Mass characteristics simulation system based on satellite 3D model

Abstract

The present invention provides a quality characteristic simulation system based on a satellite three-dimensional model, including: the parameter setting module is used to set the quality characteristic parameters of a stand-alone model or a distributed structural component model in a coordinate system with defined rules; the collaborative calculation module uses the quality characteristic parameters set by the parameter setting module to calculate and integrate the quality characteristic parameters of each satellite model in a unified whole satellite layout coordinate system; the synthesis application module uses the quality characteristic parameters output by the collaborative calculation module to carry out synthesis calculations for scene conditions with different forms of large movable parts, whether propellant is filled, and counterweight block configuration. The present invention also incorporates distributed structural components other than stand-alone equipment into the simulation calculation, which facilitates the simplified setting and processing of the quality characteristic parameters of each distributed structural component subsystem in the whole satellite plan and design stage, and more accurate quality characteristic data can be obtained in the detailed design stage and engineering implementation stage.

Description

Technical Field

[0001] The present invention relates to the general technical field of spacecraft, and in particular to a mass characteristic simulation system based on a satellite three-dimensional model and an implementation method thereof. Background Art

[0002] Traditional satellite mass characteristic calculations have the characteristics of a large number of parts, multiple product states, inaccurate quality information, and a lack of a unified quality information management platform; the input sources are not unified, and there is a lack of effective calculation tools and maintenance management tools; currently, the simulation of the quality characteristics of the entire satellite mainly uses tables for information entry, calculation and management, or by establishing a quality simulation model of the entire satellite entity, the data has poor timeliness and is difficult to maintain; in the scheme demonstration stage, the quality characteristic information of distributed structural parts of subsystems such as the entire satellite structure, thermal control, and cable network is difficult to determine and coupled together, and the calculation basis is not unified, resulting in unclear and non-independent inputs, difficult calculations, and large errors.

[0003] "A method for rapid analysis of spacecraft mass characteristics", patent application number CN201310059681.4, this patent document mainly imports the mass information of spacecraft equipment into the model, then uses auxiliary software to export the equipment position and mass information, and uses the calculation function of the EXCEL table and the mass characteristic calculation formula to complete the analysis of the mass characteristics of the spacecraft. This method realizes the real-time update of the equipment mass characteristic information and the rapid acquisition of the calculation results. This method can calculate the distributed structural parts outside the equipment, and the structural plates, thermal controls, cable networks, propellants, etc. contained in the distributed structural parts account for about one-third of the mass of the entire satellite.

[0004] "Method for Determining Spacecraft Mass Characteristics", patent application number CN201711031544.4, this patent compares and corrects the model mass characteristics of the partially loaded state with the measured mass characteristics to obtain the mass characteristics of the spacecraft in the fully loaded state. This method can accurately obtain the mass characteristics of the spacecraft by combining the three-dimensional model and some measured data.

[0005] "Spacecraft Mass Characteristics Balancing Method", patent application number CN201610903377, this patent constructs a layout optimization mathematical model and then constructs a balancing layout three-dimensional model, and obtains an optimized balancing solution through multiple corrections and comparisons, and then uses the measured data after the balancing is implemented to make adjustments to achieve the balancing purpose. This method uses multiple iterations of the optimized mathematical model and the layout three-dimensional model, and finally ensures the balancing effect through actual measurement. The process is cumbersome and difficult to implement in engineering applications.

[0006] In the Chinese patent document with the publication number CN112326120A, a method for predicting the mass characteristics of a spacecraft based on parameter identification is disclosed, which belongs to the technical field of mass characteristic calculation of aerospace vehicles. It includes: 1) collecting the mass characteristics of the spacecraft in various determined postures; 2) performing nonlinear fitting on the posture feature data and its corresponding mass characteristics to obtain a prediction model with several parameters; 3) inputting any set of spacecraft posture feature data into the prediction model obtained in step 2) to obtain the mass characteristics of the spacecraft in the posture state. Summary of the invention

[0007] In view of the defects in the prior art, the object of the present invention is to provide a quality characteristic simulation system based on a satellite three-dimensional model.

