CN115342971A - Satellite three-dimensional model-based quality characteristic simulation system - Google Patents
Satellite three-dimensional model-based quality characteristic simulation system Download PDFInfo
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- CN115342971A CN115342971A CN202210859771.0A CN202210859771A CN115342971A CN 115342971 A CN115342971 A CN 115342971A CN 202210859771 A CN202210859771 A CN 202210859771A CN 115342971 A CN115342971 A CN 115342971A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/10—Determining the moment of inertia
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M1/00—Testing static or dynamic balance of machines or structures
- G01M1/12—Static balancing; Determining position of centre of gravity
- G01M1/122—Determining position of centre of gravity
- G01M1/125—Determining position of centre of gravity of aircraft
Abstract
The invention provides a quality characteristic simulation system based on a satellite three-dimensional model, which comprises: the parameter setting module is used for setting quality characteristic parameters of the single-machine model or the distributed structural member model under a coordinate system of a defined rule; the cooperative computing module utilizes the quality characteristic parameters set by the parameter setting module to compute and synthesize the quality characteristic parameters of each model of the satellite under a unified whole satellite layout coordinate system; the synthesis application module carries out synthesis calculation according to different forms of large-scale movable parts, whether propellant is filled or not and scene working conditions of counterweight configuration by utilizing quality characteristic parameters output by the collaborative calculation module. The invention also brings distributed structural members except single-machine equipment into the simulation calculation, facilitates the simplified setting and processing of quality characteristic parameters of all distributed structural member subsystems in the whole satellite scheme and the design stage, and can obtain more accurate quality characteristic data in the detailed design stage and the engineering implementation stage.
Description
Technical Field
The invention relates to the general technical field of space vehicles, in particular to a satellite three-dimensional model-based quality characteristic simulation system and an implementation method thereof.
Background
The traditional satellite quality characteristic calculation has the advantages of large number of parts, large number of product states, inaccurate quality information and lack of a uniform quality information management platform; the input sources are not uniform, and effective calculation tools and maintenance management tools are lacked; at present, tables are mainly used for information input, calculation and management in the whole satellite quality characteristic simulation, or a quality simulation model of a whole satellite entity is established, so that the data timeliness is poor, and the maintenance difficulty is high; the quality characteristic information of the distributed structural members of the whole satellite structure, the thermal control system, the cable network equal-division system in the scheme demonstration stage is difficult to determine and coupled together, the calculation reference is not uniform, the input is unclear and independent, and the calculation difficulty and the error are large.
A method for rapidly analyzing the quality characteristics of a spacecraft is disclosed in patent application No. CN201310059681.4, and the method is mainly characterized in that the quality information of spacecraft equipment is imported into a model, the position and the quality information of the equipment are exported by using auxiliary software, and the analysis of the quality characteristics of the spacecraft is completed by utilizing the calculation function of an EXCEL table and a quality characteristic calculation formula. The method realizes real-time updating of the equipment quality characteristic information and quick acquisition of the calculation result. The method can be used for calculating the distributed structural member outside the equipment, and the structural plate, the thermal control member, the cable network, the propellant and the like contained in the distributed structural member account for about one third of the mass of the whole satellite.
A method for determining the mass characteristics of a spacecraft, patent application No. CN201711031544.4, which compares and corrects the model mass characteristics of a partially loaded state with the measured mass characteristics to obtain the mass characteristics of the spacecraft in a fully loaded state. The method can accurately obtain the quality characteristic of the spacecraft by combining the three-dimensional model and part of actually measured data.
A balancing method for the quality characteristics of a spacecraft is disclosed in the patent application No. CN201610903377, which is characterized in that a balancing layout three-dimensional model is constructed by constructing a layout optimization mathematical model, an optimization balancing scheme is obtained by multiple corrections and comparisons, and actual measurement data after balancing is utilized for adjustment, so that the balancing purpose is achieved. According to the method, interactive iteration is performed on the optimized mathematical model and the layout three-dimensional model for multiple times, and finally, the balancing effect is guaranteed through actual measurement, so that the process is complicated, and the engineering application is difficult to realize.
In chinese patent publication No. CN112326120A, a method for predicting the quality characteristics of a spacecraft based on parameter identification is disclosed, which belongs to the technical field of calculating the quality characteristics of a spacecraft. The method comprises the following steps: 1) Acquiring the quality characteristics of the spacecraft in various determined postures; 2) Carrying out nonlinear fitting on the attitude characteristic data and the corresponding quality characteristics thereof to obtain a prediction model with a plurality of parameters; 3) Inputting any group of spacecraft attitude characteristic data into the prediction model obtained in the step 2) to obtain the quality characteristic of the spacecraft in the attitude state.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a quality characteristic simulation system based on a satellite three-dimensional model.
