Digital prototype for key links of electrical system of spacecraft

Abstract

The invention provides a digital prototype for key links of an electrical system of a spacecraft, which is a digital model of a physical prototype, can accurately reflect the characteristics of the physical prototype, has the functions of displaying and analyzing mechanical, electrical and thermal characteristics, and accurately models and simulates the core links of the physical prototype through a digital means. According to the simulation system, the simulation system and the simulation method, Multisim and LabVIEW joint simulation is carried out, dynamic simulation can be carried out on signal transmission parameters of a physical model machine so as to detect performance and potential faults of the system, simulation testing under multiple scenes and multiple working conditions is carried out through a virtual environment, and the anti-interference capability and fault tolerance of the system are evaluated. The method has the beneficial effects that through high-precision simulation and modeling, the actual working condition of the physical prototype can be accurately determined, the design scheme is closer to the design requirement, in addition, comprehensive simulation and testing can be carried out in the initial stage of design, the design reliability of the physical prototype is improved, the design period is remarkably shortened, and the development cost is reduced.

Description

Technical Field

[0001] The invention relates to a spacecraft electrical system, and in particular to a digital prototype of a key link of a spacecraft electrical system. Background Art

[0002] As spacecraft systems become increasingly complex, in order to meet the needs of physical prototypes for high precision and high reliability, digital prototypes of key links in spacecraft electrical systems (hereinafter referred to as digital prototypes) can accurately simulate the working conditions and key links of physical prototypes through computer simulation and virtual modeling, so as to conduct comprehensive performance analysis and fault prediction. For example, digital verification of the system can be carried out in the early stages of design, reducing the time and cost of actual testing, and improving the reliability and stability of system design, thereby meeting the current needs of space missions for efficient and flexible design.

[0003] The accuracy of existing digital prototype simulation results depends on the parameter selection of the model and the accuracy of the algorithm. During the electrical simulation process, due to the limitations of the device model in the component library, there are non-convergence problems when loading the model with individual key data corresponding to the components, and the model needs to be converted or replaced for verification.

[0004] Therefore, how to improve the accuracy of digital prototype simulation results is a technical problem that needs to be solved urgently by those skilled in the art. Summary of the invention

[0005] In order to solve the problems in the prior art, the present invention provides a digital prototype of a key link of a spacecraft electrical system.

[0006] The present invention provides a digital prototype of a key link of a spacecraft electrical system. The digital prototype is a digital model of a physical prototype, can accurately reflect the characteristics of the physical prototype, and has the display and analysis functions of mechanical, electrical and thermal characteristics. The core links of the physical prototype are accurately modeled and simulated by digital means, and a joint simulation of Multisim and LabVIEW is performed. The signal transmission parameters of the physical prototype can be dynamically simulated to detect the performance of the system and potential faults. Through a virtual environment, simulation tests are performed under multiple scenarios and multiple working conditions to evaluate the system's anti-interference ability and fault tolerance, thereby ensuring that the system has efficient and stable performance in practical applications.

[0007] As a further improvement of the present invention, the digital prototype provides a calling port through Multisim, and LabVIEW calls the calling port provided by Multisim to realize the display and analysis functions of the mechanical, electrical and thermal characteristics of the digital prototype.

[0008] As a further improvement of the present invention, the physical model of the digital prototype is displayed in LabVIEW.

[0009] As a further improvement of the present invention, the electrical part of the digital prototype is built by Multisim.

[0010] As a further improvement of the present invention, the digital prototype simulates the working state of the electrical part of the spacecraft through the combination of Multisim and LabVIEW and port parameters.

[0011] As a further improvement of the present invention, the digital prototype calls the calling port given in Multisim through LabVIEW, and obtains the key data of the digital prototype under different test conditions by changing the value of the calling port. The two softwares of Multisim and LabVIEW are used to realize accurate modeling and data acquisition of the electrical part.

[0012] As a further improvement of the present invention, the digital prototype models each circuit part of the electrical part of the spacecraft through Multisim, and then uses LabVIEW to collect and set data, thereby performing real-time data collection and monitoring.

[0013] The beneficial effects of the present invention are as follows: the present invention provides a digital prototype of a key link of a spacecraft electrical system, which can accurately simulate the actual working conditions of the physical prototype through high-precision simulation and modeling, so that the design scheme is closer to the design requirements. In addition, comprehensive simulation and testing can be carried out in the early stages of design to improve the design reliability of the physical prototype, significantly shorten the design cycle, and reduce development costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the description of the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other solutions can be obtained based on these drawings without paying creative work.

