture model file name as a unique identification mark to determine whether the imported architecture model is imported for the first time, as shown in fig. 3;
step 4, if the file is the first read-in file, associating the equipment in the file with the model in the simulation model library, and carrying out one-to-one correspondence on the equipment in the architecture model and the component model in the simulation model library by taking the equipment name as a unique identification mark;
and step 5, if the architecture model file is not read for the first time, comparing the architecture model with the architecture model in the history record, determining whether a new or deleted component exists or not through the component name, and determining whether a new or modified connection relation exists or not through the connection relation interface name. If the modification exists, performing the next adding and deleting operation; if not, directly correlating with the model in the simulation model library to generate a system simulation model.
Step 6, screening parameters in the architecture model and correlating the parameters with the parameters in the system simulation model; reading parameters contained in each device in the architecture model, taking the parameter name as a unique identification mark, and carrying out one-to-one correspondence on the parameters in the device and the parameters in the simulation model; if the parameters in the device correspond to the parameters in the simulation model, replacing the corresponding parameters, and the final data can be manually confirmed by a user;
and 7, laying out the simulation model to be generated, and ensuring that the generated simulation model truly reflects the system architecture composition and the position relation. By a method of defining a location template in advance. The location template includes: the method comprises the following three parts of model annotation, component annotation and connection annotation. Wherein,
annotation of model: the method is used for determining the size of a system simulation model drawing board;
such as: determining drawing board size
Diagram(coordinateSystem(extent＝(-140,-100),(140,100))；
Annotation of components: the method comprises the steps that the method comprises the steps of including a component name and the position of the component in a drawing board, wherein the component name is defined by a keyword 'name', and the component position is defined by an 'animation' keyword;
such as: component name and location information: < Component name= "dcf_2y_zszy", analysis=analysis "(transformation = (-10, 30), extension = { -10, -10}, {10,10 })); "/>
Connection notes: the position information of the connection line is also defined by the keyword of "section".
Such as: position information of the connecting wire: < Connect start= "XNQ _2r_zy", end= "zx_2r", accounting = accounting "(Line (origin= (-30, 31), points= { -10,1}, {10, -1}, color {0,127,255 }); "/>
Step 8, automatically connecting the component models after layout, and connecting interfaces between the component models according to information provided by the architecture model to form a complete system simulation model;
the invention establishes a unified interface of information interaction between the architecture model and the system simulation model, and realizes automatic and rapid generation of the system simulation model by extracting the equipment names and the connection relations in the architecture model and comparing and matching the equipment names and the connection relations with the component models in the system simulation model, thereby avoiding low-efficiency repeated modeling and improving the efficiency of the system architecture design to simulation closed-loop verification.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.
Claims (4)
1. The model conversion method for the carrier rocket system simulation is characterized by comprising the following steps of:
step 1: constructing a system architecture model;
step 2, extracting physical information of each component in the architecture model, including mass flow information of gas and liquid, change information of temperature and transmission information of pressure, so as to obtain a component model;
step 3, identifying the composition, the equipment name, the equipment description, the connection relation and the position relation of the architecture model according to the physical information of each component and in combination with the agreed format;
step 4, comparing the imported architecture model with the history record in the automatic generation module by using the architecture model name as a unique identification mark to determine whether the imported architecture model is imported for the first time;
step 5, if the file is the first imported file, associating the equipment in the file with the model in the simulation model library, and performing one-to-one correspondence between the equipment in the architecture model and the component model in the simulation model library by taking the equipment name as a unique identification mark;
step 6, if the architecture model file is not imported for the first time, comparing the architecture model with the architecture model in the history record, determining a modified part in the newly-read architecture model, and performing incremental modification on the system simulation model;
step 7, screening parameters in the architecture model and correlating the parameters with the parameters in the simulation model; reading parameters contained in each device in the architecture model, taking the parameter name as a unique identification mark, and carrying out one-to-one correspondence on the parameters in the device and the parameters in the simulation model; if the parameters in the equipment correspond to the parameters in the simulation model, the corresponding parameters are removed, and the final data can be manually confirmed by a user;
step 8, comparing the composition and the position relation of the system architecture model, and laying out the simulation model to be generated, so as to ensure that the generated simulation model truly reflects the composition and the position relation of equipment in the system architecture model;
step 9, automatically connecting each component model in the simulation model after layout, and connecting interfaces between the component models according to information provided by the architecture model to form a complete system simulation model;
the method for constructing the system architecture model comprises the following steps:
(1) Modeling of top-level physical structure
According to the top layer file of the carrier rocket, establishing a relationship between an internal physical system and an external physical system physical module, and establishing a physical structure model of the power system according to the specific association relationship between the physical modules;
(2) System attribute parameter modeling
After a top physical structure model of the system is established, supplementing attribute information of a single-machine module in a pressurizing subsystem in the power system, wherein the single-machine module comprises an electromagnetic valve single-machine module, an orifice single-machine module, a one-way valve single-machine module and a storage tank single-machine module;
(3) Modeling of physical structure of pressurizing conveying system
According to a principle diagram of the pressurizing and conveying system, a defining physical module of the pressurizing and conveying system is extracted, and a physical structure composition model of the power system is built according to the specific mutual position relation among the modules and the relation of the existence of interaction interfaces;
(4) Deriving a framework model;
the modeling method of the system attribute parameters in the step (2) comprises the following steps:
(2.1) naming the attribute of each system and assigning an initial value to construct a value attribute;
(2.2) determining a value range for the value attribute, adding a new value attribute to the value range, and associating the value range with a related system block;
(2.3) defining a system attribute related unit and a dimension to which the system attribute related unit belongs;
in the step (2.2), the method for determining the value range for the value attribute is as follows:
when the attribute range is clear, an upper limit value and a lower limit value of the attribute value are required to be established;
when the attribute range provides only a maximum or minimum, then defining the minimum or maximum of the attribute;
when the attribute range is defined as an initial value and a deviation, an upper limit value and a lower limit value of the attribute are calculated and defined.
2. The model conversion method for carrier rocket system simulation according to claim 1, wherein the method comprises the following steps: in the step (2.3), the system attribute related units and the dimension methods are defined as follows:
binding the units to the corresponding dimension;
each value attribute is associated with its specific unit type and a type is defined for the tag within that value attribute.
3. The model conversion method for carrier rocket system simulation according to claim 1, wherein the method comprises the following steps: the agreed format includes: model and description, model object instance and interfacing relationships.
4. The model conversion method for carrier rocket system simulation according to claim 1, wherein the method comprises the following steps: the top file comprises interface relation between a rocket power system and a structural system, an electric system and a ground emission support system, engine thrust and engine mounting angle.
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| CN106682323A (en) * | 2016-12-30 | 2017-05-17 | 苏州同元软控信息技术有限公司 | Transformation system for transforming architecture models into dynamic simulation models, and method thereof |
| CN107784181A (en) * | 2017-11-14 | 2018-03-09 | 北京宇航系统工程研究所 | A kind of fluid structurecoupling towards carrier rocket emulates geometric model simplification method |
| CN109491266A (en) * | 2018-11-28 | 2019-03-19 | 北京宇航系统工程研究所 | A kind of Launch vehicle flight simulation method based on more body virtual prototypes |
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