The invention provides a quality characteristic simulation system based on a satellite three-dimensional model, which comprises: the system comprises a parameter setting module, a collaborative computing module and a synthesis application module;
the parameter setting module is used for setting quality characteristic parameters of the single-machine model or the distributed structural member model under a coordinate system of a defined rule;
the cooperative computing module utilizes the quality characteristic parameters set by the parameter setting module to compute and synthesize the quality characteristic parameters of each model of the satellite under a unified whole satellite layout coordinate system;
the synthesis application module carries out synthesis calculation according to different forms of large-scale movable parts, whether propellant is filled or not and scene working conditions of counterweight configuration by utilizing quality characteristic parameters output by the collaborative calculation module.
Preferably, the quality characteristic parameters of the single-machine model are set based on a single-machine installation reference system.
Preferably, the quality characteristic parameters of the distributed structure model provide two forms of overall parameter setting and component-based component separate setting.
Preferably, the distributed structural member model comprises a structural model, a thermal control model, a propulsion model and a cable network model.
Preferably, the overall parameter setting form of the quality characteristic parameters of the distributed structural component model is based on a whole-satellite layout coordinate system, and is embedded and hung in the related subsystem model in a virtual model parameter form, and the component independent setting form based on the components is the same as the single-machine model setting form.
Preferably, the collaborative computing module comprises a whole satellite single machine layout computing module, a distributed structural member computing module and a collaborative computing module;
the whole satellite single-machine layout calculation module is used for calculating the quality characteristics of the whole satellite single-machine model, the distributed structural member calculation module is used for calculating the quality characteristics of the structural model, the thermal control model, the propulsion model and the cable network model, and the cooperative calculation module integrates the whole satellite single-machine model and the quality characteristic calculation results of the structural model, the thermal control model, the propulsion model and the cable network model to obtain the whole satellite quality characteristics.
Preferably, the distributed structure calculation module preferentially calls parameters of independent setting forms of each component for quality characteristic calculation, and when the parameter setting of each component is incomplete, overall setting parameter data is adopted.
Preferably, the whole satellite single-machine model and the structural model, the thermal control model, the propulsion model and the cable network model are calculated by taking a whole satellite layout coordinate system as reference.
Preferably, the synthetic application module comprises three types of forms of a large movable part, a propellant and a counterweight;
the large movable part comprises two states of folding and unfolding, the propellant relates to filling and non-filling and ground and on-orbit application scenes, and the counterweight is mainly used for the configuration design of the counterweight block
Preferably, the models of different states of the large-scale movable part are set according to the design requirements of the installation position of the whole star layout model, different scene forms of the propellant and the placement position of the balancing weight, and the quality characteristics of the large-scale movable part, the propellant and the balancing weight relative to the whole star layout coordinate system are embedded into the synthesis application module in an editable parameter form for calling different application scenes.
Compared with the prior art, the invention has the following beneficial effects:
1. the invention also brings distributed structural members except single-machine equipment into the simulation calculation, facilitates the simplified setting and processing of quality characteristic parameters of all distributed structural member subsystems in the whole satellite scheme and the design stage, and can obtain more accurate quality characteristic data in the detailed design stage and the engineering implementation stage.
2. Based on a unified coordinate system, quality information of the whole satellite single machine layout model and the quality information of the multiple subsystem models of the whole satellite distributed structural member class are effectively managed through different processing means, and efficient quality characteristic collaborative calculation of all the subsystems of the whole satellite is achieved.
3. The operation is simplified, the synthetic application module provides satellite quality characteristic calculation under various working conditions based on data, tedious model processing is removed, complex working condition setting is simplified, and the method can be applied to daily quality characteristic theoretical calculation and can also be used for determining field emergency temporary counterweight schemes such as test experiments.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a schematic structural diagram of a satellite three-dimensional model-based quality characteristic simulation system;
fig. 2 is a flow chart of the operation of the satellite three-dimensional model-based quality characteristic simulation system.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1, a quality characteristic simulation system based on a satellite three-dimensional model according to an embodiment of the present invention includes a parameter setting module, a collaborative calculation module, and a synthesis application module.