[0008] A quality characteristic simulation system based on a satellite three-dimensional model provided by the present invention comprises: a parameter setting module, a collaborative calculation module and a synthetic application module;

[0009] The parameter setting module is used to set the quality characteristic parameters of the single machine model or the distributed structural component model in a defined regular coordinate system;

[0010] The collaborative calculation module uses the quality characteristic parameters set by the parameter setting module to calculate and integrate the quality characteristic parameters of each satellite model in a unified whole-satellite layout coordinate system;

[0011] The synthesis application module uses the mass characteristic parameters output by the collaborative calculation module to carry out synthesis calculations for scene conditions of different forms of large movable parts, whether propellant is filled, and counterweight block configuration.

[0012] Preferably, the quality characteristic parameters of the stand-alone model are set based on the stand-alone installation reference system.

[0013] Preferably, the mass characteristic parameters of the distributed structural component model provide two forms: overall parameter setting and individual setting based on component parts.

[0014] Preferably, the distributed structural component model includes a structural model, a thermal control model, a propulsion model and a cable network model.

[0015] Preferably, the overall parameter setting form of the quality characteristic parameters of the distributed structural component model is based on the entire satellite layout coordinate system, and is embedded in the relevant subsystem model in the form of virtual model parameters. The individual setting form based on the components is the same as the single-machine model setting form.

[0016] Preferably, the collaborative computing module includes a whole-satellite stand-alone layout computing module, a distributed structural component computing module and a collaborative computing module;

[0017] The whole satellite single-machine layout calculation module is used to calculate the mass characteristics of the whole satellite single-machine model, the distributed structural component calculation module is used to calculate the mass characteristics of the structural model, thermal control model, propulsion model and cable network model, and the collaborative calculation module integrates the mass characteristic calculation results of the whole satellite single-machine model and the structural model, thermal control model, propulsion model and cable network model to obtain the mass characteristics of the whole satellite.

[0018] Preferably, the distributed structural component calculation module preferentially calls each component's independently set formal parameters for mass characteristic calculation, and adopts overall setting parameter data when the parameter settings of each component are incomplete.

[0019] Preferably, the calculation of the mass characteristic parameters of the whole satellite single machine model and structure model, thermal control model, propulsion model and cable network model are all based on the whole satellite layout coordinate system as a reference.

[0020] Preferably, the synthetic application module includes three types of forms: large movable parts, propellants and counterweights;

[0021] Large movable parts include two states: folded and unfolded. Propellants involve filling and non-filling as well as ground and on-orbit application scenarios. Counterweights are mainly used for counterweight block configuration design.

[0022] Preferably, the different state models of the large movable components are set according to the design requirements of the installation position of the entire satellite layout model, different scene forms of the propellant and the placement position of the counterweight block. The mass characteristics of the large movable components, propellant and counterweight relative to the entire satellite layout coordinate system are embedded in the synthetic application module in the form of editable parameters for call by different application scenarios.

[0023] Compared with the prior art, the present invention has the following beneficial effects:

[0024] 1. The present invention also incorporates distributed structural components other than stand-alone equipment into the simulation calculation, which facilitates the simplified setting and processing of quality characteristic parameters of each distributed structural component subsystem in the whole satellite plan and design stage, and more accurate quality characteristic data can be obtained in the detailed design stage and engineering implementation stage.

[0025] 2. Based on a unified coordinate system, the quality information of the satellite’s single-machine layout model and multiple subsystem models of the satellite’s distributed structural parts are effectively managed through different processing methods, realizing efficient collaborative calculation of the quality characteristics of each subsystem of the satellite.

[0026] 3. Simplify the operation. The synthetic application module provides satellite mass characteristic calculations under various working conditions based on data, removes tedious model processing, and simplifies complex working condition settings. It can not only be applied to daily mass characteristic theoretical calculations, but also can be used to determine temporary weight balancing plans in emergency situations such as on-site testing and experiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0028] Figure 1 It is a structural diagram of the mass characteristic simulation system based on the satellite three-dimensional model;

[0029] Figure 2 This is the workflow diagram of the quality characteristics simulation system based on the satellite three-dimensional model. DETAILED DESCRIPTION

[0030] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0031] like Figure 1 As described above, an embodiment of the present invention provides a quality characteristic simulation system based on a satellite three-dimensional model, including a parameter setting module, a collaborative calculation module and a synthetic application module.