[0015] Figure 1 It is a block diagram of the implementation of a digital prototype of a key link of a spacecraft electrical system of the present invention;

[0016] Figure 2 It is a port calling schematic diagram of a digital prototype of a key link of a spacecraft electrical system of the present invention. DETAILED DESCRIPTION

[0017] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0018] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the scope of protection of the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0019] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0020] The present invention will be further described below in conjunction with the accompanying drawings and specific implementation methods.

[0021] like Figure 1 to Figure 2 As shown, a digital prototype of a key link of a spacecraft electrical system, referred to as a digital prototype 100, is a digital model of a physical prototype, which can accurately reflect the characteristics of the physical prototype, and has the display and analysis functions of mechanical, electrical and thermal characteristics. The core links of the physical prototype are accurately modeled and simulated by digital means, and the joint simulation of Multisim and LabVIEW is performed. The key parameters such as signal transmission of the physical prototype can be dynamically simulated to detect the performance of the system and potential faults. Through the virtual environment, simulation tests under multiple scenes and multiple working conditions are carried out to evaluate the anti-interference ability and fault tolerance of the system, ensuring that the system has efficient and stable performance in practical applications.

[0022] like Figure 1 As shown, the digital prototype 100 is respectively connected to the electrical part 200, the mechanical part 300 and the thermal part 400 of the spacecraft.

[0023] The digital prototype 100 has the functions of displaying and analyzing mechanical, electrical and thermal characteristics. Multisim provides a calling port, and LabVIEW calls the port provided by Multisim to realize the characteristics of each part of the digital prototype. The physical model of the digital prototype can be displayed in LabVIEW. The electrical part is built by Multisim. The working state of the aerospace electrical system is simulated through the combination of the two and key operations such as port parameters.

[0024] like Figure 2 As shown in the figure, LabVIEW is used to call the ports given in Multisim. By changing the port values, the key data of the digital prototype under different test conditions can be obtained. The advantages of the two softwares are used to achieve accurate modeling and data acquisition of the electrical system. Multisim is used to model the various circuit parts of the spacecraft electrical system in detail, and LabVIEW is used to collect and set data, so that real-time data acquisition and monitoring can be carried out.

[0025] The invention provides a digital prototype of a key link of a spacecraft electrical system, which supports rapid iteration, optimizes the system design instantly through simulation feedback, realizes multiple iterations and improves the overall performance. At the same time, the digital prototype has flexibility and scalability, and can flexibly adjust the model parameters according to mission requirements.

[0026] The present invention provides a digital prototype of a key link of a spacecraft electrical system, which has precise modeling and simulation capabilities, multi-scenario and multi-condition simulation capabilities, can accurately reflect the characteristics of the physical prototype, and has the display and analysis functions of mechanical, electrical, and thermal characteristics.

[0027] The above contents are further detailed descriptions of the present invention in combination with specific preferred embodiments, and it cannot be determined that the specific implementation of the present invention is limited to these descriptions. For ordinary technicians in the technical field to which the present invention belongs, several simple deductions or substitutions can be made without departing from the concept of the present invention, which should be regarded as falling within the protection scope of the present invention.

Claims

1. A digital prototype of a key link of a spacecraft electrical system, characterized by: The digital prototype is a digital model of the physical prototype, which can accurately reflect the characteristics of the physical prototype and has the functions of displaying and analyzing mechanical, electrical and thermal characteristics. It can accurately model and simulate the core links of the physical prototype through digital means, and perform joint simulation of Multisim and LabVIEW. It can dynamically simulate the signal transmission parameters of the physical prototype to detect the performance of the system and potential failures. Through the virtual environment, simulation tests in multiple scenarios and working conditions are carried out to evaluate the system's anti-interference ability and fault tolerance, ensuring that the system has efficient and stable performance in actual applications.

2. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The digital prototype provides a calling port through Multisim, and LabVIEW calls the calling port provided by Multisim to realize the display and analysis functions of the mechanical, electrical and thermal characteristics of the digital prototype.

3. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The physical model of the digital prototype is displayed in LabVIEW.

4. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The electrical part of the digital prototype was built using Multisim.

5. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The digital prototype simulates the working state of the electrical part of the spacecraft through the combination of Multisim and LabVIEW and port parameters.

6. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The digital prototype uses LabVIEW to call the calling port given in Multisim, and obtains the key data of the digital prototype under different test conditions by changing the value of the calling port. Multisim and LabVIEW are used to achieve accurate modeling and data acquisition of the electrical part.

7. The digital prototype of key links of the spacecraft electrical system according to claim 1, characterized in that: The digital prototype uses Multisim to model the various circuit parts of the electrical part of the spacecraft, and then uses LabVIEW to collect and set data, thereby performing real-time data collection and monitoring.

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