The parameter setting module comprises parameter setting of a single machine model and parameter setting of a distributed structural component subsystem model; the cooperative computing module consists of a whole satellite single machine layout, a distributed structural member and a cooperative computing module; the synthetic application module consists of three types of large movable parts, propellant and balance weight;
as shown in fig. 2, the application process of the present invention is as follows, firstly, the subsystem designer sets the quality characteristics through the parameter setting module based on the unified layout coordinate system, and the single machine sets the quality characteristics of the model through the installation coordinate system. And secondly, performing integrated calculation on the quality characteristics of the branch system model and the single-machine model by using a collaborative calculation module. And finally, simulating the quality characteristics of the whole satellite under all working conditions by using a synthesis application module, if the result meets the design requirement, exporting the data and finishing, and if the result does not meet the design requirement, exporting the data and finishing after the balance weight design is carried out until the design requirement is met.
The specific implementation manner in the application flow is as follows:
the quality characteristic parameters of the single machine model are set by a three-dimensional IDS tool on the basis of a single machine installation reference coordinate system, and the quality characteristic parameter setting has two modes:
in a simplified manner, a stand-alone designer specifies the quality of a stand-alone, which is characterized by its quality characteristics calculated according to a uniformly distributed entity model. The quality attributes of the model are set into the stand-alone model through a three-dimensional IDS tool.
And a refinement mode is adopted, and a single machine designer sets the single machine model through a three-dimensional IDS tool according to the quality characteristics of the designed single machine.
The distributed structural member model comprises quality parameter settings of a structural model, a thermal control model, a propulsion model and a cable network model.
The quality parameters of the product comprise integral parameter setting and component independent setting based on composition
And (3) overall parameter setting of the structural model, calculating quality characteristics of all cabin plates and parts of the structure according to an empirical formula, and setting an estimated value of the quality characteristics into flow parameters of the structural overall star model. This approach is used in the scenario demonstration phase.
The independent setting of the structural model based on the component parts is to assign values to structural parts according to actual material density and set the mass attributes after the single deck plate is designed into the flow parameters of the structural whole star model. This approach is used in the design phase.
And the overall parameter setting of the thermal control model sets the components such as the heat pipe, the multilayer and the like into the flow parameters of the thermal control overall star model according to the preset quality attributes. This approach is used in the scenario demonstration phase.
The thermal control model is independently set according to a heat pipe layout, a heat diffusion plate layout, an OSR layout, a paint spraying protection diagram, a multilayer processing diagram and the like based on the formed components, the heat pipe and the heat diffusion plate are assigned according to the actual material density, and other components of the thermal control calculate the quality attribute of the single-plate thermal control through an empirical formula and set the quality attribute into the flow parameters of the thermal control whole star model. This approach is used in the design phase.
And the overall parameter setting of the propulsion model sets the estimated quality characteristic of the propulsion model into the flow parameter of the propulsion overall star model. This approach is used in the scenario demonstration phase.
The propulsion model is set separately based on component parts of the composition to set the characteristics related to the finished propulsion mass into the flow parameters of the propulsion whole star model. The propellant is separately provided in the mould in a full state. This approach is used in the design phase.
And the overall parameter setting of the cable network model sets the estimated quality characteristic of the cable network model into the flow parameter of the cable network overall star model. This approach is used in the scenario demonstration phase.
The cable network model is independently arranged based on component parts, and the quality of the designed cable is assigned according to the linear density of the conducting wires used by the cable. And the cable bracket is assigned according to the design quality. The formed quality attributes are set into the flow parameters of the cable whole star model. This approach is used in the design phase.
Other directories calculate their quality characteristics according to a uniformly distributed solid model and set into the model by means of a three-dimensional IDS tool. The quality characteristics of the single machine in different states are required to be set for the single machine in the unfolding and folding states.
After the parameter setting is finished, the quality characteristic parameters set by the parameter setting module are generally utilized for comprehensive calculation; the single-machine quality characteristic utilizes the relation between the quality characteristic and the single-machine installation coordinate system and combines the relation between the single-machine installation coordinate system and the layout coordinate system in the layout model to calculate the whole-satellite single-machine layout quality characteristic. And the overall satellite quality characteristic is obtained by acquiring the flow parameters in the distributed structural member model and then comprehensively calculating by using a cooperative calculation module in combination with the overall satellite single-machine layout quality characteristic and the distributed structural member quality characteristic.
The distributed structural member calculation module preferentially calls parameters of independent setting forms of all components for quality characteristic calculation, and overall setting parameter data is adopted when parameter setting of all components is incomplete.
After the cooperative calculation is finished, a synthetic application module is generally used for setting folding and unfolding states of large movable parts, and filling and non-filling states of the propellant on ground testing and on-orbit application scenes.
The installation positions of the large movable part different state models relative to the whole star layout model, the propellant different scene forms and the placement positions of the balancing weights are set according to the design requirements, and the quality characteristics of the large movable part, the propellant and the balancing weights relative to the whole star layout coordinate system are all embedded into the synthesis application module in an editable parameter form for calling different application scenes.