[0032] The parameter setting module includes the parameter settings of two models: single machine and distributed structural parts subsystem; the collaborative computing module consists of the whole satellite single machine layout, distributed structural parts and collaborative computing modules; the synthetic application module consists of three types of large active parts, propellants and counterweights;

[0033] like Figure 2 The application process of the present invention is as follows: first, 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 its installation coordinate system. Secondly, the overall collaborative calculation module is used to integrate and calculate the quality characteristics of the subsystem model and the single machine model. Finally, the overall synthesis application module is used to simulate the quality characteristics of the entire satellite under various working conditions. If the results meet the design requirements, the data is exported and the end is completed. If not, the counterweight design is performed until the design requirements are met, and the data is exported and the end is completed.

[0034] The specific implementation method in the application process is as follows:

[0035] The quality characteristic parameters of the stand-alone model are set by the 3D IDS tool based on the stand-alone installation reference coordinate system. There are two ways to set the quality characteristic parameters:

[0036] In a simplified way, the single machine designer specifies the mass of the single machine, and the single machine calculates its mass characteristics according to the uniformly distributed solid model. The mass attributes of the model are set to the single machine model through the 3D IDS tool.

[0037] Using a detailed approach, the single-machine designer sets the quality characteristics of the designed single machine into the single-machine model through the 3D IDS tool.

[0038] The distributed structural component model includes the quality parameter settings of the structural model, thermal control model, propulsion model, and cable network model.

[0039] The quality parameters include overall parameter settings and individual settings based on the components.

[0040] The overall parameter setting of the structural model calculates the mass characteristics of each cabin and component of the structure according to the empirical formula, and sets its estimated value into the flow parameter of the structural whole satellite model. This method is used in the scheme demonstration stage.

[0041] The structural model is set based on the individual components of the components. The actual material density is assigned to the structural parts and the mass properties of the single deck after design are set to the flow parameters of the structural whole star model. This method is used in the design stage.

[0042] The overall parameter setting of the thermal control model sets the heat pipes, multilayers and other components into the flow parameters of the thermal control whole star model according to the pre-designed mass properties. This method is used in the scheme demonstration stage.

[0043] The thermal control model is set up based on the individual components of the components. According to the heat pipe layout diagram, heat expansion plate layout diagram, OSR layout diagram, paint protection diagram, multi-layer processing diagram, etc., the heat pipe and heat expansion plate are assigned according to the actual material density, and the other thermal control components are calculated by empirical formulas to calculate the mass properties of the single board thermal control after implementation and set to the flow parameters of the thermal control whole star model. This method is used in the design stage.

[0044] The overall parameter setting of the propulsion model sets the estimated mass characteristics of the propulsion model into the flow parameters of the propulsion whole star model. This method is used in the scheme demonstration stage.

[0045] The propulsion model is set based on the individual components of the components. The propulsion mass characteristics after completion are set to the flow parameters of the propulsion model. The propellant is set to the model individually according to the full state. This method is used in the design stage.

[0046] The overall parameter setting of the cable network model sets the estimated quality characteristics of the cable network model into the flow parameters of the cable network whole satellite model. This method is used in the scheme demonstration stage.

[0047] The cable network model is set based on the individual components. The cable mass after design is assigned according to the line density of the cable wires. The cable bracket is assigned according to the design mass. The resulting mass attributes are set to the flow parameters of the cable star model. This method is used in the design stage.

[0048] The mass characteristics of other directly affiliated parts are calculated according to the uniformly distributed solid model and set in the model through the 3D IDS tool. For single machines with expanded and collapsed states, the mass characteristics of the single machine in different states need to be set.

[0049] After the parameter setting is completed, the overall quality characteristic parameters set by the parameter setting module are used for comprehensive calculation; the quality characteristics of a single machine are calculated by combining the relationship between its quality characteristics and the single machine installation coordinate system and the relationship between the single machine installation coordinate system and the layout coordinate system in the layout model to calculate the quality characteristics of the single machine layout of the entire satellite. The overall quality characteristics of the entire satellite are obtained by obtaining the flow parameters in the distributed structural component model, and then using the collaborative calculation module to comprehensively calculate the quality characteristics of the single machine layout of the entire satellite and the quality characteristics of the distributed structural components.

[0050] The distributed structural component calculation module gives priority to calling the independently set formal parameters of each component for mass characteristic calculation, and adopts the overall setting parameter data when the parameter settings of each component are incomplete.

[0051] After the collaborative calculation is completed, the synthetic application module is used as a whole to set the folded and deployed states of large movable components, and the filled and unfilled states of propellant for ground testing and on-orbit application scenarios.

[0052] The installation positions of different state models of large movable components relative to the whole satellite layout model, the different scenario forms of propellants and the placement positions of counterweights are set according to design requirements. The mass characteristics of large movable components, propellants and counterweights relative to the whole satellite layout coordinate system are embedded in the synthetic application module in the form of editable parameters for call by different application scenarios.

[0053] After the active parts and propellant states are set, the mass characteristics of the entire satellite are judged. If they meet the design requirements, the calculation results are exported and the end is completed. If they do not meet the design requirements, the counterweight module is used for design.

[0054] The counterweight module uses the reserved counterweight position and increases or decreases the counterweight at the reserved position. The system calculates the mass characteristics of the whole satellite after counterweighting based on the position and mass characteristics of the counterweight block and the mass characteristics of the whole satellite. If the mass characteristics of the whole satellite after counterweighting meet the design requirements, the calculation results are exported and the calculation ends. If it does not meet the design requirements, continue to use the counterweight module for design.

[0055] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0056] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A quality characteristic simulation system based on a satellite three-dimensional model, characterized in that: include: Parameter setting module, collaborative computing module and synthetic application module; The parameter setting module is used to set the quality characteristic parameters of the single machine model or the distributed structural component model in a defined regular coordinate system; The collaborative calculation module uses the quality characteristic parameters set by the parameter setting module to calculate and integrate the quality characteristic parameters of each satellite model in a unified whole-satellite layout coordinate system; The synthesis application module uses the mass characteristic parameters output by the collaborative calculation module to carry out synthesis calculation for different forms of large movable parts, whether the propellant is filled, and the configuration of the counterweight block. The collaborative computing module includes a satellite stand-alone layout computing module, a distributed structural component computing module and a collaborative computing module; The whole satellite single machine layout calculation module is used to calculate the mass characteristics of the whole satellite single machine model, the distributed structural component calculation module is used to calculate the mass characteristics of the structural model, thermal control model, propulsion model and cable network model, and the collaborative calculation module integrates the mass characteristic calculation results of the whole satellite single machine model and the structural model, thermal control model, propulsion model and cable network model to obtain the mass characteristics of the whole satellite; The distributed structural component calculation module preferentially calls each component's independently set formal parameters for mass characteristic calculation, and uses the overall setting parameter data when the parameter settings of each component are incomplete.

2. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1, characterized in that: The quality characteristic parameters of the stand-alone model are set based on the stand-alone installation reference system.

3. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1 is characterized in that: The mass characteristic parameters of the distributed structural component model provide two forms: overall parameter setting and individual setting based on component parts.

4. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1, characterized in that: The distributed structural component model includes a structural model, a thermal control model, a propulsion model and a cable network model.

5. The quality characteristic simulation system based on satellite three-dimensional model according to claim 3 is characterized in that: The overall parameter setting form of the quality characteristic parameters of the distributed structural component model is based on the entire satellite layout coordinate system and is embedded in the relevant subsystem model in the form of virtual model parameters. The individual setting form based on the components is the same as the single-machine model setting form.

6. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1, characterized in that: The calculation of the mass characteristic parameters of the whole satellite single machine model and structure model, thermal control model, propulsion model and cable network model are all based on the whole satellite layout coordinate system as a reference.

7. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1, characterized in that: The synthetic application modules include three types of forms: large movable parts, propellants and counterweights; Large movable parts include two states: folded and deployed. The propellant involves filling and unfilling as well as ground and in-orbit application scenarios. The counterweight is mainly used for counterweight block configuration design.

8. The quality characteristic simulation system based on satellite three-dimensional model according to claim 1 is characterized in that: The different state models of the large movable components are set according to the design requirements of the installation position of the entire satellite layout model, different scene forms of the propellant and the placement position of the counterweight block. The mass characteristics of the large movable components, propellants and counterweights relative to the entire satellite layout coordinate system are embedded in the synthetic application module in the form of editable parameters for call by different application scenarios.

Images