And judging the quality characteristics of the whole star after the movable part and the propellant state are set, and if the quality characteristics meet the design requirements, exporting a calculation result and finishing. And if the design requirements are not met, the counterweight module is used for designing.
The counterweight module utilizes the reserved counterweight position and increases and decreases the counterweight at the reserved position, and the system calculates the mass characteristic of the whole satellite after counterweight based on the position and the mass characteristic of the counterweight block and the mass characteristic of the whole satellite. And if the mass characteristics of the whole satellite after weight balancing meet the design requirements, deriving a calculation result and finishing. And if the design requirements are not met, continuing to use the counterweight module for design.
It is well within the knowledge of a person skilled in the art to implement the system and its various devices, modules, units provided by the present invention in a purely computer readable program code means that the same functionality can be implemented by logically programming method steps in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system and various devices, modules and units thereof provided by the invention can be regarded as a hardware component, and the devices, modules and units included in the system for realizing various functions can also be regarded as structures in the hardware component; means, modules, units for performing the various functions may also be regarded as structures within both software modules and hardware components for performing the method.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A quality characteristic simulation system based on a satellite three-dimensional model is characterized by comprising: the system comprises a parameter setting module, a collaborative computing module and a synthesis application module;
the parameter setting module is used for setting quality characteristic parameters of the single-machine model or the distributed structural member model under a coordinate system of a defined rule;
the cooperative computing module utilizes the quality characteristic parameters set by the parameter setting module to compute and synthesize the quality characteristic parameters of each model of the satellite under a unified whole satellite layout coordinate system;
the synthesis application module carries out synthesis calculation according to different forms of large-scale movable parts, whether propellant is filled or not and scene working conditions of counterweight configuration by utilizing quality characteristic parameters output by the collaborative calculation module.
2. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: and setting quality characteristic parameters of the single machine model by taking the single machine installation reference system as a reference.
3. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: the quality characteristic parameters of the distributed structural member model provide two forms of overall parameter setting and component independent setting based on composition.
4. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: the distributed structural member model comprises a structural model, a thermal control model, a propulsion model and a cable network model.
5. The satellite three-dimensional model-based quality characteristic simulation system according to claim 3, wherein: the overall parameter setting form of the quality characteristic parameters of the distributed structural member model is based on a whole-satellite layout coordinate system, is embedded and hung in the related subsystem model in a virtual model parameter form, and the independent setting form of component parts based on composition is the same as that of a single-machine model.
6. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: the cooperative computing module comprises a whole satellite single machine layout computing module, a distributed structural member computing module and a cooperative computing module;
the whole satellite single machine layout calculation module is used for calculating the quality characteristics of the whole satellite single machine model, the distributed structural member calculation module is used for calculating the quality characteristics of the structural model, the thermal control model, the propulsion model and the cable network model, and the cooperative calculation module integrates the whole satellite single machine model and the quality characteristic calculation results of the structural model, the thermal control model, the propulsion model and the cable network model to obtain the whole satellite quality characteristics.
7. The satellite three-dimensional model-based quality characteristic simulation system of claim 6, wherein: the distributed structural member calculation module preferentially calls parameters of independent setting forms of all the components for quality characteristic calculation, and overall setting parameter data is adopted when parameter setting of all the components is incomplete.
8. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: and the whole satellite single machine model and the structural model, the thermal control model, the propulsion model and the cable network model are calculated by taking a whole satellite layout coordinate system as reference.
9. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: the synthetic application module comprises three types of large movable parts, a propellant and a counterweight;
the large movable part comprises a furling state and an unfolding state, the propellant relates to filling and non-filling and ground and on-orbit application scenes, and the counterweight is mainly used for counterweight block configuration design.
10. The satellite three-dimensional model-based quality characteristic simulation system according to claim 1, wherein: the different state models of the large movable part are set according to the design requirements of the installation position of the whole star layout model, different scene forms of the propellant and the placement position of the balancing weight, and the quality characteristics of the large movable part, the propellant and the balancing weight relative to the whole star layout coordinate system are embedded into the synthesis application module in an editable parameter form for calling different application scenes.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117010094A (en) * | 2023-10-08 | 2023-11-07 | 上海航天空间技术有限公司 | Single-machine batch modeling method and system for satellite structure finite element model |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117010094A (en) * | 2023-10-08 | 2023-11-07 | 上海航天空间技术有限公司 | Single-machine batch modeling method and system for satellite structure finite element model |
| CN117010094B (en) * | 2023-10-08 | 2023-12-19 | 上海航天空间技术有限公司 | Single-machine batch modeling method and system for satellite structure finite element model |
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